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A new concept for exhaust diffusers of altitude test cellsA new exhaust diffuser concept for jet engine altitude test cells which greatly reduces operating power and cost requirements for exhausters is discussed. The concept utilizes the capture duct as an efficient diffuser only, while evacuating the secondary air via a separate path using an auxiliary suction system. Implementation of the concept would reduce the peak exhauster power requirement during a TF-30 altitude test by 48 percent and the overall exhaust power cost of the test program by 41 percent. The design accommodates various engine sizes and can achieve optimum pressure recovery performance during both A/B and IRP modes of engine operation. The pressure recovery performance of the proposed exhaust diffusers does not deteriorate with increasing cooling air fraction. The disadvantages of the proposed scheme are: increased mechanical complexity of the extended variable geometry diffuser duct and the need for an auxiliary suction system for evacuating cell-cooling air.
Document ID
19840041423
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Parikh, P. G.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Sarohia, V.
(California Institute of Technology, Jet Propulsion Laboratory, Pasadena CA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1984
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
AIAA PAPER 84-0634
Accession Number
84A24210
Distribution Limits
Public
Copyright
Other

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