Turbine Engine Cooled Air Supply
AssigneeRtx Corporation
InventorNicholas Alexander CHAHINE
Life of this patent
Estimating the term…
Abstract
An aircraft has a gas turbine engine. A first fuel flowpath passes from a fuel source to a combustor. An air-air heat exchanger has a heat donor leg along a bleed flowpath and a heat recipient leg along a bypass flowpath. An air-fuel heat exchanger has a heat donor leg along the bleed flowpath downstream of the air-air heat exchanger. A second fuel flowpath passes from the fuel source through the air-fuel heat exchanger and includes a heat recipient leg of the air-fuel heat exchanger and at least partially non-overlapping the first fuel flowpath. One or more third fuel flowpaths pass from the fuel source through fuel-driven actuators. The second fuel flow path and the one or more third fuel flowpaths return to the fuel source or the first fuel flowpath;
Claims20
An aircraft comprising:
- a fuel source;
- a gas turbine engine having:
- a compressor;
- a combustor;
- a turbine;
- a core flowpath sequentially through the compressor, combustor, and turbine;
- and
- a bypass flowpath;
- a bleed flowpath from the core flowpath to a load;
- a first fuel flowpath from the fuel source to the combustor;
- an air-air heat exchanger having a heat donor leg along the bleed flowpath and a heat recipient leg along the bypass flowpath;
- an air-fuel heat exchanger having a heat donor leg along the bleed flowpath downstream of the air-air heat exchanger;
- a second fuel flowpath from the fuel source through the air-fuel heat exchanger and including a heat recipient leg of the air-fuel heat exchanger and at least partially non-overlapping the first fuel flowpath;
- fuel-driven actuators;
- and
- one or more third fuel flowpaths from the fuel source through the fuel-driven actuators, wherein:
- the second fuel flow path and the one or more third fuel flowpaths return to the fuel source or the first fuel flowpath.
A gas turbine engine comprising:
- a compressor;
- a combustor;
- a turbine;
- a core flowpath sequentially through the compressor, combustor, and turbine;
- a bypass flowpath;
- a bleed flowpath from the core flowpath to a load;
- a first fuel flowpath to the combustor;
- an air-air heat exchanger having a heat donor leg along the bleed flowpath and a heat recipient leg along the bypass flowpath;
- an air-fuel heat exchanger having a heat donor leg along the bleed flowpath downstream of the air-air heat exchanger;
- a second fuel flowpath through the air-fuel heat exchanger and including a heat recipient leg of the air-fuel heat exchanger and at least partially non-overlapping the first fuel flowpath;
- fuel-driven actuators;
- and
- one or more third fuel flowpaths through the fuel-driven actuators, wherein:
- the second fuel flow path and the one or more third fuel flowpaths return to the first fuel flowpath.
Dependencies are inferred from the claim text.