Patent ID: 8448447
Filing Date: 2013-05-28
Classification: F01D,F02C

Abstract:
1. A gas turbine engine, comprising: a compressor section; a combustor section including a combustor; a turbine section; a gaseous fuel supply conduit with an upstream section and a downstream section; a fuel booster located in the gaseous fuel supply conduit, the fuel booster comprising: a heat exchanger, wherein the downstream section is connected to the combustor for delivering a gaseous fuel to the combustor, wherein the driving fluid inlet is in flow connection with a compressed air outlet of the compressor section, from which the driving fluid inlet receives compressor air, such that a driving fluid of the expander includes the compressor air received from the compressor section, wherein the heat exchanger is located between the driving fluid on one side and the gaseous fuel on the other side such that a heat transfer takes place between the driving fluid and the gaseous fuel, wherein the fuel booster is located on a bleed chamber, and wherein the bleed chamber is in flow connection with the compressor flow between a compressor inlet and the compressor air outlet.