Cooled Radial In-flow Turbines for Advanced Gas Turbine Engines PDF Download
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Author: J. M. Lane
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
Paper presents the results of several Army-sponsored programs, the first of which addresses the performance potential for high-temperature radial turbine.
Author: J. M. Lane
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
Paper presents the results of several Army-sponsored programs, the first of which addresses the performance potential for high-temperature radial turbine.
Author: Jeffrey E. Haas
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 36
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Book Description
Two tip clearance configurations, one with a recess in the casing and the other with a reduced rotor blade height, were investigated at design equivalent speed over a range of tip clearance from about 2.0 to 5.0 percent of the stator blade height. The optimum configuration with a recess in the casing was the one where the rotor tip diameter was equal to the stator tip diameter (zero blade extension). For this configuration there was an approximate 1.5 percent decrease in total efficiency for an increase in tip clearance of 1 percent of stator blade height. For the reduced blade height configurations there was an approximate 2.0 percent decrease in total efficiency for an increase in tip clearance of 1 percent of stator blade height.
Author: W. Byron Brown
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 32
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Book Description
Author: Richard J. Roelke
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
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Book Description
Author: Je-Chin Han
Publisher: Taylor & Francis
ISBN: 1466564903
Category : Science
Languages : en
Pages : 865
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Book Description
A comprehensive reference for engineers and researchers, this second edition focuses on gas turbine heat transfer issues and their associated cooling technologies for aircraft and land-based gas turbines. It provides information on state-of-the-art cooling technologies such as advanced turbine blade film cooling and internal cooling schemes. The book also offers updated experimental methods for gas turbine heat transfer and cooling research, as well as advanced computational models for gas turbine heat transfer and cooling performance predictions. The authors provide suggestions for future research within this technology and includes 800 illustrations to help clarify concepts and instruction.
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: W. Byron Brown
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 26
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Book Description
Author: John C. Freche
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 30
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Book Description
Author: R.S. Amano
Publisher: WIT Press
ISBN: 1845649060
Category : Science
Languages : en
Pages : 253
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Book Description
Due to the requirement for enhanced cooling technologies on modern gas turbine engines, advanced research and development has had to take place in field of thermal engineering. Among the gas turbine cooling technologies, impingement jet cooling is one of the most effective in terms of cooling effectiveness, manufacturability and cost. The chapters contained in this book describe research on state-of-the-art and advanced cooling technologies that have been developed, or that are being researched, with a variety of approaches from theoretical, experimental, and CFD studies. The authors of the chapters have been selected from some of the most active researchers and scientists on the subject. This is the first to book published on the topics of gas turbines and heat transfer to focus on impingement cooling alone.
Author: Raymond Strong Colladay
Publisher:
ISBN:
Category : Cooling
Languages : en
Pages : 52
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Book Description
The relative performance of (1) counterflow film cooling, (2) parallel-flow film cooling, (3) convection cooling, (4) adiabatic film cooling, (5) transpiration cooling, and (6) full-coverage film cooling was investigated for heat loading conditions expected in future gas turbine engines. Assumed in the analysis were hot-gas conditions of 2200 K (3500 F) recovery temperature, 5 to 40 atmospheres total pressure, and 0.6 gas Mach number and a cooling air supply temperature of 811 K (1000 F). The first three cooling methods involve film cooling from slots. Counterflow and parallel flow describe the direction of convection cooling air along the inside surface of the wall relative to the main gas flow direction. The importance of utilizing the heat sink available in the coolant for convection cooling prior to film injection is illustrated.
