Patent ID: 6098395
Filing Date: 2000-08-08
Classification: F01D,F02C,F05D

Abstract:
In a turbine engine having a multi-stage compressor and a multi-stage turbine, an apparatus for cooling the turbine, comprising:first means for flow communication between a first stage of the compressor and a first stage of the turbine for bleeding pressurized air from the compressor into said first stage of the turbine, wherein said first stage of the compressor is a high pressure, down stream stage of the compressor;second means for flow communication between said first stage of the turbine and a second stage of the compressor for returning a first portion of said pressurized air back to the compressor, wherein said second stage of the compressor is upstream and at a lower pressure than said first stage of the compressor; andthird means for flow communication between said first stage of said turbine and a second stage of said turbine for providing a second portion of said pressurized air to said second stage of said turbine, wherein said second stage of the turbine interacts with a working gas at a lower pressure than said first stage of the turbine.