Investigation of Slot Cooling for High-Speed Aircraft.

Abstract

Active film cooling for gas turbine blades has been investigated. Upstream injection at the leading edge and tangential injection downstream has been used to protect the blade.

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1975
Accession Number
ADA024316

Entities

People

  • Antonio Ferri

Organizations

  • New York University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Cooling
  • Energy Generators
  • Energy Systems
  • Film Cooling
  • Gas Turbine Blades
  • Gas Turbines
  • Generators
  • Leading Edges
  • Mechanical Equipment
  • Rotor Blades (Turbomachinery)
  • Turbine Blades
  • Turbines
  • Turbomachinery

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Space Exploration and Orbital Mechanics.
  • Thermal Physics or Thermal Science.