Gas turbine engine having a heat exchanger arrangement for heating or cooling a fuel

Patent metadata

Field	Value
Publication number	US-12516631-B2
Application number	US-202418765533-A
Country	US
Kind code	B2
Filing date	Jul 8, 2024
Priority date	May 30, 2019
Publication date	Jan 6, 2026
Grant date	Jan 6, 2026

Abstract

An engine comprises an air intake arrangement configured to receive air; a heat exchanger arrangement arranged downstream of the air intake arrangement, configured to cool the air, and comprising a plurality of heat exchanger modules; and one or more turbomachinery components configured to receive cooled air from the heat exchanger arrangement. The plurality of heat exchanger modules are arranged to be generally centred on and to be arranged along a longitudinal axis of the engine. At least one of the plurality of heat exchanger modules is arranged to at least partially overlap with at least one other one of the plurality of heat exchanger modules relative to the longitudinal axis of the engine.

First claim

The invention claimed is:

1 . An engine, comprising:
an air intake arrangement configured to receive air; a fuel tank configured to store a fuel for being supplied to an air-breathing combustion chamber; a heat exchanger arrangement arranged downstream of the air intake arrangement and configured to cool the air by providing for heat exchange between the air and a heat transfer medium; and a compressor arranged downstream of the heat exchanger arrangement and configured to supply compressed air to the air-breathing combustion chamber for the combustion of the air and the fuel; wherein the heat exchanger arrangement is configured to be selectively operated in a first operating mode which corresponds with a first operating flight speed of the engine, and a second operating mode which corresponds with a second operating flight speed of the engine that is lower than the first operating flight speed of the engine; wherein in the first operating mode of the heat exchanger arrangement, the heat transfer medium is configured to heat the fuel before the fuel is delivered to the air-breathing combustion chamber; and wherein in the second operating mode of the heat exchanger arrangement, the heat transfer medium is configured to cool the fuel before the fuel is delivered to the air-breathing combustion chamber.

2 . The engine of claim 1 , wherein the heat exchanger arrangement comprises a plurality of heat exchanger modules.

3 . A method of operating an engine as claimed in the engine of claim 1 , the method comprising:
suppling air to the air intake arrangement; causing the air to flow through the air intake arrangement, the heat exchanger arrangement, the compressor and the air-breathing combustion chamber; supplying heat transfer medium to the heat exchanger arrangement; causing the heat transfer medium to flow through the heat exchanger arrangement; supplying fuel to the fuel tank; and causing the fuel to flow from the fuel tank to the air-breathing combustion chamber; wherein the method further comprises operating the heat exchanger arrangement in
the first operating mode when the engine is operating at the first operating flight speed, and operating the heat exchanger arrangement in the second operating mode when the engine is operating at the second operating flight speed.

4 . An aircraft, flying machine or aerospace vehicle comprising an engine as claimed in the engine of claim 1 .

5 . The engine of claim 1 , wherein in the second operating mode of the heat exchanger arrangement, the heat exchanger arrangement is configured to operate in a reverse direction to the first operating mode of the heat exchanger arrangement.

6 . The engine of claim 1 , wherein the engine further comprises a first flow path for the flow of the heat transfer medium and extending between and in fluid communication with the outlet of the heat exchanger arrangement and a point in the engine downstream of the compressor, such that in the first operating mode of the heat exchanger arrangement, a portion of the heat transfer medium is used for re-heating and/or a Ramjet mode of operating the engine.

7 . The engine of claim 1 , wherein the engine further comprises a second flow path for the flow of the heat transfer medium and extending between and in fluid communication with the outlet of the heat exchanger arrangement and an inlet of the fuel tank, such that in the first and second operating modes of the heat exchanger arrangement, a portion of the heat transfer medium is placed in heat exchange with the fuel in the fuel tank.

8 . The engine of claim 1 , wherein the engine further comprises a third flow path for the flow of the heat transfer medium and extending between and in fluid communication with an outlet of the fuel tank and the inlet of the heat exchanger arrangement, such that in the first and second operating modes of the heat exchanger arrangement, the portion of the heat transfer medium that is placed in heat exchange with the fuel in the fuel tank is then configured to re-enter the heat exchanger arrangement.

9 . The engine of claim 1 , wherein in the first operating mode of the heat exchanger arrangement, hot heat transfer medium which exits the heat exchanger arrangement after it has been used to cool the air flowing through the heat exchanger arrangement is used to heat the fuel in the fuel tank.

10 . The engine of claim 1 , wherein in the first operating mode of the heat exchanger arrangement cold heat transfer medium, which has been cooled as a result of heating the fuel, exiting the fuel tank is then fed back into the heat transfer arrangement where it is used to cool the air flowing through the heat exchanger arrangement.

11 . The engine of claim 1 , wherein in the second operating mode of the heat exchanger arrangement, heat transfer medium which exits the heat exchanger arrangement after it has been used to warm the air flowing through the heat exchanger arrangement is used to cool the fuel in the fuel tank.

12 . The engine of claim 1 , wherein in the second operating mode of the heat exchanger arrangement, hot heat transfer medium, which has been heated as a result of cooling the fuel, exiting the fuel tank may then be fed back into the heat exchanger arrangement where it is used to warm the air flowing through the heat exchanger arrangement.

13 . The engine of claim 1 , wherein the heat transfer medium comprises a fuel, or the heat transfer medium comprise a fluid that is different to and separate to a fuel used in the engine.

14 . The engine of claim 1 , wherein the heat transfer medium is helium.

15 . The engine of claim 1 , wherein the fuel is hydrogen.

Assignees

• Reaction Engines Ltd
• Honeywell Int Inc

Inventors

• Bond Robert Alexander
• Evans Kathryn Rebecca
• Payne Russell Geoffrey
• Johnson Martin Christopher

Classifications

• F02C7/143

  before or between the compressor stages · CPC title

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F02C7/04 Primary

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F02K9/78

  with an air-breathing jet-propulsion plant (with a ram-jet engine F02K7/18) · CPC title

• F02K1/822

  Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors · CPC title