Operational Characteristics of an Ultra Compact Combustor

Abstract

Ultra Compact Combustors offer unique solutions to minimize engine size and weight. They accomplish this by reducing the number of components in the engine core and perform the combustion in a circumferential cavity that encircles the core flow. Within this cavity, the fuel is injected rich. Burning continues to occur in the vane passage beneath the circumferential cavity which must be completed in a controlled manner prior to the inlet plane of the turbine rotor. Furthermore, the temperature distribution at the exit of the vane passage must be controlled to generate high work extraction from the turbine. The primary metrics for comparison are the exit temperature and pressure profiles, the emissions characteristics, and the overall system losses.

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Document Details

Document Type
Technical Report
Publication Date
Mar 27, 2014
Accession Number
ADA598398

Entities

People

  • Christopher J. Damele

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Boundary Layer
  • Buoyancy
  • Chemical Reactions
  • Combustion
  • Combustion Products
  • Computational Fluid Dynamics
  • Fluid Dynamics
  • Gas Turbines
  • Heat Transfer
  • Jet Engines
  • Mechanical Energy
  • Pressure Distribution
  • Pressure Measurement
  • Turbine Components
  • Turbines

Readers

  • Aerodynamics.
  • Electrical Engineering
  • Rocket Propulsion.