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公开(公告)号：US20220403774A1
公开(公告)日：2022-12-22
申请号：US17716290
申请日：2022-04-08
摘要： A gas turbine engine for an aircraft includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A free turbine is configured to be driven by gas flow from the core engine. A propulsor section aft of the core engine and is driven by the free turbine. An exhaust duct routes exhaust gases from the core engine to the free turbine. The free turbine is disposed aft of the propulsor section and the exhaust duct includes an outlet aft of the propulsor section communicating gas flow to drive the free turbine. An aircraft is also disclosed.
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公开(公告)号：US11326555B2
公开(公告)日：2022-05-10
申请号：US16358189
申请日：2019-03-19
发明人： Stephan Uhkoetter , Uwe Kracht
摘要： A gearbox for a gas turbine engine with a rotatably mounted structural component that is formed with an at least approximately rotationally symmetrical duct into which, starting from its radially inner area, oil from an oil supply which is fixedly attached at the housing can be introduced. Starting from the oil supply, an introduction direction of the oil into the duct encloses an angle of 90° or an angle of between 60° and 90° with the axial extension direction of the duct. Additionally, in the circumferential direction of the duct, the introduction direction of the oil encloses an angle with the radial extension direction that is larger than or equal to 0° and smaller than 90°.
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公开(公告)号：US10024235B2
公开(公告)日：2018-07-17
申请号：US14608227
申请日：2015-01-29
摘要： A gas turbine engine has a propulsion unit and a gas generating core. The propulsion unit includes a fan and a free turbine, wherein the free turbine is connected to drive the fan about a first axis. The gas generating core includes a compressor, a combustion section, and a gas generating core turbine. The compressor and the gas generating core turbine are configured to rotate about a second axis. An inlet duct is configured to deliver air from the fan to the gas generating core. The inlet duct has a crescent shaped cross-section near the fan.
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公开(公告)号：US20180051627A1
公开(公告)日：2018-02-22
申请号：US15239086
申请日：2016-08-17
CPC分类号： F02C3/10 , B64D27/10 , B64D33/02 , B64D33/04 , F01D25/30 , F02C7/36 , F02K3/062 , F02K3/12 , F05D2220/32 , F05D2250/314 , F05D2260/40311
摘要： A gas turbine engine for an aircraft includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A free turbine is configured to be driven by gas flow from the core engine. A propulsor section aft of the core engine and is driven by the free turbine. An exhaust duct routes exhaust gases from the core engine to the free turbine. The free turbine is disposed aft of the propulsor section and the exhaust duct includes an outlet aft of the propulsor section communicating gas flow to drive the free turbine. An aircraft is also disclosed.
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公开(公告)号：US08887488B1
公开(公告)日：2014-11-18
申请号：US13084800
申请日：2011-04-12
申请人： Jose R. Paulino
发明人： Jose R. Paulino
CPC分类号： F01D13/003
摘要： A high efficiency power plant for a UAV with a high pressure ratio gas turbine engine used for low power operation such as loiter speed and a low pressure ratio gas turbine engine used for high power operation. A power turbine receives hot gas flows from the two engines to drive an output shaft. At low power operation, only the high pressure ratio engine is operated. At high power operation, both engines are operated where the exhaust from the high pressure ratio engine is used to drive a turbine of the low pressure ratio engine. A compressor of the low pressure ratio engine supplies compressed air to a combustor that produces a hot gas stream that is passed through the power turbine.
摘要翻译： 用于具有用于低功率操作的高压比燃气涡轮发动机的无人机的高效率发电机，例如用于大功率运行的低速运行和低压比燃气涡轮发动机。 动力涡轮机接收来自两个发动机的热气流以驱动输出轴。 在低功率运行时，只有高压比发动机运转。 在大功率操作中，两个发动机都是在来自高压比发动机的排气被用于驱动低压比发动机的涡轮机的情况下操作的。 低压比发动机的压缩机将压缩空气供给到产生通过动力涡轮机的热气流的燃烧器。
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公开(公告)号：US08844266B1
公开(公告)日：2014-09-30
申请号：US13251946
申请日：2011-10-03
申请人： Jose R. Paulino
发明人： Jose R. Paulino
CPC分类号： F02C6/12 , F01D5/025 , F01D5/043 , F05D2220/40 , F05D2260/37
摘要： A variable bypass ratio augmented gas turbine engine system for a UAV with a high pressure ratio gas turbine engine used for low power operation such as loiter speed and a low pressure ratio gas turbine engine used for high power operation. A power turbine receives hot gas flows from the two engines to drive an output shaft. At low power operation, only the high pressure ratio engine is operated. At high power operation, both engines are operated where the exhaust from the high pressure ratio engine is mixed with bleed off air form the second compressor to produce a second hot gas flow in a second combustor to drive the second turbine. The remaining compressed air from the second compressor is passed into a third combustor to produce a third hot gas flow that then flows into the power turbine.
摘要翻译： 一种用于UAV的可变旁路比增强燃气轮机发动机系统，其具有用于低功率运行的高压比燃气涡轮发动机，例如用于大功率运行的低速运行和低压比燃气涡轮发动机。 动力涡轮机接收来自两个发动机的热气流以驱动输出轴。 在低功率运行时，只有高压比发动机运转。 在高功率操作下，两个发动机都在来自高压比发动机的排气与排出空气混合形成第二压缩机的情况下操作，以在第二燃烧器中产生第二热气流以驱动第二涡轮机。 来自第二压缩机的剩余压缩空气被送入第三燃烧器，产生第三热气流，然后流入动力涡轮。
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公开(公告)号：US4254619A
公开(公告)日：1981-03-10
申请号：US901934
申请日：1978-05-01
CPC分类号： F04D29/362 , F02K3/075 , F02K3/12 , Y02T50/671
摘要： A pair of turbofan engines are cross connected such that during normal-mode operation horsepower can be shared by the respective cores, and when one engine core becomes inoperative the fan of that engine can be driven by the turbine of the operative engine to thereby maintain a substantial thrust output. In order to balance the respective thrust outputs, variable inlet guide vanes are controlled to decrease the fan mass flow in the operative engine and increase the fan mass flow in the inoperative engine. The variable inlet guide vanes are so constructed as to only partially span the fan duct so as to not appreciably affect the airflow to the core when the inlet guide vane angle setting is altered to allow the core to thereby retain a high level of supercharging during this operational period of maximum power demand.
摘要翻译： 一对涡轮风扇发动机是交叉连接的，使得在正常模式操作期间，功率可以由相应的核共享，并且当一个发动机核心变得不起作用时，该发动机的风扇可以由操作发动机的涡轮驱动，从而维持 大推力输出。 为了平衡各个推力输出，控制可变入口导向叶片以减少操作发动机中的风扇质量流量，并增加不可操作的发动机中的风扇质量流量。 可变入口引导叶片被构造成仅部分跨越风扇管道，以便当入口导向叶片角度设置被改变时不会明显地影响到气流的流动，从而允许岩心在此期间保持高水平的增压 最大电力需求运行期。
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公开(公告)号：US4185460A
公开(公告)日：1980-01-29
申请号：US864857
申请日：1977-12-27
申请人： M. Samuel Moore , Charles F. Paluka
发明人： M. Samuel Moore , Charles F. Paluka
CPC分类号： F02C9/42 , Y02T50/671
摘要： An aircraft having two turbine engines is provided with both torque and temperature sensitive electronic circuitry to control the fuel supplied to the turbine engines. Pushbutton switches are provided for the selection of the desired torque level by the pilot. The fuel to either engine is reduced, regardless of output torque and its relationship to the pushbutton values of selected torque, when the engine temperature exceeds a predetermined safety level. Failsafe operation is provided through the use of a main fuel supply path including a manual fuel control valve extending from the fuel pump to the engine fuel nozzles, and a normally closed bypass fuel control line which selectively diverts fuel from the principal path under the control of the temperature and torque responsive electronic circuitry. An electromagnetically operated valve in the bypass line is normally closed and is selectively operated to the desired open condition under the control of the torque and temperature responsive circuitry mentioned above, to reduce fuel supplied to the turbine engines.
摘要翻译： 具有两个涡轮发动机的飞机设置有扭矩和温度敏感的电子电路，以控制供应到涡轮发动机的燃料。 提供按钮开关用于由飞行员选择所需的扭矩水平。 当发动机温度超过预定的安全水平时，不管输出扭矩和其与所选转矩的按钮值的关系如何，对任一发动机的燃料减少。 通过使用包括从燃料泵延伸到发动机燃料喷嘴的手动燃料控制阀的主要燃料供给路径以及在主控制路径下选择性地转移燃料的常闭旁路燃料控制线来提供故障保护操作， 温度和转矩响应电子电路。 旁路管路中的电磁操作阀常闭，并在上述转矩和温度响应电路的控制下选择性地操作到所需的开启状态，以减少供应到涡轮发动机的燃料。
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公开(公告)号：US4062186A
公开(公告)日：1977-12-13
申请号：US686014
申请日：1976-05-13
申请人： Barton H. Snow , Frank R. Homan
发明人： Barton H. Snow , Frank R. Homan
CPC分类号： F02C7/275 , F02C7/262 , F05D2220/50 , Y02T50/671
摘要： A torque converter is interconnected between the fan and core rotor of a turbofan engine such that the speed of the core rotor can be boosted from windmill speed to a speed sufficient to allow an in-flight start by selectively extracting power from the windmilling fan during the start sequence of the engine. Control logic is included to automatically drain the oil from, and thereby unload, the torque converter whenever the engine is in the operating speed region. Further assurance is provided by an overrunning clutch which decouples the system when the core rotational speed exceeds the converter output.
摘要翻译： 变矩器在涡轮风扇发动机的风扇和转子之间相互连接，使得转子的转速可以从风车速度提升到足够的速度，从而通过选择性地从风车风扇中提取动力 引擎启动顺序。 包括控制逻辑，以便每当发动机处于操作速度区域时，自动排出油液并从而卸载变矩器。 进一步的保证由超越离合器提供，当离心转速超过转换器输出时，该离合器使系统解耦。
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公开(公告)号：US3523423A
公开(公告)日：1970-08-11
申请号：US3523423D
申请日：1968-03-11
申请人： ROLLS ROYCE
CPC分类号： F02K1/16
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