NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Energy efficient engine diffuser/combustor model technologyA full scale, full annular diffuser/combustor model test rig was tested to investigate how configurational changes affect pressure loss and flow separation characteristics. The rig was characterized by five major modules: inlet; prediffuser; strut; simulated combustor; and full combustor. The prediffuser featured a short, curved wall dump design. Performance goals included: (1) a separation-free prediffuser flow field; (2) total pressure loss limited to 3.0 percent in the prediffuser and shrouds; and (3) an overall section pressure loss of 5.5 percent P sub T3 at the design airflow distribution. The results indicated that the prediffuser configurations operate well within the program goals for pressure loss and demonstrate separation free operation over a wide range of inlet conditions.
Document ID
19810006487
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Gardner, W.
(Pratt and Whitney Aircraft East Hartford, CT, United States)
Date Acquired
September 4, 2013
Publication Date
June 1, 1980
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
PWA-5594-122
NASA-CR-165157
Report Number: PWA-5594-122
Report Number: NASA-CR-165157
Accession Number
81N15002
Funding Number(s)
CONTRACT_GRANT: NAS3-20646
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
No Preview Available