公开(公告)号：US11905892B2

公开(公告)日：2024-02-20

申请号：US17101932

申请日：2020-11-23

Applicant: ROLLS-ROYCE plc

Inventor： Vasileios Pachidis ,  Luis E Ferrer-Vidal Espana-Heredia

IPC: F04D27/00 ,  F02C9/16 ,  F01D21/00 ,  G06F30/20

CPC classification number: F02C9/16 ,  F01D21/003 ,  F04D27/001 ,  G06F30/20 ,  F05D2260/81 ,  F05D2270/304 ,  F05D2270/3015 ,  F05D2270/3061 ,  F05D2270/44

Abstract: A method of determining performance characteristics of a flow machine having a rotor interacting with a flow field. The method comprises: receiving performance data for the flow machine comprising data values of a performance parameter of the rotor and mass flow for the flow machine at one or more defined rotor condition, the performance data defining a two-dimensional array of data in which points for a common rotor condition are identifiable; determining or receiving exit mass flow values for the flow downstream of the rotor; and identifying one or more point in the received performance data and interpolating from said one or more point to a corresponding one or more point at a different rotor condition based on a correlation of the exit mass flow values for said points.

公开(公告)号：US20210164402A1

公开(公告)日：2021-06-03

申请号：US17101932

申请日：2020-11-23

Applicant: ROLLS-ROYCE plc

Inventor： Vasileios Pachidis ,  Luis E Ferrer-Vidal Espana-Heredia

IPC: F02C9/16

Abstract: A method of determining performance characteristics of a flow machine having a rotor interacting with a flow field. The method comprises: receiving performance data for the flow machine comprising data values of a performance parameter of the rotor and mass flow for the flow machine at one or more defined rotor condition, the performance data defining a two-dimensional array of data in which points for a common rotor condition are identifiable; determining or receiving exit mass flow values for the flow downstream of the rotor; and identifying one or more point in the received performance data and interpolating from said one or more point to a corresponding one or more point at a different rotor condition based on a correlation of the exit mass flow values for said points.

公开(公告)号：US11472560B2

公开(公告)日：2022-10-18

申请号：US16856442

申请日：2020-04-23

Applicant: ROLLS-ROYCE plc

Inventor： Vasileios Pachidis ,  Salvatore Ippedico

IPC: B64D13/06 ,  B64C9/00 ,  B64C13/24 ,  B64C15/14 ,  B64D13/02 ,  B64D27/10

Abstract: A system for providing active flow control in an aircraft having a gas turbine engine. The system includes an environmental control system that includes a cabin blower system having a compressor operable to compress a fluid delivered by a fan section of the gas turbine engine to generate a pressurised fluid for use by the environmental control system. The environmental control system is fluidicly connected to an active flow control system via a fluid supply line, for allowing the pressurised fluid generated by the compressor to be supplied to the active flow control system so that it can be ejected from the aircraft across an exterior surface of a movable control element of the aircraft.

公开(公告)号：US10012103B2

公开(公告)日：2018-07-03

申请号：US14925149

申请日：2015-10-28

Applicant: ROLLS-ROYCE PLC

Inventor： Vasileios Pachidis ,  Carlos Soria

IPC: F01D17/14 ,  F01D5/14 ,  F01D9/04 ,  F01D25/10 ,  F04D29/56 ,  F04D29/68 ,  F01D17/16

CPC classification number: F01D17/14 ,  F01D5/146 ,  F01D5/148 ,  F01D9/041 ,  F01D17/162 ,  F01D25/10 ,  F04D29/563 ,  F04D29/684 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2250/14 ,  F05D2250/75 ,  F05D2270/17

Abstract: A gas turbine engine variable guide vane has a fixed portion on an upstream side, a movable flap on a downstream side and a transfer slot between a fixed portion trailing surface and a movable flap leading surface. The movable flap has opposite pressure and suction sides along a chord line between leading and trailing edges, and is rotatable about an axis along a movable flap span over a range of angular positions between open and closed. The trailing surface has a substantially U-shaped profile with first and second branches respectively partially around the pressure and suction sides. The transfer slot has inlet and exhaust ports respectively on the pressure and suction sides. In the closed position the suction side contacts the second branch closing the exhaust port, and in the open position the second branch directs a first air flow through the transfer slot tangentially over the suction surface.

公开(公告)号：US11952942B2

公开(公告)日：2024-04-09

申请号：US18199260

申请日：2023-05-18

Applicant: ROLLS-ROYCE plc

Inventor： Vasileios Pachidis ,  David J Rajendran

IPC: F02C7/042 ,  F02K3/06

CPC classification number: F02C7/042 ,  F02K3/06 ,  F05D2240/12 ,  F05D2240/14 ,  F05D2260/606

Abstract: A gas turbine engine includes a core engine casing and a bypass duct defined between a nacelle and the core engine casing. The gas turbine engine further includes a plurality of diverter fences pivotally coupled to the core engine casing. Each diverter fence is pivotable relative to the core engine casing about a pivot axis, which is circumferentially and obliquely inclined with respect to a principal rotational axis. Each diverter fence is configured to move between a first position in which an outboard edge is disposed adjacent to a casing outer surface, and a second position in which the outboard edge is radially spaced apart from the casing outer surface, such that each diverter fence radially extends outwards from the casing outer surface into the bypass duct.

公开(公告)号：US11407507B2

公开(公告)日：2022-08-09

申请号：US16930008

申请日：2020-07-15

Applicant: ROLLS-ROYCE plc

Inventor： Vasileios Pachidis ,  Chana A Saias

IPC: B64C29/00 ,  B64C7/00 ,  B64C9/00 ,  B64C39/06 ,  B64C11/28 ,  B64C39/12

Abstract: A lift rotor arrangement (100) for a VTOL aircraft (200). The lift rotor arrangement (100) comprises: a fairing (6) mounted on a wing segment (10); and first and second rotor blades (17, 18) mounted on a first shaft (4) extending vertically from the fairing (6). The first shaft (4) is movable between an extended position in which the first and second rotor blades (17, 18) are vertically spaced above the wing segment (10) and are rotatable to provide vertical lift, and a retracted position in which the first and second rotor blades (17, 18) are rotationally-fixed with the first rotor blade (17) stowed within the wing segment (10). The blades (17, 18) may be rotatable around an axis substantially perpendicular to the axis of the respective first shaft (4) so as to act as ailerons/elevons in the retracted position.

公开(公告)号：US11913388B2

公开(公告)日：2024-02-27

申请号：US17712924

申请日：2022-04-04

Applicant: ROLLS-ROYCE plc

Inventor： Ibrahim Eryilmaz ,  Vasileios Pachidis

IPC: F02C9/18 ,  F02C7/32 ,  F01D25/36 ,  B64D13/06 ,  B64D27/02 ,  F01D25/34 ,  F01D15/10 ,  F01D21/14 ,  F01D21/12

CPC classification number: F02C9/18 ,  F01D25/36 ,  F02C7/32 ,  B64D2013/0644 ,  B64D2027/026 ,  F01D15/10 ,  F01D21/12 ,  F01D21/14 ,  F01D25/34 ,  F05D2220/76 ,  F05D2260/42

Abstract: A cabin blower for an aircraft, the system comprising: a cabin blower compressor; an electric machine; and a controller configured to control the cabin blower system so that: in a cabin blower mode of operation, the cabin blower compressor is driven by power extracted from one or more spools of a gas turbine engine of the aircraft and provides a flow of air to a cabin of the aircraft. The controller may be further configured to control the system so that: in a rotor bow mitigation mode of operation, the cabin blower compressor is driven by the electric machine using electrical power from an electrical power source and provides a flow of air through a core of the gas turbine engine to remove heat from the core. A method of operating a cabin blower system of an aircraft is also provided.

公开(公告)号：US11852099B1

公开(公告)日：2023-12-26

申请号：US18199245

申请日：2023-05-18

Applicant: ROLLS-ROYCE plc

Inventor： Vasileios Pachidis ,  David J Rajendran

IPC: F02K1/70 ,  F02K3/06 ,  F02K3/075

CPC classification number: F02K1/70 ,  F02K3/06 ,  F02K3/075 ,  F05D2240/14 ,  F05D2260/606

Abstract: A gas turbine engine includes a core engine casing, a bypass duct and a core engine duct. The gas turbine engine further includes a plurality of flaps pivotally coupled to the core engine casing and arranged circumferentially around a principal rotational axis. Each flap extends from a first casing end and is configured to pivotally rotate relative to core engine casing about a pivot axis between a first position and a second position. In the first position, each flap is disposed in a circumferential direction and is radially disposed between a plurality of outlet guide vanes and a plurality of stator vanes. In the second position, each flap is inclined to the first position and extends at least partially into the bypass duct and the core engine duct.

公开(公告)号：US11524778B2

公开(公告)日：2022-12-13

申请号：US17080145

申请日：2020-10-26

Applicant: ROLLS-ROYCE plc

Inventor： Chana A Saias ,  Vasileios Pachidis

IPC: B64C29/00 ,  B64C39/08 ,  B64D27/24 ,  B64D27/02

Abstract: A VTOL aircraft has fixed wings and a rotor blade system for providing lift in active and passive modes thereof. Operation of the rotor blade system may be switched between the active mode in which the rotor blade system is driven by a power system of the aircraft and the passive mode in which the rotor blade system is not driven by the power system, the rotor blade system being configurable to provide lift in the passive mode during forward flight of the aircraft. The rotor blade system provides lift in the passive mode, allowing the fixed wings to be shorter than in the case where the rotor system provides lift during vertical take-off and landing but otherwise has no function, thus providing aircraft which is lighter, more compact and more efficient than similar aircraft of the prior art.