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    Method for synchronising the engines of an airplane with dual intermediate state
    2.
    发明授权
    Method for synchronising the engines of an airplane with dual intermediate state 有权

    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.

    GAS TURBINE ENGINE WITH VARIABLE SPEED TURBINES
    4.
    发明申请
    GAS TURBINE ENGINE WITH VARIABLE SPEED TURBINES 审中-公开
    燃气涡轮发动机与可变速度涡轮机

    公开(公告)号：US20150330301A1

    公开(公告)日：2015-11-19

    申请号：US14367452

    申请日：2012-12-28

    Applicant: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.

    Inventor： Robert W. CEDOZ ,  Syed J. KHALID

    IPC: F02C3/10 ,  F02C7/36 ,  F02C3/13

    CPC classification number: F02C3/10 ,  F02C3/13 ,  F02C7/36 ,  F02C9/18 ,  F05D2260/4023 ,  F05D2270/023 ,  F05D2270/06

    Abstract: Embodiments of the present invention include unique gas turbine engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

    Abstract translation: 本发明的实施例包括独特的燃气涡轮发动机。 其他实施例包括用于燃气涡轮发动机的装置，系统，装置，硬件，方法和组合。 本申请的其它实施例，形式，特征，方面，益处和优点将从本文提供的描述和附图中变得显而易见。

    SYSTEM AND METHOD OF CONTROLLING A TWO-SHAFT GAS TURBINE
    5.
    发明申请
    SYSTEM AND METHOD OF CONTROLLING A TWO-SHAFT GAS TURBINE 审中-公开
    控制双轴瓦斯涡轮机的系统和方法

    公开(公告)号：US20150135722A1

    公开(公告)日：2015-05-21

    申请号：US14543028

    申请日：2014-11-17

    Applicant: MITSUBISHI HITCHI POWER SYSTEMS, LTD.

    Inventor： Yasuo TAKAHASHI ,  Takuya TAKEDA

    IPC: F02C3/107 ,  F02C7/36 ,  F02C9/56

    CPC classification number: F02C3/107 ,  F02C3/10 ,  F02C7/1435 ,  F02C7/36 ,  F02C9/54 ,  F02C9/56 ,  F05D2270/023 ,  F05D2270/16 ,  F05D2270/304

    Abstract: A two-shaft gas turbine control system and method are provided that can enhance the efficiency and reliability thereof by controlling the amount of intake air spray and the rotational speed of a high-pressure turbine in accordance with the aperture of an inlet guide vane in a state where a two-shaft gas turbine is being operated with the efficiency of its compressor reduced.The control system includes a droplet spray device for spraying droplets to intake air for the compressor and a controller. The controller includes a fuel control section for adjusting a flow rate of the fuel to be supplied to the combustor, a spray flow rate control section for adjusting a flow rate of spray water to be supplied to the droplet spray device, an inlet guide vane aperture control section for adjusting the aperture of the inlet guide vane, and an efficiency improvement control section for outputting a command signal for bringing a balance between driving force for the compressor and power output of the high-pressure turbine to the fuel control section, the spray flow rate control section and the inlet guide aperture control section. In response to the commands from the improvement control section, the controller reduces the rotational speed of the high-pressure turbine and controls the inlet guide vane so as to be more open, thereby appropriately controlling the flow rate of the spray water.

    Abstract translation: 提供了一种双轴燃气轮机控制系统和方法，其通过根据入口导叶的孔径控制进气喷射量和高压涡轮机的旋转速度来提高其效率和可靠性 其中双轴燃气轮机正在以其压缩机的效率降低而运行的状态。 控制系统包括用于将液滴喷射到用于压缩机的进气和控制器的液滴喷射装置。 控制器包括用于调节供给到燃烧器的燃料的流量的燃料控制部，用于调节供给到液滴喷射装置的喷射水的流量的喷雾流量控制部， 用于调节入口引导叶片的孔径的控制部分，以及效率改善控制部分，用于输出用于使压缩机的驱动力和高压涡轮机的功率输出之间的平衡的指令信号到燃料控制部分，喷雾 流量控制部和入口引导孔径控制部。 响应于来自改进控制部的命令，控制器降低高压涡轮机的转速并且控制入口导向叶片以更开放，从而适当地控制喷射水的流量。

    METHOD OF AUTOMATICALLY REGULATING AN AIRCRAFT POWER PLANT, A DEVICE, AND AN AIRCRAFT
    6.
    发明申请
    METHOD OF AUTOMATICALLY REGULATING AN AIRCRAFT POWER PLANT, A DEVICE, AND AN AIRCRAFT 有权
    自动调节飞机发电厂，装置和飞机的方法

    公开(公告)号：US20140020396A1

    公开(公告)日：2014-01-23

    申请号：US13753690

    申请日：2013-01-30

    Applicant: EUROCOPTER

    Inventor： Alban Corpron

    IPC: F02C9/00

    CPC classification number: F02C9/00 ,  B64C27/04 ,  B64C27/14 ,  B64D27/10 ,  B64D31/00 ,  F02C3/04 ,  F02C9/28 ,  F05D2220/329 ,  F05D2220/76 ,  F05D2220/90 ,  F05D2270/02 ,  F05D2270/023

    Abstract: The present invention relates to an automatic method of regulating a power plant (3′) of an aircraft (1), the power plant having at least one turbine engine (3), each engine (3) being capable of operating in an idling mode of operation. A calculation system (15) executes stored instructions in order to implement the idling mode of operation as a function of operational and ordered conditions either via a first regulation mode by regulating a first speed of rotation (Ng) of said gas generator (4), or via a second mode of regulation by regulating a second speed of rotation (NTL) of said free turbine (7).

    Abstract translation: 本发明涉及一种调节飞机（1）的发电厂（3'）的自动方法，该发电厂具有至少一个涡轮发动机（3），每个发动机（3）能够以空转模式 的操作。 计算系统（15）执行存储的指令，以便通过调节所述气体发生器（4）的第一旋转速度（Ng）来经由第一调节模式来实现作为操作和有序状态的函数的操作的空转模式， 或通过调节所述自由涡轮机（7）的第二转速（NTL）来经由第二调节模式。

    Method and a device for performing a check on the state of health of a turbine engine of a twin-engined rotorcraft
    8.
    发明授权
    Method and a device for performing a check on the state of health of a turbine engine of a twin-engined rotorcraft 有权
    用于对双发旋翼航空器的涡轮发动机的健康状况进行检查的方法和装置

    公开(公告)号：US07769521B2

    公开(公告)日：2010-08-03

    申请号：US11730835

    申请日：2007-04-04

    Applicant: Francois-Xavier Gaulmin ,  Lionel Iraudo

    Inventor： Francois-Xavier Gaulmin ,  Lionel Iraudo

    IPC: G06F19/00 ,  G06G7/70

    CPC classification number: F02C9/42 ,  F02C9/28 ,  F05D2220/90 ,  F05D2260/80 ,  F05D2270/023 ,  F05D2270/051 ,  F05D2270/304 ,  G07C3/00

    Abstract: The present invention relates to a method and to a device (D) enabling a health check to be performed on at least a first turbine engine (M1) of a rotorcraft, the rotorcraft being provided with first and second turbine engines (M1 and M2) controlled respectively by first and second control means (MC1 and MC2). The device is remarkable in that it comprises check means (C) provided with main means (C1), the main means (C1) controlling the first and second control means (MC1 and MC2) so that the surveillance parameters of the first and second turbine engines (M1 and M2) respectively reach the real first and second final values (V1f and V2f) as determined in accordance with the method of the invention.

    Abstract translation: 本发明涉及能够在旋翼航空器的至少第一涡轮发动机（M1）上执行健康检查的方法和装置（D），所述旋翼飞机设有第一和第二涡轮发动机（M1和M2） 分别由第一和第二控制装置（MC1和MC2）控制。 该装置是显着的，它包括设有主装置（C1）的检查装置（C），主装置（C1）控制第一和第二控制装置（MC1和MC2），使得第一和第二涡轮机的监视参数 发动机（M1和M2）分别达到根据本发明的方法确定的实际的第一和第二最终值（V1f和V2f）。

    Electrically coupled supercharger for a gas turbine engine
    9.
    发明授权
    Electrically coupled supercharger for a gas turbine engine 有权
    用于燃气涡轮发动机的电耦合增压器

    公开(公告)号：US07513120B2

    公开(公告)日：2009-04-07

    申请号：US11101527

    申请日：2005-04-08

    Applicant: Daniel B. Kupratis

    Inventor： Daniel B. Kupratis

    IPC: F02C3/10 ,  F02C6/00

    CPC classification number: F02C3/10 ,  F01D15/10 ,  F02C3/113 ,  F02C7/36 ,  F02C9/56 ,  F05D2220/329 ,  F05D2270/023 ,  F05D2270/101

    Abstract: A gas turbine engine, in particular a turboshaft engine, includes a spool having a turbine and a gas generator compressor mounted thereto, a source of heat positioned between the turbine and the compressor, a first shaft and a free turbine mounted to the first shaft, and a control system for transferring power between the spool and the shaft. The operating speed of the gas generator compressor is re-matched in order to improve the efficiency and surge margin of the gas generator compressor and to improve the transient performance of the gas turbine engine.

    Abstract translation: 燃气涡轮发动机，特别是涡轮轴发动机包括具有涡轮机和安装在其上的气体发生器压缩机的阀芯，位于涡轮机和压缩机之间的热源，安装在第一轴上的第一轴和自由涡轮机， 以及用于在阀芯和轴之间传递动力的控制系统。 气体发生器压缩机的运行速度重新匹配，以提高气体发生器压缩机的效率和喘振裕度，并改善燃气轮机的瞬态性能。

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