International Gas Turbine Congress 2003 Tokyo
November 2-7, 2003
(6) Recent Findings of Analytical Studies in Unsteady
Aerodynamics, Aeroacoustics and Aeroelasticity ofTurbomachines(7) Aeroengine Technology in 21st Century
The Forum, which did not require original papers, washeld for the first time during the 2003 IGTC. It enabled
participants to freely exchange their opinions and information.
Three topics were discussed in the Forum. They were
“Industry-University Cooperation in Gas Turbine Research,”“Current Status and Strategy of Electricity and Energy Supply,”and “Wave Rotor”.
Two co-chairs and five guest panelists led a Panel
Discussion entitled “Gas Turbines in the Future”. The following
topics were discussed in the Panel Discussion from theperspectives of different fields: the position of the gas turbines in
the recent technology system, the technology of large gas
turbines for the generation of electric power, aero-engines, themarine transportation system and gas turbine technology, small
gas turbine technology, fuel technology for gas turbines, and gas
turbines for aerospace engineering.
In the Technical Sessions, academic presentations andactive question-answer sessions in various research and study
areas were given. The presentation and discussion topics inthese sessions were superalloy, unsteady flow and noise,
aeroengines, cascade design, heat transfer, turbine flow
simulation, combustion control, the blade structure, thermal
barrier coating, internal flows, heat transfer and flow transition,
the micro gas turbine, the ultra-micro gas turbine, the turbulencemodel, combustor design, advanced materials, diagnosis /control / measurement, the marine gas turbine and turbo-charger,
the industrial gas turbine and power plant, and numericalanalysis.
The presentation papers were collected and made into
CD-ROMs. This is the first time that we have published IGTC
proceedings on CD. However, the one-page abstracts werecollected and published in print, and this printing material wasprovided to every participant as a reference at the congress.
The congress exhibitions were held in the exhibition hallon the first floor and in the lobby on the second floor. In the
exhibition hall, 36 companies and organizations exhibited theirproducts in 33 exhibition areas; these products included gas
turbines, turbo-super chargers, related machines, and devices fornumerical analyses. On the second floor, university researchgroups (11 research institutions from 8 universities) and the Gas
Turbine Society of Japan introduced their research activities andresults in panel sessions. There were about 3700 attendances inthe exhibition in four days, and the exhibition was a great
success.
Besides the above activities, congress participants attend
several others. One hundred thirty-five people attended the
Welcome Reception and 170 people attended the Banquet heldat the Tokyo Sea Life Park restaurant in Kasai Rinkai Park. In
addition, 74 participants attended the Tea Ceremony Lesson in
two days, and among them, 31 were foreigners.
During the congress, we arranged two tours, Plant Tour A
and Plant Tour B, which had different destinations. Twenty-nine
people joined Plant Tour A, and visited the Japan Aerospace
Exploration Agency (the National Aerospace Laboratory ofJapan) and Tanashi Factory of Ishikawajima-Harima Heavy
Industries Co., Ltd. Twenty people attended Plant Tour B, andvisited the All-Nippon Airways Power Plant MaintenanceCenter and the Shinagawa Thermal-Power Station of Tokyo
Electric Power Co., Ltd. All of these activities were successful
and received warm appreciation.

Abstractth

The 8 International Gas Turbine Congress, sponsoredby the Gas Turbine Society of Japan, was held from November
2nd to 7th, 2003, at Tower Hall Funabori in Tokyo, Japan. The
collaborating societies of this Congress included theInternational Gas Turbine Institute (IGTI), the Japan Society of
Mechanical Engineers, the Japan Society for Aeronautical andSpace Sciences, and several related societies in countries such as
China, Korea, Great Britain, France, and Germany. The
cooperation by ASME/IGTI, particularly the effort of Dr. Wisler,
the former President of IGTI and the current Vice President of
the ASME, helped increasing the number of applications andsubmissions of abstracts and papers from overseas countries.
In order to organize the 2003 International Gas Turbine
Congress, an Organizing Committee was established, and thiscommittee was placed within the Gas Turbine Society of Japan.
This is different form the previous congresses. In the past, a
one-time organizing committee was temporarily established forthe administration and organization of each congress and was anindependent committee outside of the Gas Turbine Society ofJapan. However, since open and aboveboard accounting wassought for this particular congress, the Organizing Committee
was set up within the Society as a temporary organization. Under
the Organizing Committee, an Executive Committee wascreated as the actual working committee. Similar to the previous
congresses, the Executive Committee consisted of 5 units: theGeneral Affairs Committee, the Program Committee, theExhibition Committee, the Event Committee, and the Financial
Affairs Committee. Considering the current economic situation,
we made a greater effort than ever to reduce cost as much as
possible in the administration of the congress, including theselection of the site and a minimum trust in the innovators.
Four hundred seventeen people from Japan and 117
participants from 17 foreign countries attended the congress.
The total number of 534 participants was more than our initial
goal of 450 people.
One hundred sixty papers were selected for presentation
during the congress, 87 of which were from Japan and 73 fromforeign countries. Compared to the previous congress held in
Kobe, the total number of presentation papers was increased by
15, and the total number of papers from overseas countries wasincreased by 20. The overseas presentation papers made up 46%of the total papers selected. This composition was adequate forthe international congress.
The speeches and presentations were held under thefollowing four categories:● Keynote Speech ……..
7 Presentations● Forum………………….

3 Sessions● Panel Discussion…….

1 Session● Technical Session ……
160 Presentations
Presentations by Keynote Speakers were the importantfeatures of IGTC. Similar to the previous congress, seven
Keynote Speeches were given during the 2003 IGTC, and all
were appreciated. The topics were as follows:(1) Micro- or Small-Gas Turbines(2) High Temperature Materials for Gas Turbines: The
Present and Future(3) Fuel Cells and Gas Turbine for Future Energy System(4) Future View of Energy Supply and Role of Gas Turbine
in Japan(5) Combustion Technology for Current and Future Gas
Turbines

1© Gas Turbine Society of Japanlast session concluded behind schedule on some days during thecongress, and some participants commented that this made thecongress schedule a little bit tight.

Technical Program
1. Summary of Technical Sessions

2. Summary of speech

1.1 Technical Paper Statistics
The number of selected papers is summarized in Data 1.
The total number was 160, which was 15 more than in theprevious congress. It is noteworthy that the number ofcontribution papers from overseas countries greatly increased.
There were a total of 73 papers selected from overseas
contributors, which was 20 more than in the last congress, andwas 46% of the total number of papers.

2.1 Keynote speeches
Keynote Speech 1: Micro- or Small- Gas Turbines, Terry
Simon (University of Minnesota, USA)
Recently, there have been growing interests in micro-gas
turbines, and micro-jet engines are beginning to be recognized in
micro-manned or unmanned machines. Micro-gas turbines withregenerated heat exchangers in which hot-water supplies andpower can be used concomitantly, and those combined with fuelcells, are achieving great successes as distributed power sources
or engines, as well as heat sources for reactions or in space.
When developing micro-gas turbines for power
generation, we must use utmost caution for the regenerated heatexchangers. There has been no other time since the developmentof the gas turbines for automobiles that this much focus has beenplaced on the research and development of the regenerator. The
micro-gas turbine often utilizes a radial-flow turbo machine. In
addition, the application of ceramic parts or ceramic coatings is
drawing more attention in micro-turbo machines and their parts.
Recent radial-flow turbomachines require a better understandingof radial-flow hydrodynamics, such as the effect of thestreamline curvature in the boundary layer flow.
Finally,smaller dimensions require closer attention to the effect of asmaller Reynolds number pertinent to boundary layer transition
or flow separation, particularly in the case of an axial-flow
turbine used in aircraft propulsion. In his speech, Professor
Terry Simon also mentioned the recent developments relevant to
the topic.
In terms of system integration technologies for micro-gas
turbines, the one that combines a micro-gas turbine and a fuelcell is most famous. Research and development have been
actively pursued on the endurance of new materials and parts inthe use of ceramics. For the combustor, the compact low NOx
combustion technology and diversified fuel technology arebeing studied. For the regenerated heat exchanger, the focus has
been on the improvement of manufacturing technologies in
producing highly durable and reliable products at lower costs.
For researches and developments on turbomachines,
there have been growing interests in radial-flow turbines andnew CFD analysis technologies. For radial-flow turbines orhigh-load turbine blades, more attention has been paid to theinvestigation of the flow curvature effect on flow and heattransfer. In terms of the effect of a low Reynolds number, themicro-gas turbine has a low Reynolds number and high loads. In
such cases, flow separation might greatly affect the performanceof the design. Improvements on projection technology for
turbulent transitions, such as separation and reattachment flow,
will be necessary for turbine design. Various effects of turbine
flow, including the wake in the upstream turbine blade, have an
impact on the transition.
During the speech, recent achievements in research ontransitions in the turbines were introduced in detail. The issue
surrounding flow transition on a turbine blade is the main themeat University of Minnesota, where Professor Simon holds his
research lab; therefore, we invited him to speak more about theirachievements at the University of Minnesota.

1.2 Keynote Speech
In order to help the participants to gain better knowledgeof the recent academic and technical trends in the research anddevelopment of gas turbines, 7 keynote speeches were arranged
during the congress (Data 2), and three keynote speakers wereinvited from overseas countries.

1.3 Forum
During this congress, we attempted for the first time toarrange a free discussion section, calling it the “Forum”. This
discussion section did not require any original papers. The
purpose of having this session was to enable the participants to
exchange opinions and information on related topics. Under thisgoal, three topics were arranged for the Forum, as shown in Data3.

1.4 Panel Discussion
Shown in Data 4 is a Panel Discussion with the theme of“Gas Turbine in the Future”. Two chairpersons were elected toplan and bring out active discussions in the Panel Discussion,and five guest panelists were invited. Each of panelists gave aspeech on a topic of the future of industrial large and small gas
turbines, aero-engines, the marine gas turbine, and theirprospects concerning the perspective of fuel.

1.5 Organized Session
Among the selected papers, those closely related to themarine gas turbine and the ultra-micro gas turbine were specially
put together. We organized four sessions especially for these two
topics.

1.6 Lectures for Adolescents and the Public
In the exhibition halls, a lecture for general visitors wasarranged to begin at 2 PM on Monday, November 3. Dr. Osamu
Nozaki from the Japan Aerospace Exploration Agency wasinvited as the lecturer for this activity. We gave a simple
explanation concerning the basic concepts, including the theoryof the gas turbine jet engine used in airplanes, so that adolescents
could easily understand. The lecture was held for the purpose of
spreading knowledge about the gas turbine, enlightening the
public, appealing to adolescents, and contributing to the
Funabori community. We asked the staff of Tower Hall
Funabori to distribute the guide to the elementary and juniorhigh schools in the ward through the Board of Education of the
Edogawa Ward.

1.7 Summary of Program
Keynote Speech 2: High Temperature Materials for Gas
Turbines: The Present and Future, Hiroshi Harada(National Institute of Material Science)An overview of world trends in the technologies of heat
resistant materials used for high temperature parts ofaeronautical and industrial gas turbines, as well as the efforts

The program with the plans illustrated above is given in
Data 5. Referring to the comments given by the members of theInternational Advisory Committee, we allocated 30 minutes foreach presentation and a relatively longer lunch break. As aresult, we had to arrange six parallel sessions instead of only
four in the previous IGTC. Because of the time limitation, the2© Gas Turbine Society of Japanmade within Japan centering on government projects and future
projections, were discussed in this speech.
First of all, as for the development of superalloys, thecreep strength has been improved in response to higher
temperature combustion gases for gas turbines and jet engines.
The Ni-based superalloys for turbine blades have progressedfrom cast alloys to normal casts through directional
solidification (DS) to single crystal (SC) alloys, along with theprogress of processing technologies. These single crystal alloys
have also advanced through developments from the first
generation, represented by Rene’ N4, PWA1480, CMSX-2, tothe 2nd generation, represented by Rene’ N5, CMSX4, PW1484
containing about 3% Re, to the 3rd generation, represented by
Rene’ N6, CMSX10 containing about 5% - 6% Re, and then to
the 4th generation. These were further targeted for greater
strength by stabilizing the structures.
In response to such a global trend, researches anddevelopments have been made in Japan centering on
government projects such as TMD-5, MGA1400DS for DS
alloys, TMS26 for the 1st generation SC, TMS82+ for the 2nd
generation, and TMS75 for the 3rd generation. TMS82+ and
TMS75 have also succeeded in the generating operation by theinsertion of a 1300°C class gas turbine. In addition, the 4th
generation SC was developed under the Japanese government
project, “High Temperature Materials 21 Project,” in which
structural stabilization was achieved by adding Ru to Re. The
heat resistant temperature was achieved at 1,102 °C by rafting a
γ phase and miniaturizing the γ/γ’interface misfit dislocation
network. These developed alloys have been studied to be
applied to aero-engines under the ESPER program by the
Ministry of Economy, Trade, and Industry of Japan. The project
starting in 2004 for power generation was introduced, which
would develop 1,700 °C class gas turbines using these alloys andwould perfect the combined heat efficiencies at 60% (HHV) to
reduce the emission of CO2.
As for the Ni-based superalloys for the turbine disks,developments of the next generation of alloys have been
anticipated. These superalloys can be used for long hours at
700 °C to meet conditions in which the temperatures of the highvoltage turbines increase, and their commitments to bothmaterials for casting and powder processing were introduced. In
particular, a new casting process was introduced as having the
FS for the 70,000 tons class large casting facilities.
In addition, as future materials beyond the Ni-based
superalloys,
theoxide-dispersion-strengthened
alloys,intermetallic compounds, refractory metals, ceramics, andcomposite materials were also mentioned in the speech. Past
efforts and achievements surrounding the government projects,
as well as future possibilities, were discussed as well.

bottoming cycle in which the exhaust of atmospheric HTFC isutilized as an air-heater for the GT. The pressurized type iscompact and highly efficient; however, it has someshortcomings, such as the measures required for pressure
fluctuations during emergencies and a cost increase in pressure
containers.
The progress of fuel cells has been outstanding. For
example, in the case of the MCFC 10 kW stacks 10 years ago, an
initial cell voltage of 800 mV decreased to 600 mV in only 1,500
hours, while at present, an initial cell voltage of 900 mV only
decreases to about 860 mV in 10,000 hours. This indicates ahigher efficiency and extended longevity.
Development of the performance simulation models
based on fuel cell stack performances has also progressed andbecome practically useable for the positioning of the HTFC
combined cycle system and for selecting optimum operational
conditions. Cycle efficiencies (HHV) of the combined cycle
system in the case of natural gas reformation are about 65% for
SOFC 40MW, of which GT contributes 15% points; 53% for
SOFC 300 kW, of which GT contributes 10%; 64% for MCFC
20MW, of which GT contributes 9%; and 51% for 300 kW, ofwhich GT contributes 5%. This indicates higher contributions ofgas turbines in the SOFC compared to the MCFC.
Along with the progress in the development of micro-gas
turbines (MGT) during these recent years, developments of afew 100 kW class systems have been pursued, in which HTFC
and MGT are combined.
In the case of IHI(Ishikawajima-Harima Heavy Industries, Co., Ltd.) for example,
a 300 kW system (efficiency 47% LHV) is in operation where
the MCFC of 0.4 MPa is being utilized, and a demonstration of
an atmospheric SOFC 220 kW has been completed at SWPC
(Siemens Westinghouse Power Co.). Those of a 0.3 MPapressurized 300 kW has been in development. As for the future
prospects of large systems, actual proof and cost reductions are
the important challenges in these compact systems.
Keynote Speech 4: Future View of Energy Supply andRole of Gas Turbines in Japan (View of Electric Power
Company), Hiroyuki Ino (Tokyo Electric Power Company)
Gas turbine power generation in our country has beendeveloped with circumstantial backgrounds, such asimport-dependent fuel resources, power loads that can fluctuate
greatly between seasons, and day or night and strict
environmental regulations. Out of all of them, combined cycle
power generation with gas turbines and steam turbines is themost desired power generating system.
Gas turbines were introduced into our country in the
1970’s, and the first gas turbine power generation was a simple
cycle gas turbine system taking advantage of short-term
construction. Since then, highly efficient gas turbine combined
cycle systems have been introduced, along with the outstanding
developments of gas turbine technologies. Today, it has become
to practical to use an advanced combined cycle system with a
1,300 °C TIT class gas turbine.
Based on projections for primary energy supplies andfinal energy consumption by end consumers in our country,
energy conservation and industrial rebuilding have been
progressing while the use of atomic power and natural gas has
been expanding. The balance of atomic power and natural gas in
the use of energy resources will probably be more leveled in2010. Industrial fields have been used to occupy the majority of
final energy consumption. However, there has been an evident
increase in energy consumption by consumers andtransportation divisions due to the decline in petroleum prices
and changes in lifestyles. In our country, it is likely that there
will not be major changes in the overall energy demand andsupply; nonetheless, the trend towards an increase in power
demands will also stay.
In addition to the increase in electric power demands, it

Keynote Speech 3: Development of High Efficiency Fuel
Cell Power Plant Combined with Gas Turbine, Takao
Watanabe (Central Research Institute of Electric Power
Industry)
Fuel cells possess properties that are not part of theconventional type of power generating plant, such as highefficiencies, lower environmental loads, and flexibility with theoutput scale, and are expected to be utilized for a wide range ofapplications from consumer use to large-scale power generating
plants. What has currently been developed or used are mainly
the following four types: Proton-exchange membrane fuel cells(PEFC), Phosphoric acid fuel cells (PAFC), Molten salt carbonicacid fuel cells (MCFC), and Solid oxide fuel cells (SOFC).
MCFC and SOFC are categorized as high temperature fuel cells(HTFC) and have been studied and reviewed for thedevelopment of a combined system with gas turbines.
The combined system between HTFC and gas turbines(GT) consists of a topping cycle in which GT are connected tothe exhaust side of HTFC while pressurizing HTFC and a
3© Gas Turbine Society of Japanhas been projected that the liberation of electric power retail will
advance, resulting in 60% of the entire electric volume being the
subject of liberalization by the spring of 2005. Therefore, morestrategic and flexible investments on power generation facilities
will be required for electric power companies.
Based on the energy circumstances mentioned above, theelectric power companies should address the following topics.
● Cost reduction

generation takes place within the combustor, it triggers acoustic
energy fluctuations, hence inducing small pressure fluctuations.
When the pressure fluctuations resonate with the acoustics of the
combustor system, it can grow into a vibration with powerfulenergy that can not only destroy the combustor, but also theengine.
For the combustors employing a lean, premixed
combustion, experimental research has been implemented alongwith an analysis using CFD and an acoustic network model
regarding predictions for resonance frequencies, energy
amplification, and control of combustion oscillations. When acomplex configuration such as the actual combustor is used as
the subject, an analysis using CFD has several problems in termsof the capacity of the computer; therefore, analyses using
network models are more practical. There are two methods forthe control of combustion oscillation: passive or active controls.
One of the former is a Helmholtz resonator, which is installed
onto a combustor system to instantly absorb the generated
energy that is the result to an unstable combustion. This isextremely effective when the vibration frequency is alreadyknown, but is not as effective for combustion oscillation below
200 Hz when considering the volume attached. An active
control is more effective for combustion oscillations at lower
frequencies. This is configured by a feedback control thatmonitors oscillations within the combustor and controls thevibrations by using some kind of actuator. One way to supply
the actuator is to modulate the fuel fluid to a frequency in which
the fuel vibrations are controlled, for which many experiments
are currently being conducted.

● High reliability● Adaptability of fuels● Dealing with load fluctuations● Environmental protection
In order to deal with these subjects we are expecting thedevelopment of gas turbine technologies in the following fourareas.
First of all, we must strive to increase the scale (high efficiency
and large power generation facilities) through increases intemperatures at the turbine inlet and pressure ratios. This iscurrently under development and needs to be continued further.
Tokyo Electric Power Company has developed and applied
1,500 °C class gas turbine combined cycle systems called More
Advanced Combined Cycle systems.
Next is the development of small-medium gas turbines,
although this appears inconsistent with the former statement.
They are installed corresponding to uncertain power demands
that are expected for short periods of time. The micro-gas
turbines belong to this category.
Thirdly, reliability should be improved within theexisting gas turbines. In particular, the extension of longevity
for high temperature parts of gas turbines is our major goal.
Lastly, we should expand the scope of fuels withefficiency without contaminating the environment. This equates
to the development of coal gas combined power generation
technologies, which enable the use of coals and crude oil.
Gas turbine related technologies have advanced rapidly,
making gas turbine power generation a major force for thermal
power generation, and we will continue to expand that role into
the future. Considering the energy situations in our country andthe world, gas turbine power generation must expand its role as
it makes further advancements. From the standpoint of thepower companies, we hope that the gas turbine technologies willcontinue to make progress and contribute to economicaldevelopment and protection of the environment.

Keynote speech 6: Recent findings of Analytical Studies in
Unsteady
Aerodynamics,
Aeroacoustics,
andAeroelasticity of Turbomachines, Masanobu Namba (Sojo
University)
Professor Masanobu Namba of Sojo University (alsoemeritus professor of Kyushu University) made acomprehensive lecture on the theoretical analysis by singularity
method regarding the unsteady aerodynamics of turbomachines,
aeroelasticity, and aeroacoustics.
As for the theoretical research of recent years in the said
fields, many studies consist of computational fluid dynamics(CFD) and computational aeroacoustics (CAA), while purely
theoretical analysis is considered classic. For a theoreticalanalysis, the restrictions are very tight on the flows that can behandled, and the simplicity of the boundary shapes and flow
linearity are anticipated. However, it has some great advantages,
which include that computational load is extremely light whencompared to the numerical analysis method and that an analysis
on a wide range of parameters can be conducted in a short time
period while being able to make clear insights on the physicalphenomena.
First of all, in this keynote speech, the basic ideas of thesingularity analysis methods of unsteady cascade flows wereorganized by general formulation and were uniformlyinterpreted. Three application examples, which had recently
been analyzed by Professor Masanobu Namba et al., were thenintroduced using these techniques.
First, the issue of cascaded blade vibration was analyzed
in the field of rotor-stator interaction in a counter-rotation rotor.
The results showed that the impact of adjacent cascades is
extremely great, as indicated by the case of multistage blade
flutter. Next, the analysis on discrete frequency noises due torotor-stator interaction was introduced. However, it was
indicated that in order to make an accurate projection of theacoustic field, both flow interaction and aeroacoustic interaction
between rotor and stator must be considered.
Finally, an active control analysis on interfering noises
between the gust and rotor blades was introduced. For thecontrol, an attempt was made to attenuate noises by providing an

Keynote Speech 5: The Challenges of Lean Premixed
Combustion, Ann Dowling (Cambridge University, UK)
In addition to industrial gas turbines, clean combustors
for the next generation jet engines often employ a lean premixed
combustion in order to reduce emissions, particularly nitrogenoxide NOx. In such cases, however, pressure oscillations during
combustion can become an issue. In this keynote speech,
Professor Ann Dowling outlined the unstable combustion ofsuch gas turbine combustors using a model with mathematicalformulas for heat generation caused by combustion and its
acoustic interaction. Then, the physical phenomena of vibrations
during combustion through simple lab experiments and thestudy results of CFD modeling, as well as a control method
using both still and moving images, were introduced so that
listeners could understand them easily.
The phenomenon in which noise occurs when
combustion becomes unstable had been scientifically analyzed
and clarified as an issue a long time ago. There is also a similar
phenomenon of oscillation during combustion caused by a lean,premixed combustion. In recent years, as the development of
low emission combustors for gas turbines became more popular,
this issue has drawn more attention. When an unstable heat4

© Gas Turbine Society of Japanactive acoustic disturbance in order to erase acoustic waves
generated in the rotor blades from the actuator surfaces in thedownstream field. However, the results of the analysis indicatedthat it was extremely difficult to suppress noises in general even
if an acoustic disturbance of a duct-cut-on mode is superimposed.
Instead, there was a possibility of attenuating the noises
effectively by using acoustic disturbances only in the cut-off
mode.
This lecture indicated that the theoretical analysis
techniques were an effective means of finding key factors andprovides basic knowledge for new unsteady aerodynamic
challenges. It also provides a useful benchmark to verify CFD
and CAA techniques. It is expected that a purely theoreticalanalysis will continue to go forward on the intellectual frontline
through such roles in the future.

intelligent technologies (non-compliance detection, optimized
operation, necessary maintenance timing prediction), etc.
For military engines, the F136 for JSF fighter planes andthe F414 for F18E/F are in development, although further
improvements will be necessary on the thrust-weight ratio (from9 to 20 for the F414) and studies of adaptive cycle engines
applicable to each model. These projects are being proposed forgovernment programs such as NASA’s UEET or RTA, andIHPTET or VAATE for DOD.
PDE (Pulse Detonation Engines) and fuel cells werementioned as future technologies. PDE has already been studied
at the General Electric research labs in cooperation with
universities, and the manufacturing of a full-scale demonstration
plane is being planned in 2006. Breakthrough improvements onfuel cells are indispensable, as well as switching fuel tohydrogen, which will require more time.
Finally, it was introduced that these foundations andleading technical studies have been globally outsourced. The
technology centers for General Electric’s research labs areplaced in Bengal, India; Shanghai, China; and Munich, Germany
under the global research world headquarters in NY, and studies
have been conducted by taking advantage of characteristics ateach location. Universities both in and out of the United States
use their specialties to play a part in the General Electricresearch program through cooperative relationships with eachother.

Keynote Speech 7: GEAE Propulsion Vision for the 21stCentury, Mike Benzakein (General Electric Aircraft
Engines, USA)
Dr. Benzakein introduced to us the image of aero-engines
while looking towards the 21st century and the efforts being
made at General Electric.
With an outlook for 21st century airplanes, we are
expecting an advent of med-large jets with further enhanced
safety and environmental compliance than the current regional
jet engines. A subsonic jet plane group that reaches further tolong-distance military transporters, environmentally compliant
supersonic transporters starting with ultrasonic business jet
engines, propeller planes, and various types of unmanned
airplanes are also being expected. Furthermore, there are needs
for safe and low-cost spacecrafts. What has been commonly
expected is a response to clients’ satisfactions regarding
performance, noise, emissions, reliability, and convenience andto realize ownership at lower costs. General Electric’s efforts
towards these goals were introduced as follows:
General Electric has prepared two engine platforms for
consumer engines.
The first is the CFM56/CF34-10 series (compressor of a
mid-level pressure ratio driven by single-stage turbines,
perfecting enhanced reliability and low maintenance costs) forregional and narrow body planes. The CFM56 series is abestseller engine widely adopted for the A320 and B737 series.
The development of the CF34-10 series is also progressing
smoothly, and technical developments of each engine element
for the Tech 56 project are also under way. For example, highloads and high efficiency compressors (setting the pressure ratioof CFM56 at 15/16 instead of 11/9, the number of blades isreduced from 1518 to 963 to lower the maintenance cost), TAPS
(Twin Annular Premixing Swirler), low NOx combustors, highefficiency turbines, etc., are planned to be sequentially reflectedon the products.
Another architecture is the GE90 series (compressor of ahigh pressure ratio driven by a two-stage turbine) for wide bodyand medium-long distance planes. The development of the
GE90-115B has advanced smoothly and the technical certificate
was obtained from the United States Federal Aviation
Administration. As the B7E7 engine is scheduled to fly in 2008,
the GENX engine is being developed with a targeted noise
reduction of 26 dB as compared to Stage 3 and NOx reductionsof 60% as compared to the ICAO CAEP4 with a GE90 basiscore. For the GENY engine, which is targeted for operation
around 2012 ~ 2015, goals are set for a noise reduction of 33 dB
as compared to Stage 3, NOx reductions of 85% as compared to
CAEP4, a reduction in defects during flight by 50%, and takeoff
delays and cancellation decreases by 50%. Besides these goals,
many new technologies are also being challenged. They include
noise reduction technologies, such as variable chevron nozzles
by shape memory alloys and active acoustic liners, CMC
combustors, CMC turbine blades, new alloy shaft disks, super

2.2 Forums and Organized Sessions
Forum 1:"Industry-University Cooperation in Gas Turbine
Research"
Co-Chairs: David Wisler and Toshinori Watanabe
Panelists:
David Wisler (General Electric Aircraft Engines, USA),
Xiaofeng Sun (Beijing University of Aeronautics andAstronautics, China), Chisachi Kato (University of Tokyo,
Japan)In this forum, Dr. David Wisler of General Electric in the
United States, Professor Xiaofeng Sun of Beijing University of
Aeronautics and Astronautics in China, and Professor Chisachi
Kato of the University of Tokyo provided information regarding
the current status and future outlook of industry-university joint
research.
Dr. Wisler is the manager of a section called University
Programs and Aero Technology Laboratories. In his speech, he
explained the difference in value between the manufacturers
and universities in a manner that was easy to understand. Basedon acknowledgement, he emphasized the importance of joint
research between industries and universities towards technicaldevelopments. He also appealed the necessity to change ideas inorder to overcome differences and conduct joint research. In
addition, he introduced the current status of General Electric’s
joint research with the universities. They have globally
established joint research agreements with nine universities: six
United States universities, two European universities, and one
Asian university. The only Asian university is Tsinghua
University in China. Their approach was revealed as building
joint international research strategies and effectively utilizing awide range of knowledge for products.
Professor Sun of Beijing University of Aeronautics andAstronautics introduced the current status of theindustry-university joint systems in the aero-engine field. Withaero-related industry organizations AVIC-1 and AVIC-2 as thecentral figure, it clearly indicated that the industries, universities,
and research labs are cooperatively structured. The universities
in China have actively established these international
cooperative systems. They have particularly deepened theircooperation with universities in Europe and the United States,
including mutual exchanges between the faculties. Since the5© Gas Turbine Society of Japanbasis for a strong partnership lies in human relationships, itappears that they send students to many different places and arebuilding the foundation for human exchanges.
Professor Kato from the University of Tokyo introduceda case example, the CFD industry-university joint project
implemented at the Institute of Industrial Science, University ofTokyo. The CFD codes built at the institute were disclosed in a
way that could be easily used and the system offered forindustrial use was indicated in an easy to understand manner.
Although the industry-university joint system in Japan isstill in organization, the importance has been emphasized invarious scenes and joint research has been gradually developed.
Such cooperative efforts are being anticipated on the academic
platform in the gas turbine field as well.

with a 10-mm diameter and 1-mm height and optimization(OS-101, 105) eying on ultra-micro compressors. There wasalso an example reported from outside the Research Committeethat introduced that an ultra-micro-centrifugal compressor witha 10-mm diameter using SiN was actually manufactured andwent through a rotation test. This example report drew muchattention from the audience.
The interests for ultra micro-gas turbines were great, andquestions were raised actively from the audience, particularly on
the actualization in the system analysis lecture.
Organized Session “Gas Turbines for Ships andSuperchargers”
In this session, lectures were given on the developmentsof small turbochargers, 2,500 kW gas turbines for ships, loading
WR21 gas turbines on destroyers, and the status of development
and market for the MT30.
The turbocharger developed is a small model with aturbine diameter of 44.5 mm and a rotation speed of 180,000rpm. The engine for the PWC (Personal Water Craft) currently
uses a 2-stroke engine, which is in transition to switch to a
4-stroke engine in compliance with enforced environmental
regulations, such as regulations of the Environmental Protection
Agency.
A new turbocharger was developed with thespecification for ships to increase the output of 4-stroke engines.
The diagonal flow turbines and ceramic bearings are adopted toenhance corrosion resistance against salt water and to improve
its response (OS-201).
The SMGT (Super Marine Gas Turbine) is a regenerative
gas turbine with a rated output of 2,500 kW. Its target
performance is being able to use A crude oil, a 38% heatefficiency, and NOx emission rate of 1g / kWh. It successfullycompleted a land test in March of 2003. In the future, after
passing an endurance test, it is scheduled to be loaded onto anext generation domestic vessel, the super eco-ship, in 2005 as apart of the project started by the Ministry of Land, Infrastructure
and Transportation of Japan (OS-202).
The WR21 is an ICR (Inter-Cooling and Regenerative
cycle) type gas turbine with a rated output of 21 MW, which was
loaded onto a T45 destroyer of the British Navy for the first time.
The T45 adopted an IEP (Integrated Electric Propulsion) electric
propulsive system. The power generation system consists ofWR21 direct-coupled power generators (2 units) and two 2 MWdiesel power generators and supplies 2 propulsive motors andnon-propulsive power. The WR21 has a fine part-load
performance, showing not only the reduction in life cycle cost,
but also an improvement in operation. The vessel is operated by
the CODOG method using two 20 MW gas turbines, whichmight be changed to the more cost effective WR21 (OS-203).
The MT30 is a gas turbine for ships with a standard
output of 36 MW. The output is at maximum as a single
machine output. According to detailed market analysis, needs
for large output engines are increasing for both military ships
and commercial use, and development was decided in 1999.
The durability test to obtain DNV model certification iscurrently being conducted (it is scheduled for completion by theend of 2003). 80% of the parts are shared with aircraft engine
TRENT800; therefore, the design changes corresponding tovessels are limited to the major rotation parts. There are cruisers
and aircraft carriers for the 70 MW ~ 80 MW class vessels.
Other uses are for electric and machine propulsions in large
passenger ships, LNG tankers, and high speed ferries of over 35
kt (OS-204).

Forum 2:“Current Status and Future Strategy of Electricity
and Energy Supply”
Chairperson: Keizo Tsukagoshi (Mitsubishi Heavy
Industries, Ltd.)
Panelists: Morihiro Kurushima (New Energy and Industrial
Technology Development Organization, Japan), Yuhong Li(Tsinghua University, China), Hyung Hee Cho (Yonsei
University,
Korea),
PrutichaiChonglertvanichkul(Electricity Generating Authority of Thailand, Thailand),
Alberto Dalla Rosa (Electric Power Development Co., Ltd.,
Japan)In this forum, each panelist introduced the current state,
future plans, and measures on energy supply in Japan, China,
South Korea, Thailand, and the European Union countries andregions.
Prof. Kurushima of NEDO in Japan lectured on themeasures for utilizing high efficiency energy and introduced amodel project that targets it.
Professor Li of Tsinghua University in China explained
the current status and projection for energy supply based on theeffective use of coal in China and the role of gas turbines related
to that.
From South Korea, Professor Cho of Yonsei University
spoke about the outlook of energy supply and demand andrelated academic studies.
From Thailand, Mr. Prutichai of the Energy Agency
participated and introduced their electric power situation. He
expressed their desire to propagate gas turbine power generating
systems in the future.
Mr. Alberto Dalla Rosa from Italy, who currently works
at the Electric Power Development Co., Ltd., introduced adetailed present status of European power supply and explained
the outlook for European Union energy with a strong focus onenvironmental compatibilities in the future.
Unfortunately, there were not as many listeners as we
expected, which might have been because of the fact that theforum was held in the late afternoon. However, we received very
positive responses from the participants that they had obtained
information that was not normally available.
Organized Sessions “Ultra Micro Gas Turbines”
Ten lectures were given in 3 sessions (OS - 1, 2, 3)
related to the ultra micro-gas turbines that are only a few
centimeters in size.
These organized sessions centered on achievements reported by
the Investigative Research Committee of the Gas Turbine
Society of Japan. Lectures were given on the elements ofresearch, such as a concept studies (OS-103) on ultra micro-gas
turbines, system analysis such as an overall analysis (OS-109)
and structural analysis (OS-106), concept study (OS-102) onheat exchangers, CFD / experiment analysis (OS-104, 107) onflows within the turbines, test results (OS-108) on combustors

Forum “Wave Rotor”
As an attempt to facilitate the exchange of information
among researchers specializing in the field of wave rotor, wearranged a forum called “Wave Rotor” for published treatises
6© Gas Turbine Society of Japan

and oral reports in this area. As a result in the two sessions (F - 1,
Forum 3) six reports were presented (three papers and three oral
reports.)
We usually spend a great deal of time in presenting
lectures on wave rotor to the audience, whom are unfamiliar
with the principle. However, because almost all of theparticipants in the audience are specialists in this field, every
speaker had presented his topic without the usual preamble.
Although none of the lectures had presented any new
outstanding topics, know-hows that are not normally discussed
at the usual lectures and in treatises were vigorously debated.
These sessions were highly relevant to the specialists on
wave rotor; as a result, a similar session will be arranged in the
ASME International Mechanical Engineering Congress, which
will be held in November 2004.

developed and used in application (TS-017). A report fromJapan stated that a possibly smallest foil bearing (30mm) had
been developed and tested (TS-019). On the vibration of therotary-type bearing, the effect due to the vibration resulting fromthe misalignment of the balanced shaft system was reported.
Although the study of the experimental results is not sufficiently
adequate, further contribution in this field is anticipated(TS-015). The vibrational characteristic of the rotor with a
non-circular section was analyzed with the FEM; and theprocedure of the analysis of the vibration and the solid model —instead of the beam element, which was placed on the
non-symmetric cross-section — of the vibrational analysis was
described. (RTS-016)
The number of participants of this session was small;
nonetheless, all of the participants engaged in vigorous
discussion of the issue.

2.3 Technical Paper Sessions
Aerodynamics
The numbers of participants in the aerodynamics
sessions was the largest. Totally, there were thirty-nine papers
delivered in twelve sessions.
On the utilization of the CFD for the design and analysisof the compressor, the following papers were delivered: The
effect of backward-swept blade on the compressor performance(TS-029), the analysis of the tip section flow (TS-030), CFD
application to the design of turbine blade (TS-028, TS-042),
centrifugal compressor (TS-020, TS-043, TS-049), and theeffect of surface roughness (TS-033) and humidity (TS-021) on
the performance. Also, the unsteady flow analysis on theclocking effect (TS-058), rotor-stator interaction in turbine(TS-048), and simulation of active stall control (TS-027), as wellas the relationship between the tip flow and radial flow
distribution (TS-051) were introduced. The effect of the turbine
rim seal (TS-025); the cavity flow of the compressor (TS-024);
and an analysis that included the exhaust flow system (TS-031,
TS-026), which included CFD application to problems otherthan cascade flow, were reported. The applications of the
optimization of inverse design technique to compressor design(TS-034), and to the turbine, which took into account the outletof the compressor (TS-034), were presented (TS-035 andTS-036). A higher order unsteady multi-grid CFD method wasintroduced (TS-022).
On the problem of surge and stall, passage shock was
taken into account in proposing a model of compressor stability(TS-037). Besides this, the followings were reported: The active
control of the centrifugal compressor (TS-58) and thedevelopment and verification of a surge prediction method(TS-040), the measurement of fan flow prior to or under rotatingstall (TS-039, TS-044, and TS-045). Numerical analysis of theactive flutter control, which assumed active vibration of trailingedge (TS-055), was also reported. For unsteady measurement,
detailed measurements were reported on transition phenomenaof the vaneless diffusers (TS-046), the unsteady loss of an axial
turbine (TS-056), and the wake decay in the stator passage of anaxial compressor (TS-057). On vibration problems, the forced
response of the centrifugal turbine (TS-053), and the comparisonof results between double-linearized theory and CFD on thevibration of circular cascade blades were presented (TS-054).
In the area of conceptual design, a proposal was made on thedesign tool for regenerative compressor (TS-050), and a simple
through-flow design model was proposed for replacing the mean
radius calculation (TS-052). The concept of a new turbine,
named tunnel turbine, was introduced, which conceived for
application to the micro-gas turbine (TS-041).
In addition, the followings were also reported: The
measurement of the three-dimensional PIV of the impeller’sinternal shock-wave (TS-032); the measurement of theshock-boundary layer interaction in a rectangular duct (TS-023);
the development of the multi-stage compressor test rig (TS-114);

Diagnosis, Control and Measurement
In the two sessions (F - 4 and F - 5) on diagnosis, control,and measurement, nine presentations were given. As has been
the case in other international conferences held in recent years,
studies of the diagnoses (six cases) was vigorous, while incontrast those on control (two cases) and measurement (onecase) were moderate. The following methods of diagnoses werereported: The diagnoses by neural network (TS-1, TS-2, TS-3);
the method of raising the reliability of the gas-path analysis withstatistical means (TS-4); and diagnosis (TS-5) that employs themodel of deterioration of capacity. Also there was a report(TS-6) that compares the predictability and measurability of the
APU.
On the subject of control technology, there were reports(TS-7) on start-up control and VSV control by means of the
optimizing method; and a report on a system for control andmonitoring the micro-gas turbine, designed by the author on his
PC, together with the report on the operation of the machine(TS-156).
On the measurement technology, there was a report(TS-8) on the revision of the data on the pyrometer that took into
account the radiant heat of the gas and flame.
Structure and Vibration
Nine treatises on structures and vibration were presented.
In two sessions (E – 3 and E - 5), treatises on stress andvibration, as well as on the bearing and the effect of vibration on
it were reported.
There were four presentations on the blade and structure
session (E-3). When birds had flown into the aircraft engine ofan Indian airline, the FEM stress analysis of the rotor blade
corresponded closely with the experimental result (TS009). On
the vibrational stress of the rotor blade of an axial machine, theanalysis and experiments revealed that the vibrational stress of
the rotor was reduced with uneven pitch stator (TS-010). A
theoretical and experimental study was conducted by changing
the number of the stators of the upper and lower half of the axial
flow compressor; as a result its vibration-reducing effect was
found when the difference in the number of upper and lower
blades was large. As for radial machines, the measurement
results of the vibration stress and the rate of logarithmic
attenuation were reported on a turbocharger under development(TS-011). An interface that can be used for the stress analysis of
the FEM was proposed; it uses the result of the CFD analysis; its
application to the virtual turbine model (1400°C -class) was
introduced. (TS-012).
Five reports were presented in the session “Rotor
Dynamics and Bearing” (E – 5). A report from Poland presented
a unique analysis of the oil film in the high-speed bearing(TS-018). An interesting report from the United States statedthat a maximum-size foil bearing and magnetic bearing had been
7

© Gas Turbine Society of Japana trial experiment to reduce the noise of the low-speed turbo-fan
by varying the outlet angle of the impeller (TS-047).

in a rotating duct which leads cooling air from the compressor to
the turbine rotor blade (TS-63), the effect of swirl flow due todisk rotation (TS-64). A flow analysis was conducted on arotating U-bent related to the cooling passage flow of the turbine
rotor blade (TS-65), and the result of comparison was presented
between the numerical simulation with the 2-equation
turbulence model and the DNS analysis concerning the flow
field in rotating 2 parallel passages (TS-61).

Heat Transfer
The number of contributed papers in the area of heattransfer was the second highest behind that in aerodynamics - 26
papers presented in seven sessions. Some of them are: impact of
the trailing edge injection on the heat transfer coefficient of theblade surface in a turbulence analysis of transonic turbine blades
to which film cooling was conducted (TS-70), the result of ahigh speed cascade test regarding the effect of a trailing edge
shock wave on the heat transfer coefficient or film coolingefficiency on the pressure side of the blade (TS-77) and theanalysis of film cooling on 3-dimensional blade surfaces in thecases of leading edge, suction surface, and pressure surface.
There was also a technique to optimize the shape of the film
cooling hole with CFD by suppressing the mixing with the mainstream (TS-71), and also LES analysis was tried for ananisotropic flow field where the film-cooled jet and mainstream
met (TS-60). The LES was also applied to the analysis of
mixing between the cooled air from the trailing edge slot and themainstream (TS-62). As for the heat transfer prediction on theblade surfaces, an analysis using the SST turbulence model witha high accuracy for transition was presented (TS-59). In
addition, there was another analysis of an unsteady heat transfer
coefficient that was conducted on the rotor blade surface, which
received an impact from the wake from the stator vane (TS-73).
Experimental researches were conducted on boundary layertransition on the model of a blade leading edge placed in thedownstream wake generated by moving bars (TS-68), and thetransition from the separation bubble at a surface position nearleading edge (TS-69).
For the problem solved by coupling the fluid andstructure, a coupled analysis was performed among thefilm-cooled air by the showerhead in the leading edge area of aturbine blade, the showerhead structure and the mainstream(TS-83). (TS-84) was that the cooling efficiency is solved on themulti-layered full surface film cooling structure on which the
TBC is built. In addition, the following was introduced: ananalysis on the flow path and cooling efficiency where
impingement cooling, pin-fin cooling, and full surface coolingare combined (TS-85), and an analysis on the metal temperatureof cooled blades implemented as a part of the High Temperature
Materials 21 Project (TS-66).
Regarding the issue of heat transfer in the passages witha turbulence promoter, a comparison between experimental
observation and numerical analysis of the detailed flow behavior
in a triangle shaped passage in the trailing edge portion of
turbine rotor blades (TS-78) was reported. The comparison
between numerical analysis and the experiment on the heattransfer coefficient and pressure loss on the flow surface withthe triangle passage aspect ratio as the parameter (TS-80) was
also documented. In addition, there was also an observation on
the flow by PIV in the rotating smooth U-bent and that with 90 ﾟ
– rib angle (TS-79), and the effect of a 2-passage rotation at asimilar U-bent on heat transfer efficiency was measured in detailby the Naphthalene sublimation method (TS-81). Regarding theheat transfer promotion due to the secondary flow of the ribs
placed as tilted towards the flow in a square passage, an analysis
result using RANS was reported (TS-82). For impingement
cooling, the following was reported: the effect of dimples madeon the impingement surface (TS-74), heat transfer
characteristics of the cooling structure where the ribs areattached in the direction of the mainstream and in the direction
where a cross flow occurs (TS-75), and the result of a detailed
study by the Naphthalene sublimation method on the effect ofheat transfer promotion by attaching various rib shapes to theimpingement surface (TS-76).
The following findings were also reported: pressure loss

Performance
Nine presentations were made in three sessions
concerning performance.
During the session on the water spray and filter for air
intake (Session E - 6 Performance Analysis of Gas Turbines:
Intake Air Humidification & Filtration), two presentations onwater spray towards air intake and one presentation regarding
the filter were made. Hitachi, Ltd. indicated that when they had
conducted a performance analysis in the case where the positionof a cool air outlet is changed for the AHAT system proposed, it
became the most efficient when the humidified air was used forcooling. This indicated a 1.3% efficiency improvement whencompared to the combined cycle using the gas turbine (TS-090).
On the other hand, the Alstom Company presented, after
reviewing the impact of air intake water spray on the compressor,
the development of the air intake water spray test result using theactual GT26 machine and a compressor performance model withwater spray (TS-091). In addition, Freudenberg & Nonwovens
Co. introduced their filter using non-woven fabric.
During the session on a new model system (Session F – 7
Performance Analysis of Gas Turbines and New Systems),
Tabriz University introduced that the tendency of calculated
efficiencies varies greatly between the turbine with non-coolingand the turbine with cooling. These are being considered for heatefficiency calculation for simple cycles and reheat andregenerative cycles (TS-088). The Chinese Academy of
Sciences proposed a CO2 recovering power generation system inwhich the power generation rate exceeds 50% using theequivalent ratio combustion of LNG and oxygen (TS-087).
Warsaw University presented that when they had developed andanalyzed a part load property model of the Graz cycle, the same
cycle contained superior part load properties (TS-089).
During the performance model and calculation tool
sessions (Session F - 8 Performance Analysis Modeling &Tools), Shenyang Institute of Aeronautical Engineering in China
introduced the function table in which the already proposed
thermodynamic functions were organized and made applicable
to a wide range. The programs that were developed were basedon it (TS-093). In addition, Cranfield University made apresentation on a simulation model in which a radial direction
flow profile is being considered for a low bypass ratio turbo fanengine (TS-094). Seoul National University presented ananalysis model to predict the fouling phenomenon of the axial
compressor (TS-095).
Development / Operation
For development and operational experiences of gas
turbines, a total of 16 papers were presented in a total of fivesessions. For the large power generating gas turbines and therelated complex power generating system using the turbines, six
papers were presented in two sessions (C - 7 and C - 8). One
paper is about an attempt (the Modernization & Upgrade
Program) to improve performance and reliability by applying
the latest technology to the established gas turbine of which
performance is inferior to the latest model (TS-099). Other
reports were the papers on the status regained by thermal power
plants over the years (TS-101 and TS-102). As for thedevelopment of the latest gas turbines, developments of the
M701G2 by MHI (TS-100) and the V94.3A by Siemens(TS-098) were introduced. A research paper was also presented,
8© Gas Turbine Society of Japan

discussing a gas turbine that used low calorie fuels, such as a
byproduct gas and a high furnace gas (TS-1083).
For micro power generation, four papers were presented
in the micro gas turbine session (D - 2). The cogeneration
system using the 30 kW class micro gas turbines was evaluatedfrom both the performance and operation control standpoint(motion properties) (TS-117). Another study presented thedevelopment of a 300 kW class micro gas turbine (TS-115). As
an element development, a paper regarding the concept of a new
turbine (Tunnel turbine) projecting an application to a hybrid
system with micro gas turbines and fuel cells (TS-116) and thedevelopment of a micro jet engine test system for university
education (TS-113) were introduced.
For aero-engines, six papers were presented in two
sessions (C - 1, C - 2). To introduce the achievements of the past
four years in engine development for helicopters (TS-107) andthe environmentally compatible next generation ultrasonicpropulsion system (ESPR project) (TS-104), as well as
innovative aeronautical propulsion technologies in the 21st
century, two papers were presented from NASA (TS-105,
TS-106). As an element technology, two papers were also
submitted regarding the tandem cascades (TS-108, TS-109).

which is-basedd on Hafnia (HfO2) developed by “Nanostructure
coating project,” were introduced, respectively. Hafnia TBC has,when compared to zirconia, a low heat transfer rate within
1000 °C to 1300 °C, and it became clear that the sintering starttemperature improves it by as much as 100 °C.
During the session for the next generation materials, as
related to turbine disk materials, results were reported on
rotation test (TS-126) for disk materials using SiC fiber
dispersion reinforced type Ti-based complex materials. Also,
results were reported for a dual property disk (TS-127) in which
the inside is made of fine particles and the outside is structurally
controlled as coarse particles by the heat treatment. As for thedual property disk, the impacts of heat treatment conditions on
the structural control to N18 and U720Li, and the hightemperature strength of the materials to creep, etc., werereported. Furthermore, a study on the applicability of metal
growth composites consisting of eutectic complex materials tothe actual products was introduced (TS-125). The eutectic
complex materials are represented by AI203 and Y3AI5012(YAG), and A1203 and GdA103 (GAP), in which the target for
application is 1,700 °C class gas turbine materials. Also, thestatus of the development for the Nb-based alloys, which has
been in development centering on Japan Ultra-high Temperature
Materials Research Institute, was introduced (TS-128). Paying
attention to the environmental proof issue will be importantwhen applying the Nb-based alloys, about which active
discussions were exchanged.

Materials
In this division, a total of 14 progressive technical papers
were presented on materials. They consist of the superalloy
session related to Ni-based single crystal alloys (Superalloy-1
and Superalloy-2), a thermal barrier coating session, and thenext generation materials session handling products besides
steel materials, such as ceramics (Advanced Materials).
During the superalloy session, single crystal alloys
developed in Japan from the 2nd to 4th generations were
presented. For the 2nd generation alloys, the casting property of
the YH61 materials in which a low tilted-angle particle strength
is enhanced (TS-124) was reported. The study on TMS-82+
materials in which W and Re were added to improve the creep
strength and promoted the form of the raft structure within thecreep (TS-123) was also included. For the 3rd generation alloys,
a report on the impact of thermal treatment on the properties ofsingle crystal alloys that had been designed based on thed-electro-theory (TS-121) was made. The TMS-82+ wasoffered to the rotation test by the 15 MW class gas turbines andreported that oxidation and damages, such as fatigue cracks, will
not occur. For the 4th generation alloys, Ru and Re were added
to stabilize the structure, and improved the mechanicalproperties, such as fatigue. Materials TMS-138 (TS-118) andTMS-162 in which high-temperature strength had been
improved with TMS-138 as the base (TS-119) were reported. In
particular, TMS-162 has the world’s top-level strength and isindicated to have achieved the target value (Creep resistanttemperature was 1,100 °C at 137 MPa/1,000 hours).
Furthermore, as the technology related to the Ni-based
superalloys and as the longevity extension technology for gas
turbine rotor blades that had been disposed due to the end ofmanageable longevity, the following was reported:“Regenerative treatment technology where hot isostatic press(HIP) and thermal treatment are combined” (TS-120), as well as“The development of a simulated turbine system where the alloy
design program and gas turbine design program are combined
and the turbine performance is simulated from the materials”(TS-122).
During the thermal barrier coating session (TBC), newplasma flame-coating TBC technology was reported. It was
about flame-coating the La2Zr2O7 or Nd2Zr207 layer on theconventional Zirconia layer (ZrO2-Y2O3) in order to improveheat cycle properties (TS0129). Furthermore, TBC technology(TS-130) studied by the government project, “Development oftechnology for 1700°C -class closed-cycle gas turbine
corresponding to CO2 collection” and TBC technology (TS-131),

Combustion
Presentations related to combustion and combustors
were: four papers in session D - 2 (combustion control), four
papers in session D - 4 (combustor development), five papers insession D - 5 (low emission combustors), and four papers insession E - 7 (Combustor design), totaling 17 papers. There
were many papers on NOx reductions; however, there were only
five cases on the clarification of combustion vibrations that
occur at premix combustion and on control technology. It isevident that interests in combustion vibration control are rising.
TS-146 in D - 2 states two Helmholtz resonators have provencombustion vibration control. TS-147 has proven the combustor
pressure fluctuation control system by using the combined cycle
power plant. TS-148 tested the acoustic properties of the laminarflow diffusion flame by which fuel flow is controlled. TS-132 is
a research on LES for inter-combustor vibration combustion.
TS-150 and TS-151 in D - 4 are reports on the development of
the low NOx combustors for the ESPR project for which thisyear is the last year. TS-149, TS-141, and TS-142 in D - 5 areresearches on a new concept for diluted premixed combustion.
TS-149 concerns the impact of the shape of fuel supply unit,
TS-141 is a comparison between the conical flame holder andthe swirl flow type flame holder in combustion properties, andTS-142 reports about the research on the diluted two-stage
combustion system for realizing a low NOx in a wide
equivalence ratio. TS-139 is a research on a diluted limit
expansion where a recirculation flow and a premixed pilot flame
are used. TS-135 and TS-136 are researches on low NOx by astrong circulation of diffusion combustion. TS-152 in D - 4 is aninvestigation on the pre-vaporized, premixed combustion for
HCRF for the purpose of low emissions, and TS-144 in E - 7 is a
study on a low NOx by the oxygen injection IGCC usingsynthetic gas cleansing. TS-143 is a research on a coolingstructure for a combustor liner using MGC materials, TS-145 is
an improvement of combustors using CFD, and TS-134 is ananalysis of a two-stage premixed combustor using LES.

2.4 Panel Discussion
Title:“Gas Turbines in the Future”
Co-chairs: Nobuhide Kasagi (University of Tokyo) and9© Gas Turbine Society of Japan

contributions to the society?

Kimio Sakata (Japan Aerospace Exploration Agency)
Panelists: Yoshiaki Tsukuda (Mitsubishi Heavy Industries,
Ltd., Japan), Mike Benzakein (GE Aircraft Engines, USA)
Shoichiro Inoue (Ministry of Land, Infrastructure andTransport, Japan), Terry Simon (University of Minnesota,USA), Mikio Sato (Central Research Institute of ElectricPower Industry, Japan)

Conclusion and Acknowledgment
The contents and topics of the speeches on the IGTC
have been expanded with the congresses. During this congress,
many of the contributed papers were from overseas countries.
We believe that this was an active and profound international
congress. We sincerely hope that the gas turbine research andtechnology of Japan can contribute to the great international
development in this area and help to stimulate and expand theexchanges among European, American, and Asian countries’
institutes, industries, research fellows, and engineers.
We thank the many participants that made this congress a
successful one with a decent, academic environment. Although,there were a few things that could have been improved, we canconclude that this congress was a great success.
We want to thank every participant and speaker, every
reviewer, chair, and co-chair. We also want to thank everyone
who helped us to make this event possible and successful. We
are also grateful to all of the hard-working students who helped
us, traveling to all of the meeting destinations. We can now
announce that our wonderful congress is successfully closed.

In order to help our panelists lead successful free
discussions and exchanges of opinion, the committee speciallyselected several topics on the “Future and Outlook of the Gas
Turbine” for these panelists when determining the schedule andagenda of the first created Panel Discussion. Since thechairpersons were important to guarantee that the discussion be
more active, Professor Nobuhide Kasagi of the University ofTokyo and Mr. Kimio Sakata of the Japan Aerospace
Exploration Agency were invited to chair the Panel Discussion.
On the Panel Discussion, each panelist was asked to give a
15-minute speech at the beginning, and then 30-minutediscussions on the schedule were arranged.
Co-chair Professor Nobuhide Kasagi made an outline
opening speech. He described the positions of energy
technology and the gas turbines in the current technologicalsystem. He also introduced the future development direction of
the gas turbine and its functions in the future energy network.
After his brief outline speech, the following speakers gave theirspeeches:
Mr. Yoshiaki Tsukuda from Mitsubishi Heavy Industries,
Ltd. introduced the current development in the technology oflarge gas turbines for the generation of electric power and future
development, including related environmental concerns. He also
introduced and explained the outlook of the gas turbine in the
future electricity supply system.
Dr. Mike Benzakein from General Electric Co. usedinsightful materials and information and described the current
development and future outlook of energy used in aerospacetechnology.
Mr. Shoichiro Inoue from the Maritime Bureau, theMinistry of Land, Infrastructure and Transport, Japan, talked
about the future of the Japanese ocean shipment andtransportation system, including the future and outlook of
SMGT gas turbine engine technology.
Professor Terry Simon of the University of Minnesota
described the future of small gas turbine technology and its
related technology. His speech gave us some future outlook intovery wide application area and possibility of the technology.
Dr. Mikio Sato from the Central Research Institute of theElectric Power Industry, Japan, introduced and described thefuture diversification of gas turbine fuels. He also evaluatedcharacteristics of several fuels in details.
Finally, co-chair Mr. Kimio Sakata made a concluding
remark on the future and outlook of the contribution of the gas
turbine to the development of aerospace technology.
The enthusiastic speeches given by the panelists
contained much information and were extremely meaningful.
Since the impressive speeches drew many excited responses anddiscussions, the meeting times often had to extend past the
timetable. Finally, we had to limit the discussion time and ask
each participant to briefly answer the co-chair’s question.
The main questions prepared by our co-chair, Professor.
Nobuhide Kasagi, were the followings:
1. How can gas turbine technology play a major role insupporting and improving the quality of human life in the
future? Please talk about what kind of scenario and/or concept
you may dream?
2. How do you think about possible merger and fusion of gas
turbine technology with other technologies and disciplines, suchas bio-, nano-, and information technologies? Do you think weshould make much more effort in such direction, if we want tomake major breakthroughs in gas turbine technology and better
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