Accession Number : ADP006203

Title :   The Unsteady Gas Flow through Stator and Rotor of a Turbomachine,

Corporate Author : STUTTGART UNIV (GERMANY F R)

Personal Author(s) : Foerster, K. M.

Report Date : SEP 1987

Pagination or Media Count : 10

Abstract : The difficulties of computing unsteady transonic flow in multiply connected domains with a minimum of neglections and approximations have been overcome by using: individual computational grids fixed to each cascade; a novel grid-less finite difference scheme; and physically real in- and outflow boundaries. The resulting computer program is capable of computing the inviscid, plane gas-flow through stator and rotor of a turbomachine stage made up from arbitrarily shaped (thick, round-nosed) blades of arbitrary spacing, up to local Mach Numbers of 1.8.

Descriptors :   *TURBOMACHINERY, TURBINE COMPONENTS, GAS FLOW, ROTOR BLADES, TRANSONIC FLOW, GRIDS, COMPUTER PROGRAMS, BOUNDARIES, COMPUTATIONS, GAS FLOW, GRIDS, MACH NUMBER, STATORS, TRANSONIC FLOW, TURBOMACHINERY, UNSTEADY FLOW.

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE