Cold-air Performance of Compressor-drive Turbine of Department of Energy Upgraded Automobile Gas Turbine Engine PDF Download
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Author: Richard J. Roelke
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Book Description
Author: Richard J. Roelke
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Book Description
The aerodynamic performance of the inlet manifold and stator assembly of the compressor-drive turbine was experimentally determined with cold air as the working fluid. The investigation included measurements of mass flow and stator-exit fluid torque as well as radial surveys of total pressure and flow angle at the stator inlet and annulus surveys of total pressure and flow angle at the stator exit. The stator-exit aftermixed flow conditions and overall stator efficiency were obtained and compared with their design values and the experimental results from three other stators. In addition, an analysis was made to determine the constituent aerodynamic losses that made up the stator kinetic energy loss. (Author).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
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Book Description
The aerodynamic performance of the compressor-drive turbine of the DOE Upgraded Gas Turbine (UGT) engine was determined in low-temperature air. The nominal turbine-inlet temperature was 320 K. Inlet pressures were varied between 0.4 and 2.4 bars absolute. The turbine blading used in these tests consisted of duplicates of the stator and rotor castings used in development engine tests. The as-received cast rotor blades had a significantly thicker profile than design and a fairly rough surface finish. Because of these blade profile imperfections three turbine rotor configurations were evaluated. These were the as-cast rotor, a reduced-roughness rotor, and a rotor with the blade profiles thinned to near the design profile. Tests to determine the effect of Reynolds number on the turbine performance were also made. (Author).
Author: Richard J. Roelke
Publisher:
ISBN:
Category : Automotive gas turbines
Languages : en
Pages : 26
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Author:
Publisher:
ISBN:
Category : Fuel
Languages : en
Pages : 680
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723419041
Category :
Languages : en
Pages : 24
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Book Description
The aerodynamic performance of the compressor-drive turbine of the DOE upgraded gas turbine engine was determined in low temperature air. The as-received cast rotor blading had a significantly thicker profile than design and a fairly rough surface finish. Because of these blading imperfections a series of stage tests with modified rotors were made. These included the as-cast rotor, a reduced-roughness rotor, and a rotor with blades thinned to near design. Significant performance changes were measured. Tests were also made to determine the effect of Reynolds number on the turbine performance. Comparisons are made between this turbine and the compressor-drive turbine of the DOE baseline gas turbine engine. Roelke, R. J. and Haas, J. E. Glenn Research Center NASA-TM-82818, DOE/NASA/1011-36, NAS 1.15:82818, AVRADCOM-TR-82-C-1 EC-77-A-31-1011
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1572
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Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1252
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Author:
Publisher:
ISBN:
Category : Power resources
Languages : en
Pages : 662
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