Gas Turbine Ceramic-Coated-Vane Concept with Convection-Cooled Porous Metal Core.

Abstract

Analysis and flow experiments on a ceramic-coated-porous-metal vane concept indicated the feasibility, from a heat transfer standpoint, of operating in a high-temperature (1644 K; 2500 deg F) gas turbine cascade facility. The heat transfer and pressure drop calculations provided a basis for selecting the ceramic layer thickness (to 2.03 mm; 0.08 in.), which was found to be the dominant factor in the overall heat transfer coefficient. Also an approximate analysis of the heat transfer in the vane trailing edge revealed that with trailing-edge ejection the ceramic thickness could be reduced to 0.254 mm (0.01 in.) in this portion of the vane. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1981
Accession Number
ADA108807

Entities

People

  • Albert F. Kascak
  • Curt H. Liebert
  • Lawrence P. Ludwig
  • Robert F. Handschuh

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Air Temperature
  • Ceramic Coatings
  • Equations
  • Films
  • Flow
  • Gas Turbines
  • Heat Flux
  • Heat Transfer
  • Heat Transfer Coefficients
  • Hot Gases
  • Mass Flow
  • Materials
  • Porous Metals
  • Pressure Transducers
  • Reynolds Number
  • Thermal Conductivity
  • Trailing Edges

Readers

  • Aerodynamics.
  • Fluid Dynamics.
  • Reinforced Composite Materials