Patent ID: 9605593
Date: 2017-03-28
CPC Classifications: F01D,F02C,F23R

Claim:
1. A gas turbine engine comprising: a compressor; a turbine; a combustor disposed between the compressor and the turbine, the combustor having an inner casing, the combustor defining a front chamber, the combustor further defining a bypass chamber in contact with the inner casing; and a pre-swirl nozzle configured to receive a cooling stream from the compressor, and to direct at least a portion of the cooling stream to the turbine, wherein the cooling stream exits the pre-swirl nozzle into a pre-swirl chamber, and a bypass channel extends through the pre-swirl nozzle from the front chamber to the bypass chamber to enable reverse flow from the pre-swirl chamber to the front chamber; wherein the pre-swirl nozzle is flexibly mounted to the combustor inner casing.