Numerical study of film cooling from converging slot-hole on a gas turbine blade suction side

2014 ◽  
Vol 52 ◽  
pp. 61-72 ◽  
Author(s):  
Yu Yao ◽  
Jing-zhou Zhang ◽  
Xiao-ming Tan
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Film Cooling ◽  
Numerical Study ◽  
Suction Side ◽  
Gas Turbine Blade

A Numerical Study on the Film-Cooling Characteristics of Gas Turbine Blade using CO2

2012 ◽  
Vol 15 (2) ◽  
pp. 41-44
Author(s):  
Sang-Gwon Kim ◽  
Jong-Chul Lee ◽  
Youn-Jea Kim
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Film Cooling ◽  
Numerical Study ◽  
Gas Turbine Blade

Unsteady Wake Effect on Film Temperature and Effectiveness Distributions for a Gas Turbine Blade

1999 ◽  
Vol 122 (2) ◽  
pp. 340-347 ◽  
Author(s):  
Shuye Teng ◽  
Dong Kee Sohn ◽  
Je-Chin Han
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Film Cooling ◽  
Suction Side ◽  
Boundary Layer Transition ◽  
Gas Turbine Blade ◽  
Wake Effect ◽  
Layer Transition ◽  
Film Cooling Effectiveness ◽  
Unsteady Wake

The film effectiveness and coolant jet temperature profile on the suction side of a gas turbine blade were measured using a transient liquid crystal and a cold-wire technique, respectively. The blade has only one row of film holes near the gill hole portion on the suction side of the blade. 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 5.3×105. Upstream unsteady wakes were simulated using a spoke-wheel type wake generator. Coolant blowing ratio was varied from 0.6 to 1.2. Wake Strouhal number was kept at 0 and 0.1. Results show that unsteady wake reduces film cooling effectiveness. Results also show that film injection enhances local heat transfer coefficient while the unsteady wake promotes earlier boundary-layer transition. The development of coolant jet temperature profiles could be used to explain the film cooling performance. [S0889-504X(00)00402-5]

Short-Duration Measurements and Numerical Simulation of Heat Transfer Along the Suction Side of a Film-Cooled Gas Turbine Blade

1985 ◽  
Vol 107 (4) ◽  
pp. 991-997 ◽  
Author(s):  
C. Camci ◽  
T. Arts
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Film Cooling ◽  
Suction Side ◽  
Gas Turbine Blade ◽  
Transfer Coefficients ◽  
Isentropic Compression ◽  
Curvature Effects ◽  
Convex Wall

This paper deals with an experimental investigation of heat transfer across the suction side of a high-pressure, film-cooled gas turbine blade and with an attempt to numerically predict this quantity both with and without film cooling. The measurements were performed in the VKI isentropic compression tube facility under well-simulated gas turbine conditions. Data measured in a stationary frame, with and without film cooling, are presented. The predictions of convective heat transfer, including streamwise curvature effects, are compared with the measurements. A new approach to determine the augmented mixing lengths near the ejection holes on a highly convex wall is discussed and numerical results agree well with experimentally determined heat transfer coefficients in the presence of film cooling.

scholarly journals Unsteady Wake Effect on Film Temperature and Effectiveness Distributions for a Gas Turbine Blade

1999 ◽  
Author(s):  
Shuye Teng ◽  
Dong Kee Sohn ◽  
Je-Chin Han
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Film Cooling ◽  
Suction Side ◽  
Boundary Layer Transition ◽  
Gas Turbine Blade ◽  
Wake Effect ◽  
Layer Transition ◽  
Film Cooling Effectiveness ◽  
Unsteady Wake

The film effectiveness and coolant jet temperature profile on the suction side of a gas turbine blade were measured using a transient liquid crystal and a cold-wire technique, respectively. The blade has only one row of film holes oear the gill hole portion on the suction side of the blade. 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 5.3×105. Upstream unsteady wakes were simulated using a spoke-wheel type wake generator. Coolant blowing ratio was varied from 0.6 to 1.2. Wake Strouhal number was kept at 0 and 0.1. Results show that unsteady wake reduces film cooling effectiveness. Results also show that film injection enhances local heat transfer coefficient while the unsteady wake promotes earlier boundary-layer transition. The development of coolant jet temperature profiles could be used to explain the film cooling performance.

Numerical Study of Liquid Cooling Gas Turbine Blade

1982 ◽  
Author(s):  
R. S. Amano
Keyword(s):  
Turbulent Flow ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Numerical Study ◽  
Suction Side ◽  
Viscous Sublayer ◽  
Gas Turbine Blade ◽  
Liquid Cooling ◽  
Turbulent Length Scale ◽  
Free Stream Turbulence

Numerical study is reported of a turbulent flow and a convective heat transfer rate around a gas turbine blade. In the computation of turbulent flow, a hybrid method of the central and the upwind finite differencing is used with the standard k-e turbulence model. The quasi-linear transformed coordinate is adopted for a grid system. For the computation of wall boundaries, the wall function is based on the idea that, beyond the viscous sublayer, the turbulent length scale is universal, increasing linearly with distance from the wall. The computed results display more effects of free stream turbulence level on the suction side where a strong favorable pressure gradient takes place than on the pressure side. The model illustrated here shows results superior to the analytic solution as a whole.

Recent Advances in the Study of Film Cooling on the Gas Turbine Blade

2014 ◽  
Vol 971-973 ◽  
pp. 143-147 ◽  
Author(s):  
Ping Dai ◽  
Shuang Xiu Li
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Film Cooling ◽  
Gas Turbines ◽  
High Performance ◽  
Leading Edge ◽  
Development Trend ◽  
Research Progress ◽  
Gas Turbine Blade ◽  
New Generation

The development of a new generation of high performance gas turbine engines requires gas turbines to be operated at very high inlet temperatures, which are much higher than the allowable metal temperatures. Consequently, this necessitates the need for advanced cooling techniques. Among the numerous cooling technologies, the film cooling technology has superior advantages and relatively favorable application prospect. The recent research progress of film cooling techniques for gas turbine blade is reviewed and basic principle of film cooling is also illustrated. Progress on rotor blade and stationary blade of film cooling are introduced. Film cooling development of leading-edge was also generalized. Effect of various factor on cooling effectiveness and effect of the shape of the injection holes on plate film cooling are discussed. In addition, with respect to progress of discharge coefficient is presented. In the last, the future development trend and future investigation direction of film cooling are prospected.

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