Accession Number:

ADA232902

Title:

Viscous Design and Analysis Methods for Transonic Compressor Blading

Descriptive Note:

Final technical rept. 15 May 1989-30 Sep 1990

Corporate Author:

MASSACHUSETTS INST OF TECH CAMBRIDGE DEPT OF AERONAUTICS AND ASTRONAUTICS

Personal Author(s):

Report Date:

1991-02-13

Pagination or Media Count:

170.0

Abstract:

A viscousinviscid computational method for the design and analysis of quasi-3D cascades has been developed. The specific application targeted is supersonic compressor blading with splitter blades, although the method is applicable to any type of cascade. The method is an extension of the ISES viscousinviscid methodology. A streamline-based inviscid Euler formulation is fully coupled to an integral boundary layer formulation to describe the overall viscous flowfield. Rotation and streamtube contraction effects have been incorporated. The method is accurate with regards to loading and loss, and is substantially faster than equivalent Navier-Stokes solvers. Inverse design and optimization capabilities are also implemented giving an effective design analysis system. Existing supersonic splittered cascades were investigated to determine what characteristics are desirable or undesirable in this type of blading. Sensitivity studies indicate that tangential splitter position and splitter loading details have little influence on performance. Substantial improvements are possible if the splitter is moved aft into a tandem-blade arrangement with the main blade. Comparisons between computational results and measured data strongly suggest that traditional supersonic cascade tests involve substantial three-dimensional effects which are not correctable by measured streamtube contraction.

Subject Categories:

  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE