Experimental and computational investigation of cold-flow through the turbine of the space-shuttle main engine high-pressure fuel turbopump
By: Joseph R. McKee
Publisher: Naval Postgraduate School; Available from National Technical Information Service
Published: 1998
Place of publication: Monterey, Calif; Springfield, Va
Language: eng
Number of pages: 118
Description: Computational predictions and experimental measurements were made on the Naval Postgraduate School's cold-flow turbine test rig. The test turbine was the Space-Shuttle Main Engine, High-Pressure Fuel Turbopump, Alternate Development Model, designed and manufactured by Pratt & Whitney. The flow-field around the first-stage rotor end-wall region was measured using a laser-Doppler velocimetry (LDV) system.     Measurements were taken at two axial locations over the rotor blade tip and at three radial locations from the end-wall casing. Three circumferential velocity profile measurements were taken downstream of the first-stage      using a three-hole pressure probe. All measurements were taken at a referred rotational speed between 4781 and 4904 rpm. A computational fluid dynamics model of the combined first-stage stator and rotor was developed. Predicted velocity data from this model were extracted for comparison to the rotor exit planeprobe measurements.
Notes: "September 1998."

Thesis advisor(s): Garth V. Hobson.

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

Includes bibliographical references (p. 115-116)

Approved for public release; distribution unlimited.

Also available online.

Mode of access: World Wide Web.

System Requirements: Adobe Acrobat reader.

US Navy (USN) author.

dk/dk cc:9116 11/23/98