A Rapid Blade-to-Blade Solution for Use in Turbomachinery Design

McFarland, E. R.

doi:10.1115/1.3239574

Cited by 37 publications

(14 citation statements)

References 7 publications

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“…The flow analysis was done using the MERIDL code developed by Katsanis and McNally 4 coupled to the PANEL code of McFarland. 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.…”

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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“…For its twist in the circumferential direction is very small, S 1 stream surfaces are usually assumed to be symmetric in the engineering practice [17].…”

Section: Governing Equation On S 1 Stream Surfacesmentioning

confidence: 99%

Design optimization of axial flow hydraulic turbine runner: Part I—an improved Q3D inverse method

Peng

Cao

Ishizuka

et al. 2002

Numerical Methods in Fluids

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SUMMARYWith the aim of constructing a comprehensive design optimization procedure of axial ow hydraulic turbine, an improved quasi-three-dimensional inverse method has been proposed from the viewpoint of system and a set of rotational ow governing equations as well as a blade geometry design equation has been derived. The computation domain is ÿrstly taken from the inlet of guide vane to the far outlet of runner blade in the inverse method and ows in di erent regions are solved simultaneously. So the in uence of wicket gate parameters on the runner blade design can be considered and the di culty to deÿne the ow condition at the runner blade inlet is surmounted. As a pre-computation of initial blade design on S 2m surface is newly adopted, the iteration of S 1 and S 2m surfaces has been reduced greatly and the convergence of inverse computation has been improved. The present model has been applied to the inverse computation of a Kaplan turbine runner. Experimental results and the direct ow analysis have proved the validation of inverse computation. Numerical investigations show that a proper enlargement of guide vane distribution diameter is advantageous to improve the performance of axial hydraulic turbine runner.

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“…7 This analysis uses a panel method formulation to solve the inviscid irrotational compressible blade-to-blade ow equations on a surface of revolution. The exit ow angle is determined as part of the solution by using the Kutta condition to set the circulation around the airfoil.…”

Section: Steady Flow Modelmentioning

confidence: 99%

Impeller Blade Unsteady Aerodynamic Response to Vaned Diffuser Potential Fields

Gottfried

Fleeter

2002

Journal of Propulsion and Power

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To predict the unsteady aerodynamic response of centrifugal compressor impeller blades to the potential eld generated by the downstream vaned diffuser, a small perturbation model is developed that considers the number of impeller blades and diffuser vanes, the impeller blade backsweep angle, the impeller rotational speed, and the mass ow rate. The unsteady ow is analyzed in the impeller exit region and the vaneless diffuser space between the impeller and the diffuser leading edge radius, where the unsteady ow generated by the diffuser vane potential eld is most signi cant. The unsteady ow perturbations are superimposed on an irrotational two-dimensional steady ow model, resulting in an analysis that is consistent with the small perturbation velocity potential equation. This model is then applied to a representative modern high speed impeller-vaned diffuser con guration. NomenclatureA = speed of sound A 0i = stagnation speed of sound at in ow boundary G = impeller blade spacing vector k = reduced frequency k m d = tangential wave number at inlet boundary k m µ = tangential wave number for continuous analytic solution M r= stagnation pressure at the in ow boundary p = perturbation pressure r; µ ; t = cylindrical coordinate directions and time in rotating impeller frame r i = grid inlet radius r t = impeller tip radius r v = radius of diffuser vane leading edges (radius of grid exit) T oh = stagnation temperature at the in ow boundary V = velocity in the stationary frame of reference V r = radial velocity V rel = velocity in the rotating impeller frame V µ = tangential velocity in the stationary frame V µ rel = tangential velocity in the rotating frame v = perturbation velocity ® = impeller blade angle with respect to radial ® t = impeller blade angle at impeller exit 0 2 = 1 ¡ M 2 r 1C p = pressure coef cient differential across the impeller blade, 1p=. 1 2 ½ oi A 2 oh / ½ = perturbation density ½ 0i = stagnation density at in ow boundary ¾ = interblade phase angle Á = perturbation velocity potential

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A Rapid Blade-to-Blade Solution for Use in Turbomachinery Design

Cited by 37 publications

References 7 publications

Turbine blading designed for high heat load space propulsion applications

Turbine blading designed for high heat load space propulsion applications

Design optimization of axial flow hydraulic turbine runner: Part I—an improved Q3D inverse method

Impeller Blade Unsteady Aerodynamic Response to Vaned Diffuser Potential Fields

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