公开(公告)号：US11975860B2

公开(公告)日：2024-05-07

申请号：US17569996

申请日：2022-01-06

Applicant: Bell Textron Inc.

Inventor： Thomas Dewey Parsons

IPC: B64C27/57 ,  B64D31/06 ,  F02C9/42

CPC classification number: B64D31/06 ,  F02C9/42 ,  F05D2220/329 ,  F05D2270/093 ,  F05D2270/13

Abstract: Various implementations described herein are directed to an aircraft having a multi-engine configuration with multiple engines. The aircraft may have a flight control system coupled to the multiple engines with a multi-engine interface. The flight control system may be configured to shutdown at least one engine of the multiple engines during reduced-engine operation by continuously calculating altitude for the reduced-engine operation based on one or more of an aircraft descent rate of the aircraft and an engine restart time of the at least one engine.

公开(公告)号：US20230211876A1

公开(公告)日：2023-07-06

申请号：US17569996

申请日：2022-01-06

Applicant: Bell Textron Inc.

Inventor： Thomas Dewey Parsons

IPC: B64C27/12 ,  B64D31/12 ,  B64D31/10 ,  B64D45/04 ,  F02C9/42

CPC classification number: B64C27/12 ,  B64D31/12 ,  B64D31/10 ,  B64D45/04 ,  F02C9/42 ,  F05D2220/329 ,  F05D2270/093 ,  F05D2270/13

Abstract: Various implementations described herein are directed to an aircraft having a multi-engine configuration with multiple engines. The aircraft may have a flight control system coupled to the multiple engines with a multi-engine interface. The flight control system may be configured to shutdown at least one engine of the multiple engines during reduced-engine operation by continuously calculating altitude for the reduced-engine operation based on one or more of an aircraft descent rate of the aircraft and an engine restart time of the at least one engine.

公开(公告)号：US11643978B2

公开(公告)日：2023-05-09

申请号：US17570433

申请日：2022-01-07

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  Christopher P Madden

IPC: F02C9/28 ,  F23R3/34 ,  F02C7/22

CPC classification number: F02C9/28 ,  F23R3/343 ,  F02C7/22 ,  F05D2220/323 ,  F05D2270/07 ,  F05D2270/13 ,  F05D2270/303 ,  F05D2270/311 ,  F05D2270/313 ,  F05D2270/335

Abstract: An aircraft including lean-burn gas turbine engines operating in pilot-plus-mains mode with a given initial fuel flow W0, a method of controlling the optical depth of contrails produced by a first group of engines includes the steps of (i) reducing fuel flow to each engine in the first group to change the operation of each engine from pilot-plus-mains mode to pilot-only mode, and (ii) adjusting fuel flow to one or more engines in a second group of engines such that the total fuel flow to engines of the second group is increased, all engines of the second group remaining in pilot-plus-mains mode, and wherein the set of lean-burn engines consists of the first and second groups. Depending on atmospheric conditions, the average optical depth of contrails produced by the engines may be enhanced or reduced compared to when all engines operate in pilot-plus-mains mode with a fuel flow W0.

公开(公告)号：US09849997B2

公开(公告)日：2017-12-26

申请号：US15304008

申请日：2015-04-15

Applicant: Safran Aircraft Engines

Inventor： Florent Nobelen

IPC: B64D31/12 ,  F02C9/42 ,  F01D21/14 ,  F02C9/16

CPC classification number: B64D31/12 ,  F01D21/14 ,  F02C9/16 ,  F02C9/42 ,  F05D2220/323 ,  F05D2270/023 ,  F05D2270/13 ,  F05D2270/301 ,  F05D2270/304 ,  F05D2270/306

Abstract: A method for synchronizing the engines of an airplane according to one activation logic having a deactivated state (20), an armed state (22), and one activated state (16), in which: the switching (36) of the synchronization from the armed state to the activated state is carried out via a first and then a second successive intermediate state (38, 39) of the activation logic, every instance of the activation logic switching from the second intermediate state (39) to the activated state involves the following: taking into consideration, on each engine, the activation state of the synchronization, and exchanging said data between the engines, the switching of the activation logic of one of the engines to the activated state requires that the safety and activation conditions of the other engine are all met. if one of the engines enters the deactivated state, the other engine does so as well; and for each engine, the switching (36, 42) of the synchronization from the armed state to the first and then to the second intermediate state takes place automatically when a first portion and then a second portion of the safety and/or activation conditions are met.

公开(公告)号：US09677504B2

公开(公告)日：2017-06-13

申请号：US12777508

申请日：2010-05-11

Applicant: Sean S. Stroud ,  Michael J. Piovoso

Inventor： Sean S. Stroud ,  Michael J. Piovoso

IPC: F02K9/08 ,  F02K9/80 ,  F02K9/58

CPC classification number: F02K9/80 ,  F02K9/08 ,  F02K9/58 ,  F05D2200/23 ,  F05D2200/24 ,  F05D2270/12 ,  F05D2270/13 ,  F05D2270/701

Abstract: Rockets, rocket motors, methods of controlling a rocket and methods of evaluating a rocket design are disclosed. In some embodiments, a method of controlling a rocket may include measuring a combustion chamber pressure, calculating a logarithm of the measured combustion chamber pressure, and computing the difference between the logarithm of the measured combustion chamber pressure and the logarithm of a reference combustion chamber pressure value to generate an error signal. The method may further include filtering the error signal to generate a compensated signal in the logarithm domain, and exponentiating of the compensated signal in the logarithm domain to provide a compensated signal in the physical domain.

公开(公告)号：US09581025B2

公开(公告)日：2017-02-28

申请号：US14142166

申请日：2013-12-27

Applicant: Rolls-Royce Corporation

Inventor： David John Howard Eames

IPC: B64D33/00 ,  F02C7/36 ,  F01B23/00 ,  F02C9/44 ,  F02C9/42 ,  B64D27/02 ,  B64D33/02 ,  B64D27/00

CPC classification number: F01B23/00 ,  B64D27/02 ,  B64D2027/005 ,  B64D2027/026 ,  B64D2033/0293 ,  F02C7/36 ,  F02C9/42 ,  F02C9/44 ,  F05D2270/13 ,  Y02T50/64 ,  Y02T50/66

Abstract: An aircraft power plant is disclosed having a plurality of bladed rotors in flow communication driven by separate work producing devices. The work producing devices can take a variety of forms including an internal combustion engine and electric motor, for example. The bladed rotors can be associated with an aircraft pylon and can be driven independently to separate operating conditions to provide optimum performance. For example, the bladed rotors can be driven to separate operating conditions that improve a noise signature or performance of the aircraft.

Abstract translation: 公开了一种具有由单独的作业产生装置驱动的多个流动通过的叶片转子的飞机发电厂。 作业生产装置可以采用例如内燃机和电动机等各种形式。 叶片式转子可以与飞机塔相关联，并可独立驱动，以分离操作条件以提供最佳性能。 例如，叶片转子可以被驱动以分离改善飞行器噪声特征或性能的操作条件。

公开(公告)号：US20160010589A1

公开(公告)日：2016-01-14

申请号：US14789483

申请日：2015-07-01

Applicant: ROLLS-ROYCE PLC

Inventor： Andrew Martin ROLT

IPC: F02K3/02 ,  F02K1/64 ,  F02K3/065

CPC classification number: F02K3/025 ,  B64D27/18 ,  B64D2027/026 ,  F01D13/003 ,  F01D15/10 ,  F02C7/10 ,  F02C7/143 ,  F02K1/06 ,  F02K1/64 ,  F02K3/04 ,  F02K3/065 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2270/101 ,  F05D2270/13 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T50/675

Abstract: A gas turbine engine propulsion system in which a first propulsive unit has a core engine and a first low pressure turbine arranged to be driven by combustion products from the core engine. The first propulsive unit also has a first fan rotor and a first fan shaft drivingly connecting the first turbine and the first fan rotor. The propulsion system also has a further turbine arranged in flow series with the first turbine and a second propulsive unit spaced from the first propulsive unit. The second propulsive unit has a second fan rotor driven by the rotational output of the further turbine. The further turbine may be located in the second propulsive unit and may be in fluid communication with the first turbine via an inter-turbine duct.

Abstract translation: 一种燃气涡轮发动机推进系统，其中第一推进单元具有核心发动机和布置成由来自核心发动机的燃烧产物驱动的第一低压涡轮机。 第一推进单元还具有第一风扇转子和驱动地连接第一涡轮机和第一风扇转子的第一风扇轴。 推进系统还具有与第一涡轮机流动串联布置的另外的涡轮机和与第一推进单元间隔开的第二推进单元。 第二推进单元具有由另外的涡轮机的旋转输出驱动的第二风扇转子。 另外的涡轮机可以位于第二推进单元中，并且可以经由涡轮机间管道与第一涡轮流体连通。

公开(公告)号：US20140248121A1

公开(公告)日：2014-09-04

申请号：US14140959

申请日：2013-12-26

Applicant: Rolls-Royce Corporation

Inventor： Michael Abraham KARAM ,  Craig HEATHCO ,  Andrew EIFERT

IPC: F02C7/045

CPC classification number: F02C7/045 ,  F02C1/02 ,  F02C3/13 ,  F02C3/305 ,  F02C6/04 ,  F02C6/06 ,  F02C6/08 ,  F02C6/14 ,  F02C6/16 ,  F02C7/26 ,  F02C7/262 ,  F02C7/27 ,  F02C9/18 ,  F02C9/50 ,  F02C9/52 ,  F02K3/12 ,  F05B2260/42 ,  F05B2270/103 ,  F05B2270/1031 ,  F05B2270/1033 ,  F05B2270/1073 ,  F05B2270/111 ,  F05D2260/42 ,  F05D2260/963 ,  F05D2270/05 ,  F05D2270/051 ,  F05D2270/093 ,  F05D2270/13 ,  F05D2270/3061

Abstract: A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.

Abstract translation: 公开了一种燃气涡轮发动机，其包括在一些实施例中能够被配置为用作谐振空间的旁通通道。 谐振空间可用于衰减/加强其他地方产生的噪声。 旁路通道可以以多种方式构成以形成共振空间。 例如，空间可以具有各种几何形状，配置等。在一个非限制性形式中，谐振空间可以衰减旁路管道前方的噪声。 在另一非限制性形式中，共振空间可以衰减旁路管道的噪声。 任何数量的变化是可能的。

公开(公告)号：US08660721B2

公开(公告)日：2014-02-25

申请号：US13440390

申请日：2012-04-05

Applicant: Brice Fernandez

Inventor： Brice Fernandez

IPC: G06F19/00 ,  G06G7/70

CPC classification number: B64C19/00 ,  B64D31/12 ,  F02C7/26 ,  F02C9/00 ,  F05D2270/13

Abstract: A device for controlling engine speed of a multi-engine aircraft includes a series of components for automatically controlling the speed of the engines during the take-off, so as to avoid discrepancies in the engine speeds. To this end, as long as all engines of the aircraft do not have, at least at given intermediary moment of the take-off, a driving parameter value equal to a preset intermediate value of the parameter, the speed of all of the engines cannot exceed an intermediate speed associated with the preset intermediate value. Thus, all engines must reach the intermediate speed so that the acceleration to a higher take-off speed can continue simultaneously for all engines.

Abstract translation: 用于控制多引擎飞机的发动机转速的装置包括用于在起飞期间自动控制发动机的速度的一系列部件，以避免发动机转速的差异。 为此，只要飞机的所有发动机至少在起飞的给定中间时刻具有等于参数的预设中间值的驾驶参数值，则所有发动机的速度都不能 超过与预设中间值相关联的中间速度。 因此，所有发动机必须达到中间速度，以便所有发动机可以同时继续加速到更高的起飞速度。

公开(公告)号：US20130110327A1

公开(公告)日：2013-05-02

申请号：US13440390

申请日：2012-04-05

Applicant: Brice Fernandez

Inventor： Brice Fernandez

IPC: B64C19/00

CPC classification number: B64C19/00 ,  B64D31/12 ,  F02C7/26 ,  F02C9/00 ,  F05D2270/13

Abstract: According to the invention, the device (1) comprises means (2, 3, 4, 5) for automatically controlling the speed of engines (M1 to M4) in such a way that, as long as all engines of an aircraft (AC) do not have, at least at given moment of a take-off, a driving parameter value (N1c1 to N1c4) roughly equal to a preset intermediate value of said parameter (N1x), the speed of engines cannot exceed an intermediate speed associated with said preset intermediate value.

Abstract translation: 根据本发明，装置（1）包括用于以这样的方式自动控制发动机（M1至M4）的速度的装置（2,3,4,5），即，只要飞行器（AC）的所有发动机 至少在给定的起飞时刻，大致等于所述参数（N1x）的预设中间值的驾驶参数值（N1c1〜N1c4），发动机的速度不能超过与所述参数 预设中间值。