Author: Ernst Rudolf Georg Eckert
Publisher:
ISBN:
Category : Cooling
Languages : en
Pages : 738
Book Description
In transpiration cooling of various structural elements in gas turbines, the coolant has to be ducted within passages to the porous walls through which it is ejected into the gas stream. The passages, often arranged in rotating parts, have to be designed in such a way as to ensure the proper local distribution of the coolant. In this report, a method is presented by which either the local permeability can be predicted. The method is based on a one-dimensional treatment of the gas flow through a rotating channel with varying cross section and partially porous walls. The inlet pressure into the channel and the outside pressure along it are assumed prescribed. It is also stipulated that the passage ends blindly. However, the method can easily be extended to cover the situation where a certain mass flow leaves the open end of the passage.
One-dimensional Calculation of Flow in a Rotating Passage with Ejection Through a Porous Wall
Author: Ernst Rudolf Georg Eckert
Publisher:
ISBN:
Category : Cooling
Languages : en
Pages : 738
Book Description
In transpiration cooling of various structural elements in gas turbines, the coolant has to be ducted within passages to the porous walls through which it is ejected into the gas stream. The passages, often arranged in rotating parts, have to be designed in such a way as to ensure the proper local distribution of the coolant. In this report, a method is presented by which either the local permeability can be predicted. The method is based on a one-dimensional treatment of the gas flow through a rotating channel with varying cross section and partially porous walls. The inlet pressure into the channel and the outside pressure along it are assumed prescribed. It is also stipulated that the passage ends blindly. However, the method can easily be extended to cover the situation where a certain mass flow leaves the open end of the passage.
Publisher:
ISBN:
Category : Cooling
Languages : en
Pages : 738
Book Description
In transpiration cooling of various structural elements in gas turbines, the coolant has to be ducted within passages to the porous walls through which it is ejected into the gas stream. The passages, often arranged in rotating parts, have to be designed in such a way as to ensure the proper local distribution of the coolant. In this report, a method is presented by which either the local permeability can be predicted. The method is based on a one-dimensional treatment of the gas flow through a rotating channel with varying cross section and partially porous walls. The inlet pressure into the channel and the outside pressure along it are assumed prescribed. It is also stipulated that the passage ends blindly. However, the method can easily be extended to cover the situation where a certain mass flow leaves the open end of the passage.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 956
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 956
Book Description
Technical Note
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 386
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 386
Book Description
Research Abstracts and Reclassification Notice
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 508
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 508
Book Description
Research Abstracts
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 442
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 442
Book Description
U.S. Government Research Reports
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 48
Book Description
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 48
Book Description
Catalog of Technical Reports
Author: United States. Dept. of Commerce. Office of Technical Services
Publisher:
ISBN:
Category :
Languages : en
Pages : 850
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 850
Book Description
Monthly Catalog of United States Government Publications
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1560
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1560
Book Description
Subject Index to Unclassified ASTIA Documents
Author: Defense Documentation Center (U.S.)
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 308
Book Description
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 308
Book Description
Gas Turbine Blade Cooling
Author: Chaitanya D Ghodke
Publisher: SAE International
ISBN: 0768095034
Category : Technology & Engineering
Languages : en
Pages : 238
Book Description
Gas turbines play an extremely important role in fulfilling a variety of power needs and are mainly used for power generation and propulsion applications. The performance and efficiency of gas turbine engines are to a large extent dependent on turbine rotor inlet temperatures: typically, the hotter the better. In gas turbines, the combustion temperature and the fuel efficiency are limited by the heat transfer properties of the turbine blades. However, in pushing the limits of hot gas temperatures while preventing the melting of blade components in high-pressure turbines, the use of effective cooling technologies is critical. Increasing the turbine inlet temperature also increases heat transferred to the turbine blade, and it is possible that the operating temperature could reach far above permissible metal temperature. In such cases, insufficient cooling of turbine blades results in excessive thermal stress on the blades causing premature blade failure. This may bring hazards to the engine's safe operation. Gas Turbine Blade Cooling, edited by Dr. Chaitanya D. Ghodke, offers 10 handpicked SAE International's technical papers, which identify key aspects of turbine blade cooling and help readers understand how this process can improve the performance of turbine hardware.
Publisher: SAE International
ISBN: 0768095034
Category : Technology & Engineering
Languages : en
Pages : 238
Book Description
Gas turbines play an extremely important role in fulfilling a variety of power needs and are mainly used for power generation and propulsion applications. The performance and efficiency of gas turbine engines are to a large extent dependent on turbine rotor inlet temperatures: typically, the hotter the better. In gas turbines, the combustion temperature and the fuel efficiency are limited by the heat transfer properties of the turbine blades. However, in pushing the limits of hot gas temperatures while preventing the melting of blade components in high-pressure turbines, the use of effective cooling technologies is critical. Increasing the turbine inlet temperature also increases heat transferred to the turbine blade, and it is possible that the operating temperature could reach far above permissible metal temperature. In such cases, insufficient cooling of turbine blades results in excessive thermal stress on the blades causing premature blade failure. This may bring hazards to the engine's safe operation. Gas Turbine Blade Cooling, edited by Dr. Chaitanya D. Ghodke, offers 10 handpicked SAE International's technical papers, which identify key aspects of turbine blade cooling and help readers understand how this process can improve the performance of turbine hardware.