Accession Number : ADD011662

Title :   Strutless Diffuser for Gas Turbine Engine.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s) : Duncan,G H ,III ; Cooper,D L

Report Date : 12 Mar 1985

Pagination or Media Count : 5

Abstract : This patent discloses an improved diffuser for a gas turbine engine which is mounted between a compressor section and a burner section. The diffuser eliminates struts by using the exit guide vanes of the compressor for support. The vanes are fixedly mounted to an inner case wall and to a double outer wall. A cantilevered case wall being one of the double outer walls can flex both radially and axially to relieve thermal stress in the vanes. Additionally, probes can be mounted in access ports formed in the double outer wall. Compressor leakage gas is prevented from entering voids in the double outer wall by a seal seated between the cantilevered case wall and the other case wall.

Descriptors :   *PATENTS, *GAS TURBINES, *COMPRESSORS, *DIFFUSERS, GUIDE VANES, WALLS, THERMAL STRESSES, REDUCTION, LEAKAGE(FLUID), SEALS(STOPPERS)

Subject Categories : Hydraulic and Pneumatic Equipment
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE