Time-Averaged Heat Transfer and Pressure Measurements and Comparison With Prediction for a Two-Stage Turbine

Dunn, Michael G.; Kim, J.; Civinskas, K. C.; Boyle, R. J.

doi:10.1115/1.2928270

Cited by 47 publications

(4 citation statements)

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“…There are in fact some heat transfer data available on blade tips but are limited to discrete point measurements on locations mainly along the mean camber line of the tip of rotating blades (Dunn et al 1984a,1984band Dunn and Kim, 1992. The data do provide a useful check on the numerical prediction of heat transfer as was done by Ameri and Steinthorsson (1995Steinthorsson ( , 1996.…”

Section: Introduction •mentioning

confidence: 99%

Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine: Part 2 — Simulation Results

Ameri¹,

Bunker

1999

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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A combined experimental and computational study has been performed to investigate the detailed distribution of convective heat transfer coefficients on the first stage blade tip surface for a geometry typical of large power generation turbines (>100MW). This paper is concerned with the numerical prediction of the tip surface heat transfer. Good comparison with the experimental measured distribution was achieved through accurate modeling of the most important features of the blade passage and heating arrangement as well as the details of experimental rig likely to affect the tip heat transfer. A sharp edge and a radiused edge tip was considered. The results using the radiused edge tip agreed better with the experimental data. This improved agreement was attributed to the absence of edge separation on the tip of the radiused edge blade.

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Section: Introduction •mentioning

confidence: 99%

Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine: Part 2 — Simulation Results

Ameri¹,

Bunker

1999

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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“…Blair (1992) and Boyle (1993) suggested that k s = R 2 . Dunn et al (1992) used Ic s = R / (13 and Guo et al (1996) found that k s = Rz for the best comparison of their experimental data. Bogard et al (1996) adopted a roughness shape / density parameter of Sigal and Danberg (1990) to characterize vane roughness, and then modeled large scale, flat plate surfaces to mimic this parameter value.…”

Section: Introductionmentioning

confidence: 99%

Effects of Surface Roughness on Heat Transfer and Aerodynamic Performance of Turbine Airfoils

Abuaf

Bunker

Lee

1997

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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Aerodynamic flow path losses and turbine airfoil gas side heat transfer are strongly affected by the gas side surface finish. For high aero efficiencies and reduced cooling requirements, airfoil designs dictate extensive surface finishing processes to produce smooth surfaces and enhance engine performance. The achievement of these requirements incurs additional manufacturing finishing costs over less strict requirements. The present work quantifies the heat transfer (and aero) performance differences of three cast airfoils with varying degrees of surface finish treatment. An airfoil which was grit blast and Codep coated produced an average roughness of 2.33 μm, one which was grit blast, tumbled, and Aluminide coated produced 1.03 μm roughness, and another which received further post coating polishing produced 0.81 μm roughness. Local heat transfer coefficients were experimentally measured with a transient technique in a linear cascade with a wide range of flow Reynolds numbers covering typical engine conditions. The measured heat transfer coefficients were used with a rough surface Reynolds Analogy to determine the local skin friction coefficients, from which the drag forces and aero efficiencies were calculated. Results show that tumbling and polishing reduce the average roughness and improve performance. The largest differences are observed from the rumbling process, with smaller improvements realized from polishing.

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“…Heat transfer data on an uncooled rotor blade coupled with an upstream cooled nozzle guiding vane were reported by Dunn et al [1989]. Dunn et al [1994] Figure 2. The geometric data of the linear cascade are listed in Table I.…”

Section: Introductionmentioning

confidence: 99%

“…Chen et al [1994a] There are some studies (Dunn et al [1989(Dunn et al [ , 1994; Abhari and Epstein [1994]) which were conducted in a short duration turbine test facility rather than in a low-speed wind tunnel with a linear cascade for simulating full engine conditions. Heat transfer data on an uncooled rotor blade coupled with an upstream cooled nozzle guiding vane were reported by Dunn et al [1989].…”

Section: Introductionmentioning

confidence: 99%

Effect of Upstream Wake on Shower‐Head Film Cooling

Chen

Miao

1996

International Journal of Rotating Machinery

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The present study aims to investigate the effect of an upstream wake on the convective transport phenomena over a turbine blade with shower-head film cooling. A naphthalene sublimation technique was implemented to obtain the detailed mass transfer distributions on both suction and pressure surfaces of the test blade. All mass transfer runs were conducted on a blowing-type wind tunnel with a six-blade linear cascade. The leading edge of the test blade was drilled with three rows of equally spaced injection holes. The upstream wake was simulated by a circular bar with the same diameter as that of the trailing edge of the test blade.The test condition was fixed at Re 397,000, M 0.8, and Tu 0.4% and upstream wakes were generated at four different locations ahead of the blade cascade. Measured results show that there is a difference in mass transfer rate from the case without upstream wake. This difference is greater on the suction side than on the pressure side. The difference results from the interaction between the wake flow that is induced by the upstream wake and the injection flows that are ejected from the multi-rows of injection holes on the test blade. It was also found that the location of upstream wake generation significantly affects the mass transfer distributions on both surfaces of test blade.

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Time-Averaged Heat Transfer and Pressure Measurements and Comparison With Prediction for a Two-Stage Turbine

Cited by 47 publications

References 0 publications

Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine: Part 2 — Simulation Results

Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine: Part 2 — Simulation Results

Effects of Surface Roughness on Heat Transfer and Aerodynamic Performance of Turbine Airfoils

Effect of Upstream Wake on Shower‐Head Film Cooling

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