Gas turbine engine with thermal management

Patent metadata

Field	Value
Publication number	US-12553392-B2
Application number	US-202418747077-A
Country	US
Kind code	B2
Filing date	Jun 18, 2024
Priority date	Jun 18, 2024
Publication date	Feb 17, 2026
Grant date	Feb 17, 2026

Abstract

A fluid thermal control system for a gas turbine engine is provided. The gas turbine engine has a compressor section and an engine fluid source that produces a flow of engine fluid. The fluid thermal control system includes an airflow inlet, an airflow outlet, a heat exchanger, an airflow inlet valve, and a bleed air valve. The heat exchanger permits heat transfer between a heat exchanger airflow and the flow of engine fluid. The airflow inlet valve permits the airflow from the source of airflow to engage with the heat exchanger as at least part of the heat exchanger airflow. The bleed air valve is controllable between closed and open configurations. The bleed air valve is in communication with the compressor section and is configured to receive compressor bleed air. In the open configuration, the bleed air valve allows compressor bleed air to engage with the heat exchanger.

First claim

The invention claimed is:

1 . A fluid thermal control system for a gas turbine engine, the gas turbine engine having a compressor section and an engine fluid source that produces a flow of engine fluid, the fluid thermal control system comprising:
an airflow inlet exposed to a source of airflow; an airflow outlet; a heat exchanger configured to permit heat transfer between a heat exchanger airflow and the flow of engine fluid; an airflow inlet valve configured to permit the airflow from the source of airflow to engage with the heat exchanger as at least part of the heat exchanger airflow; and a bleed air valve controllable to be disposed in a closed bleed air configuration and an open bleed air configuration, wherein the bleed air valve is in communication with the compressor section of the gas turbine engine and is configured to receive compressor bleed air from the compressor section, wherein in the open bleed air configuration, the bleed air valve allows the compressor bleed air to engage with the heat exchanger as at least part of the heat exchanger airflow, and wherein the bleed air valve is controllable to selectively allow at least part of the compressor bleed air to discharge to the source of airflow upstream of the airflow inlet; wherein subsequent to engaging with the heat exchanger, the heat exchanger airflow exits the system through the airflow outlet.

2 . The fluid thermal control system of claim 1 , further comprising an inlet passage fluidically connecting the airflow inlet to the heat exchanger and an outlet passage fluidically connecting the heat exchanger to the airflow outlet.

3 . The fluid thermal control system of claim 2 , wherein the airflow inlet valve is disposed within the inlet passage.

4 . The fluid thermal control system of claim 3 , wherein the airflow inlet valve is a controllable valve operable to be disposed in a closed airflow inlet configuration or an open airflow inlet configuration, and in the open airflow inlet configuration the airflow inlet valve allows passage of the airflow toward the heat exchanger.

5 . The fluid thermal control system of claim 4 , wherein the open airflow inlet configuration includes a first open airflow inlet configuration and a second open airflow inlet configuration, wherein the first open airflow inlet configuration is a fully open configuration and the second open airflow inlet configuration is a less than fully open configuration.

6 . The fluid thermal control system of claim 5 , further comprising a controller in communication with the airflow inlet valve, the bleed air valve, and a non-transitory memory storing instructions, which instructions when executed cause the controller to control the airflow inlet valve and the bleed air valve.

7 . The fluid thermal control system of claim 3 , wherein the airflow inlet valve is a one-way passive valve disposable in a closed airflow inlet configuration or an open airflow inlet configuration, and in the open airflow inlet configuration the airflow inlet valve allows passage of the airflow toward the heat exchanger.

8 . The fluid thermal control system of claim 7 , wherein the open airflow inlet configuration includes a first open airflow inlet configuration and a second open airflow inlet configuration, wherein the first open airflow inlet configuration is a fully open configuration and the second open airflow inlet configuration is a less than fully open configuration.

9 . The fluid thermal control system of claim 1 , wherein the gas turbine engine is in communication with a bypass air duct and the airflow inlet is in fluid communication with the bypass air duct, and wherein the source of airflow is bypass airflow.

10 . The fluid thermal control system of claim 9 , wherein the airflow outlet is in fluid communication with the bypass air duct.

11 . A gas turbine engine, comprising:
a compressor section; a combustor section; a turbine section; an engine fluid source that produces a flow of engine fluid; and a fluid thermal control system that includes:
an airflow inlet exposed to a source of airflow;
an airflow outlet;
a heat exchanger configured to permit heat transfer between a heat exchanger airflow and the flow of engine fluid;
an airflow inlet valve (AIV) configured to permit the airflow from the source of airflow to engage with the heat exchanger as at least part of the heat exchanger airflow; and
a bleed air valve (BAV) controllable to be disposed in a BAV closed configuration and a BAV open configuration, wherein the BAV is in communication with the compressor section of the gas turbine engine and is configured to receive compressor bleed air from the compressor section, wherein in the BAV open configuration, the BAV allows the compressor bleed air to engage with the heat exchanger as at least part of the heat exchanger airflow, and wherein the BAV is controllable to selectively allow at least part of the compressor bleed air to discharge to the source of airflow upstream of the airflow inlet;
wherein subsequent to engaging with the heat exchanger, the heat exchanger airflow exits the system through the airflow outlet.

12 . The gas turbine engine of claim 11 , further comprising an inlet passage fluidically connecting the airflow inlet to the heat exchanger and an outlet passage fluidically connecting the heat exchanger to the airflow outlet, wherein the AIV is disposed within the inlet passage.

13 . The gas turbine engine of claim 12 , wherein the AIV is a one-way passive valve disposed to allow passage of the airflow toward the heat exchanger.

14 . The gas turbine engine of claim 12 , wherein the AIV is a controllable valve operable to be disposed in an AIV closed configuration or an AIV open configuration, and in the AIV open configuration the AIV allows passage of the airflow toward the heat exchanger;
wherein the AIV open configuration includes a first AIV open configuration and a second AIV open configuration, wherein the first AIV open configuration is a fully open configuration and the second AIV open configuration is a less than fully open configuration.

15 . The gas turbine engine of claim 14 , wherein the BAV open configuration includes a first BAV open configuration and a second BAV open configuration, wherein the first BAV open configuration is a fully open configuration and the second BAV open configuration is a less than fully open configuration.

16 . The gas turbine engine of claim 15 , further comprising a controller in communication with the AIV, the BAV, and a non-transitory memory storing instructions, which instructions when executed cause the controller to control the AIV and the BAV.

17 . The gas turbine engine of claim 11 , wherein the gas turbine engine is in communication with a bypass air duct and the airflow inlet is in fluid communication with the bypass air duct, and wherein the source of airflow is bypass airflow, and wherein the airflow outlet is in fluid communication with the bypass air duct.

18 . A method of cooling an engine fluid utilized within a gas turbine engine, wherein the gas turbine engine includes a compressor section and an engine fluid source that produces a flow of engine fluid, the method comprising:
operating a bleed air valve (BAV) to selectively bleed a flow of compressor bleed air off of the compressor section of the gas turbine engine; using an airflow inlet to capture an airflow from an airflow source and directing the airflow to an airflow inlet valve (AIV); passing the flow of engine fluid from the engine fluid source through a heat ex

Assignees

• Rtx Corp

Inventors

• Yazici Murat
• Breault Andrew E
• Morton Jeffrey T

Classifications

• F05D2260/606

  Bypassing the fluid · CPC title

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title

• F02C7/14

  of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} · CPC title

• F02C7/057

  Control or regulation (conjointly with fuel supply control F02C9/50, with nozzle area control F02K1/16) · CPC title

• F02K3/115

  by means of indirect heat exchange · CPC title