Patent Number: 6,305,157

Title: Gas turbine engine

Abstract: A gas turbine engine has a turbine blade flow portion located between a blade inlet edge and outlet edge, and having a compressor to supply a fluid flow comprising a substantial portion of the compressor fluid output along the outside surface of the blade flow portion, thus providing a thermal insulating boundary layer for the turbine blades over which flows heated fluid from the combustor. Heated fluid formed in the combustor flows without further cooling directly to the turbine blades, thereby reducing losses associated with cooling.

Inventors: Rakhmailov; Anatoly (Bataysk, RU)

Assignee: ALM Development, Inc.

International Classification: F04D 27/02 (20060101); F01D 9/00 (20060101); F01D 5/02 (20060101); F01D 9/04 (20060101); F02C 3/00 (20060101); F01D 5/08 (20060101); F01D 5/18 (20060101); F01D 9/02 (20060101); F02C 3/36 (20060101); F02C 7/18 (20060101); F01D 9/06 (20060101); F02C 7/16 (20060101); F02C 007/18 ()

Expiration Date: 10/23/2018