US 11,946,416 B2
Heat exchanger integration
Lars Ellbrant, Trollhättan (SE); Hans Mårtensson, Trollhättan (SE); Carlos Arroyo, Trollhättan (SE); Fredrik Wallin, Trollhättan (SE); and Mattias Billson, Trollhättan (SE)
Assigned to GKN Aerospace Sweden AB, Trollhättan (SE)
Appl. No. 17/777,647
Filed by GKN Aerospace Sweden AB, Trollhättan (SE)
PCT Filed Nov. 19, 2020, PCT No. PCT/EP2020/082718
§ 371(c)(1), (2) Date May 18, 2022,
PCT Pub. No. WO2021/099482, PCT Pub. Date May 27, 2021.
Claims priority of application No. 1916989 (GB), filed on Nov. 21, 2019.
Prior Publication US 2022/0412260 A1, Dec. 29, 2022
Int. Cl. F01D 9/04 (2006.01); F01D 25/12 (2006.01); F02C 7/12 (2006.01)
CPC F02C 7/12 (2013.01) [F01D 9/04 (2013.01); F01D 25/12 (2013.01); F05D 2220/32 (2013.01); F05D 2240/12 (2013.01); F05D 2260/208 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A front center body (FCB) structure for a geared turbofan engine, comprising:
a central hub and a coaxial shroud spaced from said hub and defining an annular passage between the hub and shroud for communicating air to a compressor; and
a body including a plurality of vanes extending across the passage from the hub to the shroud,
wherein one or more of the vanes form a heat exchanging structure that includes a fluid passage contained within the respective vane and extending between a fluid inlet intersecting the hub proximate a leading edge of the vane and a fluid outlet intersecting with the hub proximate a trailing edge of the vane, and
wherein at least one cavity is provided between inner and outer surfaces of at least one of the vanes to define at least one of the fluid passages.