INVESTIGATIONS OF VARIOUS TYPES OF NOZZLES TO DETERMINE THE MOST FEASIBLE CONCEPTS APPLICABLE TO IMPROVED TURBINE NOZZLE PERFORMANCE AT OFF- DESIGN PRESSURE RATIOS FOR PARTIAL ADMISSION IMPULSE TURBINES.

Abstract

Five test nozzle configurations have been selected for design and testing to support the requirements of this contract. All designs are of the converging-diverging supersonic type. Two are of straight conical divergent wall design, one each for a design Mach number of two and of four. The remaining 3 nozzles consist of one each axi-symmetric shock-cancellation type, free expansion type, and a unique plug nozzle. Fabrication of all designs is complete but for the plug design. Testing has begun and preliminary data is herein presented. A literature search was conducted and a summary of reports on hand is presented. Also, a theoretical nozzle performance prediction analysis has been started. No serious problems are foreseen and the program will be completed on schedule.

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Document Details

Document Type
Technical Report
Publication Date
Oct 31, 1966
Accession Number
AD0803559

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Boundary Layer
  • Cancellation
  • Classification
  • Conical Nozzles
  • Contracts
  • Experimental Data
  • Flow Visualization
  • Gas Turbine Nozzles
  • Mach Number
  • Mechanical Engineering
  • Nozzles
  • Plug Nozzles
  • Pressure Distribution
  • Rocket Nozzles
  • Security
  • Two Dimensional

Readers

  • Aerodynamics.
  • Software Engineering
  • Systems Analysis and Design

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow