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EJECTOR BASED EXTERNAL BLEED SYSTEM FOR A GAS TURBINE ENGINE

United States Patent Application

20170074172
A1
View the Complete Application at the US Patent & Trademark Office
A method and system for providing a cooling flow from a compressor to a turbine in a gas turbine engine. First, second and third cooling air flows are provided from the compressor through respective ejectors as external bleed air flows to stages of the turbine. A first ejector combines a first bleed air flow extracted from the compressor with a lower pressure air flow extracted from the compressor to form the first cooling air flow. A second ejector combines a second bleed air flow extracted from the compressor with a secondary portion extracted from the first bleed air flow to form the second cooling air flow. A third ejector combines a third bleed air flow extracted from the compressor with a secondary portion extracted from the second bleed air flow to form the third cooling air flow.
Little, David A. (Mount Dora, FL)
15/ 309,239
May 21, 2014
STATEMENT REGARDING FEDERALLY SPONSORED DEVELOPMENT [0001] Development for this invention was supported in part by Contract No. DE-FC26-05NT42644, awarded by the United States Department of Energy. Accordingly, the United States Government may have certain rights in this invention.