公开(公告)号：US20180010479A1

公开(公告)日：2018-01-11

申请号：US15622659

申请日：2017-06-14

Applicant: ROLLS-ROYCE plc

Inventor： John R. MASON ,  David E. BROWN

IPC: F01D21/00 ,  F01D21/02 ,  F01D5/06 ,  G01P3/481 ,  F02C9/28

CPC classification number: F01D21/003 ,  F01D5/06 ,  F01D21/02 ,  F02C9/28 ,  F05D2220/32 ,  F05D2220/329 ,  G01P3/481

Abstract: A turbine arrangement for a gas turbine engine comprising a turbine shaft. An axial array of turbine rotors, having a first axial end and a second axial end. A drive arm coupled between the turbine shaft and the first axial end. A measurement system arranged to measure a parameter of the turbine arrangement, the measurement system positioned at the second axial end. The parameter may be rotational speed.

公开(公告)号：US20190316522A1

公开(公告)日：2019-10-17

申请号：US16382832

申请日：2019-04-12

Applicant: Rolls-Royce Deutschland Ltd & Co KG ,  Rolls-Royce plc

Inventor： Stefan MENCZYKALSKI ,  Stephan UHKOETTER ,  John R. MASON ,  David A. EDWARDS ,  Neil DAVIES ,  Lynn HAMMOND ,  David WILLIAMS

IPC: F02C7/06 ,  F02C3/04

Abstract: A gas turbine engine for an aircraft including a unit supplied with oil from a first oil circuit and a second oil circuit. The first oil circuit and the second oil circuit each are fluidly coupled with at least one inlet and with at least one outlet of the unit and with at least one inlet and with at least one outlet of an oil tank. The first oil circuit and the second oil circuit are configured to receive oil from the oil tank and to direct the received oil to the unit. The oil tank is incorporating offset outlets to each of the oil circuits. The offset outlet of the second oil circuit is positioned higher in the oil tank than the offset outlet of the first oil circuit.

公开(公告)号：US20190323433A1

公开(公告)日：2019-10-24

申请号：US16379915

申请日：2019-04-10

Applicant: ROLLS-ROYCE plc

Inventor： Clare L. BEWICK ,  Zahid M. HUSSAIN ,  David P. SCOTHERN ,  John R. MASON

IPC: F02C7/18 ,  F02C3/06

Abstract: A gas turbine engine (10) comprising: an engine core (11), comprising a compressor (14, 15); an outer casing (25A) separating the engine core (11) from a bypass airflow; a compressor bleed valve (50) in communication with the compressor (14, 15) and configured to release bleed air from the compressor (14, 15); a bleed air duct (51) connected to the compressor bleed valve (50) and configured to eject the bleed air released by the compressor bleed valve (50) into an airflow at a location radially inward of the outer casing (25A).

公开(公告)号：US20190316488A1

公开(公告)日：2019-10-17

申请号：US16382923

申请日：2019-04-12

Applicant: Rolls-Royce Deutschland Ltd & Co KG ,  Rolls-Royce plc

Inventor： Stefan MENCZYKALSKI ,  Stephan UHKOETTER ,  John R. MASON ,  David A. EDWARDS ,  Neil DAVIES ,  Lynn HAMMOND ,  David WILLIAMS

IPC: F01D25/20 ,  F02C7/36 ,  F02C7/06 ,  F02C7/14

Abstract: A gas turbine engine includes a gearbox receiving input from a core shaft and driving a fan at a lower speed than the core shaft. First and second oil circuits fluidly couple with an inlet and outlet of the gearbox. A third oil circuit fluidly couples with an inlet and outlet of the gearbox. The outlet of the gearbox includes a device directing oil from the gearbox to the first oil circuit, to the second oil circuit and to the third oil circuit when feeding to the gearbox exceeds a predefined oil flow rate, or deviates an operational value corresponding with that oil flow rate, and directs oil from the gearbox to the third oil circuit when feeding to the gearbox is the predefined flow rate or is a corresponding operational value or is greater than or equal to a further corresponding operational value.

公开(公告)号：US20190292937A1

公开(公告)日：2019-09-26

申请号：US16294144

申请日：2019-03-06

Applicant: ROLLS-ROYCE plc

Inventor： John R. MASON

IPC: F01D21/14 ,  F01D25/20 ,  F02C7/22 ,  F02C7/32

Abstract: The present disclosure relates to an oil/fuel pump system for an accessory gear box of a gas turbine engine. The system comprises an oil pump, the oil pump having an oil pump shaft that can be operatively coupled to the drive shaft, and a fuel pump, the fuel pump having a fuel pump shaft. The fuel pump shaft is operatively coupled to the oil pump shaft such that the fuel pump is only operational when the oil pump is operational.