Skip to Content
Find More Like This
Return to Search

High pressure compressor diffuser for an industrial gas turbine engine

United States Patent Application

20170022834
A1
View the Complete Application at the US Patent & Trademark Office
A gas turbine engine with an air cooled turbine part in which spent cooling air for the turbine part is discharged into the combustor instead of into the hot gas stream of the turbine in order to increase efficiency of the engine. Turbine rotor blades and stator vanes are cooled. The spent cooling air is passed into a diffuser located between the HPC outlet and the combustor inlet where the spent cooling air is discharged along the inner and outer endwalls of the diffuser in directions substantially parallel to the inner and outer diffuser endwalls and at a greater velocity in order to energize the diffuser endwall boundary layers so that they can sustain higher diffusion rates and levels.
Orosa, John A. (Palm Beach Gardens, FL)
15/ 146,036
May 4, 2016
GOVERNMENT LICENSE RIGHTS [0002] This invention was made with Government support under contract number DE-FE0023975 awarded by Department of Energy. The Government has certain rights in the invention.