Laser doppler velocimetry in the space-shuttle main engine high-pressure fuel turbopump
By: James D. Southward
Publisher: Naval Postgraduate School; Available from National Technical Information Service
Published: 1998
Place of publication: Monterey, Calif; Springfield, Va
Language: eng
Number of pages: 149
Description: Modifications were made to the Naval Postgraduate School cold-flow turbine test rig to enable integration of a      two-component laser-doppler velocimetry (LDV) system. The test turbine was the Space-Shuttle Main Engine,      High-Pressure Fuel Turbopump, Alternate-Turbopump Development Model, manufactured by Pratt &      Whitney. Flow field measurements were obtained, using a the LDV system, in the first-stage rotor end-wall      region of the test turbine, at three axial locations and at three depths from the end wall. For each survey      location, velocity ratios, absolute flow angle, turbulence intensities, and correlation coefficients were examined.      The laser data exhibited distinct trends with axial position, depth from the end wall, and with circumferential      position. In addition to the laser data, velocity profiles were determined at the first- stage stator inlet and rotor      exit planes, using a three-hole pressure probe. Both laser and probe data were taken at referred rotational      speeds in the range 4815 to 4853 rpm. Phase-locked measurements were recorded using a once-per-      revolution signal from a magnetic pick-up as a trigger. TSI Phase-resolved software version 2.06 was used for      laser data acquisition and reduction.
Notes: Thesis advisor(s): Garth V. Hobson.

"March 1998."

Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, March 1998.

Includes bibliographical references (p. 145-147)

Approved for public release; distribution unlimited.

Also available online.

Mode of access: World Wide Web.

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US Navy (USN) author.

dk/dk cc:9116 8/19/98.