公开(公告)号：US20230407815A1

公开(公告)日：2023-12-21

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 ,  F05D2240/14 ,  F05D2260/606 ,  F02K3/075

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：US20230027032A1

公开(公告)日：2023-01-26

申请号：US17865908

申请日：2022-07-15

Applicant: ROLLS-ROYCE PLC

Inventor： Vasileios PACHIDIS ,  David J RAJENDRAN

IPC: F02K1/66

Abstract: A ducted gas turbine engine comprising a fan and a guide vane downstream of the fan, wherein the fan is a Variable Pitch Fan (VPF) configured to operate in a first position for generating forward thrust and a second position for generating reverse thrust; wherein a duct wall positioned radially outside the Variable Pitch Fan comprises one or more vents extending through the duct wall, and wherein each vent is located forward of the guide vane.

公开(公告)号：US20230374939A1

公开(公告)日：2023-11-23

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 ,  F05D2240/14 ,  F05D2240/12 ,  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：US20210122465A1

公开(公告)日：2021-04-29

申请号：US17080145

申请日：2020-10-26

Applicant: ROLLS-ROYCE plc

Inventor： Chana A. SAIAS ,  Vasileios PACHIDIS

IPC: B64C29/00 ,  B64C11/00 ,  B64C9/00 ,  B64C39/08 ,  B64D27/24 ,  B64D41/00 ,  B64D27/10 ,  B64D35/02

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.

公开(公告)号：US20210031909A1

公开(公告)日：2021-02-04

申请号：US16930008

申请日：2020-07-15

Applicant: ROLLS-ROYCE plc

Inventor： Vasileios PACHIDIS ,  Chana A. SAIAS

IPC: B64C27/473 ,  B64C29/00 ,  B64C7/00 ,  B64C39/06 ,  B64C9/00

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：US20250002160A1

公开(公告)日：2025-01-02

申请号：US18754879

申请日：2024-06-26

Applicant: ROLLS-ROYCE plc

Inventor： Marko BACIC ,  Vasileios PACHIDIS ,  Chana A SAIAS

IPC: B64D13/06 ,  B64D41/00 ,  F02C7/32 ,  F04D17/10 ,  F04D25/02 ,  F04D25/06

Abstract: An aircraft includes a turbofan engine, a cabin blower system and a PEM fuel cell stack. The cabin blower system includes a cabin blower compressor arranged to be driven by mechanical power derived from a shaft of the turbofan engine. A ducting system delivers respective portions of the mass flow rate of compressed air output by the cabin blower system to a cabin space of the aircraft via an air-conditioning unit and to the cathode input of the fuel cell stack. An electric motor receives electrical power from the fuel cell stack and provides mechanical power to the compressor via a drive arrangement of the cabin blower system. Power associated with excess capacity of the cabin blower system is recovered to the cabin blower compressor, thereby mitigating or eliminating the fuel consumption penalty on the turbofan engine associated with the excess capacity.

公开(公告)号：US20220355939A1

公开(公告)日：2022-11-10

申请号：US17712924

申请日：2022-04-04

Applicant: ROLLS-ROYCE plc

Inventor： Ibrahim ERYILMAZ ,  Vasileios PACHIDIS

IPC: B64D13/08 ,  F04D25/06 ,  F04D27/00

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：US20200346762A1

公开(公告)日：2020-11-05

申请号：US16856442

申请日：2020-04-23

Applicant: ROLLS-ROYCE plc

Inventor： Vasileios PACHIDIS ,  Salvatore IPPEDICO

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

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：US20160130973A1

公开(公告)日：2016-05-12

申请号：US14925149

申请日：2015-10-28

Applicant: ROLLS-ROYCE PLC

Inventor： Vasileios PACHIDIS ,  Carlos SORIA

IPC: F01D17/14 ,  F01D25/10 ,  F01D9/04

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.

Abstract translation: 燃气涡轮发动机可变导向叶片具有上游侧的固定部分，下游侧的可动翼片和固定部分后表面与可动翼片前导表面之间的传送槽。 可移动翼片沿着前缘和后缘之间的弦线具有相对的压力和吸力侧，并且在开和关之间的角位置范围内可沿着可移动的翼片跨度绕轴线旋转。 后表面具有基本上U形的轮廓，其中第一和第二分支分别部分地围绕压力侧和吸力侧。 输送槽分别在压力和吸力侧有进气口和排气口。 在关闭位置，吸入侧接触关闭排气口的第二分支，并且在打开位置，第二分支引导第一气流沿切向切向吸引表面。