Advancement of Small Gas Turbine Component Technology, Advanced Small Axial Compressor. Volume 1. Analysis and Design

Abstract

A cursory design study of the gas generator involving the preliminary design and analysis of a family of axial compressors was conducted. Each axial compressor was designed to be capable of match with advanced centrifugal technology. The minimum overall axial-centrifugal design pressure ratio for each compressor configuration was 16:1. The engine performance using the characteristics of the compressor designs was evaluated and an optimum gas generator configuration was selected. The axial compressor for the optimum gas generator configuration was detail designed for test rig evaluation. This axial compressor has two stages and a 3.0:1 design pressure ratio. The design flow rate is 5.0 pound-per-second and the inlet tip radius is 2.72 inches.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1969
Accession Number
AD0864281

Entities

People

  • James V. Davis

Tags

Communities of Interest

  • Energy and Power Technologies
  • Human Systems

DTIC Thesaurus Topics

  • Calorific Value
  • Centrifugal Compressors
  • Contracts
  • Department Of Defense
  • Gas Turbines
  • Geometric Forms
  • Geometry
  • Government Procurement
  • High Pressure
  • High Pressure Compressors
  • Mach Number
  • Resonant Frequency
  • Tensile Strength
  • Test And Evaluation
  • Turbine Components
  • Turbines
  • Turboshaft Engines

Fields of Study

  • Engineering
  • Physics

Readers

  • Aerodynamics.
  • Systems Analysis and Design