US 12,173,624 B2
Axially offset vane arrays in turbine engine bypass
Jon E. Sobanski, Glastonbury, CT (US); and Neil J. Terwilliger, Cheshire, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on May 19, 2023, as Appl. No. 18/199,742.
Prior Publication US 2024/0384659 A1, Nov. 21, 2024
Int. Cl. F01D 9/06 (2006.01); F02C 7/141 (2006.01); F02K 3/06 (2006.01)
CPC F01D 9/065 (2013.01) [F02C 7/141 (2013.01); F02K 3/06 (2013.01); F05D 2240/12 (2013.01); F05D 2260/213 (2013.01); F05D 2260/606 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A turbine engine, comprising:
a fan section;
a turbine engine core configured to power the fan section, the turbine engine core including a core compressor section, a core combustor section and a core turbine section;
a bypass flowpath fluidly coupled with and downstream of the fan section, the bypass flowpath bypassing the turbine engine core;
a plurality of upstream vanes arranged circumferentially about an axis in an upstream vane array, each of the plurality of upstream vanes extending radially across the bypass flowpath, and a trailing edge of a first of the plurality of upstream vanes extending axially towards the fan section as the trailing edge of the first of the plurality of upstream vanes extends radially outward away from the axis;
a plurality of downstream vanes arranged circumferentially about the axis in a downstream vane array, the plurality of downstream vanes circumferentially interspersed with the plurality of upstream vanes, each of the plurality of downstream vanes extending radially across the bypass flowpath, a first of the plurality of downstream vanes axially offset from the first of the plurality of upstream vanes along the axis, and a trailing edge of the first of the plurality of downstream vanes extending axially towards the fan section as the trailing edge of the first of the plurality of downstream vanes extends radially outward away from the axis;
a first heat exchanger module including an upstream vane internal passage extending through the first of the plurality of upstream vanes;
a second heat exchanger module including a downstream vane internal passage extending through the first of the plurality of downstream vanes; and
a core flowpath extending sequentially through the core compressor section, the core combustor section, the core turbine section and at least one of the upstream vane internal passage or the downstream vane internal passage from an inlet into the core flowpath to an exhaust from the core flowpath.