Solution of Plane Cascade Flow Using Improved Surface Singularity Methods

McFarland, E. R.

doi:10.1115/1.3227330

Cited by 25 publications

(11 citation statements)

References 1 publication

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“…To improve the precision in determining when separation occurs, if it occurs near the leading edge, a blade-toblade solver such as described in Ref. 26 would be useful. This program determines a more accurate solution in the leading edge region through the use of body fitted coordinates.…”

Section: Discussionmentioning

confidence: 99%

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

Boyle

Katsanis

Haas

1984

20th Joint Propulsion Conference

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A method for calculating turbine stage performance is described. The usefulness of the method is demonstrated by comparing measured and predicted efficiencies for nine different stages. Comparisons are made over a range of turbine pressure ratios and rotor speeds. A quasi-3D flow analysis is used to account for complex passage geometries. Boundary layer analyses are done to account for losses due to friction. Empirical loss models are used to account for incidence, secondary flow, disc windage, and clearance losses. Nomenclature

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Section: Discussionmentioning

confidence: 99%

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

Boyle

Katsanis

Haas

1984

20th Joint Propulsion Conference

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“…The integral equation solution is second order accurate in terms of the elements used to approximate the tlade shape. Its accuracy was discussed in reference [3]. Numerical integration of the terms in equations (15a) and (15b) was accomplished using a simple trapezoidal method.…”

Section: Methods Accuracymentioning

confidence: 99%

“…The above conditions, along with the conservation of angular momentum (rV 9 = constant) in areas outside the blade row and equations (15), are used to develop a system of equations similar to equations (17)-(19) in reference [3]. This system of equations is solved by upper and lower triangular matrix decomposition.…”

Section: Original Pier Ici Of Poor Qualitymentioning

confidence: 99%

“…In the notation of this paper, the 2. At the upstream boundary, onset velocity reference [3] becomes, …”

Section: In Xmentioning

confidence: 99%

“…In the present work, the velocity part of this transformation is modified to the following W x -r P bWm ; W = rpbW9 (7) Note that the transformation preserves the relative flow angle from the m-♦ surface to the x-y surface. S ince equations (11) and (12) In this study a solution to these equations was developed by using the integral equation approach of reference [3]. In the notation of this paper, the 2.…”

Section: In Xmentioning

confidence: 99%

See 2 more Smart Citations

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

McFarland

1984

Journal of Engineering for Gas Turbines and Power

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A rapid technique for solving the blade-to-blade turbomachinery flow problem has been developed. Approximate governing flow equations, which include the effects of compressibility, radius change, rotation, and variable stream sheet thickness are solved using an improved panel method. The development and solution of these equations are described. Sample calculations are presented to illustrate the method’s capabilities and accuracy.

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Inverse design of multiholed internally cooled turbine blades

Kennon

Dulikravich

1986

Numerical Meth Engineering

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SUMMARYA methodology is described for the inverse design and/or analysis of coolant flow passage shapes in multiholed internally cooled turbine blades. The user of this technique may specify the temperature (or heat flux) distribution along the aerofoil outer surface. In addition, the temperature on the surface of each of interior coolant flow passages (holes) may be specified. The numerical solution of the outer hot gas flow field determines the remaining unspecified aerofoil outer surface quantity-surface heat flux if temperature was originally specified or vice versa. The position and shape of each turbine blade coolant hole is then found iteratively by solving the heat conduction problem within the solid portions of the blade. This solution procedure involves satisfying the dual Dirichlet and Neumann specified boundary conditions of temperature and heat flux on the outer boundary of the aerofoil. The inner hole geometry is then modified using an optimization procedure in such a way as to minimize the error in satisfying the specified Dirichlet temperature boundary condition on the surface of each of the evolving interior holes. Results are shown for single-hole and double-hole configurations that have analytic solutions and for a realistic turbine blade design problem.

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Solution of Plane Cascade Flow Using Improved Surface Singularity Methods

Cited by 25 publications

References 1 publication

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

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

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

Inverse design of multiholed internally cooled turbine blades

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