Numerical design of transonic cascades

Journal Article · Sun Oct 01 00:00:00 EDT 1978 · J. Comput. Phys.; (United States)

DOI:https://doi.org/10.1016/0021-9991(78)90106-7· OSTI ID:6773591

Korn, D G

The method developed by Bauer, Garabedian, and Korn (''Supercritical wing Sections,'' Springer-Verlag, Berlin, 1975) for the design of wing sections that exhibit shock-free flow at high subsonic speeds has been applied to the problem of cascade design. A cascade is a periodic distribution of two-dimensional blade cross sections that serves as a basis for the design of axial flow compressors and turbines. Those aspects of the design procedure that are used for both airfoil and cascade design are reviewed briefly in this paper. Emphasis has been placed on the difference between airfoil and cascade design. In particular, the form of the singular solution in the hodograph plane is different in the two cases.

• Research Organization: Bell Laboratories, Crawfords Corner Road, Holmdel, New Jersey 07733
• OSTI ID: 6773591
• Journal Information: J. Comput. Phys.; (United States), Journal Name: J. Comput. Phys.; (United States) Vol. 29:1; ISSN JCTPA
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
420100 -- Engineering-- General Engineering-- (-1987)
640410* -- Fluid Physics-- General Fluid Dynamics
75 CONDENSED MATTER PHYSICS
SUPERCONDUCTIVITY AND SUPERFLUIDITY
AIRFOILS
COMPRESSOR BLADES
DESIGN
DIFFERENTIAL EQUATIONS
EQUATIONS
EQUATIONS OF MOTION
FINITE DIFFERENCE METHOD
FLUID FLOW
IDEAL FLOW
ITERATIVE METHODS
NUMERICAL SOLUTION
TRANSONIC FLOW
TURBINE BLADES
TWO-DIMENSIONAL CALCULATIONS