# US 11,440,669 B2 · Integrated support structure for an aircraft engine and its auxiliary components

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- Number: US 11,440,669 B2
- Document ID: US11440669B2
- Status: Granted
- Kind: B2
- Application number: 16/210,919
- Filed: 2018-12-05
- Published: 2019-06-06
- Granted: 2022-09-13
- Earliest claimed: 2017-12-06
- Assignees: Rolls-Royce Deutschland Ltd & Co KG
- Applicants: Rolls-Royce Deutschland Ltd & Co KG
- Inventors: Carsten Buchholz
- Web page: https://patentgrep.com/patent/US11440669B2

## CPC

- F01D 25/28: Supporting or mounting arrangements, e.g. for turbine casing
- B64C 1/16: specially adapted for mounting power plant
- B64D 27/14: within, or attached to, fuselages
- B64D 27/20: within, or attached to, fuselages
- B64D 27/402: {comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant}
- F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep
- F02C 7/32: Arrangement, mounting, or driving, of auxiliaries
- F05D 2240/90: Mounting on supporting structures or systems
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- B64C: AEROPLANES; HELICOPTERS
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A supporting structure arrangement for fastening an aircraft gas turbine engine to an aircraft, including: a supporting structural element of the aircraft engine and a supporting structure with at least one support and at least one bearing, by means of which the support can be connected or is connected to the aircraft, wherein the support can be connected or is connected rigidly to the supporting structural element of the aircraft engine by means of a connecting device.

## Claims

### Claim 1

An aircraft comprising:
a fuselage with an outer shell and a pocket set inwardly from the outer shell of the fuselage of the aircraft;
an aircraft engine;
a supporting structure arrangement for fastening the aircraft engine to the aircraft, comprising:
a core engine of the aircraft engine, the core engine including a supporting structural element,
a supporting structure configured to be a primary bad support of the aircraft engine with respect to the aircraft, the supporting structure including an engine side connected to the supporting structural element and an aircraft side connected to the aircraft, the supporting structure including at least one support and at least one bearing,
at least one connecting device at the engine side rigidly connecting the support to the supporting structural element of the core engine, the connecting device including a surface that at least partially surrounds the core engine and lies flat against the supporting structural element of the core engine;
wherein the at least one support includes two spaced-apart supports;
wherein, with the two spaced-apart supports connected to the aircraft engine, the at least one bearing of one of the two spaced-apart supports is positioned at a distance from the at least one bearing of another of the two spaced-apart supports, the distance being greater than a length of at least one chosen from the core engine and a casing of the aircraft engine:
the aircraft engine being fastened by the supporting structure of the supporting structure arrangement to the fuselage of the aircraft:
wherein the at least one bearing comprises at least one fastening point, which is fixedly connected to the fuselage of the aircraft and which is arranged in the pocket set inwardly from the outer shell of the fuselage of the aircraft;
wherein at least one accessory component of the aircraft engine is arrange in an installation space between the two supports, entirely outside the casing of the aircraft engine and at least partially within the pocket set inwardly from the outer shell of the fuselage of the aircraft.

### Claim 2 (depends on 1)

The aircraft according to claim 1, wherein the at least one bearing includes two bearings, each of the two bearings having at least one degree of freedom.

### Claim 3 (depends on 1)

The aircraft according to claim 1, wherein the at least one bearing includes two bearings for connecting the support to the aircraft, a distance of which from one another is greater than a minimum diameter of the supporting structure between the aircraft engine and the aircraft in a direction parallel to a direct connecting line between the two bearings.

### Claim 4 (depends on 1)

The aircraft according to claim 1, wherein the two supports are spaced apart in an axial direction of the aircraft and the at least one accessory component of the aircraft engine is arranged between the two spaced-apart supports.

### Claim 5 (depends on 4)

The aircraft according to claim 4, wherein the at least one accessory component comprises at least one chosen from a gearbox, an arrangement of lines, a supply device and a control computer.

### Claim 6 (depends on 4)

The aircraft according to claim 4, and further comprising an installation frame, which is arranged between the two spaced-apart supports and to which the at least one accessory component is fastened.

### Claim 7 (depends on 6)

The aircraft according to claim 6, and further comprising at least one shock absorber mounting the installation frame on at least one chosen from the aircraft engine, the supporting structure and the aircraft.

### Claim 8 (depends on 1)

The aircraft according to claim 1, wherein the at least one bearing comprises at least one chosen from a shock absorber and an elastic element arranged in a load path of the supporting structure between the aircraft engine and the aircraft.

### Claim 9 (depends on 1)

The aircraft according to claim 1, wherein the at least one accessory component comprises at least one chosen from a gearbox, an arrangement of lines, a supply device and a control computer.

### Claim 10

A supporting structure arrangement for fastening an aircraft engine to an aircraft having a fuselage with an outer shell, comprising:
a core engine of the aircraft engine, the core engine including a supporting structural element,
a supporting structure configured to be a primary load support of the aircraft engine with respect to the aircraft, the supporting structure including an engine side connected to the supporting structural element and an aircraft side connected to the aircraft, the supporting structure including at least one support and at least one bearing,
at least one connecting device at the engine side rigidly connecting the support to the supporting structural element of the core engine, the connecting device including a surface that at least partially surrounds the core engine and lies flat against the supporting structural element of the core engine;
wherein the at least one support includes two supports spaced apart from one another in an axial direction of the aircraft and defining an installation space therebetween positioned entirely outside an external casing of the engine and at least partially within a pocket set inwardly from the outer shell of the fuselage of the aircraft; and
at least one accessory component of the aircraft engine being arranged in the installation space between the two supports, entirely outside the external casing of the engine and at least partially within the pocket set inwardly from the outer shell of the fuselage of the aircraft.

### Claim 11 (depends on 10)

The supporting structure arrangement according to claim 10, wherein the at least one accessory component comprises at least one chosen from a gearbox, an arrangement of lines, a supply device and a control computer.