Modifications to the inlet flow field of a transonic compressor rotor
By: F. Neuhoff
Contributors: Naval Postgraduate School (U.S.). Dept. of Aeronautics
Publisher: Naval Postgraduate School; Available from National Technical Information Service
Published: 1985
Place of publication: Monterey, Calif; Springfield, Va
Language: eng
Number of pages: 44
Subjects: TRANSONIC FLOW; AXIAL FLOW COMPRESSOR BLADES; COMPRESSOR ROTORS
Other titles: NPS-67-85-008CR.
Description: The flow to the rotor of a single stage axial transonic compressor was found to be in disagreement with design requirements. The incidence angle to the rotor blading was measured to be towards stall in the hub and tip regions when close to design near center-span. Hardware modifications were made, guided by flow field calculations. Predictions were compared with measurements. The most significant improvement was obtained by increasing the flow rate at open throttle. No practical method to correct the flow near the hub was found. Keywords: MERIDL computer program; Transonic compressor; Inlet flow field; Distortion screens.
Notes: Title from cover.

"NPS-67-85-008CR."

"July 1985."."

AD A178 746.

"Final 1 June 1985 - 31 July 1985."

Includes bibliographical references (p. 42)

aq/aq cc:9116 04/19/99.