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Comparisons Between Unsteady Aerodynamic Events in a Gas Turbine Generator and an Identical Compressor RigExtensive testing done on a T55-L-712 turboshaft engine compressor in a compressor test rig is being followed by engine tests in progress as part of the Army Non-Recoverable Stall Program. Goals include a greater understanding of the gas turbine engine start cycle and compressor/engine operation in the regions 'beyond' the normal compressor stall line (rotating stall/surge). Rig steady state instrumentation consisted of 497 steady state pressure sensors and 153 temperature sensors. Engine instrumentation was placed in similar radial/axial locations and consists of 122 steady state pressure sensors and 65 temperature sensors. High response rig instrumentation consisted of 34 wall static pressure transducers. Rig and engine high response pressure transducers were located in the same axial/radial/circumferential locations in front of the first three stages. Additional engine high response instrumentation was placed in mach probes in front of the engine and on the compressor hub. This instrumentation allows for the generation of detailed stage characteristics, overall compressor mapping, and detailed analysis of dynamic compressor events.
Document ID
19960024832
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Owen, A. Karl
(Army Research Lab. Cleveland, OH United States)
Date Acquired
August 17, 2013
Publication Date
January 1, 1996
Publication Information
Publication: Loss Mechanisms and Unsteady Flows in Turbomachines
Subject Category
Aircraft Propulsion And Power
Accession Number
96N26991
Distribution Limits
Public
Copyright
Other
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