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Dynamic Modeling of Starting Aerodynamics and Stage Matching in an Axi-Centrifugal CompressorA DYNamic Turbine Engine Compressor Code (DYNTECC) has been modified to model speed transients from 0-100% of compressor design speed. The impetus for this enhancement was to investigate stage matching and stalling behavior during a start sequence as compared to rotating stall events above ground idle. The model can simulate speed and throttle excursions simultaneously as well as time varying bleed flow schedules. Results of a start simulation are presented and compared to experimental data obtained from an axi-centrifugal turboshaft engine and companion compressor rig. Stage by stage comparisons reveal the front stages to be operating in or near rotating stall through most of the start sequence. The model matches the starting operating line quite well in the forward stages with deviations appearing in the rearward stages near the start bleed. Overall, the performance of the model is very promising and adds significantly to the dynamic simulation capabilities of DYNTECC.
Document ID
19970003321
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wilkes, Kevin (Virginia Polytechnic Inst. and State Univ. Blacksburg, VA United States)
OBrien, Walter F. (Virginia Polytechnic Inst. and State Univ. Blacksburg, VA United States)
Owen, A. Karl (Army Research Lab. Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1996
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TM-107338
ARL-TR-1107
NAS 1.15:107338
E-10477
Meeting Information
Meeting: Gas Turbine and Aeroengine Congress
Location: Birmingham
Country: United Kingdom
Start Date: June 10, 1996
End Date: June 13, 1996
Sponsors: American Society of Mechanical Engineers
Accession Number
97N12065
Funding Number(s)
PROJECT: RTOP 505-62-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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