# US 11,077,954 B2 · Connection assembly for mounting engine and engine mounting system comprising the same

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- Number: US 11,077,954 B2
- Document ID: US11077954B2
- Status: Granted
- Kind: B2
- Application number: 15/847,968
- Filed: 2017-12-20
- Published: 2019-06-20
- Granted: 2021-08-03
- Earliest claimed: 2017-12-20
- Assignees: General Electric Company
- Applicants: General Electric Company
- Inventors: Timothy Leo Schelfaut; Lawrence Jerome Meyer; Anthony Michael Metz; Jonathan Edward Coleman; Thomas Peter Joseph
- Web page: https://patentgrep.com/patent/US11077954B2

## CPC

- B64D 27/14: within, or attached to, fuselages
- B64D 27/12: within, or attached to, wings
- B64D 27/402: {comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant}
- B64D 27/406: {Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links}
- B64D 2221/00: Electric power distribution systems onboard aircraft
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT

## Abstract

A connection assembly for mounting an engine to a mounting structure. The engine is rotatable about an axis of rotation and defines an axial direction extending along the axis of rotation from a forward end to an aft end. The engine has a center of gravity. The connection assembly includes: an engine coupling piece coupled to the engine; and a connection piece connecting the engine coupling piece and the mounting structure, the connection piece being inclined toward the axial direction. A mounting system including the connection assembly is also described.

## Claims

### Claim 1

A connection assembly mounting an engine to a mounting structure, the engine defining a centerline that defines an axial direction extending from a forward end to an aft end, the engine comprising a center of gravity, the connection assembly comprising:
an engine coupling piece coupled to an aft portion of a fan case of the engine, wherein the engine coupling piece comprises a pair of lugs defining a cavity therebetween opening in the axial direction; and
a connection piece including a link connecting the engine coupling piece and the mounting structure wherein the mounting structure is a pylon positioned aft of the engine coupling piece, the connection piece inclined toward the axial direction, wherein the link has a first end connected with the engine coupling piece, a second end opposite to the first end and connected with the mounting structure, and a beam between the first end and the second end and curved toward the axial direction, and the engine coupling piece configured such that force transferred from the aft portion of the fan case to the mounting structure is to be transmitted from the aft portion of the fan case to the connecting piece to the engine coupling piece and to the mounting structure.

### Claim 2 (depends on 1)

The connection assembly of claim 1, being forward of the center of gravity of the engine.

### Claim 3 (depends on 1)

The connection assembly of claim 1, wherein an inclination direction of the connection piece defines an acute angle with the axial direction.

### Claim 4 (depends on 1)

The connection assembly of claim 1, wherein the engine coupling piece is coupled to the fan case of the engine.

### Claim 5 (depends on 1)

The connection assembly of claim 1, wherein the connection piece is connected with an aircraft.

### Claim 6

An engine mounting system, comprising:
a mounting structure and the mounting structure is a pylon;
an engine defining a centerline that defines an axial direction extending from a forward end to an aft end, the engine having a center of gravity and mountable to the mounting structure;
a connection assembly, comprising:
an engine coupling piece coupled to an aft portion of a fan case of the engine, wherein the engine coupling piece comprises a pair of lugs defining a cavity therebetween opening in the axial direction; and
a connection piece including a link connecting the engine coupling piece and the pylon, the connection piece inclined toward the axial direction, wherein the link has a first end connected with the engine coupling piece, a second end opposite to the first end and connected with the mounting structure, and a beam between the first end and the second end and curved toward the axial direction, and the engine coupling piece configured such that force transferred from the aft portion of the fan case to the mounting structure is to be transmitted from the aft portion of the fan case to the connecting piece to the engine coupling piece and to the mounting structure;
an engine aft mount located aftward of the connection assembly and coupling the engine and the mounting structure; and
a thrust link located between the connection assembly and the engine aft mount and coupling the engine and the mounting structure.

### Claim 7 (depends on 6)

The engine mounting system of claim 6, wherein the connection assembly is forward of the center of gravity of the engine.

### Claim 8 (depends on 6)

The engine mounting system of claim 6, wherein an inclination direction of the connection piece defines an acute angle with the axial direction.

### Claim 9 (depends on 6)

The engine mounting system of claim 6, the engine coupling piece is coupled to the fan case of the engine.

### Claim 10 (depends on 6)

The engine mounting system of claim 6, wherein the connection piece is connected with an aircraft.