Multi-directional gearbox deflection limiter for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10495004-B2
Application number	US-201514857164-A
Country	US
Kind code	B2
Filing date	Sep 17, 2015
Priority date	Sep 17, 2015
Publication date	Dec 3, 2019
Grant date	Dec 3, 2019

Abstract

A gas turbine engine including a fan, a core including at least one rotatable shaft, and a gearbox mechanically coupling at least one rotatable shaft of the core to the fan is provided. The gas turbine engine also includes a coupling system for mounting the gearbox within the gas turbine engine. The coupling system includes a flexible coupling connected to at least one of a fan frame or a core frame, as well as a torque frame connected to the flexible coupling and the gearbox. Moreover, a deflection limiter is provided, loosely attaching the flexible coupling to the gearbox to provide a predetermined axial range of motion, radial range of motion, and circumferential range of motion between the gearbox and the frame to which the flexible coupling is attached.

First claim

What is claimed is:

1. A gas turbine engine defining an axial direction, a radial direction, and a circumferential direction, the gas turbine engine comprising:
a fan including a fan frame;
a core including a core frame and one or more rotatable shafts;
a gearbox mechanically connecting one of the one or more shafts of the core to the fan; and
a coupling system for mounting the gearbox within the gas turbine engine, the coupling system comprising
a flexible coupling connected to at least one of the fan frame or the core frame;
a torque frame connected to the flexible coupling and the gearbox; and
a deflection limiter attaching the flexible coupling to the gearbox, the deflection limiter providing for an axial range of motion, a radial range of motion, and a circumferential range of motion between the gearbox and the frame to which the flexible coupling is attached, wherein the deflection limiter comprises a pin having a head and defining a distal end opposite the head, and wherein the head of the pin and the torque frame define a first axial gap along the axial direction.

2. The gas turbine engine of claim 1 , wherein the deflection limiter blocks movement of gearbox past the axial range of motion in a forward direction and in an aft direction of the gas turbine engine, past the radial range of motion in a radially outward direction and in a radially inward direction, and past the circumferential range of motion.

3. The gas turbine engine of claim 1 , wherein the deflection limiter includes the pin extending between the flexible coupling and the torque frame.

4. The gas turbine engine of claim 3 , wherein the pin defines a radial gap with at least one of the flexible coupling or the torque frame, and wherein the pin defines a circumferential gap with at least one of the flexible coupling or the torque frame.

5. The gas turbine engine of claim 3 , wherein the distal end of the pin is attached to the flexible coupling.

6. The gas turbine engine of claim 1 , wherein the deflection limiter includes a bumper mounted to the flexible coupling.

7. The gas turbine engine of claim 6 , wherein the bumper is formed of an elastomeric material.

8. The gas turbine engine of claim 1 , wherein the deflection limiter attaches the flexible coupling to the gearbox through the torque frame.

9. The gas turbine engine of claim 1 , wherein the flexible coupling is connected to the core frame at a first end.

10. The gas turbine engine of claim 1 , wherein the gearbox includes a sun gear, a ring gear, and a plurality of star gears meshing with the sun gear and ring gear, wherein the plurality of star gears are rotatably mounted within a star gear carrier, and wherein the torque frame is mounted to the star gear carrier.

11. The gas turbine engine of claim 1 , wherein the flexible coupling is connected to at least one of the fan frame or the core frame at a first end, and wherein the deflection limiter attaches the torque frame member to the flexible coupling at a location proximate the first end of the flexible coupling.

12. The gas turbine engine of claim 1 , wherein the torque frame defines a tab, wherein the first axial gap is defined between the head of the pin and the tab of the torque frame, and wherein the deflection limiter further defines a second axial gap between the tab of the torque frame and the flexible coupling.

13. The gas turbine engine of claim 1 , wherein the torque frame defines a tab, wherein the tab defines an opening having an enclosed cross-sectional shape, wherein the pin of the deflection limiter extends through the opening of the tab, and wherein a body of the pin defines a first radial gap and a second radial gap with the tab between opposing sides of the body of the pin.

14. A gear train for a gas turbine engine defining an axial direction, a radial direction, and a circumferential direction, the gear train comprising:
a sun gear rotatable by a shaft of the gas turbine engine;
a ring gear attachable to a ring gear shaft;
a plurality of intermediate gears rotatably mounted in a gear carrier and meshing with the sun gear and ring gear; and
a coupling system comprising
a flexible coupling for connection with a nonrotating component of the gas turbine engine;
a torque frame connected to the flexible coupling and the gear carrier for connecting the flexible coupling to the gear carrier; and
a deflection limiter attaching the flexible coupling to the gear carrier, the deflection limiter providing for an axial range of motion, a radial range of motion, and a circumferential range of motion between the gear carrier and the nonrotating component to which the flexible coupling is attached, wherein the deflection limiter blocks movement of gearbox past the axial range of motion in a forward direction and in an aft direction of the gas turbine engine;
wherein the deflection limiter comprises a pin having a head and defining a distal end opposite the head, and wherein the head of the pin and the torque frame define a first axial gap along the axial direction.

15. The gear train of claim 14 , wherein the deflection limiter blocks movement of gearbox past the radial range of motion in a radially outward direction and in a radially inward direction, and past the circumferential range of motion.

16. The gear train of claim 14 , wherein the pin extends between the flexible coupling and the torque frame.

17. The gear train of claim 16 , wherein the pin defines a radial gap with at least one of the flexible coupling or the torque frame, and wherein the pin defines a circumferential gap with at least one of the flexible coupling or the torque frame.

18. The gear train of claim 14 , wherein the deflection limiter includes a bumper mounted to the flexible coupling.

19. The gear train of claim 14 , wherein the deflection limiter attaches the flexible coupling to the gearbox through the torque frame.

20. The gear train of claim 14 , wherein the flexible coupling is configured for connection with a nonrotating component of the gas turbine engine at a first end, and wherein the deflection limiter attaches the torque frame member to the flexible coupling at a location proximate the first end of the flexible coupling.

Assignees

• Gen Electric

Inventors

• Miller Brandon Wayne
• Bradley Donald Albert

Classifications

• F16H57/028

  characterised by means for reducing vibration or noise · CPC title

• F05D2250/43

  with three degrees of freedom · CPC title

• F05D2240/91

  on a stationary structure · CPC title

• F01D25/04

  Antivibration arrangements · CPC title

• F02C3/107

  with two or more rotors connected by power transmission · CPC title