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Dynamic Simulation of a Wave Rotor Topped Turboshaft EngineThe dynamic behavior of a wave rotor topped turboshaft engine is examined using a numerical simulation. The simulation utilizes an explicit, one-dimensional, multi-passage, CFD based wave rotor code in combination with an implicit, one-dimensional, component level dynamic engine simulation code. Transient responses to rapid fuel flow rate changes and compressor inlet pressure changes are simulated and compared with those of a similarly sized, untopped, turboshaft engine. Results indicate that the wave rotor topped engine responds in a stable, and rapid manner. Furthermore, during certain transient operations, the wave rotor actually tends to enhance engine stability. In particular, there is no tendency toward surge in the compressor of the wave rotor topped engine during rapid acceleration. In fact, the compressor actually moves slightly away from the surge line during this transient. This behavior is precisely the opposite to that of an untopped engine. The simulation is described. Issues associated with integrating CFD and component level codes are discussed. Results from several transient simulations are presented and discussed.
Document ID
19970026604
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Greendyke, R. B. (Texas A&M Univ. College Station, TX United States)
Paxson, D. E. (NASA Lewis Research Center Cleveland, OH United States)
Schobeiri, M. T. (Texas A&M Univ. College Station, TX United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1997
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.15:107514
NASA-TM-107514
E-10816
AIAA Paper 97-3143
Report Number: NAS 1.15:107514
Report Number: NASA-TM-107514
Report Number: E-10816
Report Number: AIAA Paper 97-3143
Meeting Information
Meeting: Joint Propulsion
Location: Seattle, WA
Country: United States
Start Date: July 6, 1997
End Date: July 9, 1997
Sponsors: American Society of Mechanical Engineers, Society of Automotive Engineers, Inc., American Society for Electrical Engineers, American Inst. of Aeronautics and Astronautics
Accession Number
97N25853
Funding Number(s)
PROJECT: RTOP 523-26-33
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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