Modified Centrifugal Compressor

Abstract

A single-stage centrifugal compressor designed to produce a 10:1 pressure ratio at a flow rate of 3.2 lb/sec was tested. An earlier version of this compressor was tested under USAAMRDL Contract DAAJ02-70-C-0006 and was found to have excessive losses in the tandem inducer. In addition, diffuser damage was incurred during that testing, which also prevented the achievement of the full design potential. The objective of this follow-on program was therefore to demonstrate improved performance for the 10:1 pressure ratio single-stage centrifugal compressor with a modified inducer and a new (undamaged) diffuser. Modifications to the design of the inducer were made to improve its high-speed (Mach number) performance and to decrease the required inlet prewhirl, and a test program was conducted to obtain overall and inducer performance data.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1974
Accession Number
ADA004002

Entities

People

  • Gary B. Reeves
  • Jeffrey K. Schweitzer

Organizations

  • Pratt & Whitney

Tags

Communities of Interest

  • Air Platforms
  • Human Systems

DTIC Thesaurus Topics

  • Accuracy
  • Aircrafts
  • Compressors
  • Computer Programs
  • Computers
  • Data Reduction
  • Gas Turbines
  • Government Procurement
  • Leading Edges
  • Materials
  • Measurement
  • Pressure Distribution
  • Recording Systems
  • Secondary Flow
  • Standards
  • Test Stands
  • Turbines

Fields of Study

  • Engineering

Readers

  • Aerodynamics.
  • Aerospace Engineering