Variable Inlet Vane Assembly for a Gas Turbine Combustor.

Abstract

This report describes a variable inlet vane assembly for use within the inlet area of a combustor, the vane assembly having a plurality of rotatable vanes situated within an annular-shaped opening in the inlet area of the combustor. Each vane is operated by the rotation of a crank assembly and actuator. The actuator meshes with the crank assembly through a sliding interface in order to accommodate axial and/or radial growth of the combustor with no loss in the precision of the control of air entering the combustor during rotation of the vanes. Such an arrangement substantially enhances the relight capability of the combustor.(Author)

Document Details

Document Type
Technical Report
Publication Date
Feb 19, 1982
Accession Number
ADD009408

Entities

People

  • Charles Marshall

Organizations

  • United States Department of the Air Force

Tags

DTIC Thesaurus Topics

  • Actuators
  • Assembly
  • Combustors
  • Engines
  • Gas Turbines
  • Heat Engines
  • Heat Transfer Devices
  • Internal Combustion Engines
  • Mechanical Equipment
  • Precision
  • Rotation
  • Turbines

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Electrical Engineering
  • Internal Combustion Engine (ICE) Technology.