Scaling Gas Turbine Film Cooling Adiabatic Effectiveness Through Simultaneous Matching of Momentum Flux Ratio and Advective Capacity Ratio

Abstract

The study of gas turbine engine performance improvement requires extracting usable work from the hot section turbine. To prevent heat damage to turbine blades, film cooling is employed. Low temperature tests are conducted at ambient pressure on scale models to analyze the effects of gas flow parameters on scaling adiabatic effectiveness at easily repeatable conditions. This research aims to determine how matching coolant flow rate parameters Momentum Flux Ratio (I) and Advective Capacity Ratio (ACR) can scale adiabatic effectiveness on flat plate and leading edge geometries between air and carbon dioxide gas. Results indicate improvement in scaling adiabatic effectiveness when both I and ACR are matched.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 2021
Accession Number
AD1139791

Entities

People

  • Evan C. Glowiak

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Carbon Dioxide
  • Computational Fluid Dynamics
  • Flow Rate
  • Fluid Dynamics
  • Fluid Flow
  • Gas Flow
  • Gas Turbines
  • Geometry
  • Heat Transfer
  • Leading Edges
  • Pressure Distribution
  • Turbine Blades
  • Turbine Components
  • Turbines
  • Turbomachinery

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Systems Analysis and Design