US 9,809,317 B2Granted

Engine mount

AssigneeROLLS-ROYCE plc

InventorsRichard Geoffrey Stretton, Kenneth Franklin Udall

Life of this patent

Estimating the term…

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Abstract

An aircraft including a pylon attached to a gas turbine engine and a mounting system attaching the engine to the pylon. The mounting system including a first and a second frame each of three elongate members arranged in a triangle, each frame respectively arranged such that a core of the engine is positioned extending through an area defined between the three elongate members of each frame. Each frame forming at least part of a load bearing connection between the pylon and the engine. Each frame consisting of two portions, each portion corresponding to each side of the engine as attached to the pylon. The triangle formed by each frame being symmetrical about a plane separating the two portions. The engine is attached to the mounting system such that both frames are positioned axially forward of a radially extending projection of a first turbine stage in the core.

Claims12

Dependent claims

An aircraft comprising:

a pylon;
a gas turbine engine attached to the pylon;
and
a mounting system attaching the gas turbine engine to the pylon, the mounting system including:
a first frame of three elongate members arranged in a triangle, the first frame being arranged such that a core of the gas turbine engine is positioned extending through an area defined between the three elongate members of the first frame, the first frame forming at least part of a load bearing connection between the pylon and the gas turbine engine, the first frame consisting of two portions, each portion respectively corresponding to each side of the gas turbine engine as attached to the pylon at a location of the first frame, the triangle formed by the first frame being symmetrical about a first plane separating the two portions of the first frame;
and
a second frame of three elongate members arranged in a triangle, the second frame being arranged such that the core of the gas turbine engine is positioned extending through an area defined between the three elongate members of the second frame, the second frame forming at least part of the load bearing connection between the pylon and the gas turbine engine, the second frame consisting of two portions, each portion respectively corresponding to each side of the gas turbine engine as attached to the pylon at a location of the second frame, the triangle formed by the second frame being symmetrical about a second plane separating the two portions of the second frame wherein
the gas turbine engine is attached to the mounting system such that both of the first frame and the second frame are positioned axially forward of a radially extending projection of a first turbine stage in the core of the gas turbine engine.

5 more elements

Dependencies are inferred from the claim text.

Facts

Application: 14/543,402Filed 17 Nov 2014
Priority: GB 1322077.713 Dec 2013
Published: US 2016/0167797 A116 Jun 2016
Granted: 7 Nov 2017
Term ends: Not estimatedThe source records don’t support an estimate.

Classification8 codes

F02C 7/20
Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for…:…
B64D 27/10
Aircraft characterised by the type or position of power plants: of gas-turbine type
B64D 27/402
Arrangements for mounting power plants in aircraft: comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant
F05D 2220/325
In gas turbines: to drive unshrouded, high solidity propeller