Improved Aerothermodynamic Measurements of the T63-A-700 Gas Turbine Engine

Abstract

This thesis contains an analysis of the failure of the instrumentation ring for measuring the combustor exit temperature and total pressure in the T63-A-700 gas turbine engine. An improved ring design has been constructed and installed. Extensions to the exhaust stacks have been installed to keep the cell temperature reasonable. A water-cooled heat exchanger was installed in place of an air-cooled heat exchanger that was not adequately cooling the oil temperature while running the engine. In the program GASTURB, a compressor map with data from the manufacturer was created and an operating line from three separate speeds was plotted.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 2005
Accession Number
ADA439420

Entities

People

  • Kristine B. Garrott

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Compressors
  • Control Knobs
  • Cooling
  • Exhaust Gases
  • Fire Extinguishers
  • Flow Rate
  • Flowmeters
  • Fuel Pumps
  • Gas Turbines
  • Heat Exchangers
  • Measurement
  • Mechanical Engineering
  • Pitot Tubes
  • Pressure Measurement
  • Static Pressure
  • Turbines
  • United States Naval Academy

Readers

  • Aerodynamics.
  • Combustion and Flow Dynamics.