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Low pressure compressor diffuser and cooling flow bleed for an industrial gas turbine engine

United States Patent Application

20170022905
A1
View the Complete Application at the US Patent & Trademark Office
An industrial gas turbine engine with a high spool and a low spool in which low pressure compressed air is supplied to the high pressure compressor, and where a portion of the low pressure compressed air is bled off for use as cooling air for hot parts in the high pressure turbine of the engine. Annular bleed off channels are located in the LPC diffuser. The bleed channels bleed off around 15% of the core flow and pass the bleed off air into a cooling flow channel that then flows into the cooling circuits in the turbine hot parts.
Orosa, John A. (Palm Beach Gardens, FL), Brostmeyer, Joseph D. (Jupiter, FL), Cejka, Justin T. (Palm Beach Gardens, FL), Jones, Russell B. (North Palm Beach, FL)
15/ 137,280
April 25, 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.