US 12,577,910 B1Granted

Gas turbine engine with compartment anti-icing system

AssigneeRtx Corporation

InventorsMurat Yazici, Thomas E. Clark

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Abstract

A gas turbine engine is provided that includes a fan section, a compressor section, a combustion section, a turbine section, an annular fan bypass air path, a bleed air structure, an annular compartment, and an anti-icing system. The compressor section has a low and high pressure compressor sections. The fan bypass air path is defined by inner and outer bypass wall structures. An outer radial boundary structure defines an outer radial boundary of a core gas path within the low pressure compressor section. The bleed air structure is disposable in an open state or in a closed state. The annular compartment is defined by the inner bypass wall structure, the outer radial boundary structure, and a firewall. The anti-icing system is disposable in an activated state or in a deactivated state. In the activated state the anti-icing system is configured to mitigate ice accumulation within the annular compartment.

Claims15

Dependent claims

A gas turbine engine, comprising:

a fan section;
a compressor section having a low pressure compressor section and a high pressure compressor section;
a combustion section;
a turbine section;
an annular fan bypass air path defined by an outer bypass wall structure and an inner bypass wall structure;
wherein a core gas path extends through the compressor section, the combustion section, and the turbine section, and wherein an outer radial boundary structure defines an outer radial boundary of the core gas path within the low pressure compressor section;
a bleed air structure that is disposable in an open state or in a closed state, the bleed air structure being downstream from the low pressure compressor section;
an annular compartment defined by the inner bypass wall structure, the outer radial boundary structure, and a firewall, wherein the firewall is disposed downstream of the bleed air structure;
wherein in the open state, the bleed air structure is configured to selectively pass a first air flow from the compressor section into the annular compartment;
and
an anti-icing system disposable in an activated state or in a deactivated state, wherein in the activated state the anti-icing system is configured to mitigate ice accumulation within the annular compartment;
wherein the first air flow from the compressor section that is passed into the annular compartment is at a first pressure and a first temperature;
wherein the anti-icing system includes an air distribution system configured to receive a second air flow and deliver the second air flow into the annular compartment, wherein the second air flow is at a second pressure and a second temperature;
wherein the second pressure is greater than the first pressure, and the second temperature is greater than the first temperature;
and
wherein the air distribution system includes an annular manifold configured to distribute the second air flow within the annular compartment, the annular manifold being attached to the firewall such that an outlet of the manifold, from which the second air flow exits to the annular compartment, is downstream from the low pressure compressor section.

13 more elements

A gas turbine engine, comprising:

a fan section;
a compressor section having a low pressure compressor section and a high pressure compressor section;
a combustion section;
a turbine section;
an annular fan bypass air path defined by an outer bypass wall structure and an inner bypass wall structure;
wherein a core gas path extends through the compressor section, the combustion section, and the turbine section, and wherein an outer radial boundary structure defines an outer radial boundary of the core gas path within the low pressure compressor section;
a bleed air structure that is disposable in an open state or in a closed state;
an annular compartment defined by the inner bypass wall structure, the outer radial boundary structure, and a firewall, wherein the firewall is disposed downstream of the bleed air structure;
wherein in the open state, the bleed air structure is configured to selectively pass a first air flow from the compressor section into the annular compartment;
and
an anti-icing system disposable in an activated state or in a deactivated state, wherein in the activated state the anti-icing system is configured to mitigate ice accumulation within the annular compartment;
wherein the anti-icing system includes a heating system that includes a plurality of heating elements that are disposed within the annular compartment and are configured to produce thermal energy;
wherein the plurality of heating elements are electrically powered;
wherein the anti-icing system utilizes a temperature sensor and a controller, wherein the temperature sensor is configured to sense temperature within the annular compartment and produce a sensor signal representative of the sensed temperature, and wherein the controller is in communication with the plurality of heating elements, the temperature sensor, and a non-transitory memory storing instructions, which instructions when executed cause the controller to control the plurality of heating elements based at least in part on the sensor signal;
wherein the first air flow from the compressor section that is passed into the annular compartment is at a first pressure and a first temperature;
wherein the anti-icing system includes an air distribution system configured to receive a second air flow and deliver the second air flow into the annular compartment, wherein the second air flow is at a second pressure and a second temperature;
and
wherein the second pressure is greater than the first pressure, and the second temperature is greater than the first temperature.

15 more elements

Dependencies are inferred from the claim text.