公开(公告)号：US20170167385A1

公开(公告)日：2017-06-15

申请号：US14963545

申请日：2015-12-09

申请人： United Technologies Corporation

发明人： James D. Hill ,  Steven J. Laporte ,  Wendell V. Twelves, JR. ,  Stephen K. Kramer ,  Simon Pickford

IPC分类号： F02C7/18

CPC分类号： F02C7/141 ,  F05D2260/213 ,  Y02T50/671 ,  Y02T50/676

摘要： A thermal energy exchange system for cooling air of a gas turbine engine includes a heat exchanger located at a diffuser of the gas turbine engine. The diffuser is positioned axially between a compressor and a combustor of the gas turbine engine. A fuel source is operably connected to the heat exchanger to direct a flow of fuel through the heat exchanger via a fuel pipe and toward a fuel nozzle of the combustor. An airflow inlet directs a cooling airflow through the heat exchanger to reduce an airflow temperature via thermal energy exchange between the cooling airflow and the flow of fuel. An airflow outlet directs the cooling airflow from the heat exchanger toward one or more of components of the turbine to cool the one or more components.