Gas turbine engine with heat exchanger

Patent metadata

Field	Value
Publication number	US-2026049574-A1
Application number	US-202418746121-A
Country	US
Kind code	A1
Filing date	Jun 18, 2024
Priority date	Jun 18, 2024
Publication date	Feb 19, 2026
Grant date	—

Abstract

A gas turbine engine includes a fan, a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining in part a working gas flowpath, the compressor section including a frame and defining a cavity forward of the frame, the compressor section further comprising a booster disposed in the working gas flowpath including a vane in fluid communication with the working gas flowpath and the cavity, the gas turbine engine defining a bypass passage over the turbomachine, and a heat exchanger disposed at least partially in the cavity, wherein the heat exchanger is in fluid communication with the booster in the working gas flowpath and is in fluid communication with the bypass passage.

First claim

What is claimed is:

1 . A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:
a fan; a turbomachine drivingly coupled to the fan and comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining, in part, a working gas flowpath, the compressor section including a frame and defining a cavity forward of the frame in the axial direction, the compressor section further comprising a booster disposed in the working gas flowpath, the booster including a vane in fluid communication with the working gas flowpath and in fluid communication with the cavity, the gas turbine engine defining a bypass passage over the turbomachine; and a heat exchanger disposed at least partially in the cavity, wherein the heat exchanger is in fluid communication with the booster in the working gas flowpath and is in fluid communication with the bypass passage.

2 . The gas turbine engine of claim 1 , wherein the vane defines an opening fluidly connecting the working gas flowpath to the cavity.

3 . The gas turbine engine of claim 1 , wherein the frame further comprises:
a cavity inlet fluidly connecting the working gas flowpath and the cavity; and a cavity outlet fluidly connecting the working gas flowpath and the bypass passage.

4 . The gas turbine engine of claim 3 , wherein the heat exchanger includes an exit in fluid communication with the cavity outlet.

5 . The gas turbine engine of claim 3 , wherein the vane is in fluid communication with the cavity inlet.

6 . The gas turbine engine of claim 1 , wherein the vane includes a scoop fluidly connecting the working gas flowpath to the cavity.

7 . The gas turbine engine of claim 6 , wherein the scoop extends outward in the radial direction and rearward in the axial direction.

8 . The gas turbine engine of claim 1 , wherein the booster includes a first booster rotor blade and a second booster rotor blade, and the vane is disposed between the first booster rotor blade and the second booster rotor blade.

9 . The gas turbine engine of claim 1 , further comprising a duct having a first end disposed in the working gas flowpath and a second end coupled to the heat exchanger.

10 . The gas turbine engine of claim 9 , wherein the first end of the duct is connected to the vane of the booster.

11 . The gas turbine engine of claim 1 , further comprising a thermal control in thermal communication with the heat exchanger.

12 . The gas turbine engine of claim 11 , wherein the thermal control is one of a high pressure turbine thermal control or a low pressure turbine thermal control.

13 . The gas turbine engine of claim 1 , wherein the heat exchanger is one of an air-cooled oil cooler or a variable frequency generator air-cooled oil cooler.

14 . The gas turbine engine of claim 1 , wherein the booster is a low pressure compressor.

15 . The gas turbine engine of claim 1 , wherein the booster is a multi-stage booster.

16 . The gas turbine engine of claim 1 , further comprising a plurality of heat exchangers disposed circumferentially around the booster, wherein the heat exchanger is a first heat exchanger of the plurality of heat exchangers.

17 . The gas turbine engine of claim 1 , further comprising a core cowl, wherein the heat exchanger is disposed forward of the core cowl in the axial direction.

18 . The gas turbine engine of claim 1 , wherein the fan includes an outlet guide vane, and the heat exchanger is disposed aft of the outlet guide vane in the axial direction.

19 . The gas turbine engine of claim 1 , wherein the heat exchanger is in fluid communication with the booster.

20 . The gas turbine engine of claim 1 , wherein the fan is a single stage fan.

Assignees

• Gen Electric

Inventors

• Miller Brandon Wayne
• Hudecki Andrew
• Barre Eric
• Hank Andrew J
• Gallier Kirk Douglas

Classifications

• F05D2260/213

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

• F02C7/14 Primary

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title