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Experimental and Computational Investigation of Cold-Flow Through the Turbine of the Space-Shuttle Main Engine High-Pressure Fuel Turbopump | 
 enlarge | Publisher: Storming Media
Category: Book
Buy New: $36.95
Sales Rank: 6483568
Media: Spiral-bound
Pages: 134
ISBN: 1423556739
EAN: 9781423556732
ASIN: 1423556739
Publication Date: 1998
Availability: Usually ships in 1-2 business days
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Condition: Please note that this is a report or document and is not a book, per se. It is 134 pages long and is Velobound in a soft linen cover. This technical report was sponsored by the Pentagon and is provided in the best form available to the government. Sometimes our report quality is picture perfect and in color; other times, particularly for older reports, extensive black-and-white photocopying has degraded the quality. If you have any questions about quality of a particular report, please ask and we would be happy to describe it in more detail.
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Product Description
This is a NAVAL POSTGRADUATE SCHOOL MONTEREY CA report procured by the Pentagon and made available for public release. It has been reproduced in the best form available to the Pentagon. It is not spiral-bound, but rather assembled with Velobinding in a soft, white linen cover. The Storming Media report number is A000653. The abstract provided by the Pentagon follows: 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 plane probe measurements.
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