Accession Number:

AD0815963

Title:

INVESTIGATION OF THE SUPERSONIC THROUGH-FLOW COMPRESSOR CONCEPT. VOLUME II. ANALYTICAL AND EXPERIMENTAL INVESTIGATIONS OF SUPERSONIC CASCADES AND DIFFUSERS.

Descriptive Note:

Final rept. 15 Nov 65-15 Feb 67,

Corporate Author:

UNITED AIRCRAFT CORP EAST HARTFORD CONN RESEARCH LABS

Report Date:

1967-06-01

Pagination or Media Count:

144.0

Abstract:

An analytical and experimental investigation of supersonic cascades and supersonic diffusers having entrance conditions representative of the flow discharging from a supersonic through-flow compressor was conducted. The performance of these cascades was predicted over a range of operating conditions using a one-dimensional analysis which included shock and friction losses. Cascade configurations designed to provide up to 65 deg of total turning were tested at supersonic approach Mach numbers over a range of incidence angles. The experimental results were in general agreement with the theoretical performance predicted by the one-dimensional analysis. The test results indicate that rotor efficiencies on the order of 80 percent can be obtained with a supersonic through-flow compressor. A theoretical analysis of the supersonic diffuser was conducted to evaluate the effects of diffuser geometry, bleed flow ratio, and entrance Mach number on the diffuser pressure recovery. Tests of an annular diffuser model ingesting supersonic flows with various amounts of wakes, swirl and boundary layer were conducted. The experimental results showed these flows can be diffused with a process efficiency greater than 90 percent. Author

Subject Categories:

  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE