Patent ID: 8459040

Claim:
A gas turbine engine comprising: a compressor; a heat exchanger, wherein a first fluid flows through a first flow path and exchanges heat with a second fluid that flows through a second flow path to cool the second fluid; the first flow path, wherein the first fluid in the first flow path flows from an early stage of the compressor, through the heat exchanger, and to a turbine, wherein the heat exchanger includes a plurality of pipes through which the first fluid flows that each extend in a radial direction, and each of the plurality of pipes are bent to extend in an axial direction; and the second flow path, wherein the second fluid in the second flow path flows from a location downstream of the compressor, through the heat exchanger, and to a portion of the compressor located between the early stage of the compressor and the location downstream of the compressor to cool the portion of the compressor.