Patent ID: 11873758
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 14:
15. An apparatus for a gas turbine engine, comprising:
a compressor section component comprising a wall and a heat exchange passage, the heat exchange passage having a first inlet and a second inlet located on an outer platform of a vane array;
the wall extending axially along and circumferentially about a centerline, the wall radially between the compressor section and the heat exchange passage, the wall at least partially forming a core flowpath and the heat exchange passage, and the core flowpath extending through the compressor section; and the heat exchange passage extending serpentinelly between the first inlet and the second inlet, the heat exchange passage including a first passage segment, a second passage segment and a third passage segment, the second passage segment fluidly coupled between the first passage segment and the third passage segment, the second passage segment axially overlapping the first passage segment and the third passage segment, and the second passage segment circumferentially between the first passage segment and the third passage segment.