Accession Number:

ADP006203

Title:

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

Descriptive Note:

Corporate Author:

STUTTGART UNIV (GERMANY F R)

Personal Author(s):

Report Date:

1987-09-01

Pagination or Media Count:

10.0

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.

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE