The Variation in Airflow Coefficient for Allison T56 Combustor Liners

Abstract

It is shown that it is possible to have a circumferential turbine inlet temperature variation in excess of 90 C in a correctly assembled T56 Series III engine. A significant part of this variation is due to differences in airflow into the liner caused by the variations in airflow area associated with manufacturing tolerances. A simple technique is described that will enable matched sets of liners to be selected to build engines and thus avoid excessive temperature maldistributions. Preliminary experimental results are described. Keywords: Turboprop engines; Combustion chamber liners; Temperature distribution; Allison T56 engine, Australia.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1987
Accession Number
ADA201072

Entities

People

  • F. W. Skidmore
  • W. H. Schofield

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Airspeed Indicators
  • Civil Engineering
  • Combustion
  • Combustion Chambers
  • Combustors
  • Department Of Defense
  • Engineering
  • Engineers
  • Engines
  • Flow
  • Gas Turbines
  • Mass Flow
  • Mechanical Engineering
  • Test Equipment
  • Turbines
  • Turboprop Engines

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  • Aerodynamics.
  • Combustion and Flow Dynamics.
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