Gas turbine engine component with integral heat exchanger

An assembly for a gas turbine engine, comprising:

• an inner wall extending circumferentially about an axial centerline of the gas turbine engine and forming an inner peripheral boundary of a core flowpath;
• an outer wall extending circumferentially about the inner wall and forming an outer peripheral boundary of the core flowpath;
• a double vane array, the double vane array including a first vane and a second vane, the first vane extending across the core flowpath between the inner wall and the outer wall, the first vane comprising a first vane passage, the second vane extending across the core flowpath between the inner wall and the outer wall, the second vane comprising a second vane passage, and a leading edge of the second vane axially adjacent a trailing edge of the first vane along the axial centerline;
• a fuel circuit configured to flow fuel sequentially longitudinally through the first vane passage and longitudinally through the second vane passage;
• and
• an inter-passage plenum fluidly coupling the first vane passage to 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.

An assembly for a gas turbine engine, comprising:

• a double vane array including an inner platform, an outer platform and a plurality of vanes, 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 a first of the plurality of vanes axially offset from a second of the plurality of vanes along the axial centerline;
• a heat exchanger integrated with the double vane array, the heat exchanger including a first plenum, a second plenum, and an inter-passage plenum, and a plurality of vane passages fluidly coupled in parallel between the first plenum and the second plenum via the inter-passage plenum, and each of the plurality of vane passages extending radially through a respective one of the plurality of vanes;
• and
• a fuel circuit configured to direct fuel from the first plenum, through the plurality of vane passages, to the second plenum;
• wherein a first vane of the double vane array includes a first vane passage extending along a first straight vane central longitudinal axis, through the outer platform, and through the inner platform;
• wherein a second vane of the double vane array includes a second vane passage extending along a second straight vane central 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.