Closure to “Discussion of ‘Computation of Supercritical Compressor and Turbine Cascades with a Design Method for Transonic Flows’” (1981, ASME J. Eng. Power, 103, p. 604)

1981 ◽  
Vol 103 (3) ◽  
pp. 604-604
Author(s):  
E. Schmidt
Keyword(s):  
Design Method ◽  
Transonic Flows ◽  
Turbine Cascades

Computation of Supercritical Compressor and Turbine Cascades with a Design Method for Transonic Flows

1980 ◽  
Vol 102 (1) ◽  
pp. 68-74 ◽  
Author(s):  
E. Schmidt
Keyword(s):  
Design Method ◽  
Density Ratio ◽  
Full Potential ◽  
Transonic Flows ◽  
Potential Equation ◽  
Contour Shape ◽  
Cascade Arrangement ◽  
Turbine Cascades ◽  
Transonic Region ◽  
Experimental Comparisons

The development of supercritical cascades follows experience with supercritical single profiles. In cascade arrangement strong inter-blade influences exist in the transonic region, so that a desired pressure distribution, starting from the contour shape, is not easy to realize. For these cases, a design method has been developed in which the boundary conditions can be prescribed in a simple and clear manner. Thickness and deflection are not restricted, since the full potential equation is treated. Variation of the axial velocity density ratio is provided for. The solution by relaxation leads to short computing times. Experimental comparisons for turbine and compressor cascades show the applicability of the method.

A Design Method and the Performance of Two-Dimensional Turbine Cascades for High Subsonic Flow

1971 ◽  
Author(s):  
A. Uenishi
Keyword(s):  
Approximate Solution ◽  
Pressure Distribution ◽  
Subsonic Flow ◽  
Design Method ◽  
Two Dimensional ◽  
Hodograph Method ◽  
Numerical Examples ◽  
Turbine Cascades ◽  
Measured Pressure ◽  
High Subsonic Flow

This paper deals with a hodograph method for design of turbine cascades in high subsonic flow and an approximate solution to a gas, specific heat ratio γ = −1 (the Karman-Tsien approximation) and γ > 1 (the gas obeying the adiabatic law). Numerical examples and a comparison of theoretical and measured pressure distribution for profiles designed by this method are given. Further, a better criterion for design to improve cascade efficiency is also presented.

Application of a Fast Pseudo-Unsteady Method to Steady Transonic Flows in Turbine Cascades

1982 ◽  
Vol 104 (2) ◽  
pp. 420-428 ◽  
Author(s):  
J. A. Essers ◽  
F. Kafyeke
Keyword(s):  
Finite Volume ◽  
Turbine Blades ◽  
Time Dependent ◽  
Finite Volume Scheme ◽  
Numerical Techniques ◽  
Transonic Flows ◽  
Kutta Condition ◽  
Volume Scheme ◽  
Comparable Accuracy ◽  
Turbine Cascades

New very fast artificial time-dependent techniques for isentropic inviscid steady transonic flows are applied to turbine cascades. An explicit dissipative finite volume scheme with splitting of the space operators is used. The efficiency of the new technique is tested for turbine blades with a relatively thick rounded supersonic trailing edge, and is compared with that of other classical methods. Different models used to apply the Kutta condition and to predict the base pressure accounting for the separation occuring in that region are fully described and tested. For a comparable accuracy, the new method is found to be faster than most of the classical numerical techniques generally applied to similar problems.

scholarly journals A Numerical Technique for the Calculation of Transonic Flows in Turbomachinery Cascades

1971 ◽  
Author(s):  
S. Gopalakrishnan ◽  
R. Bozzola
Keyword(s):  
Exact Solution ◽  
Analytical Solutions ◽  
Numerical Technique ◽  
Time Dependent ◽  
Experimental Result ◽  
Transonic Flows ◽  
Physical Problems ◽  
Dependent Form ◽  
Turbine Cascades ◽  
Turbomachinery Cascades

A numerical technique is presented for the calculation of steady inviscid transonic flows in turbomachinery cascades, wherein both subsonic and supersonic regions co-exist. The problem is posed in the time-dependent form and the aysmptotic solution at large times provides the solution of the steady physical problems. The solutions for a hyperbolic nozzle cascade and two turbine cascades are compared with other analytical solutions and with an experimental result. The agreement appears to be very good. Some preliminary results are presented for a flow containing an oblique shock and its reflection. The computed results compare satisfactorily with the exact solution.

Transonic Flows of BZT Fluids Through Turbine Cascades

2006 ◽  
pp. 227-232
Author(s):  
P. Cinnella ◽  
P. M. Congedo ◽  
D. Laforgia
Keyword(s):  
Transonic Flows ◽  
Turbine Cascades ◽  
Bzt Fluids

Numerical investigation of some special features of transonic flows in plane turbine cascades

1977 ◽  
Vol 11 (2) ◽  
pp. 293-299 ◽  
Author(s):  
A. B. Bogod ◽  
A. V. Granovskii ◽  
M. Ya. Ivanov
Keyword(s):  
Numerical Investigation ◽  
Transonic Flows ◽  
Turbine Cascades
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