Gas turbine engine and aircraft with a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2021404387-A1
Application number	US-202117362514-A
Country	US
Kind code	A1
Filing date	Jun 29, 2021
Priority date	Jun 30, 2020
Publication date	Dec 30, 2021
Grant date	—

Abstract

A gas turbine engine including an engine core and including a bypass channel of an aircraft is described. The bypass channel radially surrounds the engine core at least in part. At least one core shaft extending in the axial direction is provided, which shaft is operatively connected, by means of a drive train, to a core accessory gearbox arranged between the engine core and the bypass channel, and to an aircraft accessory gearbox. The aircraft accessory gearbox is arranged radially outside the bypass channel. The drive train extends substantially in the radial direction between the core shaft and the aircraft accessory gearbox. The drive train has an angle drive between a radial shaft and the core shaft. Furthermore, the drive train comprises another angle drive between the radial shaft and the core accessory gearbox and an additional angle drive between the radial shaft and the aircraft accessory gearbox.

First claim

1 . A gas turbine engine, comprising an engine core and comprising a bypass channel which radially surrounds the engine core at least in part,
wherein at least one core shaft extending in the axial direction is provided, wherein the core shaft is operatively connected to a core accessory gearbox arranged between the engine core and the bypass channel and to an aircraft accessory gearbox by means of a drive train, wherein the aircraft accessory gearbox is arranged radially outside the bypass channel, wherein the drive train extends substantially in the radial direction between the core shaft and the aircraft accessory gearbox, wherein the drive train has an angle drive between a radial shaft and the core shaft, and wherein the drive train comprises another angle drive between the radial shaft and the core accessory gearbox and an additional angle drive between the radial shaft and the aircraft accessory gearbox.

2 . The gas turbine engine according to claim 1 , wherein the radial shaft is formed as a single piece.

3 . The gas turbine engine according to claim 1 , wherein the radial shaft has at least two radial shaft portions which are arranged coaxially with one another and one behind the other in the radial direction at least in some regions and are interconnected for conjoint rotation.

4 . The gas turbine engine according to claim 1 , wherein engine accessories are substantially operatively connected to the drive train by means of the core accessory gearbox, which engine accessories are provided to carry out functions of the gas turbine engine and are arranged between the engine core and the bypass channel.

5 . The gas turbine engine according to claim 1 , wherein aircraft accessories are substantially operatively connected to the drive train by means of the aircraft accessory gearbox, which aircraft accessories are provided to carry out functions of an aircraft which is configured with the gas turbine engine, the aircraft accessories being arranged radially outside the bypass channel.

6 . The gas turbine engine according to claim 1 , wherein the core accessory gearbox and the aircraft accessory gearbox overlap at least in regions of connection to the drive train in the circumferential direction of the gas turbine engine.

7 . The gas turbine engine according to claim 1 , wherein the aircraft accessory gearbox is arranged in the circumferential direction at least in part in a region of the gas turbine engine in which the gas turbine engine comprises means which are designed to connect the gas turbine engine to an aircraft, the region of the gas turbine engine overlapping a fuselage of the aircraft when the engine is installed on the aircraft.

8 . The gas turbine engine according to claim 1 , wherein the core accessory gearbox is designed to transmit a torque and to drive an oil pump, a fuel pump, an air/oil separator and/or a permanent magnet alternator.

9 . The gas turbine engine according to claim 1 , wherein the aircraft accessory gearbox is designed to transmit a torque and to drive a pneumatic air turbine starter, a hydraulic pump and/or an alternator.

10 . The gas turbine engine according to claim 1 , wherein the aircraft accessory gearbox is designed to transmit a torque and to drive an electric machine, the electric machine being arranged radially outside the bypass channel and designed, during motor operation, to start the gas turbine engine and to generate electrical energy during alternator operation.

11 . The gas turbine engine according to claim 1 , wherein an electrically operable hydraulic pump is connected to the electric machine radially outside the bypass channel and can receive electrical energy from this machine.

12 . The gas turbine engine according to claim 1 , wherein the core accessory gearbox is arranged in the axial direction in the region of a rear side of a front engine frame between the engine core and the bypass channel.

13 . The gas turbine engine according to claim 1 , wherein the aircraft accessory gearbox comprises a separate oil system which is designed to supply the aircraft accessory gearbox with oil.

14 . An aircraft, comprising at least one gas turbine engine according to claim 1 , wherein the gas turbine engine is arranged on the fuselage or in the fuselage of the aircraft, and wherein the aircraft accessory gearbox and the aircraft accessories which are operatively connected thereto are arranged radially outside the bypass channel in a region of overlap between the gas turbine engine and the fuselage.

15 . The aircraft according to claim 14 , wherein the aircraft accessory gearbox and the aircraft accessories which are operatively connected thereto are arranged radially in an engine nacelle, in part radially in the engine nacelle and in part radially outside the engine nacelle in an engine pylon and/or the fuselage or radially outside the engine nacelle in the engine pylon and/or in the fuselage.

16 . The aircraft according to claim 14 , wherein the electric machine is arranged so as to be radially aligned with the radial shaft in the engine nacelle, in the engine pylon and/or in the fuselage.

17 . The aircraft according to claim 14 , wherein in each case one gas turbine engine is provided at least on both sides of the fuselage, the aircraft accessory gearbox and the core accessory gearbox each being arranged in the circumferential direction of the gas turbine engines in such a way that the core accessory gearbox and engine accessories operatively connected thereto is shielded against components which, in the event of damage, escape from a gas turbine engine which is arranged on the opposite side of the fuselage with correspondingly high kinetic energy towards the other gas turbine engine by the aircraft accessory gearbox and aircraft accessories connected thereto.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Venter Gideon Daniel
• Schacht Michael
• Kopp Sebastian
• Merz Rüdiger

Classifications

• B64D27/402

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• F02C7/32 Primary

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

• F05D2260/4031

  as in toothed gearing · CPC title