NASA/TM--2000-209916

The Alternative Low Noise Fan

James H. Dittmar, David M. Elliott, Robert J. Jeracki, and Royce D. Moore

Glenn Research Center, Cleveland, Ohio

Tony L. Parrott

Langley Research Center, Hampton, Virginia

September 2000
The NASA STI Program Office... in Profile

Since its founding, NASA has been dedicated to

the advancement of aeronautics and space

science. The NASA Scientific and Technical

Information (STI) Program Office plays a key part

in helping NASA maintain this important role.

The NASA STI Program Office is operated by

Langley Research Center, the Lead Center for

NASA's scientific and technical information. The

NASA STI Program Office provides access to the

NASA STI Database, the largest collection of

aeronautical and space science STI in the world.

The Program Office is also NASA's institutional

mechanism for disseminating the results of its

research and development activities. These results

are published by NASA in the NASA STI Report

Series, which includes the following report types:

TECHNICAL PUBLICATION. Reports of

completed research or a major significant

phase of research that present the results of

NASA programs and include extensive data

or theoretical analysis. Includes compilations

of significant scientific and technical data and

information deemed to be of continuing

reference value. NASA's counterpart of peerreviewed formal professional papers but

has less stringent limitations on manuscript

length and extent of graphic presentations.

TECHNICAL MEMORANDUM. Scientific

and technical findings that are preliminary or

of specialized interest, e.g., quick release

reports, working papers, and bibliographies

that contain minimal annotation. Does not

contain extensive analysis.

CONTRACTOR REPORT. Scientific and

technical findings by NASA-sponsored

contractors and grantees.

CONFERENCE PUBLICATION. Collected

papers from scientific and technical

conferences, symposia, seminars, or other

meetings sponsored or cosponsored by

NASA.

SPECIAL PUBLICATION. Scientific,

technical, or historical information from

NASA programs, projects, and missions,

often concerned with subjects having

substantial public interest.

TECHNICAL TRANSLATION. Englishlanguage translations of foreign scientific

and technical material pertinent to NASA's

mission.

Specialized services that complement the STI

Program Office's diverse offerings include

creating custom thesauri, building customized

data bases, organizing and publishing research

results.., even providing videos.

For more information about the NASA STI

Program Office, see the following:

• Access the NASA STI Program Home Page

at http.'//www.sti.nasa.gov

• E-mail your question via the Internet to

help@sti.nasa.gov

• Fax your question to the NASA Access

Help Desk at (301) 621-0134

• Telephone the NASA Access Help Desk at

(301) 621-0390

Write to:

NASA Access Help Desk

NASA Center for AeroSpace Information

7121 Standard Drive

Hanover, MD 21076
NASA / TM--2000-209916

The Alternative Low Noise Fan

James H. Dittmar, David M. Elliott, Robert J. Jeracki, and Royce D. Moore

Glenn Research Center, Cleveland, Ohio

Tony L. Parrott

Langley Research Center, Hampton, Virginia

National Aeronautics and

Space.Administration

Glenn Research Center

September 2000
Trade names or manufacturers' names are used in this report for

identification only. This usage does not constitute an official

endorsement, either expressed or implied, by the National

Aeronautics and Space Administration.

NASA Center for Aerospace Information

7121 Standard Drive

Hanover, MD 21076

Price Code: A99

Available from

National Technical Information Service

5285 Port Royal Road

Springfield, VA 22100

Price Code: A99
THE ALTERNATIVE LOW NOISE FAN

James H. Dittmar, David M. Elliott, Robert J. Jeracki, and Royce D. Moore

National Aeronautics and Space Administration

Glenn Research Center

Cleveland, Ohio 44135

Tony L. Parrott

National Aeronautics and Space Administration

Langley Research Center

Hampton, Virginia 23681

SUMMARY

A 106 bladed fan with a design takeoff tip speed of 1100 ft/sec was hypothesized as reducing perceived noise

because of the shift of the blade passing harmonics to frequencies beyond the perceived noise rating range. A 22 in.

model of this Alternative Low Noise Fan, ALNF, was tested in the NASA Glenn 9×15 Wind Tunnel. The fan was

tested with a 7 vane long chord stator assembly and a 70 vane conventional stator assembly in both hard and

acoustically treated configurations. In addition a partially treated 7 vane configuration was tested wherein the

acoustic material between the 7 long chord stators was made inactive.

The noise data from the 106 bladed fan with 7 long chord stators in a hard configuration was shown to be

around 4 EPNdB quieter than a low tip speed Allison fan at takeoff and around 5 EPNdB quieter at approach.

Although the tone noise behaved as hypothesized, the majority of this noise reduction was from reduced broadband

noise related to the large number of rotor blades. This 106 bladed ALNF is a research fan designed to push the technology limits and as such is probably not a practical device with present materials technology. However, a low tip

speed fan with around 50 blades would be a practical device and calculations indicate that it could be 2 to 3 EPNdB

quieter at takeoff and 3 to 4 EPNdB quieter at approach than the Allison fan.

7 vane data compared with 70 vane data indicated that the tone noise was controlled by rotor wake--stator

interaction but that the broadband noise is probably controlled by the interaction of the rotor with incoming flows.

A possible multiple pure tone noise reduction technique for a fan/acoustic treatment system was identified.

The data from the fully treated configuration showed significant noise reductions over a large frequency range

thereby providing a real tribute to this bulk absorber treatment design. The tone noise data with the partially treated

7 vane configuration indicated that acoustic material in the source noise generation region may be more effective

than similar material outside of the generation region.

INTRODUCTION

The conventional method for reducing fan noise has been to go to a low tip speed, high bypass ratio fan. This

type of fan would typically have a low number of rotor blades with the number of stator vanes selected to provide

for cutoff of the blade passing tone. In references 1 and 2 an alternative method was proposed to reduce the perceived noise of the fan tones. A paper study was conducted in these references on a 6 ft diameter fan. The baseline

fan had 53 rotor blades and 90 stator vanes. This fan had an 1100 ft/sec tip speed. A conventional low speed design

approach to the fan was undertaken. This resulted in a 20 bladed fan at 800 ft/sec tip speed with 44 stator vanes. An

alternative design approach which maintained the 1100 ft/sec tip speed was also investigated. This alternative

method used a high number of rotor blades to shift the harmonic tones to frequencies above the perceived noise rating range leaving only the blade passing tone to be rated. A set of low number, long chord stator vanes was then

used to reduce the level of the blade passing tone. In reference 1 the noise reduction possibilities of the two design

approaches, conventional and alternative, were evaluated using hypothetical spectra. The noise reduction possibilities were calculated as reductions from the baseline fan noise level.

Figure 1(a) shows a hypothetical noise spectra for the baseline fan. This is for a 6 ft fan with 53 rotor blades

turning at 1100 ft/sec tip speed. The fan has 90 stator vanes resulting in a cuton fan such that the blade passing tone

NASA/TM--2000-209916 1
propagates outthefanductingtothefarfield.Inthisfigurethebladepassingtoneisarbitrarilysetat100dBand

eachharmonicsreduced3dBfromthepreviousone.Ascanbeseentherearethreeharmonicsintheperceived

noiseratingrange.

Theconventional approachtonoisereductionisrepresented infigurel(b).Herethefanhas20rotorblades

turningat800ft/sectipspeed. Thefanhas44statorvaneswhichresultsinacutofffansonobladepassingtoneis

showninthespectrum. Thelowertipspeedresultsinallofthetonesbeingreducedby6dBfromthoseofthe

baselinefan.Theharmonicsagainareeachreduced3dBfromthepreviousone.Asseeninfigurel(b)thereare

13tonesintheratedrange.Thelargenumberoftonesistheresultofthelowertipspeedandthelowernumberof

rotorbladescombiningtoprovidealowerbladepassingfrequency. Eachofthesetonesismuchlowerinmagnitude

thanthebaselinefantones.Thenetresultisthatheconventional lownoisefanis9.l PNdBquieterthanthe

baselinefan.

Thespectrumforthealternativelownoisefanisseeninfigure1(c).Thisfanhas106rotorbladesturningat

1100ft/secwhichshiftsallbutthebladepassingtonetofrequenciesabovetheperceivednoiseratingranges. The

fanhas14longchordstatorvaneswhichshouldresultina6dBreductionithebladepassingtone.Theperceived

noisereductionofthisalternativeapproachis10.4PNdB,slightlymorereductionthantheconventional fn'snoise

reduction.

Toverifythepredictednoisereductionpotential ofthealternativelownoisefan,a22in.diametermodelwas

constructedandtestedintheGlenn9x15FootLowSpeedWindTunnel.Thispaperpresentsthedesignofthis

AlternativeLowNoiseFan(ALNF)andtheresultsfromtheacoustictestinginthewindtunnel.

APPARATUSANDPROCEDURE

A0.305scalemodelof the Alternative Low Noise Fan, 22 in. in diameter, was built and tested in the Glenn

9×15 Foot Low Speed Wind Tunnel. This fan was designed with 106 rotor blades and 14 long chord stator vanes to

be an alternative approach to a conventional low tip speed, low rotor blade number, cutoff fan such as the Allison

Engine Company model fan also tested in the 9x15 wind tunnel (ref. 3). The Alternative Low Noise Fan was also

tested using a more conventional 70 vane stator to separately examine the noise reduction achieved by the low number of long chord stators.

Aerodynamic Design

The aerodynamic design point of the Alternative Low Noise Fan was taken to be the takeoff condition. Here

the fan was designed to produce a stage pressure ratio of 1.3 at 1100 ft/sec tip speed. An existing flow path from a

20 in. fan tested previously in a test cell at Glenn Research Center (ref. 4) was scaled by a factor of 1.1 and used for

this fan. Cross section drawings of the ALNF with 14 and 70 stators are found in figures 2(a) and (b) respectively.

Both the 14 and 70 vane sets have the same solidity. Table I shows some of the key parameters for the ALNF fan

design. A complete aerodynamic design for the fan stage is found in appendix A and the blade coordinates are

shown in appendix B. The design in appendix A is for the 106 bladed rotor with the 14 vane stator. The 70 vane

design has the leading edge of the 70 vane stator at the same location as the 14 vane stator and has the same stator

inlet and exhaust conditions. The fan was designed to be tested with both hard wall and acoustically treated flow

paths.

Acoustic Treatment Design

The acoustic treatment design goal was to reduce the noise at the blade passing frequency, -18 000 Hz at takeoff for the scale model fan, and to reduce multiple pure tones that might be roughly centered at 9 000 Hz for the

22 in. model fan. To accomplish the reduction at blade passing frequency the design concentrated on reducing the

92, 78 and 64 spinning mode orders. A single degree of freedom liner was designed with a target design impedance

of (2.67+1.90i) pc. A perforated sheet over bulk absorber design was chosen to achieve this impedance. The perforated plate had 30 percent open area and was designed to be 0.037 in. thick with 0.048 in. diameter holes. The bulk

absorber was Kevlar packed to a 4.5 lb/ft 3 density in a 0.325 backing depth. A sketch of this acoustic absorber

NASA/TM--2000-209916 2
designisshowninfigure3(a).Becauseofstrengthrequirements it wasnotpossibletofabricatetheflowpathpieces

withperforatedsheetasthinasthedesiredthickness. Theactualliner as fabricated is sketched in figure 3(b). The

sheet thickness is 0.062 in. with the side facing the bulk absorber having been countersunk so that the straight portion of the hole is 0.037 in. long before the countersunk portion begins. It was hypothesized that this perforated plate

would act acoustically the same as the designed plate of 0.037 in.

The acoustic treatment was installed in the fan nacelle as shown in figure 2. The material was on the outer flow

path wall of the inlet and on the inner and outer flow path surfaces between the rotor and stator and downstream of

the stator. In the long chord stator version of figure 2(a), acoustic treatment was also placed on the inner and outer

flow path walls in the space between the stator vanes.

Fan Noise Testing

The Acoustic testing was done in the NASA Glenn 9x15 Anechoic Wind Tunnel. A photograph of the Alternative Low Noise Fan in this facility is shown in figure 4. The acoustic treatment on the tunnel wails is shown in the

photograph along with a traversing microphone used to acquire noise data. The acoustic data were obtained by both

the traversing microphone and fixed microphones installed in the wind tunnel. A top view sketch of the tunnel showing the traversing and fixed microphones is shown in figure 5.

A photograph of the 106 bladed fan is shown in figure 6(a). Here the complexity of fitting 106 blades into the

hub can be seen with two different types of blades, short and long stem, being needed to fit into the hub, figure 6(b).

A photograph of the 14 vane stator assembly is shown in figure 7 and the 70 vane stator is shown in figure 8. Acoustic data were taken both with a hard wall nacelle and with the acoustically treated nacelle. The acoustically treated

configurations were tested first. In going from the acoustically treated to the hard configurations most of the nacelle

acoustic surfaces were replaced with hard wall pieces. However for economy of manufacture, the pieces between the

stators in the long chord configuration and the pieces directly behind the stators in the short chord configuration

were made hard by filling the holes in the acoustic material with an epoxy material. This process then dictated that

the acoustically treated configurations be tested first before the holes were filled.

During the initial part of the testing schedule with the acoustically treated nacelle, aerodynamic data were

obtained before acoustic data were taken. This aerodynamic data showed that the fan flow was limited by internal

flow problems. This occurred with both the short and long chord stator versions. A plot of pressure ratio versus

weight flow is shown in figure 9. More complete aerodynamic information is found in reference 5. The first configuration, 14 vanes with acoustic treatment, showed higher pressure ratios and lower weight flows than design. Changes

in the fan nozzle area did not bring about the flow increases expected and high losses in the duct were suspected.

An attempt was made to improve the flow rate by removing every other one of the 14 long chord stators, resulting in

a 7 vane configuration. These vanes were permanently cut out of the stator assembly. A photograph of this 7 vane

configuration is found in figure 10. The removal of every other vane increased the flow but did not bring the weight

flow to the desired level. Configurations with 70 stator vanes and with only partial treatment showed additional improvements. However, the proper flows were only obtained for both the 7 and 70 vane configurations when the fan

was in the hard wall configuration. This indicates that in some way the acoustic treatment was the cause of the flow

problem. Some possible causes might include extra frictional losses from flow over the perforated plate or cross

flows inside the bulk material in the treatment.

Acoustic data were obtained for the 7 and 70 vane configurations with both hard wall and acoustically treated

nacelles. In addition a 7 vane configuration was tested where the nacelle was acoustically treated but the region

between the long chord stators was hard. This configuration was an attempt to determine if the acoustic treatment

between the stators was more effective because of its proximity to the source than other treatment in the nacelle.

Table II shows a list of the tested configurations.

The Alternative Low Noise Fan was designed to achieve a 1.3 pressure ratio at 1100 ft/sec tip speed which was

the takeoff condition. However, during the testing of the ALNF, the rotor blades encountered a high stress region at

speeds greater than 1000 ft/sec tip speed. This appeared to be a flutter instability and the stress level increased with

increasing tip speed. The coating material on the mid span dampers also showed wear after operating at tip speeds

above 1000 ft/sec. Some aerodynamic data were obtained at tip speeds above 1000 ft/sec because of the short time

needed to obtain the data but the acoustic data was limited to 1000 ft/sec because it was not deemed prudent to

remain at these high stress levels for the time needed to make an acoustic survey, -20 min. Table III shows the tip

speeds, from 600 to 1000 ft/sec where the acoustic data were obtained for the 5 configurations listed in table II.

NASA/TM--2000-209916 3
Theacoustic data were obtained by the traverse at 48 steps yielding emission angles from 24.6 ° to 135 ° at a

tunnel Mach number of 0.1 and by three fixed location microphones in the aft yielding emission angles of 136.4 °,

147.2 ° and 158.1 °. Two narrow band spectra were taken of the data at 5.9 and 59 Hz bandwidth. From these a l/3rd

Octave spectra was also constructed. Sound power and PNdB values were calculated from the l/3rd octave data. All

of the noise data presented in the report are in l fl loss less form at the emitted angles unless otherwise specifically

noted. Appendix C contains noise data taken at roughly l0 ° intervals for the 59 Hz bandwidth narrow band spectra

and the l/3rd octave spectra.

RESULTS AND DISCUSSION

Hard Wall Configurations

Comparison of 7 Vane Data With Allison Fan.--In a previous report, reference 6, some comparisons were

made between the hard wall data for the ALNF and the Allison fan at the takeoff condition. This comparison was to

be at 1100 ft/sec tip speed for the ALNF and 840 ft/sec for the Allison fan. At these conditions they were both to

yield a pressure ratio of 1.3. As mentioned previously, the ALNF data were limited to 1000 ft/sec which yielded a

pressure ratio of 1.24. At the 840 ft/sec tip speed the Allison fan had a 1.26 pressure ratio. (This is a slight correction

from the 1.27 pressure ratio stated in reference 6.) Using a noise variation of 10 log thrust the pressure rise ratio of

0.26/0.24 would result in approximately a 0.4 dB correction that should be added to the 1000 ft/sec ALNF data for

comparison with the Allison data. For most of the direct spectrum to spectrum comparisons of the two fans, this

0.4 dB is not significant and is not included on the plots. It is however, included in the effective perceived noise

comparisons that will follow.

Some of the information from reference 6 is repeated herein for completeness. A comparison between the 7

vane stator ALNF at 1,000 ft/sec tip speed and the Allison fan at 840 ft/sec is shown in figure 11. Here narrow band

spectra from 0 to 50 000 Hz with a bandwidth of 59 Hz is shown in part A at 92.5 °. This spectrum was presented in

Reference 6 as being at 90 ° but an error was made in the indexing process and the spectra are actually at 92.5 °. For

consistency with the previous report, the 92.5 ° position will be used throughout this report. These data are shown as

taken on the 22 in. diameter model which has frequencies higher than they would be for the 6 fl diameter full scale

fan. For example, the ALNF blade passing tone is apparent around 18 000 Hz and the tone at twice blade passing

frequency is just visible near 36 000 Hz. On the 6 fl diameter fan these would be about 5 000 and 10 000 Hz. On this

figure the blade passing tone for the Allison fan would be around 2 750 Hz but since it is cut-off it is not visible in

the spectra. Tones at twice blade passing frequency, 5 500 Hz and four times blade passing frequency 11 000 Hz are

clearly visible and the tone at 3 times blade passing frequency, around 8 250, can be seen above the background.

These would be lower on the full scale fan with blade passing frequency being around 840 Hz, 2 bpf at 1680 Hz,

3bpf at 2520 and 4bpf at 336 0Hz.

As can be seen by looking at figure 11(a), not only has the ALNF achieved its goal of being as quiet as the

Allison fan but it appears even quieter. The tone levels of the ALNF would have a lower perceived noise rating than

the tones of the Allison fan not only because of the frequency shift to the lower rated regions of the spectra as indicated by reference 3 but also because the levels themselves are lower. As can be seen again in figure 1l(a), the blade

passing tone sound pressure level of the ALNF is lower than that of the 2 times blade passing frequency tone of the

Allison fan and is about the same level as the 3 times blade passing frequency tone. Therefore the perceived noise of

the tones for the ALNF will be lower than the perceived noise of the tones for the Allison fan.

Possibly more interesting, however, is the broadband noise reduction apparent in the spectra. The ALNF

appears to have lower broadband noise over a frequency range from about 2 000 to 16 000 Hz. The broadband noise

reduction would be from about 600 to 5 000 Hz for the full scale 6 ft diameter fan. This broadband reduction would

have an even larger noise reduction effect on the perceived noise than would the lower tones.

The magnitude of the effect of the broadband noise reduction can be better observed in 1/3rd octave spectra as

used by the perceived noise rating method. Figure 1l(b) shows the 1/3rd octave spectra for the 92.5 ° angle. When

viewed on the 1/3rd octave basis, the broadband noise reduction becomes even more evident. This broadband noise

reduction would result in perceived noise reductions at most reasonable fan sizes.

A l/3rd octave power level plot is shown in figure 12. This power level result, integrated over the entire data

survey shows the significance of the broadband reduction.

NASA/TM----2000-209916 4
Anindicationofthisperceivednoisereductioncanbeseeninfigure 13. Here the Effective Perceived Noise for

a single fan flyover at 1000 ft altitude on a standard day has been calculated for the Allison fan and the ALNF at

scale factors ranging from 2 to 6. Here the EPNdB of the ALNF has been increased by 0.4 dB to account for the

lower pressure ratio. The scale factor is the ratio of the full scale fan diameter to the 22 in. fan diameter. For

example, the 6 ft diameter fan would be at a scale factor of -3.27.

As can be seen the ALNF is significantly quieter at all of the scale factors shown. As the scale factor increases

the two fans start to come closer together in level. This is because the frequency shift of the larger scale has

brought the higher frequencies of the model data, where the two fans have the same levels (20 000 Hz and above,

figure 11 (b)), down into the most highly rated range of the EPNdB calculation.

The previously reported results from reference 6, and summarized above, were for comparisons at the takeoff

condition. A further comparison was made at the approach condition and also showed the ALNF to be quieter. Figure 14 shows spectral comparisons at the 92.5 ° angle for the ALNF and the Allison fan at the approach condition.

Here the Allison fan approach condition is taken as 50 percent speed, 500 ft/sec tip speed, with a pressure ratio of

1.083. The ALNF data were taken from the condition closest to the Allison fan conditions. Here the ALNF data

were taken at 6402 rpmc and a pressure ratio of 1.075. Using the same l0 log of thrust correction, the pressure rise

ratio of 0.083/0.075 yields a correction of 0.35 dB that should be added to the ALNF data. Again this correction is

not applied to the spectrum but it is applied to the perceived noise calculations.

Figure 14(a) shows the narrow band data, 0 to 50 000 Hz with a bandwidth of 59 Hz for the 22 in. model fan.

Again, as for the takeoff case, the blade passing tone of the ALNF (around 12,000 Hz) is lower in level than the

Allison 2 BPF tone (around 5,000 Hz). As with the takeoff data the ALNF tones at approach will have a lower perceived noise contribution than the Allison tones. Figure 14(a) also shows broadband reduction as did the takeoff

data in the 0 to l0 000 Hz range but some broadband noise increase is also shown at higher frequencies that was not

observed in the takeoff data.

Figure 14B shows the 1/3rd octave spectra at this 92.5 ° angle. The large region where the ALNF is quieter,

1 000 to l0 000 Hz, appears to more than overcome the areas where the ALNF is noisier. Figure 15 shows the overall power level comparison for the two fans at approach power. Again the large area of noise reduction for ALNF

overshadows the area of noise increase.

The approach flyover noise at 1000 ft, standard day conditions is shown in figure 16. Calculations are shown for

Allison fan and the ALNF at scale factors ranging from 2 to 6. (A 6 ft diameter fan would have a scale factor of

3.27.) In figure 16, 0.35 dB has been added to the ALNF data to correct for its slightly lower pressure ratio. At the

lower scale factors where the low frequency for the scaled ALNF reduction dominated (fig. 14), significant EPNdB

reductions are seen for the ALNF. At a scale factor of 2 the advantage is over 10 EPNdB. As the scale factor is

increased, the higher frequencies where the noise increases for ALNF are seen (fig. 14) become part of the EPNdB

calculation and the noise increases start to offset some of the noise reduction. At a scale factor of 3, the ALNF is

about 5 dB quieter and at a scale factor of 6 the reduction is only a little over 1 EPNdB. Thus a noise improvement

is seen for all of the represented scale factors with more reduction visible at the lower scale factors.

Comparisons of the ALNF and Allison data, shown here at takeoff and approach, show a significant EPNdB

noise advantage for the high blade number ALNF. Some of this noise reduction is the result of the larger blade number shifting the tones to higher frequencies where they would be weighted lower or not weighted at all by the perceived noise calculation. This was the original design intent of the fan. However, most of the EPNdB noise

reduction results from the lower broadband levels of the ALNF.

In reference 6, two possible explanations were advanced for the broadband noise reduction: (1) A reduced turbulence strength impacting the stator brought about by a reduction in the initially generated turbulence and an increased decay of this turbulence and (2) A shift in the turbulence to smaller length scales which results in reduced

levels of low frequency noise. Both of these explanations can be related to the increased number of rotor blades.

The reduced turbulence strength explanation centers on the fact that the pressure rise of the ALNF is spread

over 106 short chord rotor blades while the Allison fan has the pressure rise provided by 18 larger chord blades. This

provides lower loading per blade for the ALNF with less losses per blade. The result would then be smaller initial

wake defects and lower initial turbulence for the ALNF. In addition, since the wake/turbulence decays with the distance downstream measured in rotor chords, the ALNF with its smaller rotor chord would have more decay resulting

in even lower turbulence levels striking the stator.

The reduced length scale mechanism comes from the increased number of rotor blades giving a smaller gap

between blades. These smaller gaps do not permit as many of the large scale turbulence eddies to be generated. This

can result in the reduction in the low frequency noise that these large scale eddies generate. Looking at this in

NASA/TM---2000-209916 5
anothermannerforaLiepmanntypeofturbulencespectra, theintegrallengthscalefortheALNFwouldbemuch

lowerthanthatfortheAllisonfan.HansonandHoran,reference7,haveindicatedthatatlowfrequenciesthese

smalllengthscalesgeneratelessnoise.Infigure10ofreference7,donefora12ft diameterfan(scalefactorof6.5),

significantoisereductionswereobservedatthelowfrequencieswithsmallerlengthscales. Athigherfrequencies,

thesmallerlengthscalesgenerateextranoise.ThisbehaviorissimilartotheALNF-Allisondatacomparisonat

approach(fig.14).ThesimilarityofthedataandtheorymayindicatethathelengthscalemechanismistheexplanationfortheALNFnoisereductionatapproach. Insummary, theALNFshowssignificant EPNdBnoiseadvantages

primarilyfromthebroadbandnoisereductionbroughtaboutbytheincreasednumberofrotorblades.

The106bladedALNFisaresearchfandesignedtopushthetechnologylevelandassuchit wouldprobablynot

beapractical devicewithpresent materialstechnology. However, afanwithabout50bladescouldbeapractical

device.Inreference6,estimatesofthenoiseofalowtipspeedfanwith50blades, donebothwiththereducedturbulencelvelmethodandthereducedlengthscalemethod,werecomparedwiththatofan18bladedlowtipspeed

fan.Anoisereductionof the order of 2 to 3 EPNdB was estimated at the takeoff condition.

Using the same noise ratios for the 50 bladed fan versus an 18 bladed fan as was done in reference 6, the

approach noise would be 3 to 4 PNdB quieter for the 50 bladed fan for a fan with a scale factor of 3.0. (More reduction would occur at lower scale factors and less at higher ones.) These results reinforce the conclusion of reference 6

that a significant noise reduction would be possible for a high blade number low tip speed fan.

Variation With Speed

The noise variation with speed of the ALNF in the hard wall configuration with 7 stators is shown in figures 17

to 21. Figure 17 shows a series of narrow band spectra taken at the 92.5 ° angle. The narrow band spectra for the

different speed are shown two at a time so they can be more easily compared. Figure 17(a) shows the 6402 rpmc

(600ft/sec tip speed) and the 7736 rpmc (725 ft/sec) data points. Increases in both the tone and broadband noise are

seen here as the speed is increased. Figure 17(b) repeats the 7736 rpm (725 ft/sec) spectrum and adds the 8537 rpmc

(800 ft/sec) spectra. In this figure the presence of some multiple pure tones (MPTs) is observed. This is very low in

tip speed for shock induced multiple pure tones to be appearing and these MPTs may be the result of blade to blade

spacing differences. Mismatch between blade spacing is entirely possible and indeed likely with this many rotor

blades in this scale model fan. In figure 17(b), the broadband noise is seen to increase with speed but the blade passing tone and its harmonics are lower at the 8537 rpm poim than at the 7736 point. This may be do in part to the

transfer of energy from these tones to the MPTs. Figure 17(c), 9604 rpmc and 8537 rpmc follows the same trend

On figure 17(d) a large increase in multiple pure tone noise is seen in going from 9604 rpmc (900 ft/sec) to

10137 rpmc (950 ft/sec). This is most likely the result of the shock induced multiple pure tone mechanism being

seen in the 10137 rpmc data. At the highest speed tested, 10671 rpmc (100ft/sec), figure 17(e), the blade passing

tone is seen to increase again.

Figure 18 shows the l/3rd octave data for the 92.5 ° angle. Here the trends are the same as seen in the

narrow band data. In particular, the increase in MPT activity from 9604 to 10147 rpmc is shown most clearly in

figure 18(d).

Figure 19 shows the l/3rd octave variation of the sound power at the different speeds. Here again in

figure 19(d) the significant increase in multiple pure tone noise is observed in going from 9604 to 10137 rpmc. As

mentioned previously, this is probably the region where the shock induced multiple pure tones are being observed.

Effective perceived noise levels were calculated for the various speed conditions and are plotted in figure 20.

These EPNdB values are for the 1000 ft flyover of one fan on a standard day. As can be seen the EPNdB level

increases as the tip speed is increased for all of the scale factors.

A typical variation of the EPNdB with speed is seen in figure 21 for the scale factor of 3.0. Here the EPNdB is

plotted versus the corrected fan rpm (rpmc). The noise is seen to increase slowly as the speed is increased from 6402

to 7736 rpmc and then to 8537 rpmc. As the speed is increased further to 9604, 10137, and 10671 rpmc, the noise

increase with speed becomes larger, thus creating a parabolic shaped curve. This corresponds to the increase in the

multiple pure tone noise which is in the rated frequency range.

NASA/TM--2000-209916 6
7VaneDataComparisonWith70VaneData

Asmentionedpreviously, a70vanestatorwasalsotestedtodeterminethenoisereduction effect of the low

number of long chord stator vanes (7 vane case). Figure 22 shows the data comparison between the 7 and 70 vane

data at two angles for two fan speeds.

Figures 22(a) and (b) show the data comparisons at a subsonic tip speed, 8537 rpmc (800 ft/sec tip speed) where

no shock induced MPTs should be present and the rotor alone blade passing tone should not propagate. Part A is for

the 24.5 ° angle and part B is for the 130.5 ° angle. These are the same two data plots shown in reference 6. In reference 6, the 130.5 ° angle data was, because of an indexing error mentioned previously, mislabeled as 128 °. Significant reductions in the blade passing tone are observed in going from 70 to 7 vanes.

Previous work has been done on the effect of stator vane number on the broadband noise generated by rotor

wake turbulence--stator interaction noise (ref. 8). This work indicated that the noise was reduced with lower stator

vane numbers, varying approximately as 10 times the log of the ratio of the stator number. Therefore it would be

expected that in going from 70 to 7 vanes that the broadband noise would be reduced about l0 dB. In the front,

24.5 °, there is no effect of the vane number on the broadband noise and there is only a small 3 dB or so effect seen

in the rear, 130.5 °. In both cases much less than the expected l0 dB. A probable explanation for this lack of broadband noise reduction is that the rotor wake turbulence-stator noise mechanism is no longer dominant for the broadband noise of the ALNF as a result of the large number of rotor blades. As indicated previously the rotor wake of

the 106 bladed fan is lower in initial magnitude, decays more rapidly in a fixed axial distance and has a smaller turbulence length scale. As a result the strength of the rotor wake turbulence-stator noise mechanism is reduced and

another noise mechanism becomes dominant.

In the 70 blade data at the 130.5 ° angle some MPT noise is seen with a significant spike at one half blade passing frequency. This is probably the result of the rotor blades having more blade to blade variations in the 70 vane

data because of mid span damper wear. This situation will be discussed more fully in the following high speed data

discussion.

Figures 22(c) and (d) show the data at 10671 rpmc, 1000 ft/sec tip speed, for the 24.5 and 130.5 ° angles respectively. As can be seen here again there is little broadband noise reduction indicating that some source other than

rotor wake turbulence--stator interaction is the dominant broadband mechanism. Of particular interest in this data is

the strong tone at one half blade passing frequency for the 70 vane data. At the 130.5 ° position this tone is significantly louder than the blade passing tone. In figure 22(d), 130.5 °, the 7 vane data exhibits multiple pure tone activity

mostly in the 3000 to 4000 Hz range. The 70 vane data has most of its MPT activity at one half blade passing frequency. An explanation for this difference may be found in the construction of the rotor. Figure 6(b) shows the construction of the rotor hub. In order to fit the 106 blades into the hub, every other blade has a longer stem. In other

works, two types of blades were installed in the hub, ones with short stems and ones with long stems. As can be seen

in figure 6(a), the blades are "locked" together with mid span dampers (part span shroud). At the beginning of the

program, during the 7 vane testing, these mid span dampers fit very tightly and effectively locked the blades together even with the fan at rest. As the testing program continued some wear was observed on these part span dampers, particularly after the high speed, high stress points taken at speeds above 1000 ft/sec tip speed. During the

70 vane testing the wheel was much looser with the ability for more blade to blade movement because of the worn

dampers. A probable explanation for the tone at one half blade passing frequency is that the long and short stem

blades are twisting differently resulting in blade to blade angle changes. This would result in a wheel with a 53 cell

pattern. This then could explain the 70 vane data having its MPT activity centered around one half blade passing

frequency.

This change in the structure of the MPT noise may point to a possible noise reduction technique. It may be possible to design a fan to generate its multiple pure tone noise at one specific frequency, like one half blade passing

frequency, which could then be more effectively removed by acoustic treatment. The acoustic treatment could be

tuned to be most effective in removing the tone at this frequency and the net result would be a quieter fan/acoustic

treatment system.

The 1/3rd octave data for two speeds, 800 and 1000 ft/sec, at two angles 24.5 ° and 130.5 ° are shown in

figure 23. Parts A and B are 24.5 ° and 130.5 ° for 800 ft/sec tip speed and parts C and D are 24.5 ° and 130.5 ° for

1000 ft/sec tip speed. These figures support the same general conclusions as drawn from the narrow band data, specifically that little change in broadband noise was observed in going from 70 to 7 vanes. This further indicates that

some source other than rotor wake turbulence--stator interaction is the primary broadband noise source for the

ALNF.

NASA/TM--2000-209916 7
Thesoundpowerlevelforthe7and70vaneconfigurations at800ft/sectipspeedand1000ft/secareshownin

figure24.Figure24(a)showsthelowspeed800ft/seccaseandonanoverallpowerbasisdoesshowafewdecibel

broadbandoisereductionwhengoingfrom70to7vanesatl 000Hzandabovebutmuchlessthantheexpected

l0dB.Atthehigherspeed,1000ft/secforfigure24(b),somebroadbandreductionisobservedbutagainmuchless

thanexpected. Thedifferenceinmultiplepuretone activity is very evident in figure 24(b). The 7 vane case has its

MPTs in a broad range from 3 000 to 4 000 Hz while the 70 vane configuration has a strong spike at one half blade

passing frequency, in the l0 000 Hz band.

Sound power levels were obtained for the front and aft quadrants to further investigate the small amount of

broadband reductions observed. Ninety degrees was arbitrarily chosen for the split between front and aft power.

Figures 25(a) and (b) are for the front and aft powers at 800 ft/sec and figures 25(c) and (d) are for the front and aft

powers for the 1000 ft/sec tip speed case. For both of the front power comparisons figures 25(a) and (c), very little

broadband noise difference exists between the 7 and 70 vane cases. This indicates that in the front some source other

than the rotor wake turbulence-stator mechanism is controlling the broadband noise for both the 70 and 7 vane cases.

In the aft, figures 25(b) and (d), some broadband noise reduction is seen but much less than the 10 dB expected. This

indicates that although some reduction in rotor wake turbulence-stator noise is observed, a noise floor is reached

such that the 7 vane data broadband noise is not controlled by rotor wake turbulence-stator interaction. This floor

level is then caused by some other source. The fact that almost no reduction occurs in the front indicates that the

controlling broadband noise source is probably related to an interaction involving the rotor. The interaction of the

wall boundary layer with the rotor or the interaction of incoming turbulence with the rotor are two possibilities for

the controlling broadband noise mechanism for the ALNF.

Acoustic Treatment Results

7 Vane-Hard Versus Fully Treated.--The ALNF was tested in both a hard configuration and an acoustically

treated configuration. As shown in figure 2, acoustic treatment was present on the outer flow path surface for the fan

inlet and on both inner and outer flow path surfaces for areas downstream of the rotor. This section compares the

noise data for the 7 vane hard configuration and the 7 vane fully treated configuration.

As indicated in figure 9, the fully treated configuration had lower flow rates and higher pressure ratio than the

hard configuration at the same tip speed. The higher losses, which give the higher pressure ratios and lower flows of

the treated case, would tend to result in the fan generating more noise. So, while the acoustic treatment would be

removing noise, the fan could be generating more noise to begin with. Therefore comparisons between hard and

treated cases are subject to question because the fan source noise has changed between the two configurations. The

exact amount of treatment attenuation is then not available from these comparisons but the comparisons are performed because they give qualitative results for the treatment performance.

Spectra comparing the hard and fully treated 7 vane configurations are found in figures 26 to 31. Figures 26 and

27 are for the 6402 rpmc, 600 ft/sec tip speed data point, figures 28 and 29 for the 8537 rpmc, 800 ft/sec, and figures 30 and 31 for the 10671 rpmc, 1000 ft/sec, data point. Each of the figures has part A for the 24.5 ° angle, B for

the 92.5 ° angle and C for the 130.5 ° angle. Narrow band spectra are found if figures 26, 28 and 30 with the corresponding l/3rd octave data in figures 27, 29 and 31.

In general, the spectral data show little attenuation at the 24.5 ° angle. In fact, at the lower speeds 6402 rpmc

(fig. 26(a)) and 8537 rpmc (fig. 28(a)), small noise increases are seen with the treated configurations. It should be

noted that not much attenuation would be expected at this far forward an inlet angle and therefore the noise increase

may be indicative of the additional fan noise present at the treated configuration operating conditions. As more aft

angles are investigated, 92.5 and 130.5 °, the treatment does show attenuation at all speeds. As the speed is increased,

more attenuation is observed until sizable attenuations are observed at the aft angles of the 10671 rpmc, 1000 ft/sec

tip speed case (figs. 30(c) and 31 (c)). Of particular note is the large frequency range over which attenuation is

observed. Again looking at the 1/3rd octave data of figure 31(c), noise attenuations are observed all the way from

1 000 to 100 000 Hz. This range of attenuation is a real tribute to the broadband nature of this bulk absorber design.

Sound power levels for the six speeds tested are found in figure 32 starting with the lowest speed, 6402 rpmc

(600 ft/sec tip speed) in part A and going up to 10671 rpmc (1000 ft/sec) in part F. As can be seen in this figure,

only small amounts of attenuation are seen at low speed with ever increasing attenuations as the speed is increased.

The most attenuation occurs at 10137 rpmc (950 ft/sec tip speed) and at 10671 rpmc (1000 ft/sec) where large

attenuations of the multiple pure tones are observed. As has been noted in the past, multiple pure tone noise is particularly attenuable by treatment and this data continues to show that trend. (see, for example, ref. 9)

NASA/TM--2000-209916 8
FrontandaftPWLsareshowninfigures33and34respectively. Forthefrontpower(90° andforward)atthe

lowerspeeds, 6402and7736rpmc,thenoiseincreaseswiththefullytreatedconfiguration. Againthisispossiblythe

resultofachangeinthefannoisegenerationsincethefanhadadifferentoperatingpoint.Asthespeedisincreased,

thetreatment sartstoshowattenuationparticularlyintheMPTfrequencyrangebelowbladepassingtoneuntilsizableattenuations areobservedat10671rpmc.TheaftPWLs,figure34,showattenuations atallspeedswiththe

amountoftheattenuationincreasingasthespeedisincreased.

Thedifferencebetweenthehardandfullytreatedpowerlevelsisshowninfigure35withthelowestspeed,

6402rpmc,beingpartAandproceedingtill partFwhichisthehighestspeed,10671rpmc.Thelevelofattenuation

isoftheorderof 3dBatthelowerspeedsandincreaseswithincreasingspeeduntilasmuchas17dBisseenaround

4000Hzatthe10671rpmc(1000ft/sectipspeed)condition.Again,lookingatfigure35(f),thelargefrequency

rangeofattenuation, from2000to100000Hzisarealtributetothebulkabsorber design.

Figures36and37showthedeltaPWLsforthefrontandrearpowerlevelsrespectively. Inthefront,figure36,

atlowspeeds, theextranoisefromthefullytreatedconfigurationisseenasnegativeattenuations. Asthespeedis

increased, theinletattenuations becomelargersothatatthehigherspeedsthefrontpowerdeltashowapositive

noisereductionforthetreatedconfiguration. Itheaft,figure37,attenuations areseenforallofthespeedswith

moreattenuationatthehigherspeedsthanatthelowerspeeds. Bycomparingtheinletandaftpowerleveldeltasit is

seenthatmorenoiseisremovedfromtheaftquadrant thanfromthefrontquadrant. Thisisparticularlytrueatthe

higherfrequencies, 10000Hzandabove.Theadditional attenuationintheaftisasexpectedbecauseoftheadditionaltreatment intheexhaust ductascomparedwiththatintheinlet.

EffectOfTreatment BetweenStators

Apartiallytreatedconfigurationwastestedwiththelongchordstators.Heretheacoustictreatment betweenthe

longchordstatorswasmadeacousticallyhardbyfillingwithanepoxyresin.Thisexperiment wasdonetodetermine

if acousticmaterial withinthenoisesourceregionwouldbemoreeffectiveatremovingnoise.

Figures38to43showspectral comparisons betweenthefullytreatedandpartiallytreatedconfigurations atthe

threespeedsof6402rpmc(600ft/sectipspeed), 8537rpmc(800ft/sec)and10671rpmc(1000ft/sec).Thesecomparisonssufferfromthesameproblemasdidthehardversusfullytreatedcomparisons ithathefanoperatingline

isnotthesameforthetwocases.Figure9showstheoperatinglineforthefullytreatedandpartiallytreatedcases.

These two operating lines are closer together than the hard and fully treated line but some differences still exist that

can obscure the acoustic results.

The spectral comparisons of figures 38 to 43 show that the acoustic material between the stators is removing a

significant amount of noise toward the aft angles. Noise reductions are seen at the tones and over a broad bandwidth.

More attenuation is seen in the aft and more attenuation is present at the higher speeds as was observed for the fully

treated cases.

Figure 44 shows the power level comparisons at the six speeds of 6402, 7736, 8537, 9604, 10137 and

10671 rpmc. Again the power level comparisons show increased differences between the fully treated and the partially treated configurations as the speed is increased.

Figures 45 and 46 show the front and aft powers. In the front only small differences are seen between the fully

treated and partially treated cases while in the aft significant amounts of attenuation are observed for the treatment

between the stators.

The delta PWL values are seen in figure 47. Positive differences in PWL correspond to increased attenuation

with full acoustic treatment.As mentioned before the total attenuation and the difference between the fully and partially treated cases increases with speed. The front and aft delta PWLs are shown if figures 48 and 49. Differences of

less than 2 dB exist in the front PWL between the fully treated and partially treated configurations. In the aft, however, the differences are larger with the treatment between the stators showing 4 to 5 dB of increased attenuation

around the blade passing tone.

When this experiment was conducted, it was believed that rotor wake turbulence-stator interaction would be the

primary source of broadband noise. In that case, the material between the stators might be more effective at broadband noise suppression because it was within the noise source region. However, as mentioned earlier in the report as

a result of reduced rotor wake strength and smaller turbulence length scale, there is strong indication that the rotor

wake turbulence-stator interaction mechanism is not the primary broadband noise source for the 7 vane stator configuration and that a rotor related source is probably dominant. In this case, the material between the stators would

NASA/TM--2000-209916 9
beexpectedto be no more effective than any other treatment downstream of the rotor in reducing the aft broadband

noise.

Table IV shows the approximate surface areas of the treatment in the 7 vane configuration. In the aft, the treatment between the stators, is ~37 percent of the total treatment downstream of the rotor. Since the passage height is

approximately the same for all of the treatment downstream of the rotor, the attenuation of each section should be

roughly proportional to the treated area. Then 37 percent of the downstream attenuation should come from the treatment between the stators. To check this a number of aft PWL points were checked at a frequency that should be

controlled by broadband noise. The total aft PWL attenuations were taken from figure 37 and the attenuations from

the treatment between the stators from figure 49. Table V contains attenuation comparisons, one at each speed for

the 25 000 Hz 1/3rd octave band. The percentage attenuation from the treatment between the stators varies from

40 percent at 6402 rpmc to 56 percent at 10671 rpmc with an average around 50 percent. This is only slightly more

than the 37 percent that this material should be removing. This indicates for the broadband noise that the material

between the stators is behaving a little better but not much different than the other lining material downstream of the

rotor.

As mentioned previously in the report, that although the broadband noise was not controlled by rotor wakestator interaction, the blade passing tone did appear to be controlled by rotor wake-stator interaction. Therefore the

material between the stators, being within the noise generation region, may have a proportionally greater effect on

the blade passing tone. If the leading edge of the stator is taken as the reference point, the acoustic treatment

between the stators represents 44 percent of the material downstream of this point. Table VI compares the l/3rd

octave band aft powers for the bands that contain the blade passing tone at the various speeds tested. Here it is seen

that the percentage of the total noise that is removed by the material between the stators is much higher for the

blade passing frequency than for the broadband noise. The percentage goes as high as 75 percent at the 10671 rpmc

case with the average being 65 percent. These high values indicate that the material between the stators may be

more effective than the other treatment material. This material may be more effective because its proximity to the

source may allow more noise to be incident onto the acoustic treatment than would occur for downstream treatment

sections.

Although the data does not prove the point conclusively, it does indicate that acoustic treatment within the

noise source region, the BPF case, does act more effectively than treatment away from the source. It is also seen that

this same treatment material between the stators acts approximately the same as the other materials in the duct when

it is not within the noise source region, the broadband case.

70 Vane-Hard Versus Fully Treated

The ALNF was tested with the 70 vane stator set in both a hard and acoustically treated configuration. As

shown in figure 2, acoustic treatment was present on the outer flow path surface for the fan inlet and on both the

inner and outer flow path surfaces for areas downstream of the rotor. This section compares the noise data for the

70 vane hard configuration and the 70 vane fully treated configuration.

As indicated in figure 9, the fully treated 70 vane configuration had lower flow rates and higher pressure ratios

than the hard configuration at the same tip speed. The difference between the hard and treated operating lines is not

as great as that which existed for the 7 vane configurations but the difference is still significant. The higher losses

which give the higher pressure ratios and lower weight flows of the treated case would tend to result in the fan generating more noise. So, while the acoustic treatment would be removing noise, the fan could be generating more

noise to begin with. Therefore comparisons between hard and treated cases are subject to question because the fan

source has changed between the two configurations. The exact amount of treatment attenuation is then not available

from these comparisons but the comparisons are performed here because they give qualitative results for the treatment performance.

Spectra comparing the hard and fully treated 70 vane configurations are found in figures 50 to 55. Figures 50

and 51 are for the 6402 rpmc, 600ft/sec tip speed data point, figures 52 and 53 for the 8537 rpmc, 800 ft/sec, and

figures 54 and 55 for the 10671 rpmc, 1000 ft/sec, data point. Each of the figures has part A for the 24.5 ° angle, B

for the 92.5 ° angle and part C for the 130.5 ° angle. Narrow band spectra are found in figures 50, 52 and 54 with the

corresponding l/3rd octave data in figures 51, 53 and 55.

In general, the spectral data show little attenuation at the 24.5 ° angle. In fact some regions of noise increase are

seen at this far forward angle (figs. 50(a), 52(a) and 54(a)). It should be noted that not much attenuation would be

NASA/TM--2000-209916 10
expectedatthisfarforwardaninletanglebutthenoiseincreasemaybeindicativeoftheadditional fannoisepresent

atthetreatedoperatingcondition.Asthemoreaftanglesareinvestigated, 92.5and130.5°,thetreatment doesshow

attenuationatallspeeds. Significant atenuationisobservedatthehighspeed,10671rpmc,conditionandtheMPT

toneat1/2bladepassingfrequencyisparticularlyattenuated(figs.54(c)and55(c)).Asmentionedpreviously, tailoringtheMPTstooccuratoneparticularfrequency, hereatonehalfbladepassingfrequency, couldbeusedasa

noisereductiontechnique. Thehighattenuationpossibleatforaspecificfrequencycouldbecombinedwiththe

MPTsatonefrequencytoprovideaveryeffectivefan/acoustictreatment system.

Againaswiththe7vanedata,thelargefrequencyrangeoverwhichattenuationisobservedisofparticular

note.Lookingatthel/3rdoctavedataoffigure55(c),noiseattenuations areobservedallthewayfrom1000to

100000Hz.Thislargefrequencyrangeofattenuationisarealtributetothebroadbandnatureofthisbulkabsorber

design.

Soundpowerlevelsforthesixspeedsarefoundinfigure56startingwiththelowestspeed,6402rpmc

(600ft/sectipspeed)inpartAandgoingupto10671rpmc(1000ft/sectipspeed)inpartF.Significant attenuations

areseenatallspeedswiththemostattenuations beingseenatthe10137and10671rpmcdatapoints.Theselarge

attenuations atthesehigherspeedsseemcenteredaroundtheremoval ofthemultiplepuretonenoise.Ashasbeen

notedinthepast,multiplepuretonenoiseisparticularlyattenuablebytreatment andthisdatacontinuesthetrend.

FrontandaftPWLsareshowninfigures57and58respectively. Atthelowerspeeds, 6402,7736,and

8537rpmc,theattenuations ithefrontpoweraresmall.Atthehigherspeedssomesignificant attenuationisseen

particularlyintheMPTregionofthespectra. TheaftPWLs,figure58,showattenuations atallspeeds. LargeattenuationsareseenatthehigherspeedsintheMPTregionsofthespectra.

Thedifferencebetweenthehardandfullytreatedpowerlevelsisseeninfigure59withthelowestspeed,

6402rpmc,beingpartAandthehighestspeed,10671rpmc,beingpartF.Significant attenuations areseenatall

speedswithasmuchas16dBbeingseenatthebladepassingfrequencyat10137rpmc(fig.59(e)).Againthefrequencyrangeoftheattenuationisofparticularnote.

Figures60and61showthedeltaPWLsforthefrontandrearpowerlevelsrespectively. Atthelowerspeedsin

thefront,6402to8537rpmc,figures60(a)to(c),thepeakattenuationisoftheorderof5dBatthelowerfrequencieswithsomeregionsofnoiseincreaseatthehigherfrequencies. Atthehigherspeeds, 10137and10671rpmc,

figures60(e)and(f),thepeakattenuationisover10dBintheregionofthebladepassingtonewithlittleornoregionsofnoiseaddition.Intheaft,figure61,thenoiseattenuations aregreaterthaninthefrontwithpeakattenuationsatallanglesbeingover10dBandwithnoregionsofnoiseaddition.Thisadditional attenuationintheaftisas

expectedbecauseoftheadditional treatment intheaftasopposedtotheinlet.

CONCLUDINGREMARKS

A106bladedfanwithadesigntakeofftipspeedof 1100ft/secwashypothesizedasreducingperceivednoise

becauseoftheshiftofthebladepassingtoneharmonicstofrequenciesbeyondtheperceivednoiseratingrange.A

22in.modelofthisalternativelownoisefan,ALNF,wastestedintheNASAGlennacousticallytreated9x15tunneltoconfirmthishypothesis. TheALNFwastestedwithbotha7vanelongchordstatorassemblytoreduceinteractionoiseanda70vaneconventional statorassembly. Boththe7and70vaneconfigurations weretestedinhard

andacousticallytreatedconfigurations. The7vaneconfigurationwasalsotestedinapartiallytreatedconfiguration

wheretheacoustictreatment betweenthe7statorvaneswasmadehardtoevaluateherelativeffectiveness ofthis

treatment thatwaspresumably inthenoisesourcegenerationregion.

Thenoisedatafromthe106bladedfanwiththe7vanelongstatorinanacousticallyhardversion,noacoustic

treatment, wascomparedwiththenoiseofalowtipspeedfanpreviouslydesignedbyAllisonandtestedinthesame

9×15windtunnel.The106bladedfanat1000ft/sectipspeedwasshowntobearound4EPNdBquieterthanthe

Allisonfanat840ft/secforthetakeoffconditionand5EPNdBquieteratapproach(600ft/secALNF,500ft/sec

Allison)fora1000ftflyoverofan-6ft diameterfanonastandardday.EPNdbreductionswereobtainedfromthe

tonenoisereductionandfrequencyshiftasexpectedfromthedesignbutthemajorityof thenoisereductioncame

fromreducedbroadbandnoiseoftheALNF.ThisbroadbandreductionwasrelatedtothelargenumberofALNF

rotorblades. Thelargenumberofrotorbladesresultedinsmallerinitialwakeswhichdecayedmorerapidlyina

fixeddistanceandhadsmallerturbulencelengthscales.

The106bladedALNFisaresearchfandesignedtopushthetechnologyandassuchit probablyisnotapracticaldevicewithpresentmaterialstechnology. However, alowtipspeedfanwith50bladescouldbeapractical

NASA/TM--2000-209916 11
device.Estimatesof the noise of a low tip speed fan indicate that it would have a 2 to 3 EPNdB advantage at takeoff

and 3 to 4 EPNdB advantage at approach speed over the Allison fan in a low tip speed device about 6 ft in diameter.

Tone noise reductions were observed in the hard wall data when the 70 vane stator was changed to the 7 vane

stator. These reductions were expected with the lower number of long chord stators reducing the rotor wake stator

interaction noise. However, the expected level of reduction in broadband noise was not observed, indicating that

some source other than rotor wake turbulence-stator interaction is the primary broadband noise source. The low

level of rotor wake turbulence-stator interaction noise is attributed to the large number of rotor blades reducing both

the magnitude and scale of the wake turbulence.

The structure of the MPTs at higher speeds changed considerably as the fan dampers started to wear. The MPTs

became strongly centered at one half blade passing frequency because the design of the blade stems allowed every

other blade to find a different operating position when the dampers were no longer keeping the blades in fixed positions. With every other blade looking differently, the MPTs came out primarily at one half blade passing frequency.

This occurrence points to a possible noise reduction technique. A net noise reduction could be achieved for a high

tip speed fan by designing blade to blade differences so that the MPTs would be generated at a specific frequency,

like the one half blade passing frequency observed herein, and designing acoustic treatment to remove that frequency. Acoustic treatment is specifically effective when it can be designed for a small frequency range. Therefore a

design combining the MPTs at one frequency and acoustic treatment tailored specifically to remove that frequency

could result in higher noise reductions from the fan/acoustic treatment system.

The Alternative Low Noise Fan results with acoustic treatment were somewhat obscured because the fan performed on a different operating line with the acoustic treatment. This different line was expected to give more fan

noise with the treatment operating line than without the treatment possibly yielding less measured attenuation than

the treatment actually provided. Even with these different operating lines, the fully treated cases, 7 and 70 vane comparisons, showed significant noise reduction over a very large frequency range. These large amounts of attenuation

over such a large frequency range are a real tribute to this bulk absorber treatment design.

Data from the partially treated configuration, acoustic treatment material between the stator vanes made hard,

was compared with the full treatment data and the effect of the material between the stators was measured. The

intent here was to see if acoustic material within the region where noise was generated would be more effective than

material outside this region. The broadband data showed the lining material between the stators to be about as effective as the other acoustic material downstream of the rotor. Since the previous 7 versus 70 vane data indicated that

the broadband noise was probably controlled by an interaction on the rotor, all of the treatment material, including

that between the stators was outside of the broadband noise generation region and would be expected to behave

similarly. The blade passing tone noise, however, was believed to be controlled by rotor wake-stator interaction

noise and the treatment material between the stators would be in the tone source generation region. The blade passing tone data appeared to show the acoustic material between the stators as being more effective than material outside of the noise generation area. This is possibly because more of the noise is incident on the acoustic material

close to the source than on material downstream. This result would indicate that acoustic treatment is more effective

if placed within the source generation region.

REFERENCES

1. Dittmar, James H., and Woodward, Richard P., An Evaluation of Some Alternative Approaches for Reducing

Fan Tone Noise, NASA TM-105356, 1992.

2. Dittmar, James H., A concept for a Counterrotating Fan with Reduced Tone Noise. NASA TM-105736,1992.

3. Woodward Richard P., et.al., Benefits of Swept and Leaned Stators foe Fan Noise Reduction, NASA TM TBD,

AST Paper AST018,1997.

4. Gelder, T.F., and Soltis, R.F., Inlet Noise of 0.5 Meter-Diameter NASA QF-1 Fan as Measured in an Unmodified Compressor Aerodynamic Test Facility and in an Anechoic Chamber, NASA TN D-8121,1975.

5. Jeracki, Robert J., The Aerodynamic Performance of the Alternative Low Noise Fan, to be published.

6. Dittmar, James H., A Method to Further Reduce the Perceived Noise of Low Tip Speed Fans, NASA AST

Report, AST 027, 1998.

NASA/TM--2000-209916 12
7. Hanson, DonaldB.,andHoran,Kelly,Turbulence/Cascade Interaction: Spectraof Inflow,CascadeResponse,

andNoise.AIAAPaper98-2319. Presentedatthe4thAIAA/CEASAeroacoustics Conference, 1998.

8. Ganz,UlrichW.,et.al.,Boeing18-InchFanRigBroadbandNoiseTest,NASACR-1998-208704, 1998.

9.Sofrin,T.G.,andPickett,G.F.,MultiplePuretoneNoiseGeneratedbyFansatSupersonicTipSpeeds, in

NASASP304,1970.

TABLEI.--ALTERNATIVELOWNOISEFANMODEL

Fandiameter.................................................................. 22in.

Takeoffpressureratio........................................................ 1.3

Takeofftipspeed.................................................. 1100ft/sec

Rotorbladenumber.......................................................... 106

Statorvanenumber........................................... 14longchord

70shortchord

Nacelleconfigurations .............................................. hardwall

acoustictreatment

TABLEII.--TESTCONFIGURATIONS

7longchordstatorvanes, acousticallytreatednacelle

7longchordstatorvanes, acousticallytreatednacelleexcept

thetreatment betweenthestatorshasbeenmadehard

7longchordstatorvanes, hardwallnacelle

70shortchordstatorvanes, acousticallytreatednacelle

70shortchordstatorvanes, hardwallnacelle

TABLEIII.--TESTCONDITIONS

Corrected,

rpm

6402

7736

8537

9604

10137

10671

Tipspeed,

ft/sec

600

725

800

900

950

1000

NASA/TM--2000-209916 13
TABLEIVa.--TREATEDAREASLONGCORDSTATOR

Treatment section

A

B

C

D

E

F

G

Totalbetweenstators

Totaldownstreamofrotor

TotaldownstreamofstatorL.E.

Approximatesurfaceareain.-

924

188

113

446

268

565

399

714

1919

1618

A'_ lI.J I I o-I F-r

106 ROTOR BLADES _ I 1 I / -,----70 STATOR VANES G

__<<,_l_._r_",,i,..Hllll//.-.." .................. _._.

_.,_w't..'rv'"Ei_:ltl¢.#lt _ u_iuul_nrl__*u_rr_,,rrx,.'.';,.',t_.'..ru;.'.'.l_'____

,,.._a_,-_ 'Yll,liil_ r) _ Ill.. r-;r---m_ -r-.,----_,,-'---- !

.,_ I_'_ _ll'_i_'_l_ .... ..._,_,,_L..-J i.... f i ,. dlj.--i

.,,. Ztii._"_-: .......... ......... ______..__

"-" (( il--llTL_"..i,_l HI ..... I- ---- - .........

TABLE IVb.--TREATED AREAS SHORT CORD STATOR

Treatment section

A

B

C

D

E

F

G

Approximate surface area in. 2

924

188

113

440

264

565

399

NASA/TM--2000-209916 14
Corrected

revolutions/minute

10671

10137

9604

8537

7736

6402

TABLEV.--BROADBANDTREATMENTATTENUATIONS

Frequencyband FulltreatmentTreatment betweenPercentage ofattenuation

containing attenuationstatorsattenuationfromtreatment between

broadbandoise

8.0

7.0

9.0

7.5

7.5

7.5

4.5

3.75

4.75

3.75

3.5

3.0

25000

25000

25000

25000

25000

25000

stators

56

54

53

50

47

40

TABLEVI.--BLADEPASSINGTONEATTENUATIONS

Corrected

revolutions/minute

10671

10137

9604

8537

7736

6402

Frequencyband

containing

broadbandnoise

20000

20000

16000

16000

12500

12500

Fulltreatment

attenuation

Treatment between

statorsattenuation

7.0

6.0

6.5

7.0

5.25

7.0

5.25

4.25

4.75

4.75

3.0

3.0

Percentage of

attenuationfrom

treatment between

stators

75

71

73

68

57

43

NASA/TM--2000-209916 15
0

mine

Z

0

"IIX:

LLI

eL

m

"O

U.

0

Z

0

m

ia

UJ

ft.

0

0

I,.,.

(/

I • ! j

0 0 0 0

!

0

uD

,r0

-W

,qD

-IJD

-¢_1

-I"

0

0

q.

N

-r

0

Z

W

0

W

Z

W

Z

m

.J

W

ffl

<

m

,i

<

I0

W

O.

Z

.1

IX

m

lk

.... ' 8P '1t^_1 3tlllSS=lUd aNnOS

NASA/TM--2000-209916 16
Ino

rrO

U.

rn

C3

UJ

(J

r_

uJ

re

In

.JzO

l-

(JmZO

rr<

2;

n-

.J

a. m

c_

u. OZOm

k-

(J

r_

uJ

rr

)

7

)

))

)

mE

a.

).

9 U. O

(J

_'II;I

O0000

0 O) QO I_. CD

I"

/

O

8P '13A31 =IUrlSS3Ud QNNOS

.O

-coN "r

(.) Z

(D I,Ll 0

I,Ll

U') n,"

U..

(',,I

. ,i,.., 0

O

,q,

Z

,<

u_

,,.I <Z0

atom

I-. Z

U.l >Z0

(..I

,g0

UJ Zm

t-ZO

(J

ILl m

U.

NASA/TM--2000-209916 17
(n

u) :E

nrr 2:

0

-r. i_-

O w

Q.

w

Z "O

O

..j (9

u. u_

O 0

n- z

-1 0

mira

rn _.

• O

Z a

wE

O

_J

e_

O

IL

"O

CD

UJ

O

tU

er

(/)

ILl

Z

O

I

O

O

I

O

J

!

O

cD

!

o

't"

o

-ol

-e0 N

-r

- h. >.T

O

Z

(D IJIJ

O

uJ

.in IE

U.

_r

.c,_

-iN

-I-

' -O I I

O O O

CD I_ q"

Z

==

111

h

.¢

d

W

,-I

Z

0

c.p

I.IJ

IJ.

laP '"l=z^=rl 31dlN_M,,a QNi'IO$

NASA/TM--20(R)-209916 18
Z

ttl

O

Z

m

Z

z

r_

Od

i11

m

NASA/TM--2000-209916 19
i

¢

a

I11

_1

(.1

Z

0

(.1

U.I

0

(n

U.I

Z

0

NASA/TM--2000-209916 20
t4

ttl

I

14.

ttl

m

a.

O

I-.

Q

©

Q

Q

W

Z

U,I

a,.

0

O

LLi

m

1,1.1

a

m

r,/)

S

i

J

J

J

J

J

J

J

cv)

0

0

Li.

r,,)

D

m

r,.)

_,1

,q.

@

rr

,.I

NASA/TM--2000-209916 21
W

I=-

.Q tc

z_E O

14,1

n"

14=

14,1

a.

144 n

ILl

a

g

7

0

-I

I.--

0

0

CO

.o.

0

0

14..

(.I

I

m

..I

14.1

NASA/TM--2000-209916 22
i:ili.iiii_!:i i i ̧

NASA/TM--2000-209916 23
u)

LUZ0

a.

a=

:Eox

u.

Z0u

F'-

LU

I--

U)

UJ

F-.

IZ)

T-- X

cr_ Zm

.J

UJ

r_0

LUm

U.

---t

b

III 0Z

o. 0m

_z w

F.-

//

/

/

/

,It

/

/

,/I

I11 0Z<Q

U.I

I--

l.- m

:E

I.U

U)

UJ

..J

2: <

I,U

U_<W

:E

NASA/TM--20(K_209916 24
nZ ..I

a ..a

IIl u_

¢,D

,r,,"

td

HI

m

tl_

NASA/TM--2000-209916 25
LONG STEM BLADE

FIGURE 6 CONTINUED

B. SECTOR OF WHEEL

NASA/TM--2000-209916 26
nO

T"'

ttl

el"

m

ILl

NASA/TM--2000-209916 27
i

Ill

Z

m

I,k

NASA/TM--2000-209916 28
ul

z

__!

le

O

Z

U.I

I.I.

\

\

LO Oq 0 I_ LI_ Cq 0 I_

CD

L_

LO

Oq

p_

0

d 0

r_

0

1.0

u_

OIJ.Vbl _HI'ISS:IHd

NASA/TM--2000-209916 29
w

it

NASA/TM--2000-209916 30
ALLISON

-ALNF-- _

......... 1-FOOT-L-OSSLESS I'_ATA

5 tB 15 2B 25 30 35 4B _.._ 5_

FREQUENCY, KHZ

FIGURE 11 COMPARISON WITH ALLISON FAN

NOMINAL TAKEOFF, ALLISON 840 FT/SEC, ALNF 1000 FT/SEC

A NARROWBAND DATA AT 92,5 DEGREES EMITTED ANGLE

NASA/TM--2000-209916 31
uJ

>

uJ

.J

uJ

o0

u3

uJ

o.

Z

0

(/) 1 FOOT LOSSLESS DATA

!

I I l

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 11 COMPARISON WITH ALLISON FAN

B

NOMINAL TAKEOFF, ALLISON 840 FT/SEC, ALNF 1000 FT/SEC

1/3RD OCTAVE DATA AT 92.5 DEGREES EMITTED ANGLE

NASAfrM--2000-209916 32
+

FREQUENCY, HZ

FIGURE 12 SOUND POWER LEVEL COMPARISON

WITH ALLISON FAN

NOMINAL TAKEOFF, ALLISON 840FT/SEC, ALNF 1000FT/SEC

NASA/TM--2000-209916 33
a

m .. ++o °./!

--.. I,... <

03 m+

,,,,__

I' I I

I_ g 0 0 m ID

uJ ""

_D

I

u_

q

q

.-lid

0

0

cO

"i

q.

NASA/TM--2000-209916 34
..I

ii

f

-,_ALLISON

FREQUENCY, KHZ

FIGURE 14 COMPARISON WITH ALLISON FAN

NOMINAL APPROACH, ALLISON 500 FT/SEC, ALNF 600FT/SEC

A. NARROWBAND DATA AT 92.5 DEGREES EMITTED ANGLE

NASA/TM_2000-209916 35
ii!

i

I

I

t

t

it

ALNI

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 14 COMPARISON WITH ALLISON FAN

NOMINAL APPROACH, ALLISON 500 FT/SEC, ALNF 600 FT/SEC

B. 1/3RD OCTAVE DATA AT 92.5 DEGREES EMITTED ANGLE

NASA/TM--2000-209916 36
r',J

m

"0

i

10 100

,.

1,000 10,000

FREQUENCY, HZ

100,000

FIGURE 15 SOUND POWER LEVEL COMPARISON

WITH ALLISON FAN

NOMINAL APPROACH, ALLISON 500 FT/SEC, ALNF 600 FT/SEC

NASA/TM--2000-209916 37
CD

m

[ ! I

CO I_-

cO

0

cD

¢o

cD

|

ul

NASA/TM--2000-209916 38
7736

i

6402

FREQUENCY, KHZ

FIGURE 17 COMPARISON OF SOUND PRESSURE LEVEL

AT DIFFERENT SPEEDS

A. 7736 RPMC, 6402 RPMC

92.5 DEGREES EMITTED ANGLE

NASA/TM_2000-209916 39
17736

5 I_ [5 2_ 25 3_ 35

FREQUENCY, KHZ

4B 4S 50

FIGURE 17 CONTINUED

B. 8537 RPMC, 7736 RPMC

92.5 DEGREES EMITTED ANGLE

NASA/TM--2000-209916 40
FREQUENCY, KHZ

FIGURE 17 CONTINUED

C. 9604 RPMC, 8537 RPMC

92.5 DEGREES EMITTED ANGLE

NASA/TM--2000-209916 41
FREQUENCY, KHZ

FIGURE 17 CONTINUED

D. 10137 RPMC, 9604 RPMC

92.5 DEGREES EMITTED ANGLE

NASA/TM--2000-209916 42
} r _" 10671 --'-'_,i

' i 1013 _ --_ [ :

i

! I

5 i_ L5 2_ 2.5 3_ 35 4iP 45 5_

FREQUENCY, KHZ

FIGURE 17 CONCLUDED

E. 10671 RPMC, 10137 RPMC

92.5 DEGREES EMITTED ANGLE

NASA/TM--2000-209916 43
113

IX3

........................ _.--_4-_ ..... "T.... 4.........!-F-t ! -i-F.......... _...... ' _..........

_.__ i _ ,'...... "-4---. --.-...; ...... _._.._l_J._l LLL:- ........ ¢ • ._ __J_ __, 0___ ...... _ i i

t i: --!i ]! ! I I , _ I _ I :, ................ Z _ :........ = ........ -' i

' : i;i ; ' ! !C I} ;

l ' ,;_ _ II i II I I _ ' i ;! J

: ! Ii I!i i_, I

i: i I li I! _11111 i ! _ ,[,7 I L_

, _i!: I I I! _ !'-_ ! i i......l'_- I _ I , !

,, -

' , [ ! _, I i

' _ :i I ! i .....

_ t ' I I I i _ , :

: i.:i I I 1 l: / / i , i;

.... ', ..... ........ _ -_--[- ZJ.............-T....... iq-i-TY ........-'--_ ................. [-[i:--

! : ! ! ii:

: _ : ; [ I ' : [ !

, i ,;; i i litlt ' : ;:

I t

10 100 1,000 10,000

J

100,000

FREQUENCY, HZ

FIGURE 18 COMPARISON OF SOUND PRESSURE LEVEL

AT DIFFERENT SPEEDS

A. 7736 RPMC, 6402 RPMC

92.5 DEGREES EMITTED ANGLE

NASA/TM--20(Kb209916 44
, ! ! iii!

i , r :.

m t

10 100 100,000

FREQUENCY, HZ

FIGURE 18 CONTINUED

B. 8537 RPMC, 7736 RPMC

92.5 DEGREES EMITTED ANGLE

NASA/TM_2000-209916 45
tO

10

i

!

i

| ! : ,

100 1,000 10,00.0

FREQUENCY, HZ

FIGURE 18 CONTINUED

C. 9604 RPMC, 8537 RPMC

92.5 DEGREES EMITTED ANGLE

NASA/TM--2000-209916 46
!

"i

10

, i ' 1 i l 1

i .... i_ I If _I I

: " :' i _ ! i ,.";"I0137.._

.. I ,j j , , -_

" ' _. 'i _ = T' I.._I It q I : I _ ,__i

............ --4..- ..... _..... :_,,.u.._L_ ___ ....... _-----._---l--_J,_.-!-,_ ..+-- _ _ ......... : ..................

_ ! ; 1 I i ! II,"-_ -F-

• : i L'' :_I t I /|/I _ _ : '__,_ : i

....._ ...... _-÷_-r"l_---_" T---'F'rT--__ .... !..... _ i _i ;, -" ..................

......-_......,-.-!-..i-_.-?..i..r._-l--_-_-,,, __ _ _-I-__,414---i--;-_L..!_:_....:. ;.,....................?

,,I I!I ,

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 18 CONTINUED

D. 10137 RPMC, 9604 RPMC

92.5 DEGREES EMITTED ANGLE

NASA/TM--2000-209916 47
,,.¢

.,-i

10

k , : ; ' ' i i i i ' _ !

.................. _...... i............i.... I______LJ_[II / i ; L 10671 !

i :ii I I-T_-_ F_........... !!i-_ ........... ' :_::,-i

i i i!i!i J J ! ! l!Ifl _! ! _ i l--i , i _ il

i i !

: i , ,! !

i _::i i I i!III I i _ :

............ _I..... ' ......... i [ i !ii ':i I;..................... ! !_-_! ir....... r--'f-_--,'--_i il;-i-_.............. :_........ : _--! ",

; I

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 18 CONCLUDED

E. 10671 RPMC, 10137 RPMC

92.5 DEGREES EMITTED ANGLE

NASA/TM--2000-209916 48
64O2

I

10,000 100,000

FIGURE 19 COMPARISON OF SOUND POWER LEVEL

AT DIFFERENT SPEEDS

A. 7736 RPMC, 6402 RPMC

NASAfI'M--2000-209916 49
IT)

i

10

I

1,000

t

10,000

I

100,000

FREQUENCY, HZ

FIGURE 19 CONTINUED

B. 8537 RPMC, 7736 RPMC

NASA/TM_2000-209916 50
r ! i !

'i 1

! !,

I i

I

I

lOO 1,000 10,000

FREQUENCY, HZ

FIGURE 19 CONTINUED

C, 9604 RPMC, 8537 RPMC

NASA/TM--2000-209916 51
r-i

e-1

! J ill

i i I IIii !

! i I _ lltl/l

........... _ :-i-h-_77-_7-

I lJ I

_ il_,

: ' i 1

......... :....... _--T-, __,7 ......

P I I I

i _ _ ill I I

, 1 _ i _ !!ltlc::t J :

i t i _ iilll ! :

i t l_iifll J

.... F--r" -_ T-'T-l-Xl-7------r--- ' iiLl i li!!_

I

t_

10 100

!

1,000

FREQUENCY, HZ

'i

I

10,000 100,000

FIGURE 19 CONTINUED

D. 10137 RPMC, 9604 RPMC

NASA/TM--2000-209916 52
,.I

!

100 1,000 10,000 100

FREQUENCY, HZ

000

FIGURE 19 CONCLUDED

E. 10671RPMC, 10137 RPMC

NASA/TM--2000-209916 53
0

_-. 0 __

I,LI

0

¢_

UJ

U.

f- ....... i ! T

0 0 0 0

,!,,-

0

8

¢_1

°i

- q.

|

Q.

ILl

NASA/TM--2000-209916 54
FIGURE 21 EPNdB VERSUS SPEED

SCALE FACTOR EQUAL 3.0

92.00 -

Z

88.00 -

84.00 -

80.00 -

76.00 -

/

J

I

0....-

72.00 1 ' i I I

6000.00 7000.00 8000.00 9000.00 10000.00

CORRECTED RPM

I

11000.00

NASA/TM--2000-209916 55
.,.I

- 70 V_NES

70 VANES

f 5 10 [5 2tl 25 3_ 35 40 45

FREQUENCY, KHZ

5_

FIGURE 22 COMPARISON OF 7 VANE AND 70 VANE DATA

A 8537 RPMC, 24.5 DEGREES

NASA/TM_2000-209916 56
9

.J - Z() __NE4

(/_ _ I/2-BPF - 7 V_NES

i

7 NES

I, Jl tlJl ! J, I

!

7 VANES _ ' -_Jl_ ..... ,, i_[J_.

# 5 1_ L5 2_ _5 3P 3B 4g 45 B_

FREQUENCY, KHZ

FIGURE 22 CONTINUED

B 8537 RPMC, 130.5 DEGREES

NASA/TM--2000-209916 57
¢-I

UO

N

N

70 VANES i

70

I

l

i

FREQUENCY, KHZ

FIGURE 22 CONTINUED

C 10671 RPMC, 24.5 DEGREES

NASA/TM--2000-209916 58
_a

io

¢-I

Cc

O

_a

D-.

5 1_ L5 2_ 25 3_ 35 aP 45 5_

FREQUENCY, KHZ

FIGURE 22 CONCLUDED

D 10671 RPMC, 130.5DEGREES

NASA/TM--2000-209916 59
c-4

b')

£

ii

I'

_a

t_

10

I

100,000

FREQUENCY, HZ

FIGURE 23 1/3RD OCTAVE COMPARISON OF

7 VANE AND 70 VANE DATA

A 8537 RPMC, 24.5 DEGREES

NASA/TM--2000-209916 60
10 100

!

1,000

FREQUENCY, HZ

10,000 100,000

FIGURE 23 CONTINUED

B 8537 RPMC, 130.5 DEGREES

NASA/TM--2000-209916 61
Er.

!

lO 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 23 CONTINUED

C 10671 RPMC, 24.5 DEGREES

NASA/TM_2000-209916 62
i

0

_0

10

: ! ! i i

! i i _ i

i i i

i !

I

100

'i ii <

I ii! I

! i l ! i;

I I

1,ooo lO,OOO 100,000

FREQUENCY, HZ

FIGURE 23 CONCLUDED

D 10671 RPMC, 130.5 DEGREES

NASA/TM--2000-209916 63
m

LU

O

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 24 SOUND POWER LEVEL COMPARISON OF '1

7 VANE AND 70 VANE DATA_

A 8537 RPMC

NASA/TM--2000-209916 64
UJ

(n

10

.I

100

!i

!

1,000

i ,

i

i

L

10,000 100,000

FREQUENCY, HZ

FIGURE 24 CONCLUDED

B 10671RPMC

NASA/TM--2000-209916 65
-70 VANES

I

i ! ! i _

I

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 25 FRONT AND AFT POWER LEVEL COMPARISONS OF

7 VANE AND 70 VANE DATA

AFRONT POWER AT 8537 RPMC

NASA/TM--2000-209916 66
h_

r',J

r.,J

,l=d

Z ""

:0

0

I0

I0

to I

10

I

1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 25 CONTINUED

B AFT POWER AT 8537 RPMC

NASA/TM--2000-209916 67
/-70 VANE

S

100,000

FREQUENCY, HZ

FIGURE 25 CONTINUED

C FRONT POWER AT 10671 RPMC

NASA/TM--2000-209916 68
10 100

I

1,000

I i+i ;:

I I

10,000 100 000

FREQUENCY, HZ

FIGURE 25 CONCLUDED

D AFT POWER AT 10671 RPMC

NASA/TM--2000-209916 69
(n

5 1_ [5 Z_ 25 3m 35 4B 45 5_

FREQUENCY, KHZ

FIGURE 26 SPECTRAL COMPARISON OF HARD AND FULLY TREATED

DATA FOR THE 7 VANE CONFIGURATION AT 6402 RPMC

A 24.5 DEGREES

NASA/TM_2000-209916 70
O

(n

HAfID i

i

FREQUENCY, KHZ

FIGURE 26 CONTINUED

B 92.5 DEGREES

NASA/TM--2000-209916 71
¢-t

U_

_4

m

#

I

FREQUENCY, KHZ

FIGURE 26 CONCLUDED

C 130.5 DEGREES

NASA/TM_2000-209916 72
t.-1

IS')

N

.J

uJ

_i

(n

i

J

..,...--TREATED I/

I

I

/

_j

ID

_O

o0 1 I I

10 100 1,000 10,000

FREQUENCY, HZ

100 000

FIGURE 27 I I3RD OCTAVE COMPARISON OF HARD AND

FULLY TREATED DATA FOR THE 7 VANE COt4RGURATION AT 6402 RPMC

A 24.5 DEGREES

NASA/TM--2000-209916 73
100 1,000

! i ! I !_II -

v

...... i_!

100,000

j i_ii  ̧

t i !i_

I i _,_i

g

I _ _ ! _ _ _ _ _ r

li !!

II _| ! i

10,ooo

FREQUENCY, HZ

FIGURE 27 CONTINUED

B 92.5 DEGREES

NASA/TM--2000-209916 74
O

li')

I)O

i

'HARD

: 'TREATED

IX:)

I i I i

10 100 1,000 10,000

FREQUENCY, HZ

1

100,000

FIGURE 27 CONCLUDED

C 130.5 DEGREES

NASA/TM--2000-209916 75
i

bD

I--.

1 i

• i i i J i

5 iO L5 2_ 25 3_ 35 4_ 45 5_

FREQUENCY, KI-_I

FIGURE 28 SPECTRAL COMPARISON OF HARD AND FULLY TREATED

DATA FOR THE 7 VANE CONFIGURATION AT 8537 RPMC

A 24.5 DEGREES

NASA/TM_2000-209916 76
F_

,:-I

b_

.P4

.Z

D

0

I",

i

TREATED

5 I_ t5 2_

FREQUENCY, KHZ

FIGURE 28 CONTINUED

B 92.5 DEGREES

NASA/TM--2000-209916 77
UJ

FIGURE 28 CONCLUDED

C 130.5 DEGREES

NASA/TM_2000-209916 78
¢-t

I/3

_J

'1-4

m_

qD

J

ILl

i I_i,I

• i i ! i ' i

!iiiii!

[O

_O

I

10 100

I

1,000 10,000 100 000

FREQUENCY, HZ

FIGURE 29 1/3RD OCTAVE COMPARISON OF HARD AND FULLY

TREATED DATA FOR THE 7 VANE CONFIGURATION AT 8537 RPMC

A 24.5 DEGREES

NASA/TM--2000-209916 79
O

I

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 29 CONTINUED

B 92.5 DEGREES

NASA/TM_2000-209916 80
10

HARD

:

TREATED

100,000

FREQUENCY, HZ

FIGURE 29 CONCLUDED

C 130.5 DEGREES

NASA/TM--2000-209916 81
U)

UJ

U)

FIGURE 30 SPECTRAL COMPARISON OF HARD AND FULLY

TREATED DATA FOR THE 7 VANE CONFIGURATION AT 10671 RPMC

A 24.5 DEGREES

NASA/TM--2000-209916 82
,F,

!

I

1£3

r'd

m

d

U.I

UJ

O.

Z

o_

(n

HARD

I

b'_

[I0

5

FIGURE 30 CONTINUED

B 92.5 DEGREES

NASA/TM_2000-209916 83
W

HARD

FREQUENCY, KHZ

FIGURE 30 CONCLUDED

C 130.5 DEGREES

NASAfFM_2000-209916 84
,r..1

LO

I)(3

tO

10 100,000

FIGURE 31 1/3RD OCTAVE COMPARISON OF HARD AND FULLY

TREATED DATA FOR THE 7 VANE CONFIGURATION AT 10671 RPMC

A 24.5 DEGREES

NASA/TM--2000-209916 85
I

1,000 100,000

FREQUENCY, HZ

FIGURE 31 CONTINUED

B 92.5 DEGREES

NASA/TM--2000-209916 86
I! ! i_

I

! !

I

1,000 10,000 100

FREQUENCY, HZ

000

FIGURE 31 CONCLUDED

C 130.5 DEGREES

NASA/TM--2000-209916 87
i

I

1,000

FREQUENCY, HZ

- HARD

! TREATED

]

I I I 1-

10. 100 10,000 100,000

FIGURE 32 SOUND POWER LEVEL COMPARISON OF HARD AND FULLY

TREATED DATA FOR THE 7 VANE CONFIGURATION

A 6402 RPMC

NASA/TM--2000-209916 88
10 1,000

FREQUENCY, HZ

FIGURE 32 CONTINUED

B 7736 RPMC

NASA/TM--2000-209916 89
' t t

i ! i i i,i_i t

_' ................ i _ !.....!--i _-:ff¢i ......... t---..............

; ! t _ _ i !  ̧ i

! i i ! ! i ti_ _ I

I ' ! : r i !!

! _i! i

'_ _',1! I ! i

! i ii , ;

..... ,iili,'il ii i i i I ,

I_ , -+...._t---_-! -

' _!il t

! i i _Ii! i !

................ _---_--_" I I-i

I ! _!,,i

' i i itl, ' i

, !

i I

i I

10 100 1,000

FREQUENCY, HZ

FIGURE 32 CONTINUED

C 8537 RPMC

NASA/TM--2000-209916 90
_z

I_J

m

"O

uJ

m

(n

1,000

FREQUENCY, HZ

10,000 1001000

FIGURE 32 CONTINUED

D 9604 RPMC

NASA/TM--2000-209916 91
f

FREQUENCY, HZ

100,000

FIGURE 32 CONTINUED

E 10137 RPMC

NASAfFM_2000-209916 92
bJ

1J.I

U.l

0

L¢)

EO

10

I

100

II

I |

II

1,000

i ! , i ii

]

10 000 100,000

FREQUENCY, HZ

FIGURE 32 CONCLUDED

F 1O671RPMC

NASA/TM--2000-209916 93
¢-I

1

u')

D_

tO

t

10 1,000

FREQUENCY, HZ

I HARD

I i

10,000 100,000

FIGURE 33 FRONT SOUND POWER LEVEL COMPARISON OF HARD

AND FULLY TREATED DATA FOR THE 7 VANE CONFIGURATION

A 6402 RPMC

NASA/TM_200(0209916 94
F_

ID

f_J

,,..d

0

GO

b")

r,o

I

10

1 /

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 33 CONTINUED

B 7736 RPMC

NASA/TM--2000-209916 95
i i _ i _

' i !; j| I|

; !i-',ii

i , i I

.......... ---r- _---_'-_- ! 7"7 ! ..............-_..... !......

i i_,'! i i

! :, i

i !! i_t

..........4.......... -4--'_-L-__4-,-- --_

i _iiil [i [ I"

m i i_ ! i i

• i i i_

i ] ! i _ i;

i fill|

'. 11,1i

..... _ _--T._. FT. K.7_

! i !!I

H

© I

10 100

........ L--J;--_..-

i i

I

1,000

FREQUENCY, HZ

FIGURE 33 CONTINUED

C 8537 RPMC

NASA/TM 2000-209916 96
r.,J

m

d_

I,I,,I

UJ

" ,,,,,,,,I

LLI

o

IO

I

10

I I I

III ,

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 33 CONTINUED

D 9604 RPMC

NASA/TM--2000-209916 97
i

100 1,000 10,000

I

100,000

FREQUENCY, HZ

FIGURE 33 CONTINUED

E 10137 RPMC

NASA/TM--2000-209916 98
to

DO

I

10

I I

i I

I

II

II

I

I 1 I

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 33 CONCLUDED

F 10671 RPMC

NASA/TM--2000-209916 99
!

iIo

lO

! iilil i i

i i i ii I fill

! I I|I I I i ! ! _ '

' '_ i,lll ' I i lI!l I I i i HARD

....... :---_!"TT-:Ti i----7-, -7-X-_F-"-_t .... -T-- t--]--: t ' _ '

, , _ _,I =_ llll | i , _iil, I _ I

: : _ :,'_ il IIL] ! h_i. mE_ll_!:ll ! Ir--t-I I < ' ! : : , * i_LJ._%z-_[.t .L_.L-.

! { i iJ_ I ! i !_ ..........

!!!!!

............... r rTTTtt-i--7 ....r 7_ 7TII L

i I I 1 i

_iI=:_ ! I ! I

IIIi I :

; ii i , _: ill i I Ii 1 { i

7 : I I r 7

_ ,,,ll i i i l tt i: ,_' • : _ I I t

t I

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 34 AFT SOUND POWER LEVEL COMPARISON OF HARD

AND FULLY TREATED DATA FOR THE 7 VANE CONFIGURATION

A 6402 RPMC

NASA/TM--2000-209916 100
O

1,000

FREQUENCY, HZ

FIGURE 34 CONTINUED

B 7736 RPMC

NASAFFM_2000-209916 l 01
J 9-i

...I

o

(n

1,000

FREQUENCY, HZ

I

100,000

FIGURE 34 CONTINUED

C 8537 RPMC

NASA/TM--2000-209916 102
,_ ,, J--! IIII . |! _ L'.HARD

;i '_',i! ) | 1]!1 ! : !1 R_ ,_:

, i! I I! | tltt / " ' ! I --1' , ,_

,,.I 113 i , : ,, {i t--,-iq _REATED , _ r-i: ' L F

........... T........... t-- -i- _'T-_T1............ _,"-_.........T-F .....l ...........---T ......... i t .......i r .....i' i

_,..,.................................. : : :._ ! !i-:_!-)_!_ .................. I !{......... _-t-4-"!i........ ......_!-IIITI_ 'i ...._-_! !; IF r"-J....... LG.-'7 . ,

± i i lilt L__L_ 1 i I

;

[ _ : , : I : ) _ I I I

; , _ i I | ' ;

, _! !1 I ! l 1 ! ! , :

" i i I !

, ,,,,iil } i i ! _ i t , i i ,1111 , , r , .....

, _ i_ ! i11 ! t / :i

' i | ' ! ....

........ :.........,, !....... Li2 .................. -4- .l-........................... !--!.!.!.!,._...........i ....... !...........

' I ! iii '=

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 34 CONTINUED

D 9604 RPMC

NASA/TM--2000-209916 103
IO0

FREQUENCY, HZ

FIGURE 34 CONTINUED

E 10137 RPMC

NASA/TM--2000-209916 104
0

I)o I

10

I

100 1,000

FREQUENCY, HZ

FIGURE 34 CONCLUDED

F 10671RPMC

NASA/TM--2000-209916 105
I

FREQUENCY, HZ

I

100,000 _

FIGURE 35 DIFFERENCE IN SOUND POWER LEVEL, HARD MINUS

TREATED, FOR THE 7 VANE CONFIGURATION

A 6402 RPMC

NASA/TM--2000-209916 106
P,,l

".I

m

o

i °

1:3

ID

10

- _ i il.

l!_i__

i [ t _ . ,

' i !iii_

j ! '_

i I i i!li !! i!

...... +---i.. +-_ .......... ..........................._..........

i I + + ; +t

+ + It t i

+ i + +

..... +....... ..++_+..+.+++:.

, ! + i +_:

: ' + i i+ +

+ + •

+ + + ++ +

I ' + + j + : t

+ + ++ ++; + i I I i + : + :

i + i + J I I I i +j l + I ; + + + +

............... ..... ,+:-_............ ; ...............I--j +-i¢-44.................. ;........ -+-._--- • ......................... f+++

i ! ++ ! ++

} i : :

; i tJl i _' : !

+ + + J + + + + _ + +

: + i i ijlF: ! _ I I '

.................................

_++++ .++..+, ? +..........:__J +....++.d_+HJ ................... +.

|

...... +.;.._,.-_.. ......... +

+ + + I+i l . +

,+ ,_ I+ + ++ .+ +

: i : + I l/ f ! : _ r-'-I : t--:

...........: ......... , '+ i.... : P+q+"+;'+............... ......... ................... +....... +"...... _"+ -+ _ ...............

! : _ _ ,

i ]i '. i

i i + : " ]

I t t

1OO 1,OOO 10,OOO 1OO,OOO

FREQUENCY, HZ

FIGURE 35 CONTINUED

B 7736 RPMC

NASA/TM--2000-209916 107
u--

FREQUENCY, HZ

FIGURE 35 CONTINUED

C 8537 RPMC

NASA/TM_2000-209916 108
FREQUENCY, HZ

FIGURE 35 CONTINUED

D 9604 RPMC

NASA/TM---2000-209916 109
r_J

d

.,I

1.1,1

1,1,1

Z

1,1,1

U,i

I,I.

u.

0

I

f

10

F :

! I

I

_!!i i i

:_' [ i

; ] I

: [

I

i : i I :

: i

:i

i ' 1

; _'il i !I j

1

100

: li

I I i ::

: ! i

i _ ] , .

"Yi ...................

1 :

'i V- ...................... i"" : ....:: ....

; _ill

:!! r-_ : i _ [-'-]

/ i -I

I I Ir--_ L_

i i :

i

t 1

1,000 10,000

FREQUENCY, HZ

100,000

FIGURE 35 CONTINUED

E 10137 RPMC

NASAfrM_2(KK)-209916 l l0
m

"O

,J

r'.J

.,I

_2

Z

0

(n

z

m

0

Z

W

rr

W

IJ.

b')

I

I

i;

l

i

I

]

i ; r

10 100 1,000

i

FREQUENCY, HZ

I

10,000 100,000

FIGURE 35 CONCLUDED

F 10671RPMC

NASA/TM--2000-209916 111
• ' !ili

I,M _ _ _ i  ̧I_I !

,ml i _ i i : ,,

, _ I t

IJLI _ i ii_

' _ I

10 100 1,000 10,000 loo,oo0

FREQUENCY, HZ

FIGURE 36 DIFFERENCE IN FRONT SOUND POWER LEVEL, HARD

MINUS TREATED, FOR THE 7 VANE CONFIGURATION

A 6402 RPMC

NASA/TM--2(KI0-209916 112
FREQUENCY, HZ

FIGURE 36 CONTINUED

B 7736 RPMC

NASA/TM--2000-209916 113
!i

Z

I,I,I

I

"qD

I

10

I

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 36 CONTINUED

C 8537 RPMC

NASA/TM--2000-209916 114
I

!i 'i

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 36 CONTINUED

D 9604 RPMC

NASA/TM--2000-209916 l 15
P,J

U,I

-I

U,I

Zm

b'_

I

10 100

! •

1,000

FREQUENCY, HZ

i :

I

10,000 100,000

FIGURE 36 CONTINUED

E 10137 RPMC

NASA/TM--2000-209916 116
_a

bJ

m

"O

.jU.l

,,>,_

--I

_3

Z

0

(n

ul

Z

W

.1

IlL

I1")

I

10

i i!!

;i!

I i!il

: _iil

: i I : i

i

i

• !

i ,

i_ i' i :

i •

i !i

i ! i

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 36 CONCLUDED

F 10671RPMC

NASA/TM--2000-209916 l 17
Z

I

_o

I

t 1 I I

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 37 DIFFERENCE IN AFT SOUND POWER LEVEL,

HARD MINUS TREATED, FOR THE 7 VANE CONFIGURATION

A 6402 RPMC

NASA/TM--2000-209916 118
o

i °

',o

I

i, ,_,_ _'_I]_i ! _'I,

: : ,_,i _ L--t_............... ;- i: :'_' _

' I I ! i ! i I i

............ _......i -PU:i-:!............. i--_ .......-t- i i-!_............ !......... ...... _--_• _ I .......

: i ii ! ! i ! Ili i i i / / r--

' I ' i

,._,, _ L t-h, 11_i _i _,

! :; ':L- ......._..kL4-LW ---_ 4L-_,_- ................. .-_-_,

............. -T' .............................. ' ....... i ........ : "Wi-/: .... :

i : i i ! _ _ Iq--4i!l I! i ; : : ' I!

k

..................... :......1.4-4 ........................ 4-......._.-i-44--.!.!-i .............. :......... -.....

i i , , I

10 100 1,000 10,000

1

100,000

FREQUENCY, HZ

FIGURE 37 CONTINUED

B 7736 RPMC

NASA/TM--2000-209916 119
,,=,

r'd

z

UJ

0

Z

UJ

ec

ILl

IZ.

u.

I

"0

I

10

I 1

100 1,000

FREQUENCY, HZ

I

10,000 100,000

FIGURE 37 CONTINUED

C 8537 RPMC

NAS A/TM_2000-209916 120
I

i i

FREQUENCY, HZ

FIGURE 37 CONTINUED

D 9604 RPMC

NASA/TM--2000-209916 121
I_J ' _ _I_ ! ii i I _ ! i i

i i i I/ _ I:1

! "i i I/ I I

i :ii i , ! I/ _ : I I

! t ; i I _ ]

: : _ : _ i i ! I/J r_ I r

: ir i '_ _1 _ i 1_._1

, i : !,: I II i ! :; :

' : ::: i--71 I .._1! " .... ai A---I

7

t"'l i _ ! 7 _ :

i i! : i

, :i!i_ 7"i. _,

• ci i i { f !

i !

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 37 CONTINUED

E 10137 RPMC

NASA/TM_2000-209916 122
i

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 37 CONCLUDED

F 10671 RPMC

NASA/TM--2000-209916 123
¢"1

to

m

d

'a

0.,

5 I_ 15 2_ 2A 3_ :35 4_ 45 5_

FREQUENCY, KHZ

FIGURE 38 SPECTRAL COMPARISON OF PARTIALLY TREATED AND

FULLY TREATED DATA FOR THE 7 VANE CONFIGURATION AT

6402 RPMC

A 24.5 DEGREES

NASA/TM--2000-209916 124
u)

U.I

a.

O

FUU_Y !

: !

•,TREAEI_ED

PARTIALLY TRE_I"ED

TI_EATED

FREQUENCY, KHZ

FIGURE 38 CONTINUED

B 925 DEGREES

NASA/TM--2000-209916 125
,:-1

.,J

(n

UJ

rr

O

(n

i

LY-TRE/

REATED

25 3P

TREA_

FREQUENCY, KHZ

FIGURE 38 CONCLUDED

C 130.5 DEGREES

NASA/TM--2000-209916 126
N

_O

_o

FIJU-Y ?I_.ATED _

\

\

\

TREATED

E

I I !

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 39 1/3RD OCTAVE COMPARISON OF PARTIALLY TREATED AND

FULLY TREATED DATA FOR THE 7 VANE CONFIGURATION AT 6402 RPMC

A 24.5 DEGREES

NASA/TM--2000-209916 127
10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 39 CONTINUED

B 92.5 DEGREES

NASA/TM--2000-209916 128
°i

i _ i i i t ! I

I :i ]! _, , ' _ '

'_ _ _ i i l | 1| : i :PARTIALLY TREATED '

• _ i _, i == I I II! - i -i ! i i _:,I I _,

! I _ _ ! L--I ! -t'-'i

! : ! i lill .1._ _ __

I

,. ! i _i ii i I I ! li! i_ ! i i :: i _ _ '

:_ I _' ' ; I ! i , [ _ ' I i _, ! _

! , _ , Ill I! | ! :i i : !,

, _ _ ! _ I it! ] ! i ! ! i '

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 39 CONCLUDED

C 130.5 DEGREES

NASA/TM--2000-209916 129
=i ,,>,

,.I

0.=

O

Z

0

I

I

5 i+ t5 2_

r

25 3m 35 4 [_ 45 5_

FREQUENCY, KHZ

FIGURE 40 SPECTRAL COMPARISON OF PARTIALLY TREATED

AND FULLY TREATED DATA FOR THE 7 VANE CONFIGURATION

AT 8537 RPMC

A 24.5 DEGREES

NASA/TM_2000-209916 130
b')

m =

"O

J_

>

u.I

rr

(n

(n

Lu

r_

n.

z

o

(n

r_

_ULLY

FREQUENCY, KHZ

FIGURE 40 CONTINUED

B 92.5 DEGREES

NASA/TM--2000-209916 131
.3

uJ

ILl

,.J

UJ

n-

(/)

UJ

a

O

5 i_ t5 2_ 25 3_ 35 4ff 45 5_

FREQUENCY, KHZ

FIGURE 40 CONCLUDED

C 130.5 DEGREES

NASA/TM--2000-209916 132
10 100 1,000

FREQUENCY, HZ

10,000 100,000

FIGURE 41 1/3RD OCTAVE COMPARISON OF PARTIALLY

TREATED AND FULLY TREATED DATA FOR THE 7 VANE

CONFIGURATION AT 8537 RPMC

A 24.5 DEGREES

NASA/TM--2000-209916 133
[ ' /1tlii J ' '

• i ! ! I I !_: I

! ! * _ | PAR_r, ALLY,TREA_ED • _ _ _ li" "" t zT.#::-.

"_ .':: l; 11--I!il II '_ . ; _ t i.

,.,,.I

__ . } _....J "

: , I I ! 1 till ' _ " -

: ,o _ , : • , d_ I i i i i ,/! /_ ! FULLY TREATED , i

m

i

: : : ii.-)i i 1 tl ,

........... : .--..:.............. :......... .____Z-LZ.Lq............ _.-.L_v_, . .._....

; ', i !1f_1 i t' ,

' _ t ' Itll I I I I:' '

i _ ! I II!1 i i i

................. ...... _ I iv ! ! t I tll I R !--_ "*

t i l llll ; _ i

i' 1 , i i _ "

! . !- ! _ ] .,

_. . . i,, , I , I. .

I _ $ I

10 100 1,000 1O,OO0 10O,O00

FREQUENCY, HZ

FIGURE 41 CONTINUED

B 92.5 DEGREES

NASA/TM--2000-209916 134
J

14,1

>

I.IJ

W

UJ

Z

0

i! PARTIALLY TREATED

I

i { _1,

!1='

! f I ::

|

:ULLY TREATED _';

1

i

1,000 10,000

!

100,000

FREQUENCY, HZ

FIGURE 41 CONCLUDED

C 130.5 DEGREES

NASA/TM--2000-209916 135
J

u.I

>

I.U

-I

I.U

(n

U')

u.I

n.'

a,.

Q

Z

o

_n

|

: !

/

•" FULLY TREATED' :_ , ,

PARTIALLY TREATED

!

FREQUENCY, KHZ

FIGURE 42 SPECTRAL COMPARISON OF PARTIALLY TREATED AND

FULLY TREATED DATA FOR THE 7 VANE CONFIGURATION

AT 10671 RPMC

A 24.5 DEGREES

NASA/TM--2000-209916 136
............................................ _............... --.............. !............ A j...........................

I

-- ........

_=I_'i........................................ i :.............. !I- .................. _- i...................... Ii............... "........................

_I............................. ;........... i........... __L ................_.............._...........

"J _ .I, PARTIALLYt TREATED

!

I................. !........ ,,i&.._.!.2._,______.__L_LL___k It.ji.l .............

....................................... ATE'D I

5 1_ 5 20 25 3(_ 35 _1_ 45 5_

FREQUENCY, KHZ

FIGURE 42 CONTINUED

B 92.5 DEGREES

NASA/TM--2000-209916 137
r_J

U.I

_J

uu_

o)

I,U

C2 -_

Z

0_

(n

to

[0

TREATED

5 20 25 31_ 35 41_ 45 5_

FREQUENCY, KHZ

FIGURE 42 CONCLUDED

C 130.5 DEGREES

N ASA/TM--2000-209916 138
¢,PARTIALLY,

F_ TREATED

FULLY TREATED

1 /

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 43 1/3RD OCTAVE COMPARISON OF PARTIALLY TREATED

AND FULLY TREATED DATA FOR THE 7 VANE CONFIGURATION

AT 10671 RPMC

A 24.5 DEGREES

NASA,rI'M--2000-209916 139
N

m

,J

uJ

..,I

UJ

oUJ

Z

0

I0

I

11

ii

I 1 I

I k

i

iFULLY TREATED i

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 43 CONTINUED

B 92.5 DEGREES

NASA/TM_2000-209916 140
J : i i i

1,000

FREQUENCY, HZ

10,000

i

100,000

FIGURE 43 CONCLUDED

C 130.5 DEGREES

NASA/TM--20(0)-209916 141
,rl

U')

bJ

a.

a •

g

51

tO

! _ : i!!! I !

i i' i_i! I i !

i I ! i :

il i ; _

....... _ _-- .....- .... -t-: ........... , -_--, " -_--..................... !........ " --I........................

: _ , ! ! ! _ I i l I PARTIALLY TREATED

! ! :!

i i !i : i

: _ _ i IRJU_TREATED i [

! ; ' !I_!

,j i

i

: :lltl '

f' ) I

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 44 SOUND POWER LEVEL COMPARISON OF PARTIALLY

TREATED AND FULLY TREATED DATA FOR THE 7 VANE

CONFIGURATION

A 6402 RPMC

NASAfl"M_2000-209916 142
Z

o

t_

10

I j i •

1 I *

i

I

1O0 1,000 10,000. 100,000

FREQUENCY, HZ

FIGURE 44 CONTINUED

B 7736 RPMC

NASA/TM--2000-209916 143
nl

Z

0

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 44 CONTINUED

C 8537 RPMC

NASA/TM_2000-209916 144
,,I

(/)

i

DO

i _ i I i

i i _'' " t

; i i

i ! i i I ! ' ! i _ I

......... -4........._..... -J-_-i-H_----I---_ -- -_

!i!,! I _ I I i I

i i_i!Ji I i i !l

,, _ | i I i ! I J !

i - f _ Ill I : _ I I I

i ir !IHi

_L. :__. J_--- J-L-..4.---J---[--L-

;'ii!l i _, i il

i ! !!!_!1 _ t ii

:: : i!i_ill ! ! i l

f [ ) ; ] {

I

10 100

i !i PARTIALLY TREATED

i |_ I : '_' i--1 ; :

/ ' i i: I__.,.L_ _ i

,L__...... i........ ;... _ -_-_ ............ ....

L_-YTREATEDI k:_ ;_ _ _ i t

r ' i lj :!,

; i i : _

l J_----+ ......¢..... _ 't,-_ ;: ................................ ........TT'

i i :_, i i .

" t i i'_ i !

/I / i i .,

! i i ;_

l_ I ! l i _i:, i r: kl........._............ ,i......-4.-;--_ ...... ........i

i ! Ii

i • '

I :,,_

1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 44 CONTINUED

D 9604 RPMC

NASA/TM--2000-209916 145
P,J

.j "_

C2

Z

0

IJo

10 100 1,000

FREQUENCY, .HZ

FIGURE 44 CONTINUED

E 10137 RPMC

NASA/TM_2000-209916 146
10

' FULLY TREATED

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 44 CONCLUDED

F 10671 RPMC

NASA/TM--20001209916 147
FIGURE 45 FRONT SOUND POWER LEVEL COMPARISON OF

PARTIALLY TREATED AND FULLY TREATED DATA FOR THE

7 VANE CONFIGURATION

A 6402 RPMC

NASA/TM--2000-209916 148
0

10

I L

100 1,000

PARTIALLY TREATED , !i

i

10,000 100,000

FIGURE 45 CONTINUED

B 7736 RPMC

NASA/TM--2000-209916 149
10,000 100,000

FREQUENCY, HZ

FIGURE 45 CONTINUED

C 8537 RPMC

NASA/TM_2000-209916 150
1,000 10,000 100,000

FREQUENCY, HZ

.FIGURE 45 CONTINUED

D 9604 RPMC

NASA/TM--2000-209916 151
m

"O

d

IJ.l

l.lJ

..I

uJ

O

O.

Z

=)

0

(n

10 100

i"

! ,

I ! i! _

I

TREATE0

1,000 10,000 100,000

FREQUENCY, HZ .

FIGURE 45 CONTINUED

E 10137 RPMC

NASA/TM--2000-209916 152
,>,,

..I

rr

I.U

O

a,.

C_

Z

O

(n

::::1

[

FULLY TREATED

! i : i,

I :

: {

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 45 CONCLUDED

F 10671 RPMC

NASA/TM--2000-209916 153
[o

FULLY "rREATI_O

10 10,000 100,000

FIGURE 46 AFT SOUND POWER LEVEL COMPARISON OF

PARTIALLY TREATED AND FULLY TREATED DATA FOR

THE 7 VANE CONFIGURATION

A 6402 RPMC

NASA/TM--2000-209916 154
IJJ

0

i i___iPARTIALLY TREATED

! :

I

FULLY TREATED

• '_....... i/, ............. ....

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 46 CONTINUED

B 7736 RPMC

NASA/TM--2000-209916 155
10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 46 CONTINUED

C 8537 RPMC

NASAfrM_2000-209916 156
in

hJ

.,-4

.J

I1.

0

IX)

_D

1

10

i

100

| !

ii,!

i

1,000 10,000 100,000 •

FREQUENCY, HZ

FIGURE 46 CONTINUED

D 9604 RPMC

NASA/TM--2000-209916 157
10

I i ! ! i-,^D!

Jl I i i !

il l i i i !

i_R_IALLY TREATED

i i r

! i

!I ..... ' i

! : j :i

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 46 CONTINUED

E 10137 RPMC

NASA/TM--2000-209916 158
m

'ID

L_

r',.I

r'd

u,I

0

Z

:3

0

i

100

I

i

I

1,000

FREQUENCY, HZ

10,000 100,000

FIGURE 46 CONCLUDED

F 1O671RPMC

NASA/TM--2000-209916 159
I _ _ li ! ] ! i ; :

_ _ • : • li _ i_ _,j , | I , , _ :

...................,_ _ _......._---_-T--I:.......... ".......... I _-"-!T __:' _............. , _........ --I- -!-,-!_....... •

>.

; : ! J; i ! ! ;

L_3

• _ i i ! I i

' i _, ' ' lit

,o _ , , '_",: i I { I !i'_li / i _ '

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 47 DIFFERENCE IN SOUND POWER LEVEL, PARTIALLY

TREATED MINUS FULLY TREATED, FOR THE

7 VANE CONFIGURATION

A 6402 RPMC

NASA/TM_2000-209916 160
i _ I !fill I I ; I _ i_  ̧ : _ :_ ...................... ;..................... r"_-'_ .................. _................ _"T'"l ........i-i"i" ................... I............. "i i " : .............. ? .....

: J i f '

i .... 1 _ : ' ! ' ! !

,,-I, ,,I .....

">'_ ...... ........... ÷i-.......... ........ _tt_-ii................ _........ :

•J i ; :_ i !i i',

:::ii : i I Ii!il i ) ! : !::

.............. -':...... 4......................... ,----.4--V-4-_.-4_!--- .... 1......... : 4-..-i...... .........

"4" " ! _ _ _ I I ....

' ! l i

_, ........ ? •-_T,__ -,r-T]FT,_............. ,........ 1.......... r--._ ....

_ i : ::iI ! I iiiiill _ I : I "

. ib _;._ I iliiill i rr-] :._I

.................: i .-i-_t- ............ _....... i---;........i r 7 : I

, II! i "

_ : : ! i I ilitl , :' !

ii: I !IIii_, : '

', i: i ; i i i t! _

I I

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 47 CONTINUED

B 7736 RPMC

NASA/TM--2000-209916 161
10 100 1,000 10,000

FREQUENCY, HZ

I

100,009

FIGURE 47 CONTINUED

C 8537 RPMC

NASA/TM--2000-209916 162
10 100 1,000 10,000

FREQUENCY, HZ

100,000

FIGURE 47 CONTINUED

D 9604 RPMC

NASA/TM--2000-209916 163
[,D

i.

n_

"el

10 100

I I I

1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 47 CONTINUED

E 10137 RPMC

NASA/TM--2000-209916 164
100,000

FREQUENCY, HZ

FIGURE 47 CONCLUDED

F 1O671RPMC

NASA/TM_2000-209916 165
m

*0

l.IJ

>

ILl

,-I

0

a.

Z

0

(n

z

illml

Ill

0

Z

i11

n"

i11

I.I..

U.

Q

_a

[i.3 ............

IM

,y

,:tI

-o

t

; j I _ !

.............. _-_ - ......T--i_-T - -i-7-I-T-I ........ --i-...--*7 ....;_ !............

' iil I !!i I _ , _'

i I ! } ! I _ ' I ii I !

i!i,. _ |i '

: liir--*-'-I L_-'. i ii]i!' |ii : _

...... ........ " ; !:'_.............. _.... i ..... 4 .................................

!i, _ i i !!',

i !li ! _ i,l i , _ ,

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 48 DIFFERENCE IN FRONT SOUND POWER LEVEL,

PARTIALLY TREATED MINUS FULLY TREATED, FOR THE 7 VANE

CONFIGURATION

N ASA/TM---2000-209916 166

A 6402 RPMC
I

lOO,OOO

FREQUENCY, HZ

FIGURE 48 CONTINUED

B 7736 RPMC

NASA/TM--2000'209916 167
_2

Z

O

(n

z

i

ul

0

Z

Ill

rr

ii1

U.

IJL

, _i ii _

i_ ! i ! J

i_--_Ji ......... I..... i,-_-.'., : ̧- ̧

It !I ! ! i _ ! i__

.i._i ........ _....... I_..-7....... -:! .....................

i i! _ i :::

Ill ! :,-_-:J: _ "

I tIN ''-_ t !, _ • _,', ii

! ! I ! : ::

I I

10 100 1,000

FREQUENCY, HZ

10,000 100,000

FIGURE 48 CONTINUED

C 8537 RPMC

NASA/TM--2000-209916 168
I

10 IO0 100,000

FREQUENCY, HZ

FIGURE 48 CONTINUED

D 9604 RPMC

NAS A/TM--2000-209916 169
,,-I ........ _.........-_i _'__-*4___-I+t............ _.......... _.+..r_._ .......... ...... _.

i ! i H ! i i i

i J !i i

i i ! ! il I _ ! i

:i i ,! ii i : i ii ! i r_.

I'lL "4" ........................ .... : .............. ' .......... !"'] _ _"_ / ....... _ _ ! ........... -" ............

, . ; _ , _ t li{/ ! !

;

i: 1!}I / ,

! I ! ! e : '

t i ] I ' i I ! i I I : { _

: : ' __, _t t I,-44 I r-l] i l : !

z

....... , i ! ! _ _ I : i I i '

----_- • -i---_ ..... --_

! - | _ , ! i "

F I I

ii! ; I i _ i i '

,} ..... i

! I: :_= : i } 1

_i : i t;{ I i _ I , ; ! ,

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 48 CONTINUED

E 10137 RPMC

NASA/TM--2000-209916 170
"o

I

I _ I I

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 48 CONCLUDED

F 10671RPMC

NASA/TM--2000-209916 171
"O

..J

U.l

>

U.l

U.l

Z N

O

Z

m

U.l

o

Z

m_

IJJ

I.I.

Ijl. _-

m

_D

I

I

10 100 1,000 10,000

FREQUENCY, HZ

100,000

FIGURE 49 DIFFERENCE IN AFT SOUND POWER LEVEL,

PARTIALLY TREATED MINUS FULLY TREATED, FOR THE 7 VANE

CONFIGURATION A 6402 RPMC

NASA/TM--2000-209916 172
i _ _ _i, i I I !I ; ! : :ii ,,>,' .......................... .......... ,................................

,....... !-I........ ........... i...................'

i: ; ! !!| I i i:'_ ,

o. { .......................... _.. i...........i---H.... Tt .....ii-H ............. t...!--T:-H .............. fi

i II | ! I _ _ :r --_ I ' i

i , _1 II il / i I' .

........... ...... _-_--_:.--,': I !-J-,-4-! ...................................,:-_-- -t ,,_........... ' .

i ',iii , i i I :

T .......... _.......... !........... ;T, .................. _- -:-I!(i-I............................................

i ' ;If i I I ! i I : :

" ! i :ii " _ I i_ i i ! ,

'0 i i i_ - Ii ; I I , I i !_ii I

I I

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 49 CONTINUED

B 7736 RPMC

NASA/TM--2000-209916 173
10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 49 CONTINUED

C 8537 RPMC

NASA/TM_2000-209916 174
,.I

10

FREQUENCY, HZ

FIGURE 49 CONTINUED

D 9604 RPMC

NASA/TM----2000-209916 175
m

"0

d

i11

>

!11

..J

nill

0

O.

Z

0

(n

z

m

U.I

r.)

Z

U.I

IZ:

U.I

IL

IJL

m

a

10 100 1,000

FREQUENCY, HZ

I

10,000

t

100,000 'i

FIGURE 49 CONTINUED

E 10137 RPMC

NASA/TM--2000-209916 176
i ,

i

1,000 10,000 100,000 t

FREQUENCY, HZ

FIGURE 49 CONCLUDED

F 10671 RPMC

NASA/TM--2000-209916 177
m

I=

J

uJ

>

uJ

uJ

r_

U)

(n

uJ

rr

o.

Q

;[

0

(n

TREATED ____

TREATED TREATED I

_. HARD !

i t

TREATED

FREQUENCY, KHZ

FIGURE 50 SPECTRAL COMPARISON OF HARD AND FULLY

TREATED DATA FOR THE 70 VANE CONFIGURATION AT 6402 RPMC

A 24.5 DEGREES

NASA/TM--20(0)-209916 178
lARD

FREQUENCY, KHZ

FIGURE 50 CONTINUED

B 92.5 DEGREES

NASA/TM--2000-209916 179
FREQUENCY, KHZ

FIGURE 50 CONCLUDED

C 130.5 DEGREES

NASA/TM--2000-209916 180
m

.o

J

i11

>

1.

..I

ILl

rr

01

(/)

111

rr

n

13

Z

:3

o

(/)

i

!

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 51 1/3RD OCTAVE COMPARISON OF HARD AND FULLY

TREATED DATA, FOR THE 70 VANE CONFIGURATION AT 6402 RPMC

A 24.5 DEGREES

NASA/TM_2000-209916 181
m

"0

!11

>

i11

_1

U.I

n-

(/)

(n

1.1.1

rr

{1.

C2

Z

0

(n

10

I

HARD

100 1,000

FREQUENCY, HZ

10,000 100,000

FIGURE 51 CONTINUED

B 92.5 DEGREES

NASA/TM_2000-209916 182
i _ 'ii_ I I' !i: *__i i

r,_ ........ , i; "i  ̧................ _.......... -Ti !-_................... i.......: _

, , ,_ 'L " HARD

_ I I ' i

; , , r :

i i i i I '

---. .......... __--_-A...i ._........... _............ L---._-.-._-,_, ..... . ,__............ _-............... i

' _ ? .ili ! i ii i! i : '

.......... ._.....:..............................---L-4.... ?........... ?..... -a-- ........... _-.-, _ ....

. : ii , I

i . : _ r'T-1 1 I I I Ii i ! i I

,,,-ii................ :i: ........... Iil i _i'...L--I--I .rIT._.EA_ !. ................... ! :............. I .......... ,;

_ ..I/') " i _ i 2:i • L --o _ _ -......... i ,,_,4. , ................................... c ...... ,.......r ................ _ ..........

, _ , i REATED ....... ..............._ ._ _-._......_ _ ............_ .... _.,_

Dr'-

l i I _I il i i I 'i

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 51 CONCLUDED

C 130.5 DEGREES

NASA/TM--2000-209916 183
m

"O

.d

ILl

>

ILl

..J

ILl

IT.

(n

r_

U.l

f_

Z

O

m

bD

IM

LO

J

TREATED

J

- |D

TI_ATED

h'_ 5 I_ t5 2_ 25 3_ 35 ,__ 4..9 5_

FREQUENCY, KHZ

FIGURE 52 SPECTRAL COMPARISON OF HARD AND FULLY

TREATED DATA FORTHE 70 VANE CONFIGURATION AT 8537 RPMC

A 24.5 DEGREES

NASA/TM_2000-209916 184
- HARD

_- TREATED

HARD

I--.

5

FREQUENCY, KHZ

FIGURE 52 CONTINUED

B 92.5 DEGREES

NASA/TM--2000-209916 185
TRI =

FREQUENCY, KHZ

FIGURE 52 CONCLUDED

C 130.5 DEGREES

NASA/TM_2000-209916 186
i_i _ i i [--! _ ! i I TREATED

i , i 1 -

U3 : '

u.-, ! i i_ _!.... _ HARD .. __1 ;

: i , : 1 i

_• ' _ _ _ t--J! ! t

i :!i ii

i i ii ', i i '_

t

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 53 1/3RD OCTAVE COMPARISON OF HARD AND FULLY

TREATED DATA FOR THE 70 VANE CONFIGURATION AT 8537 RPMC

A 24.5 DEGREES

NASA/TM--2000-209916 187
L_

N

m B

d

Ill li:,

Ill

.J

ILl :

li:

u,I

Z

0

ID

10

+ +' +_++' , + + , ,I,i+ + .... :

I } J jJ_l+ L ............ ...... _ +++ + °t ........ T............................ + T............... I--+ P...................... C ..... < ........

+ +" + ) li ' + 1 _ ;

/ ) + + ) : ) + : + m mAmi',ill',i

) ) 1++; ( n#.lrlu

) ! : { : ) ) J ) ) +

+ { + i ++ i i

? + : ; + i + + + _i i I + + H

: :- i : iii?i i ' ) )

i I

+ + + + + _ r

+ + + + I ; : : I I

......... :+ +-+--+...+ ............... ...... + .4+,+4 +_- }.......... _....... _-++ +4+--4 ..........

+ ;+++ + } + ! + +._+ ...............

+ + I- -LL ii ' +' I ) I

+ : : + +i i i + I + +

+ + :ji+i EATI_ ) + +

+, +, +),+_I-+,--i_/-_-_, m- _ + , +I+_+ _F+......Tr1 I + i : I i ; } l I III I + +I, I '-J )

++ I

it, : ' i i_A ......'

............ --....... +--. +i++ .....---4i;-Jr-!i ............................. ' ! ........ TREATED: ....... +++

+ + i ) i!

4 l _ + i i +

_ , _i! _

i , ' ) !

....... ?.... : .... T ....... +]-+

i : + + +i;:

! i i ;

r , ,

+_iii,

_+

......... !...... +i-+ -,+.-+-,+ L .....

( i '

( >

7

I

i +

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 53 CONTINUED

B 92.5 DEGREES

N ASA/TM--2000-209916 188
m

"O

.J

I.U

I.U

._1

I,U

rr

u.I

r_

a.

Z

0

10 100

HARD

'i i !

i

! ,

1,000

FREQUENCY, HZ

10,000 100,000

' FIGURE 53 CONCLUDED

C 130.5 DEGREES

NASA/TM--2000-209916 189
m

UJ

LU

..I

I,U

nCO

I.U

a

z

0

HARD

25 3_ 35 #_ 45 5_

FREQUENCY, KHZ

FIGURE 54 SPECTRAL COMPARISON OF HARD AND FULLY

TREATED DATA FOR THE 70 VANE CONFIGURATION AT 10671 RPMC

A 24.5 DEGREES

NASA/TM--2000-209916 190
rd ...............

i

....-HARD .................

! :

i

HARI_ !

5 1_ L5 2_ 25 3_ ::;_ aB 45 5_

FREQUENCY, KHZ

FIGURE 54 CONTINUED

B 92.5 DEGREES

NASA/TM--2000-209916 191
¢-I

U3

r,';

m_

d

>

m_

w,

U,I

Z u'_

0

Dri !

_HA_ ....

,

5 19 [5 2_ 25 3_ 35 4B 45 .__

FREQUENCY, KHZ

FIGURE 54 CONCLUDED

C 130.5 DEGREES

NASA/TM_2000-209916 192
m

"o

.3

U.I

>,

UJ

J

I.,U

I.U

O.

Z

0

t_

[0

r

1 I I

10 10o 1,oo0 lO,OOO 100,o00

FREQUENCY, HZ

FIGURE 55 1/3RD OCTAVE COMPARISON OF HARD AND FULLY

TREATED DATA FOR THE 70 VANE CONFIGURATION AT 10671 RPMC

A 24.5 DEGREES

NASA/TM--2000-209916 193
m

-o

uJ

>

uJ

..J

u.i

rr

(/)

I.U

nI1.

_3

z

0

(n

10

I

100

I

1,000

I

I

10,000 100,000

FREQUENCY, HZ

FIGURE 55 CONTINUED

B 92.5 DEGREES

NASA/TM--2000-209916 194
m

uJ

111

.-I

uJ

n-

_)

U)

uJ

nO.

Z

0

10 100

l

I

i

i !

1,000 10,000

: TREATED

100,000

FREQUENCY, HZ

FIGURE 55 CONCLUDED

C 130.5 DEGREES

NASA/TM--2000-209916 195
rn

"O

>

O

¢2

Z

O

(n

_TREATED

t

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 56 SOUND POWER LEVEL COMPARISON OF HARD AND

FULLY TREATED DATA FOR THE 70 VANE CONFIGURATION

A 6402 RPMC

NASA/TM--2000-209916 196
I

10,000 100,000

FREQUENCY, HZ

FIGURE 56 CONTINUED

B 7736 RPMC

NASA/TM--2000-209916 197
,:='I

1.4

q I

i_ 1 !!

; i t!'

TREATED

10 100 1,000

FREQUENCY, HZ

10,000 100,000'

'FIGURE 56 CONTINUED

C 8537 RPMC

NASA/TM--2000-209916 198
! i ' ! i ! !i ! HARD r-_

: il ! _;IlJ . ' i_ I t

...... I I I I

! I i _. !iI_ i ! i :l I !....

• : I _i !

* : I ___I_'L__ _ TREATED :

. ! I l , : i i . :

i I _!ii i i {i

L_

IX:)

p-_

, i _ Iii

i i 11!!-

: ] []

10 100

i i ,_:_

i ' i

i

1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 56 CONTINUED

D 9604 RPMC

NASAfrM_2000-209916 199
10

1-

100

I

1,000 10,000 100,000

FREQUENCY, HZ

,FIGURE 56 CONTINUED

E 10137 RPMC

NASA/TM--2000-209916 200
UJ

I

1,000

....HARD .....

TREATED

10,000 100,000

FREQUENCY, HZ

FIGURE 56 CONCLUDED

F 10671RPMC

NASA/TM--2000-209916 201
[13

N

,,>,

O

a.

Z

:::=1

0

I.O

ID

El

I

!TREATED _ --

!J !

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 57 FRONT SOUND POWER LEVEL COMPARISON OF HARD

AND FULLY TREATED DATA FOR THE 70 VANE CONFIGURATION

A 6402 RPMC

NASA/TM--2000-209916 202
_I

iIo

_ , ,_,_. _ -x -4-- _I-, _.

i !: i I i!li i 'i

: i _ !i , _ TREATED

_ _ _ ,, , ' _ !HARD

! [ I , | ', I I I I'

i ! i Iiii _ k-_ I I

i ! i i-T- _ : i I _ / "---

; i f i

I _. ! } i " '' i

! ' : I ! [ _ i i ill ! i ,i-;_ [i ,:_ : _i:

• , _ i ! :

'. ; : : i ( i

i , i

I i I i

.......... _ i........ i-= ......: ......i............ I--_!'!- ......................... _........... ' ....

_ ii i_'. i i

• i i' _ I 1

i _ i , I _ _''

I I I

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 57 CONTINUED

B 7736 RPMC

NASA/TM--2000-209916 203
[0

10 100

ilia

1,000

FREQUENCY, HZ

10,000 100,000

FIGURE 57 CONTINUED

C 8537 RPMC

NASA/TM--2000-209916 204
If)

r,d

r',J

HARD

lO

I I I

100 1,000 10,000

l

100,000

FREQUENCY, HZ

FIGURE 57 CONTINUED

D 9604 RPMC

NASAfrM--2000-209916 205
Z

::)

o

(n

+_ ' i+ _i!I_I +_ _

H_R_ TR_AT_O

rREATED :

I

100,000

FREQUENCY, HZ

FIGURE 57 CONTINUED

E 10137 RPMC

NASA/TM 2000-209916 206
,"I

--I "-'

0,._

i

i i ' iiii ! i ; I :

!_ : i : i_i _ : i i  ̧ ̧I i _;,

! . . TREATED

! i I.Ann II

i • + ! i + I j _: il 1 i ,I_ ,_--_ ...... j _-_

r"_--_=_ _?-'-_+ _ _! I' _ J

t _ ! , ' ! t " 1 , , !

i---"

i I _ _.. '__ T,..,,-,,..,-,..-,,.,,,

............ : .......++_+;...... ++++_--++ ........+ ...... ++H--F+H-+-+H-H-......... 4- .... f._.+++,•+_. ++++_u ........ ......

++++ + +++ J I+ + iJJ+ ili + " +

.... ,+ , , + .....

+ + + + , +

+ + I l t + + " + ; ; +

I ] + + _! /! ; i IILii i i ; ,,

• : + !+ i I + • I ; ; : ;

J / I ]

; i 1 i _ i

i : i i i t i ! i i

• i '.ii

' i i i

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 57 CONCLUDED

F 10671 RPMC

NASA/TM--2000-209916 207
i:_ _ ! . i i i _ i

r_ ...... _, .... -r...... : f--t-i-_ .................... : -......... t'-I'-t'';_ _.....I._,................. ;-+" ';-i _....

.........I......._........! -U-T--'_ ..................... _-"1 -"i+,_i" _ ", .......... _......... _---_---I---_--7"

H mT

Z

! ! ii ! i :i HARD _ i

I i _ i _ _

..>. [I

: ' i i_ I, i .

i _i il I '. i

i i t i i :

1

10,000

r_,

10

i _ 4 i r ̧

lI )0 1,000

FREQUENCY, HZ

:......... ry

i i • '

:i

ii

I

100,000

FIGURE 58 AFT SOUND POWER LEVEL COMPARISON OF HARD

AND FULLY TREATED DATA FOR THE 70 VANE CONFIGURATION

A 6402 RPMC

NASA/TM_2000-209916 208
HARD

TREATED

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 58 CONTINUED

B 7736 RPMC

NASA/TM--2000-209916 209
tr)

l'd

,,>,..

--I

,,=,-,

3:

o_

a..

¢3

z_

O

Er,

tO

tO

10 100

HARD

1,000

FREQUENCY, HZ

I

10,000 100,000

FIGURE 58 CONTINUED

C 8537 RPMC

NASA/TM--2000-209916 210
!i i i _ HARD

i [ ]

i ] i Jl

I I | I

! ! i_

..........T ! I _ I ! _ I ! I I _

0 i :

:ilil !

; i i _,i i

I t

10 100 1,000 10,000

....... -_ !•I_ ............... 14.

i _ _ " i i

100,000

FREQUENCY HZ

FIGURE 58 CONTINUED

D 9604 RPMC

NASA/TM--2000-209916 211
_ i _i ,i i i i_!_ i i : i il )l IIj _ HARD

" _ ! i i i !!! f _ i i If ' '_! ! _ I I I--]

! i _ ' i ,i! I I i

!

i _ _ _ ! _i IL-_ _ ! _l

: ! : ! i ! : !

,, _ i i i I tii_

i ., i ! i I _i i .

I

I

I !il _ !

J t

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 58 CONTINUED

E 10137 RPMC

N AS A/TM_2000- 209916 212
LI')

..I

i'r-.

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 58 CONCLUDED

F 10671 RPMC

NASA/TM--2000-209916 213
t

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 59 DIFFERENCE IN SOUND POWER LEVEL, HARD MINUS

TREATED, FOR THE 70 VANE CONFIGURATION

A 6402 RPMC

NASA/TM_2000-209916 214
,,...,I

ILL

I..I..

N

I

10

i J i ,

I

100 1,000 10,000 100,000

FIGURE 59 CONTINUED

B 7736 RPMC

NASA/TM_2000-209916 215
151

m

"0

.J

I,U co

>

1.1,,I

,-I

n,.

0

11.

C2

Z

0

(/)

Z

mare

UJ N

0

Z

UJ

I,M

U..

U.

r_J

I

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 59 CONTINUED

C 8537 RPMC

NASA/TM--2000-209916 216
b")

m

"O

.J

UJ

IJ.I "

..J

n..

I.U

O

a.

Z

0

(n

z

m

UJ

0

Z

U.I

I:l:

I,LI

1.1,.

U.

iml

Q

I

t

10

i , • !

1

10o 1,000

FREQUENCY, HZ

I

10,000 100,000

FIGURE 59 CONTINUED

D 9604 RPMC

NASA/TM--2000-209916 217
_a

N

m

"o

J

ILl

UJ

..I

rr

LU

0

l:

Z

0

(n

z

mmm

ILl

Z

U.I

rr

ILl

IJ.

m

I

10 100 1,000

FREQUENCY, HZ

10,000 100,000

FIGURE 59 CONTINUED

E 10137 RPMC

NASA/TM--2000-209916 218
m

'ID

J

I,U

--I

i

u_

z

,,z,

t

• ! i ; i

I

1!I

1'

• i i ,

10 100 1,000 10,000

FREQUENCY, HZ

100,000

FIGURE 59 CONCLUDED

F 10671RPMC

NASA/TM--2000-209916 219
,:tro

--I

r'd

0

n ..-,

Z

O

(n

z

m

UJ

(3

Z

I.IJ

n,,

ILl

!1

U.

i

I

_J

I

I

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 60 DIFFERENCE IN FRONT SOUND POWER LEVEL ,

HARD MINUS TREATED, FOR THE 70 VANE CONFIGURATION

A 6402 RPMC

NASA/TM--2000-209916 220
; I

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 60 CONTINUED

,B 7736 RPMC

NASA/TM--2000-209916 221
==

_i

I

= +

==

z

8

_o

I

IM

I + + I Y i !

;';+ _....., I- I i-j-+-: ............. F i / I_ :

/

,iil ! + : I i /

, • [ : |

i _. + ii J , ili_ i . I_: d

+ +

+ + P + P i +, + +t++ r+ I

i ,_ i i! if! ill /

........ : + ..........Y ++++.....+++....... _J++ ......... < I ...................

++ + + !++_+ I

i : i { !

! ! i ' ' ' ,I _1 i _ I I I ' ! : I,--,.., :

....... +....... =+........... +A ........... _ _+ +H+5+ r L++--+.......... . + ............. •....

5 + = + i ' < +

t + i+ I _ +

+ + .... + i I

+ ! + ! I + I- I+ I t + [ I + +++ + + +

! ! I _ : i | I ! +_ <+ i _ I I r--"--

i i i { f i: !

ii U_ i+ ' J L I+ i

....................... ++ ............................+....L+.................... =....

+ i i ....................................... + +

+ + , + +

! + + !

+ + ' + + + t + 1 ;

+ + + + + I : +' +

+ + ! I +

r i = i t ....

t l

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 60 CONTINUED

C 8537 RPMC

NASA/TM--2000-209916 222
N

N

I

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 60 CONTINUED

D 9604 RPMC

NASA/TM--2000-209916 223
I/3

N

d

_ r_

,,=,

0

I1,

z

0

u)

z

14J

Z

14,1

14,1

11,.

14. _

h_

I

r

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 60 CONTINUED

E 10137 RPMC

NASA/TM--2000-209916 224
m

"o

i.i.i

>

u.,I

n,.

W

0

a.

a

z

::3 '"

0

in

z

m

W

0

Z

w

I.U

U..

IJ.

b_

I

_ l!il i

i _ili

i i!:

! _Iii

: I

10

! i i '_

, ili

! I li_

i _ ii!

! i i _}!_

i I iii_i .............. i........

i ! i i i

i • _ i : i i

il, _i r

100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 60 CONCLUDED

F 10671 RPMC

NASA/TM--2000-209916 225
m

qD

f.,j

.,I

U,I

.J

,,=,

a.

z

0

(n

U;,

Z

I,LI

Z

1,1,1

U.I

I,I,.

I,I.

!

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 61 DIFFERENCE IN AFT SOUND POWER LEVEL,

HARD MINUS TREATED, FOR THE 70 VANE CONFIGURATION

A 6402 RPMC

NASAfFM_2000-209916 226
11"3

a.

P_

(n

_z

IJ'_

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 61 CONTINUED

B 7736 RPMC

NASA/TM--2000-209916 227
m

10

.J

uJ

>

I,IJ

,-I

nI,IJ

3:

O

D.

Z

0

U)

Z

m

UJ

0

Z

i,LI

n"

W

U.

U.

mmm

L_

,,.q

b'J

_z

I

i

i!

•

10 100 1,000

FREQUENCY, HZ

10,000 100,000

FIGURE 61 CONTINUED

C 8537 RPMC

NASA/TM--2000-209916 228
I

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 61 CONTINUED

D 9604 RPMC

NASA/TM--2000-209916 229
o

z

i ii_!

: i • i

Z i • ,

i

10 100 1,000 10,000 100,000

FREQUENCY, HZ

FIGURE 61 CONTINUED

E 10137 RPMC

NASA/TM--2000-209916 230
m

"0

.3

3

0

a.

13

Z

::)

0

(/)

Z

m

ILl

0

Z

U,I

rr

U.I

IL

I.I.

wmm

_3

irj

i

I

10 100 1,000 10,000

FREQUENCY, HZ

100,000

FIGURE 61 CONCLUDED

F 10671 RPMC

NASA/TM--2000-209916 231

Appendix A

The following pages are the output from a compressor design program that was used to design the Alternative

Low Noise Fan. The program uses 11 streamlines with number 1 being at the tip and number 1t at the hub. The

program uses 12 axial stations. Stations l to 3 are upstream of the rotor. Station 4 is the inlet to the rotor and station

5 is the rotor outlet. Station 6 is between the rotor and stator. Station 7 is the stator inlet and station 8 is the stator

outlet. Stations 9 to 12 are downstream of the stator. The column headings for each station are for the most part self

explanatory and the values are presented in English units.

NASA/TM_2000-209916 233

NASA/TM--2000-209916 235
N

ooQollllleo,t=o • •

• °

o

NASA/TM--2000-209916 236
_'_ ooo_ __, _,_o • • • J • • • • • • • • • • • • •

NASA/TM--2000-209916 237
| | |

i

Q" _ II.

m N

NASA/TM_2000-209916 238
5

_- :i - _'|_

oo, | . _

NASA/TM--2000-209916 239
|_||||||||._

i,

Z

It--

..,z.

__11

It--

X

m

O

N

III,I

_°°

lal

.v.

Q

W

_iIIIIIIIIiIi

v

U

Z

N

Im

NASA/TM--2000-209916 240
lid

It_

I

N

ag

,11

41

,,11

m m

_v

|

v

L

N

I,,,,,

NASA/TM_2000-209916 241
.d

,.,.I

W **

i

NASA/TM--2000-209916 242
NASA/TM--2000-209916 243
! ,

| | | |

NASA/TM--2000-209916 244
i •

°

NASA/TM--2000-209916 245
oe

=._-"N • • • •

iI ""

|

NASA/TM--2000-209916 246
°t

_ ee oeee*iee

e_ etottnloale

_U

I_ _ _._,__.

nm_n

_'' • __'

_d v

• W

• __.__

o W

W

".__,__

.-_,

NASA/TM--2000-209916 247
"m

NASA/'rM_2000-209916 248
.j

_ _ • ,. ,. ,.

_ . ____

_-I_l_r. _.°

NASA/TM--2000-209916 249
"D

o

W_ OOlelalllOI

d_;_ •

|

_d

NAS A/TM--2000-209916 250
NASA/TM--2000-209916 251
esee_eelole

'ii . ii00000 00 P

NASA/TM_2000-209916 252
i! !! i I!!!!!!! S_" _ _'_

.)

NASA/TM--2000-209916 253
'°

i i_i II_ Ie I I oe e I t I I I

no U

I!!! 'ii"" • _ "__,

._ _ ._,

I Im

_.,i!___!._..

NASA/TM_2000- 209916 254
• _ -

NASA/TM--2000-209916 255
NASA/TM--2000-209916 256
° " _ m .

2

o o _ o

.! ii o°i!!°

t

NASA/TM--2000-209916 257

Appendix B

BLADE COORDINATES

NASA/TM--2000-209916 259

PART 1

ROTOR BLADES

NASA/TM--2000-209916 261
ROTATION

I

LEADING EDGE_ S.

AXIS _ RnTATI[_ ---'/

P.

PRESSURE SURFACE--\ "X C ' ,_-"X

., ,oTAT,o._\ /J

! \\ /

-Y AXIS OF RnTATIDN_ / /I__

SURFACE

STACKING POINT

XIS DF ROTATION

ER

,,,--STACKING LINE

TYPICAL AIRFOIL SECTION

BTB, THRUBI; B,I

LEAD ING EDGE -_

B3_B,

__

B 4

Bg'

B,o,

B,f

NASA/TM_2000-209916

I

I

"T"

I

_-T.

=t:

I

I

I

STACK ING LINE

_.__ TRA IL ING EDGE

"- _ B iB3 5._ooG,_

4 4.95O GAGE

_ w5 4,.400 GAGE

I

.... _B7 _.8_._oo GAGE o_

_B8 2. 750 GAGE

_B9 1,650 GAGE

_B _, o.oooGAC_

262

IT

I

I

(R 9.360)

q_

I

_2_
LOW NOISE FAN ROTOR BLADE SECTION BOt-BO

RADIUS: I t .275000 GAGE- 6.325000

SUCTION

X

• -0 246600

• -0 229100

-0 209100

-0 98300

-0 86800

-0 74.700

-0 6200O

-0 48700

-0 34700

-0 20300

-0 05200

-0 089600

-0 075500

-0 057000

-0 039800

-0 022500

-0 004300

o ol42oo

0 033000

0 052300

0 072000

0 09200O

0 112300

• 0 154000

• 0 196900

SURFACE

Y

0 447500

0 365700

0 285600

0 246200

0 207 I00

0 168,400

0 130100

0 092 I00

0 054600

00i 7500

-0 019100

-0 055100

- 0 090600

-0 12560O

-0 159900

-0 i93400

-0 226400

-0 258400

-0 289700

-0 320000

-0 549400

-0 377800

-o 4o49oo

-0 4.55700

-0 501700

PRESSURE

X

"-0 255100

"-0 229300

-0 2O27OO

-0 89100

-0 75300

-0 61200

-0 4-6900

-0 32400

-0 17700

-0 02700

-0 087500

-0 072100

-0 056500

-0 040500

-0 024400

-0 007900

0 008900

0 025800

0 043200

0 060800

0 078800

0 O97200

0 115900

" 0 154300

" 0 193900

SURFACE

Y

0 442700

0 364700

0 287800

0 249800

0 212100

0 174700

0 137500

0 100600

0 06400O

0 027700

-0 008200

-0 043800

-0 079000

-0 113700

-0 147900

-0 181600

-0 214700

-0 247400

-0 279300

-0 310600

-0 541200

-0 370900

-0 399900

-0 455400

-0 507700

LEADING

X

- O. 205900

EDGE

Y

0.286600

O.OO34O0

CENTER

RADIUS

TRAILING EDGE

X Y

O. I 14100 -0.402500

0.002900

NASA/TM--2000-209916 263
LOW NOISE FAN ROTOR BLADE SECTION BO2-B02

RADIUS. II .000000 GAGE- 6.050000

SUCTION

X

*-0 291500

*-0 267300

-0 240600

-0 226400

-0 211600

-0 96300

-0 80300

-0 63900

-0 46900

-0 29400

-0 11400

-0 093000

-0 074100

-0 054700

-0 034800

-0 014700

0 006000

0 0270O0

0 048500

0 070300

0 092600

0 115100

0 137900

a 0 184600

I 0 232400

SURFACE

Y

0 452200

0 371500

0 292400

0 253400

0 214800

0 176500

0 138600

0 100900

0 063700

0 026800

- 0 009600

-0 045700

-0 081300

-0 116400

-0 151 I00

-0 18520O

-0 218800

-0 251300

-0 2842OO

-0 316000

-0 347000

-0 377200

-0 406700

-0 463300

-0 516700

PRESSURE

X

* 0 302400

*-0 268700

-0 2342O0

-0 216700

-0 98900

-0 81200

-0 63200

-0 45100

-0 27000

-0 08700

-0 090400

-0 071800

-0 053 I00

-0.034200

-0 015300

0 003800

0 023100

0 042500

0 062100

0 081900

0 101900

0 122100

0 142500

" 0 184000

" 0 226200

SURFACE

Y

0 4443O0

0 369600

0 295300

0 258300

0 221300

0 184700

0 148100

0 111800

0 075600

0 039600

0 003800

-0 031700

-0.067000

-0 102000

-0 136800

-0 171300

-0 205400

-0 239200

-0 2726O0

-0 305600

-0 338200

-0 370300

-0 401900

-0 463200

-0 522100

LEADING

X

-0. 237200

EDGE

Y

O. 293700

O.OO3500

CENTER

RADIUS

TRAILING EDGE

X Y

O. 140100 -0.404200

0.003300

NASA/TM--2000-209916 264
LOW NOISE FAN ROTOR BLADE SECTION BOS-BOS

RADIUS: I0. 450000 GAGE : 5. 500000

SUCTION

X

• -0 351600

• -0 317600

-0 281700

-0 262900

-0 2437O0

-0 224000

-0 203800

-0 183000

-0 161800

-0 140200

-0 118100

-0 O95500

-0 072500

-0 049100

-0 025300

-0 001000

0 023600

0 O48700

0 074100

0 099800

0 126000

0 152400

0 179200

• 0 234000

• 0 290500

SURFACE

Y

0 445700

0 368500

0 292500

0 2549O0

0 217600

0 180600

0 _43800

0 107500

0 071400

0 035600

0 000200

-0 034800

-0 069500

-0'. 103800

-0 137900

-0 171500

-0 204700

-0 23760O

-0 269900

-0 302000

-0 333500

-0 364700

-0 395400

-0 455700

-0 514500

PRESSURE

X

"- 0 365300

"-0 320500

-0 275200

-0 2524O0

- 0 229600

-0 206700

-0 183700

-0 160900

-0 138000

-0 I 15000

-0 O92000

-0 069200

-0 046200

-0 023200

- 0 000200

0 0229O0

0 045800

0 068900

0 09200O

0 115100

0 138300

0 161400

0 184600

• 0 23 I000

• 0 277400

SURFACE

Y

0 435600

0 365900

0 296300

0 261500

0 226700

0 191900

0 157100

0 122400

0.087800

0.053200

0.018700

-0.015800

-0.050300

-0.084700

-0.119000

-0.155200

-0.187400

-0.221500

-0.255500

-O.28940O

-O.32320O

-0.356900

-0.390500

-0.456900

-0.522500

LEADING

X

-0.278300

EDGE

Y

0. 2941 O0

0.003800

CENTER

RADIUS

TRAILING EDGE

X Y

O. 181700 -0.392800

0.003600

NASA/TM--2000-209916 265
LOW NOISE FAN ROTOR BLADE SECTION BO4-B04

RADIUS: 9.900000 GAGE: 4.950000

SUCTION

X

• -0 384500

• -0 345300

-0 304200

-0 282800

-0 261000

-0 238700

-0 215700

-0 192400

-0 168600.

-0 144200

-0 119400

-0 094100

-0 068400

-0 042300

-0 015600

00II40Q

0 038900

0 066900

0 095100

0 123800

0 152800

0 182200

0 212100

0 273300

• 0 336500

SU

0

0

0

0

0

0

0

0

0

0

0

-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

RFACE

Y

430800

355600

282OOO

245800

210000

174500

139400

104700

.070200

036200

002500

030900

063800

096400

128500

160400

191700

.222700

2534O0

283500

313300

342700

371600

42830O

483400

PRESSURE

X

• -0 403100

• -0 350300

- 0 298000

-0 271900

-0 246000

-0 2200O0

-0 194100

-0 168100

-0 142300

-0. II 6400

-0. 090600

-0. 064700

-0. 038900

-0.013100

O. 0 12600

0.038300

0 064000

0 089600

0 115200

0 140800

0 166400

0 191900

0 217500

• 0 268600

• 0 319700

SURFACE

Y

0.4 17800

O. 351900

0. 286300

0.253700

O. 221200

O. 188500

O. 156000

O. 123400

O. 090800

0 058 I00

0 O255OO

-0 007 I00

-0 039700

-0 072300

tO 105000

-0 137700

-0. 170300

-0 203000

- 0 235600

- O 268400

-0 301 I00

-0 333700

-0 366400

-0 4322O0

-0 498300

LEADING

X

-0.300900

EDGE

Y

0.283900

0.003800

CENTER

RADIUS

TRA I L I NG EDGE

X Y

0.214600 -0.368800

0.003800

NASA/TM--2000-209916 266
LOW NOISE FAN ROTOR BLADE SECTION t_Ob-I_Ob

RADIUS. 9.5,50000 GAGE; 4.400001

SUCTION

X

• -0 408200

°-0 365 I00

-0 320000

-0 296700

-0 272900

-0 248500

-0 223600

-0 198200

-0 1722O0

-0 145700

-0 118700

-0 091200

-0 063200

-0 034700

- 0 005800

0 023500

0 055300

0 083600

O. II 4300

0 145400

0 176900

0 208800

0 241 I00

• 0 306900

• 0 374200

SU

0

0

0

0

0

0

0

0

0

0

0

-0

-0

-0.

-0.

-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

RFACE PRE

Y

413800 ,0

341200 ,-0

270200 -0

235300 -0

200800 -0

166700 -0

133100 -0

099800 -0

066900 -0

034500 -0

002400 -0

029100 -0

060200 -0

090900 -0

121t00" 0

150800 0

180000 0

208800 0

237100 0

265000 0

292400 0

319200 0

345500 0

396600 • 0

445700 • 0

SSURE

X

4291 O0

371400

314100

285600

257200

228900

200600

172400

144200

116000

_i_87800

059700

031700

0'!,3700

024300

052200

08000O

107800

135600

163300

191000

218600

24,520O

301400

356500

SURFACE

Y

0 396900

0 335900

0 2749OO

0 244400

0 213900

0 183400

0 152900

0 122300

0 091800

0 O6 I000

0 030400

- 0 000300

-0 031000

-0 061800

-0 092600

-0 123400

-0 154200

-0 185100

-0.216000

-0 247000

-0 278000

-0 309000

-0 340000

-0 402000

-0 464000

LEAD ING EDGE

X Y

-0.316800 O. 272300

0.003800

CENTER

RADIUS

TRAILING EDGE

X Y

0.243500 -0.342600

0.003800

NASA/TM_2000-209916 267
LOW NOISE FAN ROTOR

RADIUS: 8.800000

BLADE SECTION B06-B06

GAGE. 3;. 850000

SUCTION

X

• -0 424700

• -0 378800

-0 330800

-0 306100

-0 280900

-0 255000

-0 228600

-0 201600

-0.173900

-0 145800

-0 117200

-0 088000

-0 058200

-0 028000

0 002800

0 033900

0 065700

0.097800

0.130400

0 163400

0 196900

0 230700

0 265100

• 0 335400

• 0 407600

SURFACE

Y

0 402000

0 330600

0 261300

0 227300

0 193900

0 160800

0 128400

0 096200

0 064700

0 033600

0 003100

-0 027000

- O. 056500

-0 085400

-0 113900

-0 141900

-0 169200

-0 196000

-0 222200

-0.247900

-0. 273000

-0. 297500

-0.32 I 4O0

-0.3674.00

-0.41 I000

PRE

--0

"-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

0

0

0

0

0

0

0

0

0

0

• 0

• 0

SSURE

x

447t00

385900

325100

294900

264700

234600

204500

t74400

144400

114400

084600

0548O0

024900

004800

034500

064100

0936O0

123200

152600

182000

211400

240600

2698O0

328300

386800

SURFACE

Y

0 380900

0 323600

0 266200

0 237600

0 2O8900

0 180200

0 151400

0 122600

0 093700

0 064800

0 035900

0 O0680O

-0 022300

-0 051300

-0 080500

-0 109700

-0 138900

-0 168300

-0 197700

-0 2270O0

-0 256500

-0 286000

-0 315600

-0 374700

-0 433900

LEAD I NG

X

-0.327700

EDGE

Y

0.263400

0.003800

CENTER

RADIUS

TRAILING EDGE

X Y

0.267200 -0.318300

0.003800

NASA/TM_2000-209916 268
LOW NOISE FAN ROTOR BLADE SECTION BO7-B07

RADIUS: 8.250000 GAGE: 5.500000

SUCTION

X

"-0 439000

• -0 391300

-0 341200

-0 315200

-0 288600

-0 261200

-0 233300

-0 204700

-0 175500

-0 145800

-0 115400

-0 O845O0

-0 052900

-0 02090O

0 011700

0 044800

0 078400

0 112500

0 147100

0 182100

0 217600

0 253400

0 289700

• 0 363600

" 0 439000

SURFACE

Y

0. 387500

0.318100

O. 250700

O. 2 17800

0 185300

0 153500

0 122100

0 091300

0 061200

0 031600

0 002600

-0 025800

-0 053500

-0 08O6O0

-0 107000

-0 132700

-0 157900

-0 182400

-0 206100

-0 229200

-0 251600

-0 273300

-0.294200

-0. 3341 O0

-0.371 I00

PRE

,-0

"-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

0

O.

0

0

0

0

0

0

0

0

• 0

• 0

SSURE

X

464600

400000

335800

303900

272000

240200

208500

176700

145000

113300

081700

050200

018600

012900

044300

075800

107100

138300

169700

200800

231900

263100

294100

355900

417200

SURFACE

Y

0 363300

0 309600

0 256000

0 229200

0 202400

0 175600

0 148600

0 121700

0 094 700

O-067700

0 040700

0013600

-0013600

- 0 040800

-0 068100

- 0 095400

-0 122800

-0 150300

-0 177700

-0 205200

-0 23280O

-0 260500

-0 288100

-0 343000

-0 397500

LEAD ING EDGE

X Y

-0. 338200 O. 253000

0.003800

CENTER

RADIUS

TRAILING EDGE

X Y

0.291700 -0.29!000

0.003800

NASA/TM--2000-209916 269
LOW NOISE FAN ROTOR BLADE SECTION B08-B08

RADIUS : 7. 700000 GAGE • 2. 750000

II

,I

SUCTION

X

• -0 453900

"-0 404800

-0 352500

-0 325200

-0 297000

-0 268200

-0 238700

-0 208400

-0 177500

-0 145900

-0 113600

-0 080700

-0 O47300

-0 013100

0 021500

0 05670O

0 0925OO

0 128800

0 165600

0 202800

0 240500

0 278700

0 317300

0 395200

0 474400

SURFACE

Y

0.369300

0.302100

0.236800

0.204900

0.173500

0 142900

0 112900

0 083600

0 055200

0 027300

0 OOO2OO

-0 026000

-0 O515O0

-0 076200

-0.100000

-0.123100

-0.145300

-0.166600

-0.187100

-0.206700

-0.225500

-0.243300

-0.260200

-0.291400

-0.318900

PRE

I-. 0

Q-O

-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

0

0

0

0

0

0

0

0

0

0

,, 0

,, 0

SSURE

X

481100

414200

347400

313900

280500

247100

213600

180200

146800

113300

079900

046500

013100

020400

053800

087200

120700

154100

187500

220800

254300

287600

321000

388200

455700

SURFACE

Y

0 341400

0 291900.

0 242300

0 217600

0 192800

0 168000

0 143300

0 118500

0 093700

0 069000

0 044200

0 019400

-0 O05400

-0 030100

-0 055OOO

-0 079800

-0 104600

-0 129400

-0 154300

-0 179100

-0 204000

-0 228900

-0 253700

- 0 303500

-0 353200

LEADING

I,

X

-0.349700

EDGE

Y

0. 239300

0.003800

CENTER

RADIUS

TRAILING EDGE

X Y

0.318700 -0.256700

0.003800

NASA/TM--2000-209916 270
LOW NOISE FAN ROTOR BLADE SECTION BO9-B09

RADIUS = 6 . 600000 GAGE : I . 650001

SUCTION

X

• -0 485300

• -0 432000

-0 3747O0

-0 344500

-0 313400

-0 281400

-0 248400

-0.214600

-0 179900

-0 144500

-0 108300

-0 071300

-0 O3380O

0 004500

0 043400

0 082800

0 122800

0 163300

0 204 I00

0 24540O

0 287000

0 329000

0 371100

0 456100

• 0 541900

SURFACE

Y

0.330900

0.263400

0.200200

O. 170300

O. 141400

O. II 3500

O. 086700

0 061000

0 036400

0013000

-0 009200

-0 030200

-0 050000

-0:068500

-0 O8580O

-0 01600

-0 16000

-0 29100

-0 40800

-0 51 I00

-0 59800

-0 67100

-P. 72900

-0. 79600

-0. 79900

PRESSURE

X

*-9.513700

.-0.442 I O0

-0.370200

-0. 33400O

-0.297800

-0.261300

-0. 224900

-0. 188400

-0 151600

-0 114900

-0 077900

-0 041000

-0 O038OO

0 033400

0 070700

0 108100

0 145700

0 183400

0 221000

0 258900

0 296800

0 334900

0 373 I00

, 0 449700

* 0 526800

SURFACE

Y

0 291100

0 248100

0 206200

0 185700

0 165500

0 145400

0 i25500

0 1058OO

0 086300

0 067000

0 047800

0 028900

0 010100

-0 008400

-0 026700

-0 044800

-0 062800

-0.080500

-0 097900

-0 115200

-0 132200

-0 149100

-0 165600

-0 197400

-0 227600

LEADING

X

-0. 372000

EDGE

Y

0. 202900

0.003800

CENTER

RADZUS

TRAILING EDGE

X Y

0.371600 -0. 169100

0.003800

NASA/TM_2000-209916 271
LOW NOISE FAN ROTOR BLADE Sb_CIIUN _IU-_IU

RADIUS: 5. 500000 GAGE: 0.550000

SUCTION

X

*-0.515800

,-0.457600

-0.394600

-0.361300

-0.326800

-0 291200

-0 254500

-0 216800

-0 17830Q

-0 138800

-0 098600

-0 057700

-0 016200

0 025800

0 068300

0 111200

0 154200

0 197500

0 240800

0 284100

0 327100

0 370000

0 412400

• 0 495700

• 0 577000

SURFACE

Y

0 277000

0 210900

0 150800

0 123000

0 096700

0 072000

0 048900

0 027500

0 007900

-0 010000

-0 025900

-0 040000

-0 052100

-0 062200

-0 070200

-0 076100

-0 079800

-0 081300

-0 O8060O

-0 077600

-0 072400

-0 064800

-0 054900

-0 028200

0 007700

PRESSURE

X

"-0 54 1300

1-0 466600

-0 390700

- 0 352300

-0 313600

-0 274700

-0 235600

-0 1964.00

-0 156900

-0 117300

-0 077500

-0 037500

0 002700

0 043000

0 083500

0 124100

0 164900

0 2O58O0

0 2468O0

0 287900

0 329200

0 370500

0.411900

* O. 495000

" 0.578500

SURFACE

Y

0 226500

0 190700

0 157300

0 141500

0 126300

0 111500

0 097300

0 O837OO

0 070600

0 058000

0 046 I00

0 034 700

0 024000

0 013800

ii0 004300

-0 004500

-0012700

-0 020300

-0 027100

- 0 033300

-0 038700

-0 043400

-0 047300

-0 052700

-0 054900

LEADING

X

-0. 39200O

EDGE

Y

O. 153700

0.003900

CENTER

RADIUS

TRAILING EDGE

X Y

0.41 1600 -0.051 I00

0.003900

NASA/TM_2000-209916 272
LOW NOISE FAN ROTOR BLADE SECTION B I I-BII

RADIUS : 4 . 950000 GAGE • 0 . 000000

SUCTION

X

*-0 526600

I-O 466100

-0 400400

-0 365600

-0 329500

-0 292300

-0 253900

-0 214500

-0 174200

-0 133100

-0 091200

-0 04880O

-0 005900

0 037400

0 081000

0 124600

0 ;68200

0 211700

0 254800

0.297400

0.339400

0.380600

0.420900

* 0.498800

. 0.573100

SURFACE

Y

0 253600

0 186100

0 126200

0 099 I00

0 073900

0 05060O

0 029200

0 009800

-0 007500

-0. 022500

-0. 035300

-0.045800

-0 053900

-0 059600

-0 062600"

-0 063100

-0 061000

-0 056200

-0 048700

-0 038400

-0 025500

-0 009800

0 O08600

0 053500

0 109200

PRE

*-0

,b- 0

-0

-0

-0

-0

-0

-0

-0

-0

-0

-0

0

0

O.

0

0

0

0

0

0

0

0

* 0

,i, 0

SSURE

X

553500

475400

396900

357500

318000

278100

238100

197900

157500

117000

076200

035300

005700

046800

088000

129300

170700

212100

253600

2950O0

336500

377900

419200

501500

583400

SURFACE

Y

0 194800

0 162500

0 133000

0 119300

0 106300

0 094 I00

0 082600

0 071900

0 061900

0 052700

0 044400

0 036900

0 030300

0 024600

0 019800

0 0158OO

0 012800

0 0108OO

0 009800

0 009800

0 01O8OO

0 012900

0 016100

0 025800

0 039900

LEAD ING EDGE

X Y

-0.398100 O. 129300

0.003900

CENTER

RADIUS

TRAILING EDGE

X Y

0.419400 0.0_2200

0.003900

NASA/TM--2000-209916 273

PART 2

LONG CHORD STATOR VANES

NASA/TM--2000-209916 275
B02

_ING EDGE OF BLADE

/--STACKING LINE

I

I

I

..... i .....

i.BoI

(I0,53)

DETAIL P

14 PLACES

SECTION DATUM LINES --

SUCTION SURFACE_

-- X"!L--I-_"' ÷ X

A °

f

+y

I

?- y

TYPICALA[RFOZLSECTION

B_'_BotTH"UBnB,t

NASA/TM--2000-209916 276
ALT LOW FAN STATOR BLADE

RAD I US : I O. 450000

SECT I ON BOI -BO I

GAGE : 4. 950000

SUCTION SURFACE

X Y

*-5,489900 -I,614400

*-4.768000 -I,179800

-4.024100 -0,798800

-3.643900 -0.628400

-3.258200 -0,471400

-2.867600 -0,327400

-2,472600 -0.196200

-2.073600 -0,077700

-I,671100 0.028100

-I,265400 0,121200

-0.857000 0,201400

-0.446300 0,268700

-0.033600 0,323000

0.380700 0,364100

0.796100 0.391900

1.212200 0,406500

1,628600 0,407800

2,044800 0,395800

2,460400 0,370400

2,875100 0.331900

3.288300 0.280200

3.699800 0.215400

4,109000 0,137500

* 4.920500 -0.057600

* 5.722800 -0,305100

PRESSURE SURFACE

X Y

*-5.557700 -I.376400

*-4.779700 -I.I 13200

-3.995300 -0.877200

-3,600700 -0.769400

-3. 204500 -0.668400

-2. 806600 -0,574100

-2,407200 -0.486300

-2,006400 -0. 404900

-I,604400 -0.329800

-I.201300 -0.261 I00

-0.797100 -0. 198600

-0.392000 -0. 142400

0.014000 -0,092500

0,420700 -0,049000

0.828000 -0.011700

1.235900 0.019200

I .644300 0.043700

2. 053000 0.061800

2. 462000 0.073500

2. 871200 0,078800

3,280500 0.077700

3.689700 0.070100

4. 098800 0.056100

* 4.916700 0.008900

* 5. 734200 -0.063900

LEAD ING EDGE

X Y

-4. 006500 -0,836800 CENTER

TRA I L I NG EDGE

X Y

4. 100600 0.097200

0.041930 RADIUS 0.041180

NASA/TM--2000-209916 277
ALT LOW FAN STATOR BLADE

RAD I US : 9. 900000

SECT ION BO2-B02

GAGE: 4,400000

SUCTION SURFACE

X Y

*-5.526000 -I.489000

*-4.787200 -I.107400

-4.031600 -0.766600

-3.647500 -0.611500

-3.259200 -0.466600

-2.867100 -0.332200

-2.471400 -0.208400

-2.072400 -0.095500

-I.670300 0.006200

-I.265600 0.096700

-0.858500 0.175800

-0.449300 0.249400

-0.038400 0.299500

0.374000 0.343900

0.787400 0.376700

1.201600 0.397900

1.616200 0.407400

2.030900 0.405400

2.445400 0.391700

2.859300 0.366500

3.272300 0.329700

3.684100 0.281500

4.094500 0.221700

, 4.911100 0.067300

* 5.722100 -0.133500

PRESSURE

X

*-5,585300

*-4. 797500

- 4. 005700

-3. 608300

-3. 209900

-2.810400

-2. 409900

-2.0O84OO

- I . 606100

- I . 202900

-0. 799000

-0. 394300

0.01 I000

O. 417000

O. 823500

I. 230500

I. 637900

2. 045700

2. 453800

2. 8621 O0

3. 270600

3. 679200

4. 087900

* 4. 905600

* 5. 723700

SURFACE

Y

- I. 267 I00

- I . 046500

-0. 8435OO

-0. 748600

-0. 6581 O0

-0. 572300

-0.491 I O0

-0.414700

-0. 343000

-0. 276 I00

-0.214200

-0. 157200

-0. 105 I00

-0. 058000

-0.015900

O. 021200

O. 053200

O. 080300

O. 02300

O. 19200

O. 31200

O. 38100

O. 40000

O. 28800

0.097600

LEADING EDGE

X Y

-4.015600 -0.804100 CENTER

TRA IL ING EDGE

X Y

4. 088000 0.181 I00

0.040700 RAD I US 0.041 I0

NASA/TM--2000-209916 278
ALT LOW FAN STATOR BLADE

RAD I US • 9. 625000

SECT I ON BO3-B03

GAGE : 4, 125000

SUCTION SURFACE

X Y

*-5.512300 -I.546600

*-4,776400 -I.161200

-4,024100 -0,814200

-3.641800 -0.655100

-3.255400 -0,505600

-2.864900 -0,366200

-2.470700 -0,237400

-2.073000 -0,119500

-I.672100 -0.012700

-I,268300 0.082600

-0.861900 0.166400

-0,453300 0.238600

-0.042800 0,299000

0.369300 0.347600

0.782600 0.384400

1.196700 0,409400

1.611400 0,422600

2.026300 0,424000

2,441100 0,413700

2,855400 0,391500

3.268900 0.357700

3.681200 0.312000

4.092100 0.254700

* 4.909700 0.105300

5.721700 -0.090500

PRESSURE

X

*-5,571600

*-4. 786400

-3. 997200

-3.601 I O0

-3. 204000

-2.805700

-2,406300

-2,005900

- I . 604500

- I . 2021 O0

-0. 798900

-0. 394800

0.010100

O, 415600

O. 821800

I, 228600

I, 635800

2.043500

2.451500

2. 859900

3. 268400

3. 6771 O0

4,085900

* 4. 903800

* 5,722100

SURFACE

Y

-I.332900

-I.103100

-0,890100

-0.789900

-0.693900

-0.602400

-0.515600

-0.433600

-0.356600

-0.284600

-O.217700

-0.156100

-0.099600

-0.048400

-0,002600

O,038OOO

0,073300

O, 03200

O. 27800

O. 47100

O, 61000

O, 69700

O, 73000

O. 63400

O. 32200

LEAD ING EDGE

X Y

-4. 007700 -0.851200 CENTER

TRA I L I NG EDGE

X Y

4. 085800 0,2 I 4 I O0

0.040400 RADIUS 0.041110

NASA/TM--2000-209916 279
ALT LOW FAN STATOR BLADE

RAD I US : 9,350000

SEC] 1ON _04-UU4

GAGE : 3. 850000

SUCTION SURFACE

X Y

*-5,488200 -I.629400

*-4,760800 -I.227600

-4.015000 -0,865800

-3.635200 -0.699900

-3.250800 -0.544000

-2.862200 -0,398600

-2.469500 -0,264000

-2.073000 -0.140600

-I.673100 -0.028700

-I.270100 0.071500

-0.864400 0,159900

-0,456200 0.236300

-0.046000 0.300700

0.366000 0,353000

0.779300 0.393100

1.193600 0.421200

1.608600 0.437100

2,023800 0.440800

2.439000 0.432400

2.853800 0,411900

3,267700 0,379200

3,680600 0.334500

4.091900 0.277600

* 4.909700 0.127200

* 5,721100 -0,072000

PRESSURE

X

*-5. 549000

*-4. 770600

-3. 986600

-3. 592500

-3. 197000

-2. 800200

-2. 402200

-2. 002900

- I . 602400

- I . 200800

-0. 798200

-0.394700

O. 009800

O. 415000

O, 82 I000

I. 227700

I, 634900

2. 042600

2. 450700

2. 859200

3,267800

3.676700

4. 0856OO

* 4. 903400

* 5.721200

SURFACE

Y

- I. 419400

-I, 171200

-0.941400

-0.833400

-0. 730000

-0. 631500

-0,538200

-0. 4501 O0

-0. 367400

-0. 290200

-0.218500

-0. 152400

-0, O92O00

-0, O37400

0.011600

O. O5480O

O, 092300

O, 24000

O. 49900

O. 70100

O. 84400

O, 93000

O. 958OO

O, 84000

O. 49000

LEADING EDGE

X Y

-3.998000 -0.902600 CENTER

TRA IL ING EDGE

X Y

4,085600 0.237000

0.040500 RAD I US 0.041140

NASA/TM--2000-209916 280
ALT LOW FAN STATOR BLADE

RAD I US : 8,800000

SECT ION BOS-B05

GAGE: 3,300000

SUCTION SURFACE

X Y

*-5,467200 -I.699200

*-4,747300 -I,276000

-4,007000 -0.897600

-3.629200 -0.725200

-3,246300 -0.564000

-2.858700 -0,414300

-2.466800 -0.276200

-2.070900 -0,149900

-I.671400 -0.035500

-I.268700 0.066900

-0,863100 0.157100

-0,454900 0.235200

-0,044600 0.301100

0.367500 0.354600

0.781000 0.395700

1,196600 0,424400

1,610800 0.440700

2,026300 0,444500

2.441800 0,435800

2.856800 0.414600

3.271000 0.380900

3.684000 0.334800

4,095400 0,276200

* 4.913400 0.121500

* 6.726000 -0.083200

PRESSURE

X

*-5,527200

*-4. 755800

-3. 977200

-3. 585200

-3. 191400

- 2,796000

- 2. 399000

-2. OOO500

- I . 600700

- I . 199500

-0. 79720O

-0. 393800

O. 010600

O, 416900

O. 8221 O0

I. 228900

I . 636400

2. 04430O

2. 462700

2.861500

3. 2704OO

3. 679500

4. O8860O

* 4. 906800

* 5. 725000

SURFACE

Y

- I, 497200

- I, 224000

-0. 974000

-0,867700

-0. 747200

-0. 642700

-0. 544 I00

-0,451500

-0. 365000

-0. 284700

-0.210500

-0. 142500

-0. 0806OO

-0,025000

O. 024400

O. 067500

O. 04500

O, 35100

O. 59500

O. 77600

O. 89500

O. 95000

O. 94200

O. 73700

O. 28OOO

LEAD ING EDGE

X Y

-3,989300 -0.934700 CENTER

TRA IL ING EDGE

X Y

4,089000 O. 235400

0.041130 RAD I US 0.041260

NASA/TM--2000-209916 281
ALT LOW FAN STATOR BLADE

RAD I US : 8. 250000

SECT ION BO6-B06

GAGE: 2. 750000

SUCTION SURFACE

X Y

*-5.471900 -I,682100

*-4.750200 -I.268000

-4.008900 -0.895900

-3.630900 -0.725600

-3.248000 -0,565800

-2.860500 -0.416800

-2.468700 -0.279100

-2.072800 -0,152800

-I.673300 -0.038300

-I,270500 0.064200

-0.864800 0.154500

-0.456500 0,232600

-0.046000 0,298300

0,366200 0,351600

0.780000 0.392300

1,194700 0.420400

1.610100 0.436000

2.025800 0.438900

2,441400 0.429100

2.856500 0.406700

3.270700 0.371600

3.683600 0.323700

4.094900 0.263200

* 4.912700 0.104400

* 5.724100 -0.104800

PRESSURE

X

*-5,528800

*-4,757300

-3. 979000

-3. 587300

-3, 193900

-2. 798800

-2. 4021 O0

-2. 003800

- I , 604200

- I . 2031 O0

-0,800800

-0. 397400

O. 007200

O. 412600

O. 819000

I . 2261 O0

I ,633800

2. 042000

2. 450700

2,8597OO

3. 268800

3,6781 O0

4. 087400

* 4. 906000

* 5. 724600

SURFACE

Y

- I. 493800

- I . 221400

-0. 971400

-0. 8548OO

-0. 743800

-0. 638500

-0,539 I00

-0. 445600

-0. 3583OO

-0. 277300

-0. 202600

-0. 134300

-0. 072500

-0. 017200

O, 031500

O. O7370O

O. 09200

O. 38000

O. 60200

O. 75600

O. 84300

O. 86200

O. 813OO

O. 51 I00

O. 093700

LEAD I NG EDGE

X Y

-3. 991300 -0,932600 CENTER

TRA I L I NG EDGE

X Y

4. 088200 0.222500

0.040720 RAD I US 0.041200

NASA/TM--2000-209916 282
ALT LOW FAN STATOR BLADE

RAD I US : 7,700000

SECT] ON BO7-B07

GAGE: 2. 200000

SUCTION SURFACE

X Y

*-5.446600 -I.767700

*-4.734600 -I,341900

-4.001000 -0,956900

-3.626100 -0.779700

-3.245800 -0.612700

-2.860700 -0.456500

-2.470800 -0,311700

-2.076500 -0,178500

-I.678200 -0,057500

-I.276300 0,051100

-0.871100 0,147000

-0.463000 0,230200

-0.052500 0.300400

0.360000 0.357500

0.774200 0.401400

1.189500 0.432200

1.605600 0,449700

2.022100 0.453800

2.438500 0.444600

2.854400 0.422100

3.269300 0.386000

3.682800 0,336600

4,094500 0.273600

* 4.912500 0.106800

* 5.723300 -0,114400

PRESSURE SURFACE

X Y

*-5.506300 -I .591300

*-4.741600 -I.299800

-3.969300 -I.031 I00

-3. 580300 -0. 905300

-3.189400 -0.785200

-2,796400 -0.671 I00

-2. 401600 -0.563200

-2. 004900 -0,461800

- I .606500 -0.367200

-I.206500 -0.279400

-0.804900 -0, 198700

-0.401900 -0. 125200

0.002400 -0,058900

0.407800 0.000000

0.814300 0.051600

I .221600 0.095700

1,629700 0,132300

2. 038400 O, 161400

2. 447600 O, 182900

2.8571 O0 O. 196700

3,266800 0.202900

3.676500 0.201200

4. 086200 O. 191800

* 4. 905600 O. 149900

* 5. 725000 0,077200

LEAD I NG EDGE

X Y

-3. 982600 -0.992900 CENTER

TRA IL ING EDGE

X Y

4. 087600 O. 233000

0.040450 RADIUS 0.04 190

NASA/TM--2000-209916 283
ALT LOW FAN STATOR BLADE

RAD I US • 7, 150000

SECT I ON BOB-B08

GAGE. I . 650000

SUCTION SURFACE

X Y

*-5,417700 -I.862200

*-4.714000 -I.424000

-3.988300 -I,025000

-3.617200 -0,840200

-3.240600 -0.665200

-2.858500 -0.500900

-2.471200 -0,347900

-2,079000 -0.206900

-I.682300 -0.078300

-I.281600 0.037400

-0.877100 0.139800

-0,469400 0.228900

-0.058900 0.304300

0,353900 0.366000

0.768600 0.413700

1,184700 0,447300

1.601700 0,466800

2.019000 0.472200

2.436400 0,463300

2.853200 0,440000

3,268900 0,402300

3.683000 0.350200

4,095200 0.283400

* 4.913900 0,105700

* 5.725000 -0.130800

PRESSURE SURFACE

X Y

*-5,471500 -I.699400

*-4.717700 -I,387000

-3. 954300 - I . 097800

-3. 569000 -0.961900

-3, 181300 -0.831800

-2. 791200 -0.707900

-2. 398900 -0,590700

-2.004300 -0. 480300

- I .607700 -0.377300

-I.209000 -0.281900

-0.808400 -0.194300

-0.406100 -0, 114700

-0.002200 -0. 043200

0.403t00 0,019900

0.809700 0.074700

1.217300 O. 121 I00

I . 625900 O. 158900

2. 0351 O0 O. 1881 O0

2. 444900 0.208600

2.855100 0.220300

3. 265400 0.223200

3.675600 0.217000

4,085700 0.201800

* 4. 905600 O, 144400

* 5. 7251 O0 0.051000

LEADING EDGE

X Y

-3. 968900 - I .060300 CENTER

TRA I L I NG EDGE

X Y

4. 087800 0,242900

0.040230 RAD I US 0.04 190

NASA/TM_2000-209916 284
ALT LOW FAN STATOR BLADE

RAD I US : 6. 600000

SECT ION BO9-B09

GAGE : I , I00000

SUCT I ON SURFACE

X Y

*-5.373000 -I,978700

*-4.684800 -I,527400

-3,971800 -1o112500

-3,606000 -0,918700

-3.234000 -0,734000

-2.856100 -0,559600

-2.472400 -0,396400

-2.083200 -0,245200

-t.688900 -0,106800

-I,289800 0,018200

-0.886500 0.129500

-0,479400 0,226500

-0,069000 0,309100

0,344100 0.377100

0.759400 0,430100

1,176300 0.468200

1,594400 0,491200

2.013000 0,498900

2.431600 0,491300

2.849600 0,468300

3.266500 0.429800

3,681600 0.375600

4,094400 0.305500

* 4,913100 0.117600

* 5,722600 -0.133900

PRESSURE SURFACE

X Y

*-5.431 I00 -I,828800

*-4.688600 -I.494800

-3. 936300 -I. 183200

-3,554600 -I.035800

-3. 171200 -0.894000

-2,785000 -0.758300

-2.396100 -0.629600

-2. 004400 -0.508100

-I,610100 -0.394600

-I,213200 -0.289300

-0.814100 -0. 192700

-0.412700 -0,105000

-0,009400 -0,026500

0,395700 0.042700

0.802400 O, 102400

I .210400 O. 152500

I .619500 O. 192900

2,029500 O, 223400

2,440100 0,244000

2. 851 I00 0.254500

3. 262200 O. 254800

3. 673200 0.244600

4,083800 0.224000

4.903800 O. 151600

* 5.722200 0,037600

LEADING EDGE

X Y

-3.951400 -t.146700 CENTER

TRA I L I NG EDGE

X Y

4,086600 0.265 I00

0.039850 RAD I US 0.041160

NASA/TM_2000-209916 285
ALT LOW FAN STATOR BLADE

RAD I US • 6. 050000

SECT I ON B IO-BIO

GAGE : O. 550000

SUCTION SURFACE

X Y

,-5.322400 -2.116400

*-4.649900 -I.644700

-3.950600 -I.208600

-3.590900 -I.003900

-3.224500 -0.808100

-2.851300 -0.622300

-2.471600 -0.447800

-2.085700 -0.285700

-I.694000 -0.136800

-I.296900 -0.001900

-0.894900 0.118600

-0.488500 0.224100

-0.078400 0.314400

0.334800 0.389100

0.750700 0.448000

1.168500 0.490900

1.587600 0.517800

2.007400 0.528500

2.427300 0.523000

2.846600 0.501000

3.264700 0.462500

3.680900 0.407300

4.094500 0.335400

* 4.913900 0.141500

* 5.722900 -0.119200

PRESSURE SURFACE

X Y

*-5.376800 -I.975700

*-4.650800 -I.615300

-3.911200 -I.277300

-3. 536300 -I . 116700

-3. 158000 -0.961700

-2. 776300 -0.813100

-2. 391300 -0.67t700

-2. 002900 -0.538300

-I.61 t300 -0.413400

-I.216600 -0.297700

-0.819000 -0. 191500

-0.418700 -0.095300

-0.016000 -0.009300

0.388900 0.066200

0.795700 O. 131200

1.204100 O. 185500

1.613900 0.229000

2. 024000 0.261400

2. 436100 0.282700

2. 848000 0.292800

3. 2601 O0 O. 291400

3. 671900 0.278600

4.083200 0.254000

4. 904300 O. 169400

, 5. 723400 0.037600

LEAD I NG EDGE

X Y

-3. 928900 -I.241800 CENTER

TRA I L I NG EDGE

X Y

4. 086500 0.295000

0.039670 RAD I US 0.041140

NASA/TM_2000-209916 286
ALT LOW FAN STATOR BLADE

RAD I US : 5. 500000

SECTION BI I-BI

GAGE: O. 000000

SUCTION SURFACE

X Y

*-5,268900 -2.237200

*-4.613200 -I.744200

-3.927500 -I.287200

-3.573400 -I.072200

-3.211800 -0.866200

-2,842800 -0.670600

-2,466600 -0.486800

-2,083500 -0,315800

-I,694000 -0.158600

-I.298500 -0.016000

-0.897700 0.111600

-0.492100 0.223600

-0.082300 0.319700

0.331000 0.399700

0.747200 0.463100

1.165600 0.510000

1.585500 0,540200

2,006200 0.553600

2.427000 0,550100

2.847300 0,529800

3,266400 0,492400

3,683400 0.438000

4,097800 0.366600

* 4.918800 0.172800

* 5.729400 -0.089000

PRESSURE SURFACE

X Y

*-5.321900 -2. 107100

*-4.612000 -t.718900

-3. 885700 -I .354700

-3.516400 -I. 181600

-3. 143000 -I .014500

-2. 765700 -0.854400

-2. 384200 -0,702200

- I . 998800 -0.558700

-I.609600 -0.424600

-I.2t6700 -0.300500

-0.820400 -0.186900

-0.42t000 -0,084000

-0.018700 O. 007600

0,386100 0,088000

0,793100 O. 157100

I .201900 0.214500

1,612300 0.260300

2. 023800 0.294400

2. 4361 O0 0,316600

2,848900 0.326900

3,26 1700 0,325 I00

3. 674300 0,311300

4. 086300 0,285400

* 4,908500 0.197300

* 5.728300 0,060800

LEAD ] NG EDGE

X Y

-3. 904700 - I .319800 CENTER

TRA IL ING EDGE

X Y

4. 089800 0.326300

0.039730 RAD I US 0.04 I00

NASA/TM---2000-209916 287

PART 3

SHORT CHORD STATOR VANES

NASA/TM--2000-209916 289
Bo2i

LEADING EDGE

OF BLADE

I _STACKING LINE

K

10.143

II

DETAIL C

70 PLACES

EQUALLY SPACED

(5" 8' 34")

SECTION DATUM L[NES --

SUCTION SURFACE_

-X.,_ i ....+X

_ "'M 8oP.

_-_EISS_E SURFACE

TYPICAL AIRFOIL SECTION

B_',Bo,_o Bn B ,,

÷Y

_-y

NASA/TM--2000-209916 290
ALNF SHOR T STATOR

RAD I US : IO. 450000

SECT I ON BOI -BOI

GAGE : 4. 950000

SUCTION SURFACE

X Y

*-1,098300 -0.326800

*-0.953500 -0,241200

-0,804700 -0,165200

-0,728800 -0,130800

-0,651900 -0.098800

-0.574000 -0.069400

-0.495100 -0,042400

-0.415500 -0,018100

-0.335100 0.003700

-0.254000 0,023000

-0,172400 0.039500

-0,090300 0.053500

-0.007800 0.064800

0.075100 0.073400

0,158200 0.079400

0.241400 0.082700

0.324700 0.083300

0,408000 0,081200

0,491100 0,076500

0,574100 0,069100

0,656800 0.059000

0.739200 0,046300

0,821100 0,030900

* 0,983400 -0.008000

* 1.143700 -0.057700

PRESSURE

X

*-I, I I0100

*-0. 955300

-0. 798900

-0. 7201 O0

-0. 640900

-0. 561400

-0. 4816O0

-0. 401600

-0.3213OO

-0.240700

-0. 159900

-0. O789O0

O. 0O2200

O. O835OO

O. 165000

O. 246500

O. 328200

O. 409900

O. 49 1700

O, 573600

O. 655400

O. 7373O0

0,819100

* O. 982400

* I . 145300

SURFACE

Y

-0. 281600

-0. 228500

-0. 180600

-0. 158600

-0, 137900

-0. II 8400

-0. 100200

-0. O833OO

-0. 0677O0

-0,0534O0

-0. O4O4OO

-0. 028600

-0.018200

-0,009000

-0. 001200

O. 0O54OO

O. 0 0600

O, 0 45OO

0.0 7100

O. 0 8500

O. 0 8500

O. 0 72OO

O, 0 4600

O, 005500

-0. OO88OO

LEADING EDGE

X Y

-0.801300 -0. 172700 CENTER

TRA I L I NG EDGE

X Y

0.819400 0.022800

0.008200 RADIUS 0.008200

NASA/TM--2000-209916 291
ALNF SHOR T STATOR

RAD I US: 9. '::300000

SE_CI ION UU2-UU21

GAGE: 4. 400000 I

SUCTION SURFACE

X Y

*-1,102600 -0,302500

*-0,956200 -0.224100

-0.805800 -0.154500

-0,729100 -0,123000

-0,651400 -0,093700

-0,573100 -0.066600

-0,493900 -0.041700

-0,414100 -0,019000

-0,333700 0.001400

-0,252800 0.019500

-0,171400 0.035300

-0.089500 0,048900

-0.007300 0,060100

0.075100 0.069000

0,157800 0.075600

0.240600 0,079900

0.323600 0.081800

0.406500 0.081400

0,489400 0,078600

0,572200 0.073500

0,654800 0,066100

0,737200 0.056400

0,819300 0,044400

* 0,982600 0,013500

* 1,144700 -0,026600

PRESSURE

X

*-I, 115200

*-0. 958500

-0. 800600

-0 721200

-0 641500

-0 561600

-0 481600

-0 401300

-0 320900

-0 240200

-0 159400

-0 078500

0 002600

O. 0838OO

O. 165100

O. 246500

O. 327900

0 409500

0 491 I00

0 572800

0 65450O

0 736200

0 817900

* 0 981300

* I . 144700

SURFACE

Y

-0.257700

-0.211900

-0. 170100

-0. 150700

-0. 1323O0

-0. 114800

-0. 098400

-0. O83OOO

-0.068600

-0,0551 O0

-0. 042700

-0.031300

-0.O208OO

-0. O I 1400

-0. 003000

O, 004400

O. 010800

O. 016200

O. 020600

O. 024000

O. 026300

O. 027600

O. 028000

O. 0261 O0

O, 020600

LEAD I NG EDGE

X Y

-0.802600 -0, 162100 CENTER

TRA I L I NO EDGE

X Y

0.817900 0.036300

0.008300 RADIUS 0.008300

NASA/rM--2000-209916 292
ALNF SHORT STATOR

RAD I US : 9. 625000

SECT I ON B03-B03

GAGE: 4, 125000

SUCTION SURFACE

X Y

*-1,100800 -0,315400

*-0,954300 -0.235000

-0,804200 -0.163400

-0,727800 -0,130900

-0,650500 -0,100600

-0,572400 -0.072600

-0,493600 -0,046800

-0.414000 -0.023200

-0,333800 -0,001900

-0,253000 0,017100

-0,171700 0.033700

-0.090000 0,048100

-0.007900 0,060000

0.074500 0.069700

0,157200 0.077000

0.240000 0,081900

0,322900 0,084500

0,405900 0.084700

0.488900 0.082500

0,571700 0.078000

0.654400 0.071100

0.736900 0.061900

0.819000 0,050400

* 0.982000 0,020500

* 1.143400 -0,018600

PRESSURE

X

*-I 112100

*-0 956000

-0 798700

-0 719600

-0 640200

-0 560600

-0 480700

-0 400600

-0 320400

-0 239900

-0 159200

-0 078400

0 002600

0 083700

0 165000

0 246300

0 3278O0

O. 40930O

O. 490900

0.572600

O, 654300

O. 736000

O. 8 17800

* 0,981700

* I , 146000

SURFACE

Y

-0. 2713OO

-0. 2231 O0

-0. 178900

-0. 158300

-0. 138700

-0. 120200

-0. 102700

-0. 086200

-0. 070800

-0,056500

-0.043200

-0. 030900

-0.019700

-0. 009600

-0. 000500

O, 007500

O. 014400

O. O2O30O

O. 025200

O. 029000

O. 031700

O. 03340O

O. 034000

O. 031900

0.025400

LEAD I NG EDGE

X Y

-0,800700 -0. 170900 CENTER

TRA I L I NG EDGE

X Y

0.817800 0.042200

0.008300 RADIUS O.OO82OO

NASA/TM---2000-209916 293
ALNF SHORT STATOR

RAD I US " 9. 350000

SECT I ON BO4-B04

GAGE : 3. 850000

SUCTION SURFACE

X Y

*-1,094400 -0,331100

*-0,950500 -0,248100

-0,802200 -0.173900

-0.726400 -0,140100

-0.649500 -0,108500

-0.571800 -0,079200

-0.493300 -0,052200

-0.414000 -0,027500

-0,334000 -0.005200

-0.253400 0.014800

-0,172200 0.032400

-0.090600 0,047600

-0.008500 0,060400

0.073900 0.070800

0.156500 0,078800

0.239400 0,084300

0,322400 0,087400

0,405400 0,088100

0.488500 0,086300

0,571400 0.082200

0,654200 0,075600

0,736800 0,066500

0.819000 0.055100

* 0.982200 0,025400

* 1,143800 -0.013500

PRESSURE SURFACE

X Y

*-1.107300 -0.287600

*-0.952700 -0.236400

-0.796500 -0. 189200

-0.717800 -0. 167100

-0.638700 -0.146000

-0.559400 -0. 126100

-0.479800 -0. 107300

-0.400000 -0.089600

-0.319900 -0.073000

-0. 239600 -0,057600

-0, 159000 -0,043400

-0. 078300 -0,030200

0.002600 -0.018200

0.083700 -0.007400

O. 164900 0,002300

0.246200 0,010900

O. 327600 O. 018300

O. 409200 O. 024600

O. 490800 O. 029700

0,572500 0.033700

O, 654200 O. 036500

O, 736000 O, 038200

0.817800 0.038700

* O. 981400 O, 0361 O0

* I . 145000 0.028700

LEADING EDGE

X Y

-0.798800 -0, 181300 CENTER

TRA I L I NG EDGE

X Y

0.817800 0.046900

0,008200 RADIUS 0.008200

NASA/TM--2000-209916 294
;HORT

I ON

¢

,2900

_8900

9O9O0

.725400

-0.648900

-0,571400

-0.493100

-0.414000

-0.334100

STATOR

8.800000

SURFACE

Y

-0. 343500

-0. 257800

-0. 18t 3OO

-0. 146500

-0. II 4000

-0. 083800

-0. 056000

-0. O30600

-0. O075OO

-0.253600 0,013100

-0,172500 0,031400

-0.090900 0,047100

-0.008800 0,060400

0.073600 0.071200

0,156300 0,079600

0,239200 0,085400

0,322300 0.088800

0,405400 0.089600

0,488500 0.087900

0,571500 0.083800

0,654400 0.077100

0.737000 0.068000

0,819300 0,056400

0.983000 0,025700

1.145500 -0.015000

SECT I ON BO5-B05

GAGE : 3,300000

PRESSURE

X

*-I, 105500

*-0,950800

-0,794900

-0,716500

-0,637800

-0 558800

-0 479400

-0 399700

-0 319800

-0 239600

-0 159100

-0 0785OO

O. 002400

O. 083400

O. 164700

O, 246000

O. 32750O

O. 4091 O0

O. 490800

O. 572500

O. 654300

O. 736100

O. 817900

* 0,981500

* l, 145100

SURFACE

Y

-0.304000

-0.247700

-0,196600

-0,173000

-0.150700

-0,129600

-0.109600

-0.090900

-0.073500

-0.057300

-0,042300

-0.028500

-0.016000

-0.004800

0,005200

0,014000

0,021500

0.027700

0,032700

0.036400

O,O388OO

0.040000

0.040000

0.036400

0.028000

LEAD ING EDGE

X Y

-0.797300 -0,188700

0,008200

CENTER

RADIUS

TRA IL ING EDGE

X Y

O, 817900 O. 048300

0.008300

NASAfrM--2000-209916 295
ALNF SHORT STATOR

RAD I US : 8. 250000

SECT I ON B06

GAGE : 2. 7500,

SUCTION SURFACE

X Y

*-t,090600 -0.342700

*-0.948200 -0.257700

-0,801000 -0.181500

-0,725600 -0,146700

-0.649000 -0,114100

-0.571600 -0,083900

-0,493200 -0.056000

-0,414100 -0.030600

-0.334200 -0.007500

-0,253600 0.013100

-0,172500 0,031200

-0,090800 0.046900

-0.008700 0°060000

0,073800 0,070700

0.156500 0.078900

0,239500 0.084500

0,322600 0.087600

0.405700 0,088200

0.488800 0,086200

0,571900 0.081700

0.654700 0.074700

0.737300 0.065200

0,819600 0,053200

* 0.983300 0.021700

* 1,145800 -0.019800

PRESSURE SURFACE

X Y

*-I. 105200 -0.304800

*-0. 950700 -0. 248400

-0.795000 -0. 196800

-0.716700 -0,172800

-0.638100 -0.150000

-0.5591 O0 -0. 128500

-0.479800 -0.108300

-0. 400200 -0. 089400

-0.320200 -0.071800

-0. 240000 -0.055400

-0. 159600 -0.040400

-0. 078900 -0. 026700

0.0021 O0 -0.014300

O. 083200 -0. 003200

O. 164400 0.006500

0.245900 0.015000

0.327400 0.022100

0.409100 0.027800

0.490800 0.032300

0.572600 0.035400

0.654400 0.037200

0.736300 0.037700

O. 8181 O0 0.036800

* 0.981400 0.030800

* I. 144300 0.019200

LEAD ING EDGE

X Y

-0.797400 -0. 188900 CENTER

TRA I L I NG EDGE

X Y

O. 8 18200 0.045 I O0

0.008200 RADIUS 0.008300

NASA/TM--2000-209916 296
ALNF SHORT STATOR

RAD I US: 7. 700000

SECT ION BO7-B07

GAGE" 2. 200000

SUCTION SURFACE

X Y

*-1,086900 -0,364500

*-0.945000 -0.274500

-0,798700 -0.194100

-0.723900 -0.157500

-0,648000 -0,123300

-0,571100 -0.091500

-0.493100 -0.062100

-0,414300 -0.035300

-0,334600 -0.010900

-0.254200 0.010900

-0.173200 0.030100

-0.091600 0,046700

-0.009500 0.060700

0.073100 0.072100

0.155900 0.080900

0,239000 0,087000

0.322200 0.090400

0.405500 0.091200

0.488800 0.089300

0.571900 0.084700

0.654900 0.077500

0.737600 0.067700

0.820000 0.055200

* 0.983900 0.022100

* 1,146600 -0.021800

PRESSURE SURFACE

X Y

• -I. I00100 -0.329500

• -0,946800 -0.266400

-0.792300 -0.209300

-0.714600 -0. 183000

-0.636600 -0. 158200

-0.558100 -0. 134800

-0.479100 -0. I 12800

-0.399800 -0.092200

-0. 320100 -0.073100

-0.240100 -0.055500

-0.159800 -0.039300

-0.079200 -0.024600

0.001700 -0,0 I 1400

O. 082700 O. 000400

O. 164000 0.010600

O. 245500 0.019400

0.327t00 0.026700

0.408900 0.032500

0.490700 0.036700

0.572600 0.039500

O. 654500 O. 040800

0.736400 0.040500

O. 818400 0.038800

• O. 982700 0.031200

• I. 147400 0.018000

LEAD ING EDGE

X Y

-0.794900 -0.201500 CENTER

TRA I L I NG EDGE

X Y

0.818500 0.0471 O0

0.008300 RADIUS 0.008300

NASA/TM_2000-209916 297
ALNF SHORT STATOR

RAD I US • "7. 150000

SECTI ON BOB-B081

GAGE : I . 650000

SUCTION SURFACE

X Y

*-1.078400 -0,388800

*-0.939700 -0.293900

-0.795800 -0.209000

-0.721900 -0.170300

-0.646700 -0.134100

-0.570400 -0.100300

-0.492900 -0.069200

-0.414500 -0.040700

-0.335200 -0.014800

-0,255000 0.008500

-0.174100 0,029000

-0.092500 0.046700

-0.010400 0.061800

0.072200 0.074000

0.155100 0.083400

0,238400 0.090100

0,321800 0,093900

0.405200 0,094900

0.488700 0.093100

0,572000 0.088400

0,655200 0.080900

0,738000 0,070600

0.820500 0.057500

* 0.984600 0.022900

* 1.147500 -0.022900

PRESSURE SURFACE

X Y

*-1.091000 -0.355100

*-0. 940900 -0. 286300

-0. 788800 -0.223900

-0.712000 -0.195100

-0.634700 -0. t67900

-0.556700 -0.142300

-0.478300 -0.118200

-0. 399400 -0. 095800

-0.320100 -0.075000

-0. 240300 -0,055800

-0.160200 -0,038200

-0,079700 -0. 022300

0.001 I00 -0.008100

0.082200 0.004400

O. 163500 0.015300

0.245100 0,024500

0.326800 0.032000

0.408600 0.037800

0.490600 0.041900

0.572600 0.044300

O. 654600 O. 044900

0.736700 0.043900

0.818700 0.041 I00

* 0.982400 0.030100

* I. 145700 0.011900

LEAD ING EDGE

X Y

-0.791700 -0.216200

0.008300

CENTER

RADIUS

TRA I L I NG EDGE

X Y

O. 819000 O. 049400

0.008300 I

NASA/TM--2000-209916 298
ALNF SHORT STATOR

RAD I US : 6. 600000

SECT I ON BO9-B09

GAGE: I o I00000

SUCTION SURFACE

X Y

*-1.068300 -0.419900

*-0.932700 -0.318900

-0.791500 -0.228300

-0.718800 -0,186900

-0.644700 -0.148100

-0.569300 -0.111900

-0.492600 -0.078400

-0.414700 -0.047700

-0.335800 -0.019700

-0.256000 0.005400

-0.175200 0.027600

-0,093800 0,046900

-0.011700 0,063200

0.071000 0.076600

0.154000 0.087100

0.237400 0,094500

0.321100 0,098900

0.404800 0.100200

0.488500 0.098600

0.572100 0,093800

0.655600 0.086100

0.738500 0,075300

0.821100 0,061500

* 0.985;00 0,024900

* 1,147500 -0,023700

PRESSURE SURFACE

X Y

*-1.079800 -0.387500

*-0.933300 -0.311800

-0.784000 -0.242900

-0.708300 -0.21 I000

-0.631900 -0.180800

-0.554800 -0.152400

-0.477100 -0. 125700

-0.398800 -0.100900

-0.319900 -0.077800

-0.240500 -0.056700

-0, 160600 -0.037300

-0.080200 -0.019900

0.000500 -0.004300

0.081500 0.009300

O. 162900 0.021 I00

0.244500 0,030900

0.326300 0.038800

0,408300 0.044700

0.490400 0.048700

O, 572600 O, 050800

O. 654800 O. 050900

0.737000 0,049000

O. 8191 O0 0.045200

* 0.983000 0,031900

* I. 146500 0,01 I000

LEAD I NG EDGE

X Y

-0.787300 -0.235400 CENTER

TRA [ L i NG EDGE

X Y

0.819600 0,053400

0.008200 RADIUS 0.008200

NASA/TM--2000-209916 299
ALNF SHORT STATOR

R AD I US : 6. 050000

SECI ION UIO-UIU

GAGE : O. 550000

SUCTION SURFACE

X Y

*-1.056400 -0.450500

*-0.924800 -0.343400

-0.786800 -0,247100

-0.715400 -0.203000

-0.642400 -0.161600

-0,567900 -0.123000

-0,491900 -0.087300

-0,414700 -0,054400

-0,336300 -0,024500

-0.256700 0.002400

-0.176200 0.026200

-0,094900 0,047000

-0,012800 0,064700

0.069900 0.079200

0,153100 0.090500

0.236700 0.098700

0,320500 0,103700

0.404400 0.105400

0,488400 0.104000

0.572200 0.099300

0,655800 0,091400

0,739000 0,080400

0.821700 0.066100

* 0,985600 0,027600

* 1,147500 -0.024100

PRESSURE SURFACE

X Y

*-1.068700 -0.419400

*-0.925300 -0.336800

-0.778700 -0.261400

-0,704200 -0.226400

-0.628900 -0, 193200

-0.552700 -0. 162100

-0,475700 -0, 132900

-0.397900 -0.105700

-0,319500 -0.080600

-0.240500 -0.057500

-0.160800 -0.036500

-0,080700 -0.017500

-0.000100 -0,000700

0.08 1000 0.0 14000

O. 162300 0.026600

0.244000 0.037100

0.326000 0.045400

O. 4081 O0 0.051500

O, 490400 O, 055500

0,572700 0,057300

0.655100 0.057000

0.737400 0,054500

0.819600 0,049800

* 0.983700 0.033800

* I . 147400 0.009000

LEAD I NG EDGE

X Y

-0.782300 -0.254000 CENTER

TRA IL I NG EDGE

X Y

0.820200 0.058000

0.008200 RADIUS O.OO820O

NASA/TM--2000-209916 300
ALNF SHORT STATOR

RAD I US : 5. 500000

SECTION BI I-BII

GAGE : O. 000000

SUCTION SURFACE

X Y

*-1,050500 -0.468400

*-0,920300 -0.356700

-0.783700 -0,256600

-0.713000 -0.210900

-0,640700 -0.168100

-0.566700 -0.128200

-0.491100 -0.091200

-0.414200 -0.057300

-0.336000 -0,026500

-0.256600 0,001300

-0,176200 0,025800

-0,094900 0.047200

-0,012800 0.065400

0.069900 0.080300

0.153100 0.091900

0.236800 0.100300

0.320700 0,105400

0.404800 0,107200

0.488800 0,105800

0.572800 0.101100

0.656500 0.093100

0.739800 0.081900

0.822600 0.067600

* 0.986700 0.029700

* 1.148800 -0.020600

PRESSURE

X

*-I ,060100

*-0.919700

-0. 775300

-0. 701600

-0.626900

-0.551200

-0. 4747OO

-0 3973OO

-0 319100

-0 24O3OO

-0 1607O0

-0 080700

-0 0001 O0

0 O81000

0 162400

0 244200

0 326200

O. 408500

0 490900

0 573300

0 655800

0 738200

0 820500

* 0 984800

* I 148700

SURFACE

Y

-0.438200

-0.350400

-0.270600

-0.233700

-0.198800

-0.166100

-0.135400

-0.107000

-0.080800

-0.056700

-0,034900

-0.016300

0.002100

0.017200

0.030000

0,040600

0,048900

0,054900

0,058700

0,060200

0.059500

0.056500

0.051300

0,034300

0.008500

LEAD ING EDGE

X Y

-0,779100 -0.263400 CENTER

TRA I L I NG EDGE

X Y

0.821 I O0 0.059500

0.008200 RADIUS 0.008200

NASA/TM--2000-209916 301

Appendix C

The noise data from the Alternative Low Noise Fan is presented in this appendix. The data is arranged in 5 sections corresponding to the five tested configurations: 7 vane hard, 7 vane fully treated, 7 vane partially treated,

70 vane hard and 70 vane fully treated. In each of these sections the data from the six fan speeds is presented. These

are 10671, 10137, 9604, 8537, 7736, and 6402 rpmc. The data are presented at roughly 10° angular positions from

158 ° in the aft to 24.5 ° in the front. Even this mass of data is only a sampling of the data since the data is taken at

roughly every 2.5 °. At each of the speeds both narrow band data from 0 to 50 000 Hz and l/3rd octave data are presented with the narrow band data being presented first. The narrow band data plots are sound pressure level in decibels plotted versus frequency in kilohertz. The title of the plot gives both the speed and the angle of the plot. The

1/3rd octave plots are sound pressure level in decibels plotted versus frequency in hertz. The frequency axis is a log

scale with the lowest frequency shown being 10 Hz and the highest frequency being 100 000 Hz. Again the title of

the plot gives both the speed and the angle of the plot.

Appendix C Section 1--7 Vane hard configuration

Appendix C Section 2--7 Vane fully treated configuration

Appendix C Section 3--7 Vane partially treated configuration

Appendix C Section 4----70 Vane hard configuration

Appendix C Section 5--70 Vane fully treated configuration

Appendix C is contained on the enclosed CD.

NASA/TM--2000-209916 303
REPORT DOCUMENTATION PAGE FormA_provea

OMB No. 0704-0188

Public reporting burden for this collection Of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources,

gathering and maintaining the data needed, and completing and reviewing the collection o1 irdormation. Send comments regarding this burden estimate or any other aspect of this

collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson

Davis Highway, Suite 1204, Adington, VA 22202-4302, and to the Office of Management and Budget, Paperwork Reduction Project (0704-0188), Washington, DC 20503.

1. AGENCY USE ONLY (Leave blank) 12. REPORT DATE

I September 2000

4, TITLE AND SUBTITLE

The Alternative Low Noise Fan

6. AUTHOR(S)

James H. Dittmar, David M. Elliott, Robert J. Jeracki,

Royce D. Moore, and Tony L. Parrott

7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)

National Aeronautics and Space Administration

John H. Glenn Research Center at Lewis Field

Cleveland, Ohio 44135- 3191

9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)

National Aeronautics and Space Administration

Washington, DC 20546-0001

3. REPORT TYPE AND DATES COVERED

Technical Memorandum

5. FUNDING NUMBERS

WU-522-81-11-00

8. PERFORMING ORGANIZATION

REPORT NUMBER

E-12153

10. SPONSORING/MONITORING

AGENCY REPORT NUMBER

NASA TM--2000-209916

11. SUPPLEMENTARY NOTES

James H. Dittmar, David M. Elliott, Robert J. Jeracki, and Royce D. Moore, NASA Glenn Research Center,

Tony L. Parrott, Langley Research Center, Hampton, Virginia 23681. Responsible person, James H. Dittmar,

organization code 5940; (216) 433-3921. The noise data from the Alternative Low Noise Fan is presented in Appendix C,

which is only contained on the enclosed CD.

12a. DISTRIBUTION/AVAILABILITY STATEMENT

Unclassified - Unlimited

Subject Category: 71 Distribution: Nonstandard

This publication is available from the NASA Center for AeroSpace Information, (301) 621-0390.

12b. DISTRIBUTION CODE

13. ABSTRACT (Maximum 200 words)

A 106 bladed fan with a design takeoff tip speed of 1100 ft/sec was hypothesized as reducing perceived noise because of the shift of the blade passing

harmonics to frequencies beyond the perceived noise rating range. A 22 in. model of this Alternative Low Noise Fan, ALNF, was tested in the NASA

Glenn 9><15Wind Tunnel. The fan was tested with a 7 vane long chord stator assembly and a 70 vane conventional stator assembly in both hard and

acoustically treated configurations. In addition a partially treated 7 vane configuration was tested wherein the acoustic material between the 7 long

chord stators was made inactive. The noise data from the 106 bladed fan with 7 long chord stators in a hard configuration was shown to be around

4 EPNdB quieter than a low tip speed Allison fan at takeoff and around 5 EPNdB quieter at approach. Although the tone noise behaved as hypothesized, the majority of this noise reduction was from reduced broadband noise related to the large number of rotor blades. This 106 bladed ALNF is a

research fan designed to push the technology limits and as such is probably not a practical device with present materials technology. However, a low

tip speed fan with around 50 blades would be a practical device and calculations indicate that it could be 2 to 3 EPNdB quieter at takeoff and 3 to

4 EPNdB quieter at approach than the Allison fan. 7 vane data compared with 70 vane data indicated that the tone noise was controlled by rotor

wake--stator interaction but that the broadband noise is probably controlled by the interaction of the rotor with incoming flows. A possible multiple

pure tone noise reduction technique for a fan/acoustic treatment system was identified. The data from the fully treated configuration showed significant

noise reductions over a large frequency range thereby providing a real tribute to this bulk absorber treatment design. The tone noise data with the

partially treated 7 vane configuration indicated that acoustic material in the source noise generation region may be more effective than similar material

outside of the generation region.

14. SUBJECT TERMS

Noise; Fan noise; Acoustic treatment

17. SECURITY CLASSIFICATION 18. SECURITY CLASSIFICATION

OF REPORT OF THIS PAGE

Unclassified Unclassified

NSN 7540-01-280-5500

19. SECURITY CLASSIFICATION

OF ABSTRACT

Unclassified

15. NUMBER OF PAGES

1_9

16. PRICE CODE

A_

20. LIMITATION OF ABSTRACT

Standard Form 298 (Rev. 2-89)

Prescribedby ANSI Std. Z39-18

298-102