EFFECT OF BLADE-TIP CROSSOVER PASSAGES ON NATURAL-CONVECTION WATER-COOLING OF GAS-TURBINE BLADES

Abstract

A water-cooled turbine was fabricated and tested to determine the effect of a connecting passage at the turbine rotor blade tip between a radial coolant passage 0.10 inch in diameter (length-diameter ratio = 25.5) and radial coolant passages in the legnth-diameter range of 5.1 to 20.4. Coolant flow through the connecting passage is induced by free-convection forces in the radial passages.

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Document Details

Document Type
Technical Report
Publication Date
Mar 02, 1956
Accession Number
AD0102458

Entities

People

  • Arthur N. Curren
  • Charles F. Zalabak

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Blade Tips
  • Boundary Layer
  • Equations
  • Flow
  • Fluids
  • Gas Flow
  • Gas Turbine Blades
  • Gas Turbines
  • Heat Transfer
  • Heat Transfer Coefficients
  • Heat Transmission
  • Leading Edges
  • Prandtl Number
  • Reynolds Number
  • Surface Temperature
  • Trailing Edges
  • Turbine Blades

Readers

  • Aerodynamics.
  • Combustion and Flow Dynamics.