US 2025/0198328 A1Published application

Ventilation system for aircraft propulsion system

AssigneeRtx Corporation

InventorsFederico Papa, William K. Ackermann, Reza Rezvani

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Abstract

An assembly is provided for an aircraft propulsion system. This assembly includes a compressor section, a combustor section, a turbine section, a flowpath, a tail cone structure and a ventilation system. The flowpath extends through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath. The tail cone structure is arranged at the exhaust from the flowpath. The ventilation system is configured to bleed compressed air from the flowpath along the compressor section to provide ventilation air. The ventilation system is configured to direct the ventilation air into an internal volume in the tail cone structure.

Claims22

Dependent claims

An assembly for an aircraft propulsion system, comprising:

a compressor section comprising a low pressure compressor section and a high pressure compressor section;
a combustor section;
a turbine section;
a flowpath extending through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath;
a tail cone structure arranged at the exhaust from the flowpath, the tail cone structure forming an inner peripheral boundary of the exhaust from the flowpath;
and
a ventilation system configured to bleed compressed air from the flowpath along the compressor section to provide ventilation air, and the ventilation system including an air-to-air heat exchanger, a ventilation air circuit and a cooling air circuit, the ventilation system configured to direct the ventilation air through the air-to-air heat exchanger and into an internal volume in the tail cone structure;
the ventilation air circuit extending through the air-to-air heat exchanger and fluidly coupled between a ventilation circuit bleed port and the internal volume, and the ventilation circuit bleed port configured to bleed the compressed air from the flowpath along the high pressure compressor section to provide the ventilation air within the ventilation air circuit;
the cooling air circuit extending through the air-to-air heat exchanger and fluidly coupled to a cooling circuit bleed port, the cooling circuit bleed port configured to bleed additional compressed air from the flowpath along the high pressure compressor section to provide the cooling air within the cooling air circuit, the cooling circuit bleed port disposed upstream of the ventilation circuit bleed port along the flowpath, and the cooling air circuit fluidly independent of the ventilation air circuit;
and
the air-to-air heat exchanger configured to transfer heat energy from the ventilation air into cooling air;
wherein the cooling circuit bleed port is separated from the ventilation circuit bleed port along the flowpath by five or more stages of the high pressure compressor section.

9 more elements

An assembly for an aircraft propulsion system, comprising:

a compressor section;
a combustor section;
a turbine section;
a flowpath extending through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath;
an electronic device located in an internal volume of the aircraft propulsion system;
and
a ventilation system configured to bleed compressed air from the flowpath along the compressor section to provide ventilation air, the ventilation system configured to direct the ventilation air through an air-to-air heat exchanger and into the internal volume to ventilate the electronic device, and the ventilation system including a ventilation air circuit, a cooling air circuit and the air-to-air heat exchanger;
the ventilation air circuit extending through the air-to-air heat exchanger and fluidly coupled between a ventilation circuit bleed port and the internal volume, the ventilation circuit bleed port configured to bleed the compressed air from the flowpath along the compressor section to provide the ventilation air within the ventilation air circuit;
the cooling air circuit extending through the air-to-air heat exchanger and fluidly coupled to a cooling circuit bleed port, the cooling circuit bleed port configured to bleed additional compressed air from the flowpath along the compressor section to provide cooling air within the cooling air circuit, and the cooling circuit bleed port disposed upstream of the ventilation circuit bleed port along the flowpath;
and
the air-to-air heat exchanger configured to transfer heat energy from the ventilation air into the cooling air to cool the ventilation air.

8 more elements

An assembly for an aircraft propulsion system, comprising:

a compressor section;
a combustor section;
a turbine section;
a flowpath extending through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath;
an electronic device located in an internal volume of the aircraft propulsion system;
and
a ventilation system configured to bleed compressed air from the flowpath along the compressor section to provide ventilation air, the ventilation system configured to direct the ventilation air through an air-to-air heat exchanger and an air-to-working fluid heat exchanger and into the internal volume to ventilate the electronic device, and the ventilation system including a ventilation air circuit, a working fluid circuit, the air-to-air heat exchanger, and the air-to-working fluid heat exchanger;
the ventilation air circuit extending through the air-to-air heat exchanger and the air-to-working fluid heat exchanger, the ventilation air circuit fluidly coupled between a ventilation circuit bleed port and the internal volume, the ventilation circuit bleed port configured to bleed the compressed air from the flowpath along the compressor section to provide the ventilation air within the ventilation air circuit;
the working fluid circuit extending through the air-to-working fluid heat exchanger, and the working fluid circuit fluidly independent of the ventilation air circuit;
and
the air-to-working fluid heat exchanger configured to transfer heat energy from the ventilation air into a liquid working fluid flowing within the working fluid circuit to cool the ventilation air.

8 more elements

Dependencies are inferred from the claim text.

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Abstract

An assembly for an aircraft propulsion system, comprising:

a compressor section comprising a low pressure compressor section and a high pressure compressor section;
a combustor section;
a turbine section;
a flowpath extending through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath;
a tail cone structure arranged at the exhaust from the flowpath, the tail cone structure forming an inner peripheral boundary of the exhaust from the flowpath;
and
a ventilation system configured to bleed compressed air from the flowpath along the compressor section to provide ventilation air, and the ventilation system including an air-to-air heat exchanger, a ventilation air circuit and a cooling air circuit, the ventilation system configured to direct the ventilation air through the air-to-air heat exchanger and into an internal volume in the tail cone structure;
the ventilation air circuit extending through the air-to-air heat exchanger and fluidly coupled between a ventilation circuit bleed port and the internal volume, and the ventilation circuit bleed port configured to bleed the compressed air from the flowpath along the high pressure compressor section to provide the ventilation air within the ventilation air circuit;
the cooling air circuit extending through the air-to-air heat exchanger and fluidly coupled to a cooling circuit bleed port, the cooling circuit bleed port configured to bleed additional compressed air from the flowpath along the high pressure compressor section to provide the cooling air within the cooling air circuit, the cooling circuit bleed port disposed upstream of the ventilation circuit bleed port along the flowpath, and the cooling air circuit fluidly independent of the ventilation air circuit;
and
the air-to-air heat exchanger configured to transfer heat energy from the ventilation air into cooling air;
wherein the cooling circuit bleed port is separated from the ventilation circuit bleed port along the flowpath by five or more stages of the high pressure compressor section.

9 more elements