Author: Edwin R. YarbroughPublisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 0
Book Description
Stagnation Region Gas Film Cooling
Author: D. W. LuckeyPublisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 388
Book Description
Stagnation Region Gas Film Cooling
Author: Edwin R. YarbroughPublisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 0
Book Description
An Approximate Analysis of Film Cooling on Blunt Bodies by Gas Injection Near the Stagnation Point
Author: Byron L. SwensonPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44
Book Description
An Experimental Study of Stagnation Region Film Cooling for Application to Gas Turbine Airfoils
Author: Warren J. MickStagnation Region Gas Film Cooling Spanwise Angled Coolant Injection
Author: David W. LuckeyPublisher:
ISBN:
Category :
Languages : en
Pages : 357
Book Description
This experimental investigation involved the study of gas film cooling from a single row of spanwise angled holes using the stagnation region of a cylinder in cross flow to model the leading edge of a turbine vane. The objective was to obtain data for the local convective heat transfer rates to a highly cooled, curved surface exposed to a turbulent hot mainstream flow and a secondary, film coolant flow. Since the leading edge of the first stage, inlet turbine vane experiences some of the most severe thermal loads found in the turbine engine, effective film cooling is most important in this area. Film cooling of the leading edge area was modeled by making heat transfer measurements on the front stagnation region of a cylinder in cross flow. Experiments were conducted in a rectangular duct using a film cooled cylindrical test surface normal to a two-dimensional freestream flow. A gas turbine combustor provided heated air flow to simulate a Reynolds number typical of a high pressure, high temperature turbine vane. Internal convection cooling of the cylinder allowed a gas-to-wall temperature ratio of 2.1 to be achieved while using a moderate freestream gas temperature (1000R; 555K. The film coolant was chilled to obtain a coolant-to-freestream density ratio of 2.2, representative of the gas turbine environment. The cylindrical test surface was instrumented with miniature heat flux gages, and wall thermocouples to determine the influence of the film coolant blowing ratio and the injection hole geometry on the film cooling performance.
Stagnation Region Gas Film Cooling
Author: David Wilson LuckeyAn Approximate Analysis of Film Cooling on Blunt Bodies by Gas Injection Near the Stagnation Point
Author: Byron L. SwensonPublisher: BiblioGov
ISBN: 9781289269203
Category :
Languages : en
Pages : 44
Book Description
An approximate method for the estimation of laminar heat transfer to blunt bodies with gaseous film cooling i s developed. Attention is focused on the parameters which are important for the design of an attractive heat protection system. Application of the analysis is made to calculate the approximate coolant weight requirement for both a circular and a parabolic entry.
Survey of Advantages and Problems Associated with Transpiration Cooling and Film Cooling of Gas-turbine Blades
Author: Ernst Rudolf Georg EckertPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44
Book Description
Summary: Transpiration and film cooling promise to be effective methods of cooling gas-turbine blades; consequently, analytical and experimental investigations are being conducted to obtain a better understanding of these processes. This report serves as an introduction to these cooling methods, explains the physical processes, and surveys the information available for predicting blade temperatures and heat-transfer rates. In addition, the difficulties encountered in obtaining a uniform blade temperature are discussed, and the possibilities of correcting these difficulties are indicated. Air is the only coolant considered in the application of these cooling methods.
An Approximate Analysis of Film Cooling on Blunt Bodies by Gas Injection Near the Stagnation Point
Author: Byron L. SwensonPublisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
An approximate method for the estimation of laminar heat transfer to blunt bodies with gaseous film cooling is developed. Attention is focused on the parameters which are important for the design of an attractive heat protection system. Application of the analysis is made to calculate the approximate coolant weight requirement for both a circular and a parabolic entry. (Author).
Film cooling effectiveness in the showerhead region of a gas turbine vane Part I: Stagnation region and near-pressure side, ASME 99-GT-48
Author: Marc D. PolankaPublisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, Indiana, June 7-June 10, 1999.