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US 12,655,792 B2Granted
Combustion engine including turbomachine
AssigneeGE Aviation Systems LLC
InventorsKevin P. Hallisey, Dominique Patrick Sautron
Life of this patent
Estimating the term…
Abstract
A combustion engine including at least one combustion chamber, a first bleed air supply fluidly coupled to a portion of the combustion engine upstream the combustion chamber, a second bleed air supply fluidly coupled to a portion of the combustion engine downstream the combustion chamber, and a turbomachine comprising a first compressor, a second compressor, and a first turbine mounted to a common shaft, with the first and second compressors in serial flow arrangement. The turbomachine, further comprising an intercooler serially fluidly coupling a portion of the first compressor to a portion of the second compressor.
Claims17
A combustion engine comprising:
- a combustion chamber;
- a first bleed air supply selectively fluidly coupled to a portion of the combustion engine upstream of the combustion chamber, via a first controllable valve;
- a second bleed air supply selectively fluidly coupled to a portion of the combustion engine downstream of the combustion chamber, via both a second controllable valve and a check valve along the second bleed air supply downstream from the second controllable valve;
- a third bleed air supply selectively fluidly coupled to a portion of the combustion engine downstream of the combustion chamber, via a third controllable valve;
- and
- a turbomachine comprising:
- a first compressor, a second compressor, and a first turbine mounted to a common shaft with the first and second compressors in serial flow arrangement, with the first compressor fluidly coupled to the first bleed air supply, and
- an intercooler serially fluidly coupling a portion of the first compressor to a portion of the second compressor;
- wherein the third bleed air supply and the second bleed air supply meet at a junction downstream of the second controllable valve and the third controllable valve, the junction being fluidly coupled to the first turbine;
- wherein the first bleed air supply is fluidly coupled to the junction via a fluid path;
- wherein the check valve is disposed along the second bleed air supply upstream from the junction and is biased such that fluid within the second bleed air supply can flow through the check valve, but fluid downstream the check valve cannot flow past the check valve and into the second bleed air supply;
- and wherein the third bleed air supply includes a branch with a first leg and a second leg, separate from the first leg, with the first leg being selectively fluidly coupled to the junction.
9 more elements
A combustion engine comprising:
- a combustion chamber;
- a subsystem;
- an upstream bleed air supply fluidly coupled to a first fluid flow from a portion of the combustion engine that is upstream of the combustion chamber;
- a first downstream bleed air supply fluidly coupled to a second fluid flow from a portion of the combustion engine that is downstream of the combustion chamber and selectively fluidly coupled to the subsystem;
- a second downstream bleed air supply fluidly coupled to a third fluid flow from a portion of the combustion engine that is downstream of the combustion chamber and selectively fluidly coupled to the subsystem;
- a turbomachine selectively fluidly coupled to a system external to the combustion engine and separate from the subsystem, the turbomachine comprising:
- a first compressor that is selectively fluidly coupled to the first fluid flow from the upstream bleed air supply;
- and
- a first turbine that is selectively fluidly coupled to at least the second fluid flow from the first downstream bleed air supply and the third fluid flow from the second downstream bleed air supply, with the first turbine being mounted to a common shaft with the first compressor in serial flow arrangement;
- a first controllable valve selectively fluidly coupling the upstream bleed air supply to the turbomachine;
- a second controllable valve selectively fluidly coupling the first downstream bleed air supply to the first turbine;
- a third controllable valve selectively fluidly coupling the second downstream bleed air supply to the first turbine, the third fluid flow and the second fluid flow meeting at a junction downstream of the second controllable valve and the third controllable valve;
- and
- a check valve fluidly coupling the first downstream bleed air supply to the junction between the second controllable valve and the junction, the check valve being biased such that fluid within the first downstream bleed air supply can flow through the check valve, but fluid downstream the check valve cannot flow past the check valve and into the first downstream bleed air supply.
11 more elements
An aircraft comprising:
- a gas turbine engine having a fan section, compressor section, combustion section, and turbine section in serial flow arrangement;
- an Environmental Control System (ECS);
- a first bleed air supply fluidly coupled, via a first controllable valve, to a first fluid flow from a portion of the gas turbine engine that is upstream of the combustion section;
- a second bleed air supply fluidly coupled, via a second controllable valve and a check valve, to a second fluid flow from a portion of the gas turbine engine that is downstream of the combustion section;
- a third bleed air supply fluidly coupled, via a third controllable valve, to a third fluid flow from a portion of the gas turbine engine that is downstream of the combustion section, the second bleed air supply and the third bleed air supply meeting at a junction that is downstream of both the second controllable valve and the third controllable valve;
- and
- a turbomachine comprising:
- a first compressor that is selectively fluidly coupled to the first fluid flow from the first bleed air supply;
- and
- a first turbine that is selectively fluidly coupled to at least the second fluid flow from the second bleed air supply and the third fluid flow from the third bleed air supply, with the first turbine being mounted to a common shaft with the first compressor;
- wherein the first fluid flow, the second fluid flow, and the third fluid flow are selectively fluidly coupled to the ECS via the first compressor and the first turbine, respectively, wherein the check valve is disposed downstream of the second controllable valve and upstream of the junction on the second bleed air supply, the check valve being biased such that fluid within the second bleed air supply can flow through the check valve, but fluid downstream the check valve cannot flow past the check valve and into the second bleed air supply.
8 more elements
Dependencies are inferred from the claim text.