Stagnation Region Gas Film Cooling for Turbine Blade Leading-Edge Applications

Luckey, D. W.; Winstanley, David; Hanus, G. J.; Lecuyer, M. R.

doi:10.2514/3.58806

Cited by 31 publications

(9 citation statements)

References 9 publications

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“…Film cooling performance over a film cooled test surface is better demonstrated by ratio of heat flux with ejected coolant flow to that without, for film cooling effectiveness and heat transfer coefficient at the same location over a test piece. The heat flux ratio can be expressed as (Luckey et al [13]):…”

Section: Transient Liquid Crystal Techniquementioning

confidence: 99%

Effects of injection angle orientation on concave and convex surfaces film cooling

Hung¹,

Ding²,

Chen³

2009

Experimental Thermal and Fluid Science

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Section: Transient Liquid Crystal Techniquementioning

confidence: 99%

Effects of injection angle orientation on concave and convex surfaces film cooling

Hung¹,

Ding²,

Chen³

2009

Experimental Thermal and Fluid Science

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“…Thus, it would be very important to investigate the phenomena of film injection on the leading-edge region. Several investigators simulated the airfoil leading-edge film cooling using a cylinder with several film-cooling rows (e.g., Luckey et al, 101 Mick and Mayle, 102 and a few papers reviewed and cited in Chapter 3 of Han et al 1 ). Mehendale et al 103 and Mehendale and Han 104 investigated the effect of freestream turbulence on heat transfer and film-cooling effectiveness using a cylindrical leading-edge model.…”

Section: High Freestream Turbulence Effect On Turbine Blade Leading-ementioning

confidence: 99%

Turbine Blade Cooling Studies at Texas A&M University: 1980-2004

Han

2006

Journal of Thermophysics and Heat Transfer

104

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Gas turbines are used extensively for aircraft propulsion, land-based power generation, and industrial applications. Developments in turbine cooling technology play a critical role in increasing the thermal efficiency and power output of advanced high-temperature gas turbine engines. Gas turbine blades are cooled internally by passing the coolant through several rib-enhanced serpentine passages to remove heat conducted from the outside surface. External cooling of turbine blades by film cooling is achieved by injecting relatively cooler air from the internal coolant passages out of the blade surface to form a protective layer between the blade surface and hot gas-path flow. The most important research contributions on turbine blade cooling studies at Texas A&M University's Turbine Heat Transfer Laboratory from 1980 to 2004 are summarized. For turbine blade internal cooling, the focus is on the effect of rotation on rotor blade coolant passage heat transfer with rib turbulators, pin fins, dimples, and impinging jets. For turbine blade external cooling, the focus is on unsteady high freestream turbulence effects on film-cooling performance with a special emphasis on turbine blade edge region heat transfer and cooling problems. Nomenclature A = cooling channel width A R = cooling channel aspect ratio, A:B B = cooling channel height Bo = buoyancy parameter, ( ρ/ρ)Ro 2 (R/D h ) D = cooling channel hydraulic diameter, dimple diameter d = pin-fin diameter e = rib height F c,cor = Coriolis force acting on the coolant flow F cen = centrifugal force F j,cor = Coriolis force acting on the jet flow f = friction factor f 0 = Blasius fully developed friction factor in a nonrotating, smooth tube H = cooling channel height h = heat transfer coefficient L = cooling channel length; cooling channel leading surface M = blowing ratio for film coolant, (ρV ) c /(ρV ) ∞ N u = regionally averaged Nusselt number, h D/k N u r = ribbed-side Nusselt Number N u 0 = Nusselt number for fully-developed, turbulent flow in a non-rotating, smooth tube P = rib pitch R = cooling channel rotating radius Re = Reynolds number, ρV D/μ Ro = rotation number, D/V s = equivalent slot length for film cooling holes T = cooling channel trailing surface= bulk velocity in streamwise direction x = streamwise location within cooling channel z 0 = cooling channel streamwise location β = angle of cooling channel orientation ρ/ρ = coolant-to-wall density ratio δ = dimple depth η = film cooling effectiveness, (T − T

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“…Initial studies into film cooling effectiveness near the leading edge were performed by Luckey et al (1977). Shower-head holes inclined at different angles were tested and a correlation for the optimum blowing ratio was arrived at.…”

Section: Leading Edge Film Coolingmentioning

confidence: 99%

Turbine Blade Film Cooling Using PSP Technique

Han¹,

Rallabandi²

2010

Frontiers in Heat and Mass Transfer

191

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Film cooling is widely used to protect modern gas turbine blades and vanes from the ever increasing inlet temperatures. Film cooling involves a very complex turbulent flow-field, the characterization of which is necessary for reliable and economical design. Several experimental studies have focused on gas turbine blade, vane and end-wall film cooling over the past few decades. Measurements of heat transfer coefficients, film cooling effectiveness values and heat flux ratios using several different experimental methods have been reported. The emphasis of this current review is on the Pressure Sensitive Paint (PSP) mass transfer analogy to determine the film cooling effectiveness. The theoretical basis of the method is presented in detail. Important results in the open literature obtained using the PSP method are presented, discussing parametric effects of blowing ratio, momentum ratio, density ratio, hole shape, surface geometry, free-stream turbulence on flat plates, turbine blades, vanes and end-walls. The PSP method provides very high resolution contours of film cooling effectiveness, without being subject to the conduction error in high thermal gradient regions near the hole.

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Stagnation Region Gas Film Cooling for Turbine Blade Leading-Edge Applications

Cited by 31 publications

References 9 publications

Effects of injection angle orientation on concave and convex surfaces film cooling

Effects of injection angle orientation on concave and convex surfaces film cooling

Turbine Blade Cooling Studies at Texas A&M University: 1980-2004

Turbine Blade Film Cooling Using PSP Technique

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