Aircraft system with heat exchanger for environmental control system
An aircraft system includes an environmental control system and a propulsion system. The propulsion system includes a compressor section, a combustor section, a turbine section, a bypass flowpath, an air circuit, a working fluid system and a heat exchanger. The bypass flowpath bypasses the compressor section, the combustor section and the turbine section. The air circuit includes a circuit inlet fluidly coupled to the bypass flowpath. The air circuit is configured to direct air received from the bypass flowpath through the circuit inlet to the environmental control system. The working fluid system includes a fluid circuit. The working fluid system is configured to service one or more components of the propulsion system using a liquid working fluid directed through the fluid circuit. The heat exchanger is configured to transfer heat energy between the air in the air circuit and the liquid working fluid in the fluid circuit.
1 . A system for an aircraft, comprising:
an environmental control system; and
a propulsion system including an inner housing structure, an outer housing structure, a compressor section, a combustor section, a turbine section, a bypass flowpath, an air circuit, a working fluid system and a heat exchanger;
the inner housing structure housing the compressor section, the combustor section and the turbine section, the inner housing structure forming an inner peripheral boundary of the bypass flowpath;
the outer housing structure spaced radially outboard of the inner housing structure, the outer housing structure forming an outer peripheral boundary of the bypass flowpath;
the bypass flowpath bypassing the compressor section, the combustor section and the turbine section;
the air circuit comprising a circuit inlet fluidly coupled to the bypass flowpath, and the air circuit configured to direct air received from the bypass flowpath through the circuit inlet to the environmental control system, wherein the circuit inlet is disposed along the inner peripheral boundary of the bypass flowpath;
the working fluid system comprising a fluid circuit, and the working fluid system configured to service one or more components of the propulsion system using a liquid working fluid directed through the fluid circuit; and
the heat exchanger configured to transfer heat energy between the air in the air circuit and the liquid working fluid in the fluid circuit.
2 . The system of claim 1 , wherein the heat exchanger is configured as
a heater for the air in the air circuit; and
a cooler for the liquid working fluid in the fluid circuit.
3 . The system of claim 1 , wherein the liquid working fluid comprises lubricant.
4 . The system of claim 1 , wherein the working fluid system is configured to lubricate the one or more components of the propulsion system using the liquid working fluid directed through the fluid circuit.
5 . The system of claim 1 , wherein the working fluid system is configured to cool the one or more components of the propulsion system using the liquid working fluid directed through the fluid circuit.
6 . The system of claim 1 , wherein the one or more components of the propulsion system comprise a bearing.
7 . The system of claim 1 , wherein the one or more components of the propulsion system comprise a gear system.
8 . The system of claim 1 , wherein the propulsion system further includes
a core flowpath extending through the compressor section, the combustor section and the turbine section; and
a fan section upstream of an airflow inlet into the core flowpath and an airflow inlet into the bypass flowpath.
9 . The system of claim 1 , wherein
the heat exchanger is disposed in a compartment of the inner housing structure.
10 . The system of claim 1 , wherein the environmental control system comprises an electric compressor configured to pressurize the air received from the bypass flowpath through the air circuit to provide pressurized air.
11 . The system of claim 10 , wherein the environmental control system further comprises a second heat exchanger configured to cool the pressurized air.
12 . A system for an aircraft, comprising:
a turbine engine comprising an air source and a plurality of engine components;
an inner housing structure housing the plurality of engine components, the inner housing structure forming an inner peripheral boundary of the air source;
an outer housing structure spaced radially outboard of the inner housing structure, the outer housing structure forming an outer peripheral boundary of the air source;
an air system including an air circuit and an environmental control system, the air circuit configured to direct air received from the air source to the environmental control system, wherein a circuit inlet of the air circuit is disposed along the inner peripheral boundary of the air source;
a working fluid system comprising a fluid circuit, the working fluid system configured to lubricate and/or cool the plurality of engine components using a working fluid directed through the fluid circuit; and
a heat exchanger arranged along the air circuit between the air source and the environmental control system, the heat exchanger configured to transfer heat energy between the air in the air circuit and the working fluid in the fluid circuit to heat the air and cool the working fluid.
13 . The system of claim 12 , wherein the turbine engine is a turbofan engine, and the air source is a bypass flowpath of the turbofan engine.
14 . The system of claim 12 , wherein the turbine engine further includes an engine core, the engine core includes a compressor section, a combustor section and a turbine section, and the air source is located outside of the engine core.
15 . The system of claim 12 , wherein the turbine engine further includes
a compressor section;
a combustor section;
a turbine section; and
a flowpath extending through the compressor section, the combustor section and the turbine section, wherein the air source is fluidly independent of the flowpath.
16 . A system for an aircraft, comprising:
an environmental control system; and
a propulsion system including an inner housing structure, an outer housing structure, a vane structure, a compressor section, a combustor section, a turbine section, a bypass flowpath, an air circuit, a working fluid system and a heat exchanger;
the inner housing structure housing the compressor section, the combustor section and the turbine section, the inner housing structure forming an inner peripheral boundary of the bypass flowpath;
the outer housing structure spaced radially outboard of the inner housing structure, the outer housing structure forming an outer peripheral boundary of the bypass flowpath;
the vane structure extending radially across the bypass flowpath from the inner housing structure to the outer housing structure;
the bypass flowpath bypassing the compressor section, the combustor section and the turbine section;
the air circuit comprising a circuit inlet fluidly coupled to the bypass flowpath, and the air circuit configured to direct air received from the bypass flowpath through the circuit inlet to the environmental control system, wherein the circuit inlet is arranged on the vane structure;
the working fluid system comprising a fluid circuit, and the working fluid system configured to service one or more components of the propulsion system using a liquid working fluid directed through the fluid circuit; and
the heat exchanger configured to transfer heat energy between the air in the air circuit and the liquid working fluid in the fluid circuit.
17 . The system of claim 16 , wherein the circuit inlet is disposed at a leading edge of the vane structure.
18 . The system of claim 16 , wherein the vane structure comprises a bifurcation structure.
19 . The system of claim 16 , wherein the heat exchanger is arranged in the vane structure.