US 2010/0058768 A1 · AXIAL DIFFUSOR FOR A TURBINE ENGINE

Abstract

A turbine engine having a plenum for passing fluids from an outlet of a compressor to an inlet of a combustor that may increase the efficiency of the turbine engine. The turbine engine may include a combustor, a compressor positioned upstream of the combustor, a transition channel extending from the compressor to the combustor, and a shell extending between the compressor and a combustor portal and positioned around the at least one transition channel. The turbine engine may also include an axial diffusor in the shell near the at least one transition channel, wherein the axial diffusor may include a fluid flow recess in a trailing edge of the axial diffusor. The turbine engine may also include a wave protrusion extending from a surface positioned radially inward of the axial diffusor. The fluid flow recess and the wave protrusion may reduce fluid flow loss within the shell.

Claims20

Dependent claims

A turbine engine, comprising:

a combustor;
a compressor positioned upstream of the combustor;
at least one transition channel forming at least a portion of a plenum between the compressor and the combustor;
a shell forming at least a portion of the plenum between the compressor and a combustor portal of the combustor and positioned around the at least one transition channel;
an axial diffusor protruding from a downstream wall of the shell toward the at least one transition channel;
and
wherein the axial diffusor includes a fluid flow recess in a trailing edge of the axial diffusor.

4 more elements

Dependencies are inferred from the claim text.

Axial diffusor for a turbine engine

Life of this patent

Axial diffusor for a turbine engine

Life of this patent

Abstract

Claims20