公开(公告)号：US11761448B2

公开(公告)日：2023-09-19

申请号：US16395996

申请日：2019-04-26

Applicant: ROLLS-ROYCE plc

Inventor： Giles E Harvey

IPC: F04D25/06 ,  B64D27/24 ,  B64D35/02

CPC classification number: F04D25/06 ,  B64D27/24 ,  B64D35/02

Abstract: The present disclosure concerns an electric aircraft propulsion system. Example embodiments include an aircraft propulsion system (200) comprising: a fan (213) mounted on a central shaft (214); a first electric motor (215) mounted on the central shaft (214) and arranged to drive rotation of the fan (213) via the central shaft; and a second electric motor (216) arranged to drive rotation of the fan (213) via the central shaft (214), wherein the second electric motor (216) is coaxially mounted downstream of the first electric motor (215) and an outer diameter (D2) of the second electric motor (216) is smaller than an outer diameter (D1) of the first electric motor (215).

公开(公告)号：US11761380B2

公开(公告)日：2023-09-19

申请号：US17484873

申请日：2021-09-24

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C Wong ,  Thomas S Binnington ,  David A Jones ,  Daniel Blacker

IPC: F02C7/14

CPC classification number: F02C7/14 ,  F05D2260/213 ,  F05D2270/20

Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly includes a plurality of fan blades defining a fan diameter, and the heat exchanger module is in fluid communication with the fan assembly by an inlet duct. The heat exchanger module includes a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. At full-power condition, the engine produces a maximum thrust T (N), the heat exchanger module transfers a maximum heat rejection H (W) from the first fluid to the airflow, and a Heat Exchanger Performance parameter PEX (W/N) defined as PEX=H/T is 0.4 to 6.0.

公开(公告)号：US20230286658A1

公开(公告)日：2023-09-14

申请号：US18170604

申请日：2023-02-17

Applicant: ROLLS-ROYCE plc

Inventor： Graeme E F SUTCLIFFE ,  Richard G MOCHRIE ,  Jade WHITTLE

IPC: F02K7/16 ,  F02C7/04

CPC classification number: F02K7/16 ,  F02C7/04 ,  F05D2220/10 ,  F05D2220/323 ,  F05D2240/10 ,  F05D2260/213

Abstract: A ram-air duct system includes a ram-air duct configured to receive a flow of ram-air from a ram-air inlet and discharge the flow to a ram-air outlet. The system also includes a heat exchanger configured to exchange heat with air within the ram-air duct, an auxiliary air passageway and an electrically-driven air mover configured to move a flow of auxiliary air along the auxiliary air passageway for discharge into the ram-air duct through an intermediate inlet between the ram-air inlet and the ram-air outlet. The air duct system further includes a controller configured to selectively operate the ram-air duct system in an auxiliary supply mode in which the air mover and/or a control valve are controlled to cause the flow of auxiliary air to be discharged into the duct through the intermediate inlet, to thereby control a rate of heat exchange between the heat exchanger and air within the duct.

公开(公告)号：US11752544B2

公开(公告)日：2023-09-12

申请号：US17519207

申请日：2021-11-04

Applicant: ROLLS-ROYCE PLC

Inventor： Rui Yang ,  Yuyou Cui ,  Paul A Withey ,  Nicholas Green ,  Feiyang Liu

IPC: B22D13/10

CPC classification number: B22D13/101

Abstract: A centrifugal casting apparatus comprising an upper portion into which molten material is poured, the upper portion having a central rotational axis about which the apparatus is rotated; at least one block runner is connected to the upper portion at the proximal end of the block runner and to at least one mould at the distal end of the block runner, the block runner being mounted substantially perpendicular to the axis of rotation; and wherein the moulds are oriented substantially parallel to the axis of rotation of the centrifugal casting apparatus.

公开(公告)号：US20230280032A1

公开(公告)日：2023-09-07

申请号：US18176784

申请日：2023-03-01

Applicant: ROLLS-ROYCE plc

Inventor： Nathan CLARK ,  Robert J. MILLER ,  Chloe J PALMER ,  Jacopo TACCONI

IPC: F23R3/00 ,  F02C7/224 ,  F02C7/36

CPC classification number: F23R3/005 ,  F02C7/224 ,  F02C7/36 ,  F05D2260/40311

Abstract: A combined cycle engine is formed of a gas turbine cycle coupled with a fuel expansion cycle in which fuel for the gas turbine cycle is the working fluid of the fuel expansion cycle. The fuel expansion cycle comprises, in flow series, a fuel pump for pumping a cryogenic fuel for the gas turbine cycle, a first heat exchanger for heating the fuel, an expander to recover power by expansion of the fuel and to thereby drive a load, and a second heat exchanger to reheat the fuel. The gas turbine cycle comprises, in flow series, a compressor, a combustor for combustion of reheated fuel delivered from the second heat exchanger, and a turbine configured to drive the compressor. The first heat exchanger and the second heat exchanger are stationed downstream of the combustor and configured to transfer heat from combustion products to the fuel in the fuel expansion cycle.

公开(公告)号：US20230279813A1

公开(公告)日：2023-09-07

申请号：US18166285

申请日：2023-02-08

Applicant: ROLLS-ROYCE plc

Inventor： Richard G.. Mochrie ,  David A. Jones ,  Gordon Illing

IPC: F02C7/224

CPC classification number: F02C7/224 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/213 ,  F05D2270/07

Abstract: There is provided a fuel management system for a gas turbine engine. The fuel management system comprises: a fuel tank configured to store fuel for the gas turbine engine; a fuel supply line configured to supply fuel from the fuel tank to a combustor of the gas turbine engine; a reheat fuel supply line configured to supply fuel from the fuel tank to a reheat of the gas turbine engine, the reheat fuel supply line extending from a reheat branching point on the fuel supply line to the reheat; a fuel supply pump disposed along the fuel supply line upstream of the reheat branching point; a reheat pump disposed along the reheat fuel supply line, the reheat pump configured to pressurise fuel to a reheat delivery pressure for delivery to the reheat; and a reheat recirculation line configured to recirculate fuel from the reheat fuel supply line to a location upstream of the fuel supply pump, the reheat recirculation line extending from a reheat recirculation branching point on the reheat fuel supply line downstream of the reheat pump.

公开(公告)号：US20230279812A1

公开(公告)日：2023-09-07

申请号：US18166253

申请日：2023-02-08

Applicant: ROLLS-ROYCE plc

Inventor： Richard G. MOCHRIE ,  Graeme E F SUTCLIFFE ,  Jade WHITTLE

IPC: F02C9/28 ,  F02C7/224 ,  F02C7/16

CPC classification number: F02C9/28 ,  F02C7/224 ,  F02C7/16 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/213 ,  F05D2260/232

Abstract: A fuel management system for a gas turbine engine, the fuel management system comprising a fuel supply line configured to supply fuel from a system inlet to a combustor of the gas turbine engine via a combustor pump and combustor valve. A heat exchanger is configured to reject heat from a thermal load of the gas turbine engine to fuel in the fuel supply line between the system inlet and the combustor valve. There is a downstream recirculation line configured to recirculate a downstream excess portion of fuel from the fuel supply line, the downstream recirculation line extending from a downstream recirculation point on the fuel supply line between the heat exchanger and the combustor valve.

公开(公告)号：US20230278721A1

公开(公告)日：2023-09-07

申请号：US18165061

申请日：2023-02-06

Applicant: ROLLS-ROYCE plc

Inventor： David R TRAINER ,  Francisco Javier CHIVITE ZABALZA ,  Ellis F H CHONG

IPC: B64D35/00 ,  B64D27/24 ,  B64C29/00 ,  B60L50/60 ,  H02P5/74

CPC classification number: B64D35/00 ,  B60L50/60 ,  B64C29/0008 ,  B64D27/24 ,  H02P5/74 ,  B60L2200/10 ,  B60L2210/40 ,  B64D2221/00

Abstract: The disclosure relates to an electric aircraft propulsion assembly for an electric vertical takeoff and landing, eVTOL, aircraft, the assembly comprising: an electric storage unit; a first electric motor connected to power a first propulsor; a first converter configured as a DC:AC converter for driving the first electric motor and a second electric motor connected to power a second propulsor, a second converter. A controller is connected to control operation of the first and second converters and is configured to operate in a first mode in which the first and second converters are operated as DC:AC converters to drive the first and second electric motors and a second mode in which the first converter is operated to drive the first electric motor to power the first propulsor and the second converter is operated to drive the second electric motor to provide a braking torque on the second propulsor.

公开(公告)号：US11746713B2

公开(公告)日：2023-09-05

申请号：US16794620

申请日：2020-02-19

Applicant: ROLLS-ROYCE plc

Inventor： Ibrahim Sanusi ,  Andrew R Mills ,  Derek S Wall

IPC: F02C9/52 ,  F02C9/54

CPC classification number: F02C9/52 ,  F02C9/54 ,  F05D2270/30 ,  F05D2270/303 ,  F05D2270/44

Abstract: A control system of a gas turbine engine is provided. The engine has a fuel flow metering valve which regulates a fuel flow to the engine, and one or more variable geometry components which are movable between different set points to vary an operating configuration of the engine. The control system has an engine fuel control sub-system which provides a fuel flow demand signal for controlling the fuel flow metering valve. The control system further has a variable geometry control sub-system which determines current set points to be adopted by the variable geometry components given the current engine operating condition in order to comply with one or more engine constraints. The control system further has an optimiser that receives the current set points and determines adjusted values of the set points which optimise, while complying with the engine constraints, an objective function modelling a performance characteristic of the engine, the objective function adapting to change in engine performance with time. The control system further has a feedback loop in which the adjusted values of the set points thus-determined are sent to the variable geometry control sub-system to vary the current set points.

公开(公告)号：US11738877B2

公开(公告)日：2023-08-29

申请号：US16832607

申请日：2020-03-27

Applicant: ROLLS-ROYCE plc

Inventor： Steven A Radomski ,  Richard G Stretton

IPC: B64D27/26 ,  F16J15/10 ,  B64C7/00 ,  F01D11/00

CPC classification number: B64D27/26 ,  B64C7/00 ,  F01D11/005 ,  F16J15/102 ,  B64D2027/262 ,  F05D2240/55

Abstract: A seal assembly for a gas turbine engine having a rotor arranged to rotate about an axis in use. The seal assembly has a static support structure for the gas turbine engine and a casing structure of the engine. Rotation of the engine rotor causes a deflection of the casing structure relative to the static support structure in a first direction. A seal is provided at an interface between the static support structure and the casing structure, and comprising a first seal portion and a second seal portion spaced from one another in the first direction. The first seal portion is provided against a first surface of the casing structure and the second seal portion is provided against a second surface of the casing structure opposing the first surface. In an at-rest state in which the engine is not operational, the first and second surfaces are offset from an equilibrium position with respect to the static support structure such that there is a difference in compression of the first seal portion and the second seal portion between the static support structure and the casing structure. The offset is in a direction opposite to the first direction.