US 12,454,913 B2
Gas turbine engine component with integral heat exchanger
Eric S. Durocher, Boucherville (CA)
Assigned to Pratt & Whitney Canada Corp., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Oct. 28, 2022, as Appl. No. 17/976,413.
Prior Publication US 2024/0141836 A1, May 2, 2024
Int. Cl. F02C 7/00 (2006.01); F02C 3/04 (2006.01); F02C 7/22 (2006.01); F23R 3/28 (2006.01); F28D 7/16 (2006.01); F28D 21/00 (2006.01)
CPC F02C 7/22 (2013.01) [F02C 3/04 (2013.01); F23R 3/28 (2013.01); F28D 7/1669 (2013.01); F28D 2021/0026 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An assembly for a gas turbine engine, comprising:
a bladed rotor;
a double vane array including an inner platform, an outer platform and a plurality of vanes, the plurality of vanes including a first vane and a second vane, the inner platform extending circumferentially about an axial centerline of the gas turbine engine and forming an inner peripheral boundary of a core flowpath through the double vane array, the outer platform extending circumferentially about the axial centerline and forming an outer peripheral boundary of the core flowpath through the double vane array, the plurality of vanes extending across the core flowpath between the inner platform and the outer platform, and the plurality of vanes arranged downstream of a stage of the bladed rotor along the core flowpath; and
a heat exchanger integrated with the double vane array, the heat exchanger including a first vane passage and a second vane passage fluidly coupled with and downstream of the first vane passage, the first vane passage extending radially through the first vane, and the second vane passage extending radially through the second vane, wherein the heat exchanger further includes an inter-passage plenum formed by the inner platform, and wherein the inter-passage plenum fluidly couples the first vane passage to the second vane passage;
a fuel circuit configured to flow fuel sequentially through the first vane passage and the second vane passage;
wherein the first vane passage extends along a first straight vane passage central longitudinal axis, through the outer platform, and through the inner platform;
wherein the second vane passage extends along a second straight vane passage longitudinal axis, through the outer platform, and through the inner platform;
wherein the first straight vane passage central longitudinal axis forms a first acute angle with the axial centerline of the gas turbine engine;
wherein the second straight vane passage central longitudinal axis forms a second acute angle with the axial centerline of the gas turbine engine; and
wherein the first acute angle is different than the second acute angle.