US 11,988,141 B2
Aircraft
Natalie C Wong, Bristol (GB); Thomas S Binnington, Bristol (GB); David A Jones, Bristol (GB); and Daniel Blacker, Bristol (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE plc, London (GB)
Filed on Oct. 5, 2021, as Appl. No. 17/494,537.
Claims priority of application No. 2016000 (GB), filed on Oct. 9, 2020; and application No. 2101015 (GB), filed on Jan. 26, 2021.
Prior Publication US 2022/0205388 A1, Jun. 30, 2022
Int. Cl. F02C 7/04 (2006.01); F02C 7/18 (2006.01); B64D 27/10 (2006.01); B64D 33/02 (2006.01); B64D 33/04 (2006.01); B64D 33/08 (2006.01); B64D 27/20 (2006.01); B64D 33/10 (2006.01); F02K 3/06 (2006.01); F02K 3/075 (2006.01); F02C 7/08 (2006.01); F02C 7/12 (2006.01); F01D 9/06 (2006.01); F02C 7/14 (2006.01); F02K 3/115 (2006.01)
CPC F02C 7/04 (2013.01) [B64D 27/10 (2013.01); B64D 27/20 (2013.01); B64D 33/02 (2013.01); B64D 33/04 (2013.01); B64D 33/08 (2013.01); B64D 33/10 (2013.01); F01D 9/065 (2013.01); F02C 7/08 (2013.01); F02C 7/12 (2013.01); F02C 7/18 (2013.01); F02K 3/06 (2013.01); F02K 3/075 (2013.01); B64D 2033/024 (2013.01); B64D 2033/0286 (2013.01); F02C 7/14 (2013.01); F02K 3/115 (2013.01); F05D 2220/323 (2013.01); F05D 2220/36 (2013.01); F05D 2260/213 (2013.01)] 9 Claims
OG exemplary drawing
 
1. An aircraft comprising:
a machine body, the machine body enclosing a turbofan gas turbine engine and a plurality of ancillary systems, the turbofan gas turbine engine comprising, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a combustor module, a turbine module, and an exhaust module, wherein
the machine body comprises either one or two fluid inlet apertures, the or each fluid inlet aperture being configured to allow a fluid flow to enter the machine body and to pass through the heat exchanger module, the heat exchanger module being configured to transfer a waste heat load from a first fluid circulating through the gas turbine engine and the ancillary systems to the fluid flow prior to an entry of the fluid flow into the fan assembly, and thence into the compressor module, the turbine module, the combustor module, and the exhaust module, wherein the first fluid is a different type of fluid from the fluid flow,
the heat exchanger module includes a plurality of radially extending vanes extending from a radially outermost inner surface of the heat exchanger module to a position closer to a central axis of the heat exchanger module than to the radially outermost inner surface, and
the turbofan gas turbine engine further comprises a second heat exchanger module positioned separately from the heat exchanger module, the first fluid being routed to the second heat exchanger when a temperature of the first fluid is above a first limit, and the second heat exchanger module being configured to transfer the waste heat load from the first fluid using a second fluid that is different from both the first fluid and the fluid flow.