Gas turbine engine having a thrust reverser system with drag link connectors at inter-compressor frame structure

Patent metadata

Field	Value
Publication number	US-12553403-B1
Application number	US-202519277730-A
Country	US
Kind code	B1
Filing date	Jul 23, 2025
Priority date	Jul 23, 2025
Publication date	Feb 17, 2026
Grant date	Feb 17, 2026

Abstract

A gas turbine engine includes a fan assembly, a turbo-engine encased within a turbo-engine cowl structure, a nacelle, and a thrust reverser system arranged, at least in part, in the nacelle. The turbo-engine includes a low-pressure compressor, a high-pressure compressor, an inter-compressor frame structure between the low-pressure compressor and the high-pressure compressor and including an outer frame portion having a cowl door engagement member on an upstream side of the outer frame portion, and a plurality of cowl doors defining the turbo-engine cowl structure. Each cowl door includes an inter-compressor frame engagement portion that engages with the cowl door engagement member of the inter-compressor frame structure, and a plurality of thrust reverser drag link connectors arranged on an outer side of the cowl door and arranged between the upstream side of the inter-compressor frame structure and a downstream side of the inter-compressor frame structure.

First claim

We claim:

1 . A gas turbine engine comprising:
a fan assembly; a turbo-engine arranged to drive the fan assembly, the turbo-engine at least partially encased within a turbo-engine cowl structure; a nacelle surrounding the fan assembly and at least a portion of the turbo-engine, a fan bypass airflow passage being arranged between the nacelle and the turbo-engine cowl structure; and a thrust reverser system arranged, at least in part, in the nacelle and including a plurality of actuators, a plurality of thrust reverser blocking doors, and a plurality of drag links connected with respective ones of the plurality of thrust reverser blocking doors and with the turbo-engine cowl structure via a plurality of thrust reverser drag link connectors, wherein the turbo-engine includes (a) a low-pressure compressor, (b) a high-pressure compressor arranged downstream of the low-pressure compressor, (c) an inter-compressor frame structure arranged between the low-pressure compressor and the high-pressure compressor, the inter-compressor frame structure including an outer frame portion having a cowl door engagement member arranged on an upstream side of the outer frame portion, and (d) a plurality of cowl doors defining at least a portion of the turbo-engine cowl structure, each cowl door among the plurality of cowl doors includes (i) an inter-compressor frame engagement portion arranged to engage with the cowl door engagement member of the inter-compressor frame structure, and (ii) the plurality of thrust reverser drag link connectors arranged on an outer side of the cowl door and arranged between the upstream side of the inter-compressor frame structure and a downstream side of the inter-compressor frame structure.

2 . The gas turbine engine according to claim 1 , wherein the plurality of drag links are connected with the turbo-engine cowl structure via respective ones of the plurality of thrust reverser drag link connectors.

3 . The gas turbine engine according to claim 1 , wherein the thrust reverser system is a cold stream cascade thrust reverser system.

4 . The gas turbine engine according to claim 1 , wherein the cowl door engagement member is at least one of a V-groove or a fire seal.

5 . The gas turbine engine according to claim 4 , wherein the inter-compressor frame engagement portion is a flange that engages with the V-groove or with the fire seal.

6 . The gas turbine engine according to claim 1 , wherein the plurality of cowl doors comprises two cowl doors, each cowl door being hinged via a cowl door hinge so as to translate the cowl doors between a closed position and an open position.

7 . The gas turbine engine according to claim 6 , wherein, in the closed position, for each cowl door of the plurality of cowl doors, the inter-compressor frame engagement portion of each cowl door engages in a circumferential direction with the cowl door engagement member of the inter-compressor frame structure.

8 . The gas turbine engine according to claim 1 , wherein the inter-compressor frame structure further includes an upstream wall and a downstream wall, and a plurality of bleed air openings are provided through the outer frame portion, a bleed air plenum being defined between the upstream wall and the downstream wall.

9 . The gas turbine engine according to claim 8 , further comprising a variable compressor bleed air valve providing a flow of compressor bleed air from the low-pressure compressor into the bleed air plenum.

10 . The gas turbine engine according to claim 9 , wherein the plurality of cowl doors each includes a plurality of bleed air vents extending therethrough for providing a flow of the compressor bleed air flowing from the bleed air plenum and through the plurality of bleed air openings of the outer frame portion to flow therethrough into the fan bypass airflow passage.

11 . The gas turbine engine according to claim 9 , wherein the variable compressor bleed air valve is an operability bleed valve that controls a flow of compressed air flowing from the low-pressure compressor to the high-pressure compressor by controlling the flow of the compressor bleed air flowing into the bleed air plenum.

12 . The gas turbine engine according to claim 1 , wherein the inter-compressor frame structure further includes a second cowl door engagement member arranged on the downstream side of the outer frame portion.

13 . The gas turbine engine according to claim 12 , wherein each cowl door further includes a second inter-compressor frame engagement portion arranged to engage with the second cowl door engagement member.

14 . The gas turbine engine according to claim 13 , wherein the second cowl door engagement member is at least one of a V-groove or a fire seal.

15 . The gas turbine engine according to claim 14 , wherein the second inter-compressor frame engagement portion is a flange that engages with the V-groove or with the fire seal of the second cowl door engagement member.

16 . The gas turbine engine according to claim 13 , wherein the gas turbine engine defines a longitudinal centerline axis extending from an upstream end of the gas turbine engine to a downstream end of the gas turbine engine, the inter-compressor frame structure extends circumferentially about the longitudinal centerline axis, and the plurality of cowl doors extend circumferentially about the longitudinal centerline axis.

17 . The gas turbine engine according to claim 16 , wherein respective ones of the plurality of thrust reverser drag link connectors are arranged circumferentially spaced apart from each other about the outer side of the plurality of cowl doors, and are arranged longitudinally on the outer side of the plurality of cowl doors between the inter-compressor frame engagement portion and the second inter-compressor frame engagement portion.

18 . The gas turbine engine according to claim 17 , wherein the plurality of cowl doors each includes a plurality of bleed air vents extending therethrough for providing a flow of compressor bleed air into the fan bypass airflow passage, and respective ones of the plurality of thrust reverser drag link connectors are arranged circumferentially between respective ones of the plurality of bleed air vents.

19 . The gas turbine engine according to claim 16 , wherein the inter-compressor frame structure extends outward from an outer side of a compressor casing that encases the low-pressure compressor and the high-pressure compressor.

20 . The gas turbine engine according to claim 19 , wherein, in a closed position, for each cowl door, the inter-compressor frame engagement portion engages with the cowl door engagement member, and the second inter-compressor frame engagement portion engages with the second cowl door engagement member.

Assignees

• Gen Electric

Inventors

• Miller Brandon W
• Matava Stephen G
• Barre Eric

Classifications

• F02K1/15

  Control or regulation · CPC title

• F02K1/80

  Couplings or connections · CPC title

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title

• F02K1/72 Primary

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title

• F02C9/52

  by bleeding or by-passing the working fluid · CPC title