Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Book Description
Heat Transfer on a Film-Cooled Blade - Effect of Hole Physics
Author: Heat transfer on a film-cooled blade - effect of hole physics, ASME 98-GT-404
Author: Vijay K. GargPublisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Stockholm, Sweden, Jun 2-5, 1998.
Heat Transfer on a Film-Cooled Rotating Blade
Author: Vijay K. GargEffect of Film-Hole Shape on Turbine Blade Film Cooling Performance
Author: Leading Edge Film Cooling Effects on Turbine Blade Heat Transfer
Author: Vijay K. GargPublisher:
ISBN:
Category :
Languages : en
Pages : 26
Book Description
Presented at the International Gas Turbine and Aeroengine Congress and Exposition, Houston, Texas - June 5-8, 1995.
Effect of Film-Hole Shape on Turbine Blade Film Cooling Performance
Author: National Aeronautics and Space Adm NasaPublisher: Independently Published
ISBN: 9781723829673
Category : Science
Languages : en
Pages : 66
Book Description
The detailed heat transfer coefficient and film cooling effectiveness distributions as well as tile detailed coolant jet temperature profiles on the suction side of a gas turbine blade A, ere measured using a transient liquid crystal image method and a traversing cold wire and a traversing thermocouple probe, respectively. The blade has only one row of film holes near the gill hole portion on the suction side of the blade. The hole geometries studied include standard cylindrical holes and holes with diffuser shaped exit portion (i.e. fanshaped holes and laidback fanshaped holes). Tests were performed on a five-blade linear cascade in a low-speed wind tunnel. The mainstream Reynolds number based on cascade exit velocity was 5.3 x 10(exp 5). Upstream unsteady wakes were simulated using a spoke-wheel type wake generator. The wake Strouhal number was kept at 0 or 0.1. Coolant blowing ratio was varied from 0.4 to 1.2. Results show that both expanded holes have significantly improved thermal protection over the surface downstream of the ejection location, particularly at high blowing ratios. However, the expanded hole injections induce earlier boundary layer transition to turbulence and enhance heat transfer coefficients at the latter part of the blade suction surface. In general, the unsteady wake tends to reduce film cooling effectiveness.Han, J. C. and Teng, S.Glenn Research CenterHEAT TRANSFER COEFFICIENTS; COOLANTS; TEMPERATURE PROFILES; SUCTION; TURBINE BLADES; HEAT MEASUREMENT; FILM COOLING; BOUNDARY LAYER TRANSITION; CASCADE WIND TUNNELS; CYLINDRICAL BODIES; EJECTION; GAS TURBINES; HOLE DISTRIBUTION (MECHANICS); LIQUID CRYSTALS; LOW SPEED; THERMAL PROTECTION; THERMOCOUPLES; WIND TUNNEL
Unsteady High Turbulence Effects on Turbine Blade Film Cooling Heat Transfer Performance Using a Transient Liquid Crystal Technique
Author: A Numerical Study of the Effect of Wake Passing on Turbine Blade Film Cooling
Author: James D. HeidmannFilm Cooling and Turbine Blade Heat Transfer
Author: Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 262
Book Description
A Numerical Analysis of Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781721189052
Category :
Languages : en
Pages : 26
Book Description
A computational study has been performed to predict the distribution of convective heat transfer coefficient on a simulated blade tip with cooling holes. The purpose of the examination was to assess the ability of a three-dimensional Reynolds-averaged Navier-Stokes solver to predict the rate of tip heat transfer and the distribution of cooling effectiveness. To this end, the simulation of tip clearance flow with blowing of Kim and Metzger was used. The agreement of the computed effectiveness with the data was quite good. The agreement with the heat transfer coefficient was not as good but improved away from the cooling holes. Numerical flow visualization showed that the uniformity of wetting of the surface by the film cooling jet is helped by the reverse flow due to edge separation of the main flow. Ameri, A. A. and Rigby, D. L. Glenn Research Center NASA/CR-1999-209165, NAS 1.26:209165, E-11756