Cooling of Gas Turbines. 1 - Effects of Admission of Fins to Blade Tips and Rotor, Admission of Cooling Air Through Part of Nozzles and Change in Thermal Conductivity of Turbine Components

Abstract

Analysis was made for calculating the approximate radial temperature distribution in components of a turbosupercharger bucket wheel. Gas temperatures at nozzle box are used in calculations ranging from 1600 degree to 2000 deg F. Only temperatures of the gas, cooling air, and surface heat-transfer coefficients were known. Results show that indirect cooling of turbine blades will not permit large increases in effective gas temperature. With low conductivity materials, some method of direct cooling other than partial admission of cooling air is essential.

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Document Details

Document Type
Technical Report
Publication Date
Feb 11, 1947
Accession Number
ADB814159

Entities

People

  • Byron W. Brown

Organizations

  • Glenn Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautics
  • Air Temperature
  • Blade Tips
  • Coefficients
  • Conductivity
  • Exhaust Gases
  • Gas Turbines
  • Gases
  • Heat Transfer
  • Heat Transfer Coefficients
  • Heat Transmission
  • Hot Spots
  • Materials
  • Thermal Conductivity
  • Turbine Blades
  • Turbine Components
  • Turbosuperchargers

Fields of Study

  • Engineering

Readers

  • Aerodynamics.
  • Combustion and Flow Dynamics.