公开(公告)号：US20220292987A1

公开(公告)日：2022-09-15

申请号：US17672430

申请日：2022-02-15

Applicant: ROLLS-ROYCE plc

Inventor： Marko BACIC ,  Peter A BEECROFT

IPC: G08G5/00 ,  B64D27/24 ,  B64C29/00 ,  B64D13/06 ,  G01W1/02

Abstract: Computer-implemented methods for controlling the operation of aircraft, particularly electric or hybrid electric aircraft, are described. One such method, which may be implemented on a Flight Management System of the aircraft, comprises: receiving weather data indicative of weather conditions between a flight origin and a flight destination of the aircraft; and determining, using a constrained optimization method and a weather data dependent aircraft energy usage model, a three-dimensional flight path for the aircraft from the origin to the destination. The constrained optimization method may determine a flight path constrained by, amongst other things the energy required by an Environmental Control System of the aircraft.

公开(公告)号：US20150308282A1

公开(公告)日：2015-10-29

申请号：US14554094

申请日：2014-11-26

Applicant: ROLLS-ROYCE PLC

Inventor： Marko BACIC ,  Leo Vivian LEWIS ,  Robert John IRVING

IPC: F01D11/24 ,  F01D25/24 ,  F01D25/12 ,  F01D9/02 ,  F01D5/06

CPC classification number: F01D11/24 ,  F01D5/06 ,  F01D9/02 ,  F01D25/12 ,  F01D25/24 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/20

Abstract: A gas turbine engine comprising first and second axially spaced turbine rotor stages (46, 48) and a turbine casing (56) radially outside the rotor stages. A first seal segment arrangement (58) forms a cavity (64) radially between the first turbine rotor stage (46) and the turbine casing (56). A first air source (82) is coupled to the first seal segment arrangement (58). A second seal segment arrangement (70) forms a cavity (74) radially between the second turbine rotor stage (48) and the turbine casing (56). A heating chamber (84) is provided radially between the second seal segment arrangement (70) and the turbine casing (56). A duct (86) is coupled between the first air source (82) and the heating chamber (84).

Abstract translation: 一种燃气涡轮发动机，包括第一和第二轴向间隔开的涡轮转子级（46,48）和在转子级的径向外侧的涡轮机壳体（56）。 第一密封段装置（58）在第一涡轮转子级（46）和涡轮壳体（56）之间径向形成空腔（64）。 第一空气源（82）联接到第一密封段装置（58）。 第二密封段装置（70）在第二涡轮转子级（48）和涡轮壳体（56）之间径向形成空腔（74）。 加热室（84）径向地设置在第二密封段装置（70）和涡轮壳体（56）之间。 管道（86）联接在第一空气源（82）和加热室（84）之间。

公开(公告)号：US20140208768A1

公开(公告)日：2014-07-31

申请号：US13719899

申请日：2012-12-19

Applicant: ROLLS-ROYCE PLC

Inventor： Marko BACIC

IPC: F02C7/18 ,  F01D25/12

CPC classification number: F02C7/185 ,  F01D5/082 ,  F01D25/12 ,  F05D2260/201 ,  F05D2260/213 ,  Y02T50/673 ,  Y02T50/676

Abstract: A cooling system for a gas turbine engine (10) having a compressor (14), a combustor (16) and a turbine section arranged to receive combustion products from the combustor. The cooling system includes ducting (32,44) defining a flow path from the compressor to a component, such as a turbine blade (26) to be cooled within the turbine section. The ducting (32) bypasses the combustor (16). A heat exchanger (34) may be arranged in the flow path to extract heat from the flow between the compressor and the component. One or more valves (36;64;66) in the flow path are actuated under the control of a controller (48;60) at a predetermined frequency of actuation so as to pulse the flow between the heat exchanger and the component, typically to improve the aerodynamic efficiency of turbine blades in use.

Abstract translation: 一种用于燃气涡轮发动机（10）的冷却系统，其具有压缩机（14），燃烧器（16）和涡轮部分，其布置成接收来自燃烧器的燃烧产物。 该冷却系统包括管道（32,44），其限定从压缩机到诸如在涡轮部分内被冷却的涡轮叶片（26）的部件的流动路径。 管道（32）绕过燃烧器（16）。 热交换器（34）可以布置在流动路径中以从压缩机和部件之间的流中提取热量。 流动路径中的一个或多个阀（36; 64; 66）在控制器（48; 60）的控制下以预定的致动频率被致动，以便脉动热交换器和部件之间的流动，通常为 提高使用中涡轮叶片的空气动力学效率。

公开(公告)号：US20130152601A1

公开(公告)日：2013-06-20

申请号：US13682122

申请日：2012-11-20

Applicant: ROLLS-ROYCE PLC

Inventor： Marko BACIC

IPC: F01D11/24

CPC classification number: F01D11/24 ,  F01D5/081 ,  F01D17/02 ,  F01D17/085 ,  F01D25/14 ,  F02C3/13 ,  F02C6/08 ,  F02C7/18 ,  F02C7/185 ,  F02C9/18 ,  F05D2260/205 ,  F05D2270/303 ,  F05D2270/305 ,  F05D2270/44

Abstract: A gas turbine engine has, in flow series, a compressor section, a combustor, and a turbine section. The gas turbine engine further has a system for cooling the turbine section and providing tip clearance control between turbine blades and circumferentially distributed segments forming an annular shroud surrounding the blades outer tips. The turbine section cooling sub-system diverts a first cooling air flow, regulated by a first valve arrangement, from the compressor section to a heat exchanger and then to the turbine section to cool its components. The tip clearance control sub-system supplies a second cooling air flow, regulated by a second valve arrangement, to an engine case where the segments are mounted, which regulates thermal expansion of the case and controls the clearance between the segments and outer tips. The system further includes a closed-loop controller which issues demand signals to the first and second valve arrangements.

Abstract translation: 燃气涡轮发动机以流动方式具有压缩机部分，燃烧器和涡轮部分。 燃气涡轮发动机还具有用于冷却涡轮机部分的系统，并且在涡轮机叶片和周向分布的分段之间提供顶端间隙控制，其形成围绕叶片外部尖端的环形护罩。 涡轮部分冷却子系统将由第一阀装置调节的第一冷却空气流从压缩机部分转移到热交换器，然后转移到涡轮部分以冷却其部件。 顶端间隙控制子系统将由第二阀装置调节的第二冷却空气流提供给安装有段的发动机壳体，其调节壳体的热膨胀并控制段和外部尖端之间的间隙。 该系统还包括一个向第一和第二阀装置发出需求信号的闭环控制器。

公开(公告)号：US20130133333A1

公开(公告)日：2013-05-30

申请号：US13667220

申请日：2012-11-02

Applicant: Rolls-Royce PLC

Inventor： Marko BACIC

IPC: G06F17/11 ,  F02C7/00 ,  G01P3/00

CPC classification number: F01D21/04 ,  F01D17/04 ,  F01D17/06 ,  F01D17/08 ,  F01D17/085 ,  F01D21/003 ,  F01D21/045

Abstract: The present invention provides a method of detecting shaft break in a shaft system comprising a shaft coupled between two masses. The method comprises a number of steps. Firstly, to define a time-dependent rotational speed equation for the shaft in terms of system inertia for an engine transient event. Then to discretize the rotational speed equation in terms of a discrete time constant in the discrete domain. Then to recursively define the discretized equation to give a recursive equation and to solve the recursive equation to determine the discrete time constant. Then to define a threshold as a function of engine power and then to set a shaft break signal to TRUE if the discrete time constant is greater than the threshold. A shaft break detection system is also provided by the present invention.

Abstract translation: 本发明提供了一种在轴系中检测轴断裂的方法，该轴系包括联接在两个质量块之间的轴。 该方法包括多个步骤。 首先，根据发动机瞬态事件的系统惯性来定义轴的时间相关转速方程。 然后根据离散域中的离散时间常数离散转速方程。 然后递归地定义离散方程以给出递归方程，并求解递归方程以确定离散时间常数。 然后定义阈值作为发动机功率的函数，然后如果离散时间常数大于阈值，则将轴断点信号设置为TRUE。 本发明还提供了轴断裂检测系统。

公开(公告)号：US20240132227A1

公开(公告)日：2024-04-25

申请号：US18483106

申请日：2023-10-08

Applicant: ROLLS-ROYCE plc

Inventor： Marko BACIC ,  John COULL

IPC: B64D37/30 ,  B64D37/34 ,  F02C7/22

CPC classification number: B64D37/30 ,  B64D37/34 ,  F02C7/22

Abstract: An aircraft propulsion system fuel system comprises a fuel line configured to receive liquid hydrogen fuel from a fuel tank, a vaporizer configured to vaporize liquid hydrogen fuel from the fuel line to generate a supercritical or gaseous fuel, a main fuel pump configured to receive and to pump the gaseous or supercritical fuel from the vaporizer during operation of the propulsion system, and a heater provided downstream in fuel flow to the main fuel pump, and configured to raise the temperature of the gaseous or supercritical fuel to a propulsion system delivery temperature.

公开(公告)号：US20230146869A1

公开(公告)日：2023-05-11

申请号：US17883815

申请日：2022-08-09

Applicant: ROLLS-ROYCE PLC

Inventor： Derek S. WALL ,  Andrew R. MILLS ,  Peter A. BEECROFT ,  Marko BACIC ,  Romain GUICHERD

IPC: G08G5/00

CPC classification number: G08G5/0065 ,  G08G5/003

Abstract: A computer-implemented method of enabling optimisation of derate for a propulsion system of a vehicle, the method comprising: determining a derate for the propulsion system of the vehicle using: an algorithm; a vehicle model defining path constraints for the vehicle through space; a propulsion system model defining parameters of the propulsion system; an objective function defining one or more objectives; and controlling output of the determined derate.

公开(公告)号：US20210103297A1

公开(公告)日：2021-04-08

申请号：US16907617

申请日：2020-06-22

Applicant: ROLLS-ROYCE plc

Inventor： David FILLINGHAM ,  Marko BACIC

IPC: G05D1/10 ,  G08G5/00 ,  B64C29/00

Abstract: A method of determining a flight trajectory of a vertical take-off aircraft (10) having vectorable propulsion (30, 32). The method comprises: receiving one or more aircraft flight constraints; inputting the aircraft flight constraints to a trajectory planning algorithm to determine a minimum energy aircraft transition trajectory; and outputting a control schedule to fly the aircraft (10) to the flight trajectory.

公开(公告)号：US20190031321A1

公开(公告)日：2019-01-31

申请号：US16038328

申请日：2018-07-18

Applicant: ROLLS-ROYCE plc

Inventor： Pawel CHMIELARCZYK ,  Richard A. YOUNG ,  Marko BACIC

IPC: B64C21/02 ,  F15B21/12 ,  F15C1/22 ,  F15C1/00

Abstract: A fluidic device for providing analogue output control includes a main channel, a first control channel, a second control channel, a comparator which receives respective input fluid flows from the main, the first and the second control channels. The first control channel is configured such that the input fluid flow therefrom carries an oscillating pressure wave signal, the second control channel includes a flow regulator controllable to vary the mass flow rate of the input fluid flow from the second control channel, and the main channel is configured such that the input fluid flow therefrom is at a reference mass flow rate. The comparator is configured such that the input fluid flows from the first control and the second control channels act in combination on the input fluid flow from the main channel to produce an output fluid flow from the comparator having a PWM mass flow rate characteristic.

公开(公告)号：US20180079510A1

公开(公告)日：2018-03-22

申请号：US15704831

申请日：2017-09-14

Applicant: ROLLS-ROYCE plc

Inventor： Marko BACIC ,  Benjamin J. SELLERS ,  Rory D. STIEGER

IPC: B64D13/04 ,  B64D27/16 ,  F04D25/02 ,  F04D27/00 ,  F02C7/32

CPC classification number: B64D13/04 ,  B64D27/16 ,  B64D2013/0603 ,  F02C7/32 ,  F04D25/02 ,  F04D27/002 ,  F04D27/0261 ,  F05D2220/323 ,  F05D2260/40 ,  F05D2270/101 ,  F05D2270/30 ,  Y02T50/671

Abstract: A control system for use in controlling a cabin blower system. The cabin blower system includes a gas turbine engine spool, a cabin blower compressor powered by the spool and arranged in use to compress fluid used in a cabin of an aircraft, and one or more control mechanisms via which the control system controls the power extracted by the cabin blower compressor from the spool. The control system is arranged in use to control the power extracted from the spool by the cabin blower compressor in accordance with one or more primary control parameters. The control system is arranged in use to alter the spool power extracted by the cabin blower compressor by comparison with the power that would have been extracted in accordance with the primary control parameters alone, in response to modifications in a secondary control parameter indicative of the commencement or occurrence of an engine transient.