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Author Wilkes, Kevin, author.

Title Dynamic modeling of starting aerodynamics and stage matching in an axi-centrifugal compressor / Kevin Wilkes and Walter F. O'Brien, A. Karl Owen.

Publication Info. Cleveland, Ohio : National Aeronautics and Space Administration, Lewis Research Center : U.S. Army Research Laboratory, October 1996.

Copies

Location Call No. OPAC Message Status
 Axe Federal Documents Online  NAS 1.15:107338    ---  Available
Description 1 online resource (7 pages) : illustrations.
text txt rdacontent
computer c rdamedia
online resource cr rdacarrier
Series NASA technical memorandum ; 107338
Army Research Laboratory technical report ; ARL-TR-1107
NASA technical memorandum ; 107338.
ARL-TR (Aberdeen Proving Ground, Md.) ; 1107.
Note Title from title screen (viewed July 26, 2016).
"October 1996"--Report documentation page.
"Prepared for the 41st Gas Turbine and Aeroengine Congress sponsored by the International Gas Turbine Institute of the American Society of Mechanical Engineers, Birmingham, United Kingdom, June 10-13, 1996."
"Performing organization: NASA Lewis Research Center and Vehicle Propulsion Directorate, U.S. Army Research Laboratory"--Report documentation page.
Bibliography Includes bibliographical references (page 7).
Funding Sponsored by the National Aeronautics and Space Administration and U.S. Army Research Laboratory WU-505-62-0L E-10477
Access APPROVED FOR PUBLIC RELEASE.
Summary A 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.
Subject Aerodynamics.
Centrifugal compressors.
Turbine engines.
Turboshafts.
Rotating stalls.
Turboshaft engines.
Centrifugal compressors.
Axial flow compressors.
Operational effectiveness.
Combustors.
Gas turbines.
Mass flow.
Stalling.
Starting.
Static pressure.
Transonic flow.
Jet and Gas Turbine Engines.
Fluid Mechanics.
Added Author O'Brien, Walter F., author.
Owen, A. Karl, author.
Lewis Research Center, issuing body.
U.S. Army Research Laboratory, sponsoring body.
United States. National Aeronautics and Space Administration, sponsoring body.
Other Form: Print version: Dynamic Modeling of Starting Aerodynamics and Stage Matching in an Axi-Centrifugal Compressor (OCoLC)946108298
Microfiche version: Wilkes, Kevin. Dynamic modeling of starting aerodynamics and stage matching in an axi-centrifugal compressor (OCoLC)39722390
Standard No. DTICE ADA326234
Gpo Item No. 0830-H-15 (online)
Sudoc No. NAS 1.15:107338

 
    
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