Thermal Response Turbine Shroud.

Abstract

The Thermal Response Turbine Shroud program studied and evaluated overall engine active clearance control designs and payoffs for a broad range of engine/aircraft combinations. Both turbine and compressor active clearance control systems were considered for gas turbine engines that encompassed high and low fan bypass ratios, single and two stage turbines, and commercial and military missions. The study of active clearance control included detailed material, heat transfer and thermal and mechanical growth analyses. The study effort looked at the active control of clearance at transient as well as steady state engine operation. The evaluation included an overall assessment of active clearance control benefits and penalties in both performance and cost for the particular aircraft/engine system studied. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1979
Accession Number
ADA082754

Entities

People

  • C. H. Gay

Organizations

  • General Electric

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Actuators
  • Air Force
  • Air Supplies
  • Airborne Warning And Control System
  • Aircrafts
  • Compressors
  • Computer Programs
  • Control Systems
  • Costs
  • Detectors
  • Engine Components
  • Failure Mode And Effect Analysis
  • Gas Turbines
  • Heat Exchangers
  • Heat Transfer
  • High Pressure
  • Turbines

Fields of Study

  • Engineering

Readers

  • Aerospace Engineering
  • Combustion and Flow Dynamics.
  • Military Mobilization and Reserve Forces Studies.