US 12,031,488 B2
Combustion engine including turbomachine
Kevin P. Hallisey, Ave Maria, FL (US); and Dominique Patrick Sautron, Chicago, IL (US)
Assigned to GE Aviation Systems LLC, Grand Rapids, MI (US)
Filed by GE Aviation Systems LLC, Grand Rapids, MI (US)
Filed on Mar. 24, 2023, as Appl. No. 18/189,670.
Application 18/189,670 is a continuation of application No. 17/362,124, filed on Jun. 29, 2021, granted, now 11,619,177.
Application 17/362,124 is a continuation of application No. 17/091,156, filed on Nov. 6, 2020, granted, now 11,486,315, issued on Nov. 1, 2022.
Prior Publication US 2023/0250764 A1, Aug. 10, 2023
Int. Cl. F02C 9/18 (2006.01); B64D 13/06 (2006.01); B64D 27/10 (2006.01); B64D 29/00 (2006.01); F04D 27/02 (2006.01)
CPC F02C 9/18 (2013.01) [B64D 13/06 (2013.01); B64D 27/10 (2013.01); B64D 29/00 (2013.01); F04D 27/0207 (2013.01); B64D 2013/0618 (2013.01); F05D 2260/606 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A combustion engine comprising:
at least one combustion chamber including a combustion gas;
a first bleed air supply fluidly coupled to a first fluid from a portion of the combustion engine that is upstream of the combustion chamber;
a second bleed air supply fluidly coupled to a second fluid from a portion of the combustion engine that is downstream of the combustion chamber, the second fluid including at least a portion of the combustion gas;
a first thermal bus including a first thermal source and a thermal dump provided downstream of the first thermal source, the first thermal bus including a first heat transfer fluid, the first thermal bus being fluidly coupled to a system external the combustion engine;
a second thermal bus, separate from the first thermal bus, including a second thermal source and a thermal bus exhaust fluidly coupled with and provided downstream of the second thermal source, the second thermal bus being fluidly coupled to a second heat transfer fluid, separate from the first heat transfer fluid; and
a turbomachine comprising;
a compressor fluidly coupled to the first bleed air supply, the first fluid at least partially defining a working fluid within the compressor, the compressor coupled to a portion of the first thermal bus such that the compressor pumps the first heat transfer fluid through the first thermal bus, the first heat transfer fluid being separate from the working fluid; and
a turbine fluidly coupled to both of the second bleed air supply and the second thermal bus, with the second heat transfer fluid being at least a portion of the second fluid that flows through the turbine.