Comparison between measured turbine stage performance and the predicted performance using quasi-3D flow and boundary layer analyses

Boyle, R. J.; Katsanis, T.; Haas, J. E.

doi:10.2514/6.1984-1299

Cited by 16 publications

(8 citation statements)

References 3 publications

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“…5 The results of the flow analysis were coupled to boundary-layer analyses. The predicted aerodynamic efficiency was calculated using the procedure given by Boyle et al 6 The heat-transfer analysis used the STAN5 finite-difference boundary-layer code of Crawford and Kays. 7 The aerodynamic efficiency procedure utilized the integral boundary-layer code BLAYER, developed by McNally.…”

Section: Methods Of Analysismentioning

confidence: 99%

Turbine blading designed for high heat load space propulsion applications

Civinskas

Boyle

Mcconnaughey

1990

Journal of Propulsion and Power

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The operating conditions and the propellant transport properties used in Earth-to-orbit (ETO) applications affect the aerothermodynamic design of ETO turbomachinery in a number of ways. This paper discusses some aerodynamic and heat-transfer implications of the low molecular weight fluids and high Reynolds number operating conditions on future ETO turbomachinery. The objective of this work was to examine turbine blading concepts for increasing life and reliability by reducing thermal heat load. Using the current Space Shuttle main engine high-pressure fuel turbine as a baseline, aerothermodynamic comparisons were made for two alternate fuel turbine geometries. The first was a revised first-stage rotor blade designed to reduce peak heat transfer. This alternate design resulted in a 23% reduction in peak heat transfer. The second design concept was a single-stage rotor designed to yield the same power output as the baseline two-stage rotor. Since the rotor tip speed was held constant, the turbine work factor doubled. In this alternate design, the peak heat transfer remained the same as the baseline. Although the efficiency of the single-stage design was 3.1 points less than the baseline two-stage turbine, the design was aerothermodynamically feasible and may be structurally desirable. NomenclatureC\ = slope of heat-transfer augmentation curve C p = specific heat c = chord D = leading-edge diameter e = kinetic energy loss coefficient h = heat-transfer coefficient / = enthalpy m = exponent in heat-transfer correlation N s = number of stages Nu -Nusselt number based on diameter Pr = Prandtl number p = pressure q -heat flux R = gas constant Re = Reynolds number based on blade leading-edge diameter T = temperature T u = turbulence intensity U = wheel speed V -absolute velocity v = specific volume W = relative velocity Z = compressibility factor a = absolute flow angle | 8 = relative flow angle 7 A/T = ratio of specific heats = output specific work = efficiencyPresented as Paper 88-3091 at the AIAA/ASME/SAE/ASEE 24th

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Section: Methods Of Analysismentioning

confidence: 99%

Turbine blading designed for high heat load space propulsion applications

Civinskas

Boyle

Mcconnaughey

1990

Journal of Propulsion and Power

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“…The steady-state aerodynamic loads acting on the compressor blades as well as the blade row efficiency are determined using MTSB, a quasi-three-dimensional, inviscid turbomachinery analysis code [36]. The static response of the blade due to the aerodynamic and centrifugal loads is determined using NIKE3D, a nonlinear, implicit three-dimensional finite element code developed and distributed by Lawrence Livermore National Laboratory [37].…”

confidence: 99%

Applications of Reliability Assessment

Sues¹,

Shin²,

Wu³

2004

Engineering Design Reliability Handbook

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This example considers a detailed airplane wing design problem [38]. The baseline airplane is a Mach 0.3, 20-seat transport with a payload capacity on the order of 5000 lb. RBDO FormulationObjective: Maximize expected cruise range Subject to reliability constraints: P(upper surface root stress 1 £ yield) ≥ 99.0% P(upper surface root stress 2 £ yield) ≥ 99.0% P(lower surface root stress 1 £ yield) ≥ 99.0% P(lower surface root stress 2 £ yield) ≥ 99.0% P(takeoff distance £ 3000 ft) ≥ 99.0% P(wing area £ 600 ft 2 ) ≥ 50.0%

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“…Two-dimensional boundary layer codes have been extensively studied to evaluate their potential for predicting film cooling performance. Crawford and Kays (1976), ICatsanis andMcNally 1977, Crawford et at (1980), Boyle et at (1984), Shonung and Roth (1987), Tafti and Yavuzkurt (1990), Norton et at (1990), andHaas et at (1992) used twodimensional boundary layer codes to predict surface heat transfer performance. Many two-dimensional boundary layer models used empirical parameters for particular flow situations.…”

Section: Previous Computational Studiesmentioning

confidence: 99%

Film Cooling Effectiveness Predictions for Short Holes Fed by a Narrow Plenum

Hale

Ramadhyani

Plesniak

1999

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

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This study evaluates the ability of available turbulence models in the commercial software FLUENT to predict film cooling effectiveness for a single row of short (LID = 2.91) . film cooling holes fed by a narrow plenum (H /D = 1). The results are compared to experimental data obtained by the present investigators. The study concentrates on the near-hole region for the geometry being studied experimentally by the present investigators. The results of the study indicate that the use of wall functions to predict film cooling effectiveness in the near-hole region is inappropriate due to the boundary layer separation in that region. Also, the ability of the Reynolds Stress turbulence model to better predict spanwise spreading of the jet indicates the need for anisotropic turbulnce model capabilities to better predict film cooling effectiveness.

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Comparison between measured turbine stage performance and the predicted performance using quasi-3D flow and boundary layer analyses

Cited by 16 publications

References 3 publications

Turbine blading designed for high heat load space propulsion applications

Turbine blading designed for high heat load space propulsion applications

Applications of Reliability Assessment

Film Cooling Effectiveness Predictions for Short Holes Fed by a Narrow Plenum

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