The external heat transfer distribution on film cooled turbine vanes

Lander, Richard D.; Fish, R. W.; Suo, M.

doi:10.2514/6.1972-9

Cited by 5 publications

(3 citation statements)

References 2 publications

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“…Each airfoil has 32 thermocouples with locations indicated in the results. This equation represents a thin-walled section energy balance having negligible radiation and conduction losses, which include the net lateral conduction within the wall and the conduction through the thermocouple leads (Lander, Fish and Suo [1972]). The lumped parameter approximation is usually valid for small values of the Him number, defined as Si = hit / k m , and based on the metallic airfoil thin wall thickness (I).…”

Section: Cast + Vapor Blastedmentioning

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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Section: Cast + Vapor Blastedmentioning

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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“…More recent cascade investigations tested with the normal heat flow direction by pumping air through the airfoil (6) or individual channels (7) or by metering water through individual channels embedded in copper (8,9). A transient technique was used in (10) by rapidly shuttling the cascade into the hot primary gas. Most recently, short duration measurements have been conducted in a shock tunnel (11) and an isentropic light piston tunnel (12).…”

Section: Introductionmentioning

confidence: 99%

Short Duration Heat Transfer Studies at High Free-Stream Temperatures

Kercher

Sheer

1982

Volume 4: Heat Transfer; Electric Power

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This paper describes short duration heat transfer measurements on aflat plate and a gas turbine nozzle airfoil at high free-stream temperatures. A shock tube generated the high temperature and pressure air flow. Thin-film heat gages recorded the surface heat flux. The flat plate was tested both in the shock tube and in a shock tunnel placed aft of the tube. Shock tunnel tests on the nozzle airfoil measured the local heat transfer distribution. The flat plate free-stream temperatures varied from 830 °R (460 K) to 3190 °R (1770 K) for a T. /T T g temperature ratio of 0.17 to 0.64 at Mach numbers from 0.12 to 1.34. The nozzle measurements at a Tµ,/Tr,g of 0.35 to 0.39 generally indicate that pressure (concave) surface heat transfer coefficients are high, whereas the suction (convex) surface shows much lower heat transfer coefficients than a turbulent flat plate correlation.

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“…Three-dimensional film cooling studies with injection through holes have been carried out by many researchers. Some examples are found in Liess (1975) and Lander et al (1972). Eckert (1983) analysed fullcoverage film cooling of gas turbine blades.…”

mentioning

confidence: 99%

Simulation of Cooling Film Density Ratios in a Mass Transfer Technique

Ammari

Hay

Lampard

1989

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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A systematic investigation of the influence of molecular Schmidt number on cooling film mass transfer coefficient has been conducted using a swollen polymer technique and laser holographic interferometry. A variation in Schmidt number by about 28% was accomplished by injection of a foreign gas and gas mixtures through a single normal hole at a blowing rate of one. The experiments were performed at a constant temperature in a subsonic, zero mainstream pressure gradient turbulent boundary layer on a flat plate.

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The external heat transfer distribution on film cooled turbine vanes

Cited by 5 publications

References 2 publications

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

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

Short Duration Heat Transfer Studies at High Free-Stream Temperatures

Simulation of Cooling Film Density Ratios in a Mass Transfer Technique

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