NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
The effect of inlet temperature and pressure distortion on turbojet performanceThe effects on stability of steady-state, 180 degree extent circumferential distortions of inlet total temperature and pressure were experimentally determined for a turbojet engine. Results for both individual and combined temperature and pressure distortions are presented showing the losses incurred in stall pressure ratio and are compared with results predicted using a simplified parallel compressor model. The loss due to combined distortions was dependent upon the relative orientation between the low pressure and high temperature regions. Reasonable agreement was achieved between the predicted and observed loss in stall pressure ratio when based on a constant corrected speed relationship.
Document ID
19740028561
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Braithwaite, W. M.
Graber, E. J., Jr.
Mehalic, C. M.
(NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 7, 2013
Publication Date
November 1, 1973
Subject Category
Propulsion Systems
Report/Patent Number
AIAA PAPER 73-1316
Meeting Information
Meeting: Propulsion Conference
Location: Las Vegas, NV
Country: US
Start Date: November 5, 1973
End Date: November 7, 1973
Sponsors: American Institute of Aeronautics and Astronautics, Society of Automotive Engineers
Accession Number
74A11311
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available