Fully Scaled Transonic Turbine Rotor Heat Transfer Measurements

Guenette, G. R.; Epstein, A. H.; Giles, Michael B.; Haimes, Robert; Norton, R. J. G.

doi:10.1115/1.3262231

Cited by 75 publications

(40 citation statements)

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“…2 Nu = Nusselt number based on C ax , inlet blade relative total temperature, T w , and main gas thermal conductivity at the wall P -pressure 6 = nondimensional coolant temperature = (7V -T c )/T r -T w ) p = density S = surface length from the stagnation point T = temperature U = velocity X = axial distance £ = orthogonal coordinate normal to jet centerline, shown in were not available to the author. The hub section geometry was reconstructed from photographs and drawings available in the public domain (Abhari, 1991;Norton et al, 1990;Guenette et al, 1989). Aerodynamic boundary conditions for the numerical simulations at different test conditions are obtained from Abhari (1991).…”

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confidence: 99%

Impact of Rotor–Stator Interaction on Turbine Blade Film Cooling

Abhari

1996

Journal of Turbomachinery

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The goal of this study is to quantify the impact of rotor-stator interaction on surface heat transfer of film cooled turbine blades. In Section I, a steady-state injection model of the film cooling is incorporated into a two-dimensional, thin shear layer, multiblade row CFD code. This injection model accounts for the penetration and spreading of the coolant jet, as well as the entrainment of the boundary layer fluid by the coolant. The code is validated, in the steady state, by comparing its predictions to data from a blade tested in linear cascade. In Section II, time-resolved film cooled turbine rotor heat transfer measurements are compared with numerical predictions. Data were taken on a fully film cooled blade in a transonic, high pressure ratio, single-stage turbine in a short duration turbine test facility, which simulates full-engine nondimensional conditions. Film cooled heat flux on the pressure surface is predicted to be as much as a factor of two higher in the time average of the unsteady calculations compared to the steady-state case. Time-resolved film cooled heat transfer comparison of data to prediction at two spanwise positions is used to validate the numerical code. The unsteady stator-rotor interaction results in the pulsation of the coolant injection flow out of the film holes with large-scale fluctuations. The combination of pulsating coolant flow and the interaction of the coolant with this unsteady external flow is shown to lower the local pressure side adiabatic film effectiveness by as much as 64 percent when compared to the steady-state case.

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confidence: 99%

Impact of Rotor–Stator Interaction on Turbine Blade Film Cooling

Abhari

1996

Journal of Turbomachinery

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“…Turbine blade film cooling has been studied since the early 1970s. Since the 1980s, others have studied the effects of simulated engine flows such as unsteady, high freestream turbulence on turbine blade heat transfer penalty (e.g., Dunn et al, 94,95 Nealy, 96 Blair et al, 97,98 Guenette et al, 99 Dullenkopf et al, 100 and many previous papers reviewed and cited in Chapter 2 of Han et al 1 ). In contrast, studies of film-cooling performance under unsteady, high freestream turbulence conditions with turbulence intensities up to 15-20% were not generally available until the late 1980s and the early 1990s.…”

Section: Turbine Blade Film Coolingmentioning

confidence: 97%

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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“…This may affect the behavior of the tip leakage flow and consequently heat transfer patterns around the blade tip. Some research [25][26][27][28][29][30][31][32][33] has dealt with the effect of vane/blade interaction and operating conditions on blade heat transfer and showed periodic variation in the heat transfer pattern due to the interaction.…”

Section: Introductionmentioning

confidence: 99%