US 2017/0370292 A1Published application

Accessory mounting for a gas turbine engine

AssigneeRolls-Royce Deutschland Ltd & Co KG

InventorsJürgen BEIER, Gideon Daniel VENTER

Life of this patent

Estimating the term…

Loading patent…

Abstract

A gas turbine engine assembly is connected to a pylon for mounting the gas turbine engine to an aircraft. The assembly has a frame supporting at least one accessory independently of the gas turbine engine. Frame is attached to the pylon at forward and rearward engine mounting locations. The frame includes at least one hollow tube and at least one hollow tube is fluid tight. The one hollow tube is evacuated or contains pressurised fluid and a pressure sensor is provided to detect a change in pressure in the at least one hollow tube to determine if there is a leak in the at least one hollow tube and hence if the frame is damaged. This ensures that the frame may be repaired or replaced before there is a loss of operation of one or more of the accessories which may result in a failure of the gas turbine engine.

Claims2

Dependent claims

A gas turbine engine assembly connected to a pylon structure for mounting the gas turbine engine to an aircraft,

the gas turbine engine assembly having a frame supporting at least one accessory independently of the gas turbine engine,
the frame being attached to the pylon structure at a forward engine mounting location, the frame having a pair of front struts, each strut of the pair of front struts having a first end adjacent the forward engine mounting location and a second end remote from the forward engine mounting location, each strut of the pair of front struts passing the engine on opposing sides,
the at least one accessory being mounted at the second end of the pair of front struts, the pair of forward struts providing a direct load path between the at least one accessory and the forward engine mounting location,
the frame comprising at least one hollow tube, the at least one hollow tube being fluid tight, the at least one hollow tube being evacuated or containing pressurised fluid, and
a pressure sensor being arranged to detect a change in the pressure in the at least one hollow tube to determine if there is a leak in the at least one hollow tube and hence if the frame is damaged.

2 more elements

Dependencies are inferred from the claim text.

Facts

Application: 15/681,106Filed 18 Aug 2017
Priority: GB 1311072.121 Jun 2013
Published: 28 Dec 2017
Term ends: Not estimatedThe source records don’t support an estimate.

Classification13 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 27/402
Arrangements for mounting power plants in aircraft: comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant
B64D 27/404
Arrangements for mounting power plants in aircraft: suspension arrangements specially adapted for supporting vertical loads
B64D 27/406
Arrangements for mounting power plants in aircraft: suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links

Family

Application14/300,543Continuation · filed 10 Jun 2014
Application15/681,106Continuation
US 10,309,311 B2Related patent
US 2014/0373555 A1Published application
US 9,765,696 B2Related patent
US 2017/0370292 A1This patent

From the US filing history. Foreign family members aren’t listed.