# US 2010/0163671 A1 · A mounting element for a gas turbine engine, and a structure and an aircraft with such a mounting element

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- Number: US 2010/0163671 A1
- Document ID: US20100163671A1
- Status: Published application
- Kind: A1
- Application number: 12/600,534
- Filed: 2008-06-09
- Published: 2010-07-01
- Earliest claimed: 2007-06-08
- Assignees: Volvo Aero Corporation
- Inventors: Jan-Erik Svensson; Roger Sjoqvist
- Web page: https://patentgrep.com/patent/US20100163671A1

## CPC

- B64D 27/404: {Suspension arrangements specially adapted for supporting vertical loads}
- F01D 25/28: Supporting or mounting arrangements, e.g. for turbine casing
- Y02T 50/40: Weight reduction
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A mounting element for transferring loads between a gas turbine engine and an airframe is provided, the mounting element presenting a cylindrical hole for receiving a fastening element, such as a pin or a bolt. The mounting element includes a collapsible element surrounding the hole, and is adapted to operate in a first mode, and to operate, upon a collapse of the collapsible element, in a second mode, in which the stiffness of the mounting element is lower than in the first mode. In a second aspect of the invention the energy absorption capacity of the mounting element is higher in the second mode than in the first mode.

## Claims

### Claim 1

A mounting element for transferring loads between a gas turbine engine and an airframe, the mounting element presenting a cylindrical hole for receiving a fastening element, such as a pin or a bolt, comprising a collapsible element surrounding the hole, the mounting element being adapted to operate in a first mode, and to operate, upon a collapse of the collapsible element, in a second mode, in which the stiffness of the mounting element is lower than in the first mode.

### Claim 2 (depends on 1)

A mounting element according to claim 1, comprising a solid portion surrounding the collapsible element.

### Claim 3 (depends on 1)

A mounting element according to claim 1, comprising a reduced stiffness element surrounding the hole, and being adapted to provide a load path in the second mode.

### Claim 4 (depends on 3)

A mounting element according to claim 3, wherein the reduced stiffness element is provided adjacent to or in the vicinity of the collapsible element.

### Claim 5 (depends on 3)

A mounting element according to claim 3, comprising a solid portion surrounding the collapsible element and the reduced stiffness element.

### Claim 6 (depends on 1)

A mounting element according to claim 1, wherein the collapsible element provides a load path in the second mode, the stiffness of the collapsible element being lower in the second mode than in the first mode.

### Claim 7 (depends on 6)

A mounting element according to claim 6, wherein the collapsible element is adapted to at least partially disintegrate.

### Claim 8 (depends on 7)

A mounting element according to claim 7, wherein the collapsible element comprises a brittle material.

### Claim 9

A mounting element for transferring loads between a gas turbine engine and an airframe, the mounting element presenting a cylindrical hole for receiving a fastening element, such as a pin or a bolt, comprising a collapsible element surrounding the hole, and the mounting element being adapted to operate in a first mode, and to operate, upon a collapse of the collapsible element, in a second mode, in which the energy absorption capacity of the mounting element is higher than in the first mode.

### Claim 10 (depends on 9)

A mounting element according to claim 9, comprising a solid portion surrounding the collapsible element.

### Claim 11 (depends on 9)

A mounting element according to claim 9, comprising an energy absorbing element surrounding the hole, and being adapted to provide a load path in the second mode.

### Claim 12 (depends on 9)

A mounting element according to claim 9, wherein the collapsible element provides a load path in the second mode, the energy absorption capacity of the collapsible element being higher in the second mode than in the first mode.

### Claim 13 (depends on 1)

A structure for transferring loads between a gas turbine engine and an airframe, the structure comprising a mounting element according claim 1, the structure further comprising an auxiliary load transferring element adapted to provide in the second mode a further load path for transferring loads between the gas turbine engine and the airframe.

### Claim 14 (depends on 1)

An aircraft comprising a mounting element according to claim 1.

### Claim 15 (depends on 9)

A structure for transferring loads between a gas turbine engine and an airframe, the structure comprising a mounting element, according claim 9, the structure further comprising an auxiliary load transferring element adapted to provide in the second mode a further load path for transferring loads between the gas turbine engine and the airframe.

### Claim 16 (depends on 9)

An aircraft comprising a mounting element according to claim 9.