Accession Number:

AD0855019

Title:

Radial Outflow Compressor Component Development. Volume 1, Phase 1. Aerodynamic and Mechanical Design Analysis and Diffuser Tests

Descriptive Note:

Technical rept.

Corporate Author:

GENERAL ELECTRIC CO CINCINNATI OH FLIGHT PROPULSION DIV

Personal Author(s):

Report Date:

1969-05-01

Pagination or Media Count:

417.0

Abstract:

This phase consisted of compressor component analyses and investigations conducted using an existing low-speed compressor model and a transonic cascade tunnel. Aerodynamic information for the design of the high- speed radial outflow supersonic compressor to be investigated in Phase II was obtained. A stress analysis and bench tests of several possible rotor designs were conducted as well as an investigation of methods of fabricating and joining blades, rotating shroud, and discs. Target performance values are 111 pressure ratio with 81 adiabatic efficiency at 4.5 lbsec airflow.

Subject Categories:

  • Hydraulic and Pneumatic Equipment
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE