公开(公告)号：US09416676B2

公开(公告)日：2016-08-16

申请号：US14584811

申请日：2014-12-29

申请人： MTU Aero Engines AG

发明人： Walter Gieg ,  Petra Kufner ,  Rudolf Stanka

IPC分类号： F01D5/20 ,  F01D11/00 ,  F01D11/12 ,  F01D25/24 ,  F01D25/28 ,  B23P15/04 ,  B25B27/14 ,  F01D11/08

CPC分类号： F01D11/08 ,  F01D11/00 ,  F01D11/12 ,  F01D11/122 ,  F01D11/127 ,  F01D25/24 ,  F01D25/246 ,  F01D25/285 ,  F05D2200/11 ,  F05D2220/3212 ,  F05D2230/60 ,  F05D2230/68 ,  F05D2230/70 ,  F05D2240/11 ,  F05D2260/36 ,  F05D2260/37

摘要： The present invention relates to a gas turbine having a housing (1), an outer sealing ring (2) that can be fastened detachably to the housing, a clamping member (3) for clamping the outer sealing ring and the housing together radially, and a rotation locking member that has at least one housing groove (10) and a radial flange (20) of the outer sealing ring that can be locked against rotation in the housing groove in form-fitting manner with play (sa) in the axial and/or peripheral direction.

摘要翻译： 本发明涉及一种具有壳体（1），能够可拆卸地固定到壳体的外密封环（2）的燃气轮机，用于将外密封环和壳体径向夹持的夹紧构件（3），以及 旋转锁定构件具有至少一个外部密封环的容纳凹槽（10）和径向凸缘（20），该外部密封环能够以与轴向和（或）轴向成形配合的方式在壳体凹槽中防止旋转而锁定， /或周边方向。

公开(公告)号：US20070204593A1

公开(公告)日：2007-09-06

申请号：US11366252

申请日：2006-03-02

申请人： Cary Cover ,  Sean Stroud ,  Michael Piovoso ,  Timothy Kelly

发明人： Cary Cover ,  Sean Stroud ,  Michael Piovoso ,  Timothy Kelly

IPC分类号： F03H5/00

CPC分类号： F02K9/80 ,  F02K9/08 ,  F05D2200/11

摘要： A propulsion thrust control system and method for controlling thrust in a rocket motor includes configuring valves of an energized rocket motor to an initial total valve area according to a total thrust command. The total thrust command is converted into a commanded propellant mass flow discharge rate. A varying total valve area is computed from an error between the commanded propellant mass flow discharge rate and a calculated propellant mass flow discharge rate. The valves are reconfigured according to a distribution of the varying total valve area. The propulsion system includes a pressure vessel with valves and a controller for regulating the valve area according to a propellant mass flow discharge rate from the pressure vessel.

摘要翻译： 用于控制火箭发动机中的推力的推进推力控制系统和方法包括根据总推力命令将通电火箭发动机的阀构成初始总阀面积。 总推力命令转换为指挥推进剂质量流量排放率。 根据指挥的推进剂质量流量排出速率与计算的推进剂质量流量排放速率之间的误差计算变化的总阀面积。 根据变化的总阀面积的分布重新配置阀。 推进系统包括具有阀的压力容器和用于根据来自压力容器的推进剂质量流量排出速率来调节阀门面积的控制器。

公开(公告)号：US06851303B2

公开(公告)日：2005-02-08

申请号：US10334803

申请日：2003-01-02

申请人： Robert N Parfitt ,  Colin A. Whittle ,  Martin R Turville

发明人： Robert N Parfitt ,  Colin A. Whittle ,  Martin R Turville

IPC分类号： F01D21/00 ,  F01D25/28 ,  G01L5/13 ,  G01M15/00

CPC分类号： F01D25/285 ,  F01D21/003 ,  F05D2200/11 ,  F05D2200/211 ,  F05D2200/221 ,  G01L5/133

摘要： A method for determining the free-field thrust of a gas turbine engine using an enclosed gas turbine engine test facility without recourse to an outdoor gas turbine engine test facility. The method includes calculating the gas turbine engine intake momentum drag and cradle drag generated and compensating for these losses. In a further embodiment, the base drag is calculated and also compensated for.

摘要翻译： 一种用于使用封闭的燃气涡轮发动机测试设备来确定燃气涡轮发动机的自由场推力的方法，而不需要借助室外燃气涡轮发动机测试设备。 该方法包括计算产生的燃气涡轮发动机进气动量阻力和摇篮阻力并补偿这些损失。 在另一个实施例中，计算基础阻力并补偿。

公开(公告)号：US20040088997A1

公开(公告)日：2004-05-13

申请号：US10699847

申请日：2003-11-04

申请人： ALSTOM (Switzerland) Ltd.

发明人： Jaan Hellat ,  Frank Reiss ,  Pirmin Schiessel

IPC分类号： F23R003/30

CPC分类号： F02C3/305 ,  F05D2200/11 ,  F23L2900/07008 ,  F23R2900/00013 ,  F23R2900/00014

摘要： In a method for operating a premix burner a water quantity is introduced into at least one of the burner and the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method can also be used if a burner is operated dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable. The method enables measured parameters to be kept below a permissible upper limit.

公开(公告)号：US06216437B1

公开(公告)日：2001-04-17

申请号：US09153020

申请日：1998-09-15

申请人： Stephan Hepner ,  Hans-Kaspar Scherrer

发明人： Stephan Hepner ,  Hans-Kaspar Scherrer

IPC分类号： F02C900

CPC分类号： F02C9/54 ,  F01D17/04 ,  F01D17/06 ,  F05D2200/11 ,  F05D2270/053 ,  F05D2270/061 ,  F05D2270/304 ,  H02P9/04

摘要： In a method for regulating the power of a turbo set (10) converting thermal power into electric power, said turbo set (10) comprising, on a common shaft (17), a turbine (11) driven by the thermal power and a generator (16) driven by the turbine (11) and delivering electric power (PG) to a network (18), the electric power (PG) delivered by the generator (16) is determined and the thermal power (PT) for the turbine (11) is regulated as a function of the measured electric power (PG). Destabilization of the network and overloading of the turbo set (10) are avoided by additionally determining the kinetic power (Pkin) consumed or delivered by the shaft (17) and by regulating the thermal power (PT) in accordance with the sum of the electric power (PG) and kinetic power (Pkin).

摘要翻译： 在一种用于调节将热功率转换成电力的涡轮机组（10）的功率的方法中，所述涡轮机组（10）包括在公共轴（17）上的由热力驱动的涡轮机（11）和发电机 （16）由涡轮机（11）驱动并将电力（PG）输送到网络（18），确定由发电机（16）输送的电力（PG），并且确定涡轮机的热功率（PT） 11）作为测量电力（PG）的函数进行调节。 通过另外确定由轴（17）消耗或输送的动能（Pkin）并且通过根据电气（17）的总和来调节热功率（PT）来避免网络的不稳定和涡轮组（10）的超载 功率（PG）和动力（Pkin）。

公开(公告)号：US5711348A

公开(公告)日：1998-01-27

申请号：US696612

申请日：1996-08-14

申请人： Douglas H. Morash ,  Hans G. Toews

发明人： Douglas H. Morash ,  Hans G. Toews

IPC分类号： B64G1/26 ,  B64G1/40 ,  F02K9/30 ,  F02K9/32 ,  F02K9/80 ,  F02K9/88 ,  F16K11/087 ,  F16K11/076

CPC分类号： F02K9/805 ,  B64G1/26 ,  B64G1/403 ,  F42B10/663 ,  F05D2200/11 ,  Y10T137/86855 ,  Y10T137/87812

摘要： The present invention provides an improved hot gas control valve (20) which is adapted to apportion a gas flow, such as that issuing from a solid propellent gas generator, among a plurality of outlets communicating with rocket thruster nozzles (36). The improved valve has a body (21) and a valve member (22). The body has an inlet (24) communicating with an internal cavity. The cavity is partially bounded by a partially-spherical concave surface (32). The body has a plurality of outlet passages terminating in ports at the concave body surface. The valve member is operatively arranged within the cavity for omni-directional pivotal movement therewithin. The valve member has a surface (40) sealingly engaging the body concave surface and terminating in an edge (41). This valve member edge cooperates with the body ports to form variable-area metering orifices (A, B, C and D) therebetween. These orifices are so configured and arranged as to vary the areas of the orifices as a function of the angular position of the valve member relative to the body such that sum of the individual open areas of the metering orifices is substantially independent of valve member position over an operating range of valve member movement relative to the body.

摘要翻译： 本发明提供了一种改进的热气控制阀（20），其适于在与火箭推进器喷嘴（36）连通的多个出口之间分配气流，例如从固体推进燃气发生器发出的气流。 改进的阀具有主体（21）和阀构件（22）。 主体具有与内部空腔连通的入口（24）。 腔部分地由部分球形的凹面（32）界定。 主体具有多个出口通道，其终止于凹体表面的端口。 阀构件可操作地布置在空腔内以在其中进行全方位的枢转运动。 阀构件具有密封地接合主体凹面并终止于边缘（41）的表面（40）。 该阀构件边缘与主体端口配合以在其间形成可变区域计量孔（A，B，C和D）。 这些孔被构造和布置成根据阀构件相对于主体的角位置来改变孔的面积，使得计量孔的各个开放区域的总和基本上不依赖于阀构件位置 阀构件相对于主体的运动范围。

公开(公告)号：US5031398A

公开(公告)日：1991-07-16

申请号：US443159

申请日：1989-11-30

申请人： Steven W. Lampe ,  Ashley W. Timmis

发明人： Steven W. Lampe ,  Ashley W. Timmis

IPC分类号： F02C7/277 ,  F02C9/28

CPC分类号： F02C9/28 ,  F02C7/277 ,  F05D2200/11

摘要： A fuel control system (10) for a power unit used for generating power used for operating an airframe in accordance with the invention includes an air supply (18) for supplying pressurized air blown down from a storage vessel (14) to a combustor (16) which generates a gas stream by burning fuel supplied by a fuel supply (32) driving a turbine (50) to produce the power; a pressure sensor (26) coupled to the air supply for producing an analog signal proportional to pressure upstream in the air supply from the combustor; a digital to analog converter (54) having an offset input coupled to a signal proportional to the sensed pressure, a digital input for receiving a digital input signal, and an analog output which varies in proportion to the sum of the signal applied to the offset input and the digital input signal; a fuel control valve (38) contained with the fuel supply which is controlled as a function of the analog output signal of the digital to analog converter; an analog to digital converter (56) having at least one input and at least one output with the analog to digital converter outputting a digital signal proportional to each input signal applied to the at least one input of the analog to digital converter; and a system controller (24), responsive to the at least one output of the analog to digital converter, controlling the fuel with a periodically generated digital input signal applied to the digital to analog converter.

摘要翻译： 根据本发明的用于产生用于操作机身的动力单元的燃料控制系统（10）包括用于将从储存容器（14）吹出的加压空气供应到燃烧器（16）的空气供应源（18） ），其通过燃烧由驱动涡轮（50）的燃料供应（32）供应的燃料来产生气流，以产生电力; 耦合到空气供应的压力传感器（26），用于产生与来自燃烧器的空气供应中的上游压力成比例的模拟信号; 数模转换器（54），其具有耦合到与感测到的压力成比例的信号的偏移输入，用于接收数字输入信号的数字输入和与施加到偏移的信号的和成比例地变化的模拟输出 输入和数字输入信号; 燃料控制阀（38），其容纳有作为所述数模转换器的模拟输出信号的函数而被控制的燃料供应; 模数转换器（56）具有至少一个输入和至少一个输出，模数转换器输出与施加到模数转换器的至少一个输入端的每个输入信号成比例的数字信号; 以及系统控制器（24），其响应于所述模数转换器的所述至少一个输出，利用施加到所述数模转换器的周期性产生的数字输入信号来控制所述燃料。

公开(公告)号：US4879792A

公开(公告)日：1989-11-14

申请号：US268138

申请日：1988-11-07

申请人： Gerald J. O'Connor

发明人： Gerald J. O'Connor

IPC分类号： F01D5/02 ,  F16F15/32 ,  G01M1/16 ,  G01M1/32

CPC分类号： F16F15/32 ,  F01D5/027 ,  G01M1/16 ,  G01M1/32 ,  F05D2200/11 ,  Y10T29/49316 ,  Y10T464/50

摘要： Given limitations on potential locations, weight sizes and amount of weights all possible applied unbalance magnitudes and angles are calculated after determining the initial unbalance magnitude and angle of the rotor this result is vector summed with all possible applied unbalances. The lowest resultant magnitude is determined, independent of the angle. The corresponding weight combination produces the lowest possible residual unbalance within the constraints.

摘要翻译： 给定潜在位置的限制，权重大小和权重量，所有可能应用的不平衡量值和角度在确定转子的初始不平衡量值和角度后计算，该结果与所有可能的应用不平衡相加。 确定最低的结果幅度，与角度无关。 相应的重量组合在约束条件内产生最小可能的剩余不平衡。

公开(公告)号：US4811565A

公开(公告)日：1989-03-14

申请号：US153301

申请日：1988-02-05

申请人： Edward Y. Hwang

发明人： Edward Y. Hwang

IPC分类号： F01D17/20 ,  F01D17/18 ,  F01D17/24 ,  F01K13/02

CPC分类号： F01D17/18 ,  F05D2200/11

摘要： A steam turbine inlet valve control system includes separately tunable valve characteristics for single valve and sequential valve operation modes. The sequential valve characteristics include both normal and alternate sequences which can be selected during operation of the steam turbine. The characteristics may be displayed to an operator and modified by graphical manipulation to simplify tuning the control system's characteristics to the steam turbine's operation. The control system also performs direct tracking of flow through the valves by converting sensed position signals to individual valve flow signals using a lift-to-flow conversion characteristic. Individual valve flow signals are summed and corrected for choked flow conditions to produce a tracked flow demand signal.

摘要翻译： 蒸汽轮机进气阀控制系统包括单阀和顺序阀操作模式的独立可调阀特性。 顺序阀特性包括可以在蒸汽轮机运行期间选择的正常和替代顺序。 特征可以显示给操作者并通过图形操作进行修改，以简化将控制系统的特性调整到蒸汽轮机的操作。 控制系统还通过使用升降流转换特性将感测到的位置信号转换为单独的阀流量信号来直接跟踪通过阀的流量。 单独的阀流量信号被加总和校正扼流流动条件以产生跟踪的流量需求信号。

公开(公告)号：US4272040A

公开(公告)日：1981-06-09

申请号：US924594

申请日：1978-07-14

申请人： Thomas W. Bastian ,  Garry T. Lacy ,  John J. Vink

发明人： Thomas W. Bastian ,  Garry T. Lacy ,  John J. Vink

IPC分类号： F02K9/90 ,  F42B15/18

CPC分类号： F42B10/665 ,  F02K9/90 ,  F05D2200/11

摘要： A rocket thrust vector control system including jet tabs and aerodynamic control surfaces is disclosed. The control system removes roll information present in commands to the aerodynamic surfaces and provides only pitch and yaw information to the jet tabs for the thrust vector control. The roll information is removed by a geared summing mechanism. The resulting pitch and yaw output is used to drive the thrust vector control jet tabs. The same powered actuators are used for both the aerodynamic control surfaces and the jet tabs.

摘要翻译： 公开了一种包括喷射翼片和空气动力学控制表面的火箭推力矢量控制系统。 控制系统将存在于命令中的滚动信息移除到空气动力学表面，并且仅为推力矢量控制的喷射翼片提供俯仰和偏航信息。 滚动信息通过齿轮求和机制去除。 所产生的桨距和偏航输出用于驱动推力矢量控制喷射翼片。 相同的动力执行器用于空气动力学控制表面和喷射翼片。