Jet engine with a linking device

Patent metadata

Field	Value
Publication number	US-11077955-B2
Application number	US-201816159076-A
Country	US
Kind code	B2
Filing date	Oct 12, 2018
Priority date	Oct 16, 2017
Publication date	Aug 3, 2021
Grant date	Aug 3, 2021

Abstract

A jet engine with a linking device for linking the jet engine at an element of an aircraft optionally in a first mounting position and at least one second mounting position, and with at least one operating equipment appliance that has a first fluid area and a second fluid area. In the first mounting position, the first fluid area is assigned to a first functionality and the second fluid area is assigned to a second functionality. In the second mounting position, the fluid areas are assigned to the respectively other functionality. What is further described is an aircraft with at least one such jet engine.

First claim

The invention claimed is:

1. A jet engine comprising:
an attachment member for linking the jet engine at an element of an aircraft in a first mounting position and a second mounting position,
an operating equipment appliance which has a first fluid area and a second fluid area for connect to the aircraft,
wherein, in the first mounting position the first fluid area is assigned to a first functionality and the second fluid area is assigned to a second functionality,
wherein, in the second mounting position, the first fluid area is assigned to the second functionality and the second fluid area is assigned to the first functionality.

2. The jet engine according to claim 1 , wherein the fluid areas are assigned to re-circulation and venting as functionalities.

3. The jet engine according to claim 1 , wherein the fluid areas have conduit areas that are arranged at a distance to each other in a circumferential direction of the jet engine, wherein the conduit areas are arranged so as to be symmetrical to the attachment member in the circumferential direction of the jet engine.

4. The jet engine according to claim 1 , wherein the attachment member includes two engine attachment points, wherein the attachment member is connected to a carrier structure of the jet engine in an area of the engine attachment points.

5. The jet engine according to claim 4 , wherein the attachment member comprises an interface device to the aircraft positioned centrally to the two engine attachment points in the circumferential direction.

6. The jet engine according to claim 1 , and further comprising two lifting points configured for mounting the jet engine distributed in a circumferential direction of the jet engine, wherein the lifting points are arranged to be symmetrical to the interface device in the circumferential direction.

7. The jet engine according to claim 1 , and further comprising a support strut extending in a radial direction through a bypass channel of the jet engine, wherein the fluid areas extend inside the support strut.

8. The aircraft with a jet engine according to claim 1 , and further comprising a radially outer engine cladding and an auxiliary device gear appliance that comprises multiple auxiliary devices and that is configured to be driven by an auxiliary shaft that is in operative connection with an engine shaft that rotates about a central axis, wherein the auxiliary device gear appliance is arranged in a radial direction of the jet engine substantially outside the outer engine cladding of the jet engine.

9. The aircraft according to claim 8 , wherein the auxiliary device gear appliance is linked to a frame appliance that is directly connected to at least one chosen from an aircraft fuselage and an aircraft wing.

10. The aircraft according to claim 9 , wherein the frame appliance is arranged at least partially inside an engine pylon that is assigned to the jet engine.

11. The aircraft according to claim 9 , wherein the frame appliance has linking elements for at least one chosen from the auxiliary devices, a conduit, a tube and a wiring harness.

12. The aircraft according to claim 8 , wherein the auxiliary device gear appliance is arranged at least partially inside at least one chosen from an aircraft fuselage, an engine pylon and an aircraft wing.

13. The aircraft according to claim 12 , wherein the auxiliary shaft that drives the auxiliary device gear appliance extends through a support strut of the jet engine, with the jet engine being linked to the at least one chosen from the aircraft fuselage, the engine pylon, and the aircraft wing in an area of the support strut.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Venter Gideon Daniel
• Schacht Michael

Classifications

• B64D27/402

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• B64D27/20 Primary

  within, or attached to, fuselages · CPC title

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F05D2240/90

  Mounting on supporting structures or systems · CPC title

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title