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51. 发明申请

WO2014175946A3 AIRCRAFT POWER SYSTEM 审中-公开
标题翻译：飞机电源系统
公开(公告)号：WO2014175946A3
公开(公告)日：2014-12-24
申请号：PCT/US2014016859
申请日：2014-02-18
申请人： ROLLS ROYCE CORP
发明人： KARAM MICHAEL ABRAHAM , HEATHCO CRAIG , EIFERT ANDREW
IPC分类号： F02K3/12 , F02C3/30
CPC分类号： 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
摘要： A system is disclosed in which an aircraft includes a tank capable of storing a pressurized working fluid and delivering the working fluid to an engine. The working fluid can be used to increase the power of the aircraft engine by increasing mass flow through the engine and cooling temperatures in a combustor of the engine. In one embodiment the engine is a gas turbine engine. The aircraft can be a multi-engine aircraft in which when one engine experiences operational difficulties the tank can provide pressurized working fluid to another of the aircraft engines to boost power.
摘要翻译：公开了一种系统，其中飞机包括能够存储加压工作流体并将工作流体输送到发动机的罐。工作流体可用于通过增加通过发动机的质量流量和发动机的燃烧室中的冷却温度来增加飞机发动机的功率。在一个实施例中，发动机是燃气涡轮发动机。该飞机可以是多引擎飞机，其中当一个发动机遇到操作困难时，该油箱可以向另一个飞机发动机提供加压工作流体以提升功率。

52. 发明申请

WO2013137980A1 AEROSPACE ENGINE WITH AUGMENTING TURBOJET 审中-公开
标题翻译：航空发动机带有增压涡轮
公开(公告)号：WO2013137980A1
公开(公告)日：2013-09-19
申请号：PCT/US2013/022961
申请日：2013-01-24
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： KUPRATIS, Daniel, Bernard , STAUBACH, Joseph, B.
IPC分类号： F02K3/12
CPC分类号： F02C3/04 , F02C3/13 , F02C6/00 , F02C6/02 , F02C9/18 , F02K3/12 , F05D2250/30 , F05D2250/311 , F05D2270/07
摘要： A gas turbine engine system includes a fan section, a low pressure compressor section downstream of the fan section, a first engine core downstream from the low pressure compressor section, a second engine core downstream from the low pressure compressor section, and a flowpath control mechanism configured to selectively restrict fluid flow through the second engine core. The first engine core includes a first engine core compressor section, a first engine core combustor downstream of the first engine core compressor section, and a first engine core turbine section downstream of the first engine core combustor. The second engine core includes a second engine core compressor section, a second engine core combustor downstream of the second engine core compressor section, and a second engine core turbine section downstream of the second engine core combustor.
摘要翻译：燃气涡轮发动机系统包括风扇部分，风扇部分下游的低压压缩机部分，低压压缩机部分下游的第一发动机芯，低压压缩机部分下游的第二发动机芯，以及流路控制机构被配置为选择性地限制流过第二发动机芯的流体。第一发动机机芯包括第一发动机核心压缩机部分，第一发动机核心压缩机部分下游的第一发动机核心燃烧器和第一发动机核心燃烧器下游的第一发动机芯涡轮机部分。第二发动机机芯包括第二发动机芯压缩机部分，第二发动机芯压缩机部分下游的第二发动机核心燃烧器和第二发动机芯燃烧器下游的第二发动机芯涡轮机部分。

53. 发明公开

KR1020130125712A 제트 엔진 无效
标题翻译：喷气发动机
公开(公告)号：KR1020130125712A
公开(公告)日：2013-11-19
申请号：KR1020130032346
申请日：2013-03-26
申请人： 박병만
发明人： 박병만
IPC分类号： F02K3/12 , F02K7/14 , F02C6/20
摘要： A jet engine of the present invention comprises: an air compression part including air suction ports provided on both sides of the air compression part to suck external air, a compressor combined between the air suction ports to be rotated to correspond to the air suction ports, compressing air sucked through the air suction ports, and guiding the compressed air to a turbine, the turbine provided on the outside of the compressor to provide the compressor with power, and a separation duct provided between the compressor and the turbine to guide the compressed air such that the compressed air is supplied to a combustion chamber via the upper part of the turbine; a combustion part disposed in front of the air compression part to burn, with fuel, the compressed air supplied from the air compression part; and an air exhaust part disposed in the rear of the air compression part to discharge, to the outside, combustion gas discharged from the combustion part and generate thrust. According to the present invention, a jet engine can solve the problem of air resistance to the cross-sectional area by sucking air in the side to the advancing direction of the aircraft, can naturally cool the turbine by allowing the sucked air to be compressed and pass through the turbine, and can generate a high thrust by inducing greater expansion energy in the combustion part as the compressed air which has cooled the turbine is preheated by the heat exchange with the turbine to improve the compressibility of the compressed air. Also, the jet engine can jointly operate a subsonic fuel engine and a supersonic fuel engine.
摘要翻译：本发明的喷气发动机包括：空气压缩部，包括设置在空气压缩部的两侧的空气吸入口，以吸入外部空气;压缩机，组合在要旋转的空气吸入口之间以对应于空气吸入口; 压缩通过空气吸入口吸入的空气，以及将压缩空气引导到涡轮机，所述涡轮机设置在压缩机的外侧，为压缩机提供动力;以及分离管道，设置在压缩机和涡轮机之间以引导压缩空气使得压缩空气经由涡轮机的上部供应到燃烧室; 燃烧部，其设置在所述空气压缩部的前方，利用燃料将从所述空气压缩部供给的压缩空气燃烧; 以及排气部，其设置在所述空气压缩部的后部，以将从所述燃烧部排出的燃烧气体排出到外部，并产生推力。根据本发明，喷气发动机可以通过在飞行器的前进方向上吸入空气来解决对横截面积的空气阻力的问题，通过允许吸入的空气被压缩自然地冷却涡轮机，通过涡轮机，并且当通过与涡轮机的热交换来预热涡轮机冷却的压缩空气以提高压缩空气的压缩性时，可以通过在燃烧部分中引起更大的膨胀能而产生高推力。此外，喷气发动机可以共同操作亚音速燃料发动机和超音速燃料发动机。

54. 发明公开

KR1020160140703A 쌍발 엔진 헬리콥터의 제 1 터빈 엔진의 고장을 탐지하는 것 및 제 2 터빈 엔진을 작동시키는 것을 위한 방법, 및 대응하는 장치 审中-实审
标题翻译： 1 2检测双发动机直升机第一涡轮发动机故障的方法及运行第二台涡轮发动机及相应装置的方法
公开(公告)号：KR1020160140703A
公开(公告)日：2016-12-07
申请号：KR1020167027526
申请日：2015-03-20
申请人： 사프란 헬리콥터 엔진스
发明人： 레셔파비앙 , 마린쟝필리프쟈크 , 에쉐파르필리프
IPC分类号： F02K3/12 , B64D31/12 , F02C3/10 , F02C9/46 , F02C9/56
CPC分类号： F02C9/56 , B64D31/06 , F02C3/10 , F02C9/46 , F02K3/12 , F05D2220/329 , F05D2270/091 , F05D2270/093 , F05D2270/095 , F05D2270/335 , Y02T50/671 , B64D31/12
摘要： 쌍발엔진헬리콥터의제 1 터빈엔진의고장을탐지하는것 및제 2 터빈엔진을제어하는것을위한방법, 및대응하는장치본 발명은쌍발엔진헬리콥터의오작동하는엔진(4)으로지칭되는제 1 터보샤프트엔진의기능장애를탐지하는것 및정상작동하는엔진(5)으로지칭되는제 2 터보샤프트엔진을제어하는것을위한방법에관한것이고, 각각의엔진(4, 5)은최대동력상황을정의하는조절장치에의해조절되는비상정지수단들을구비하고, 다음의단계들, 즉: 상기오작동하는엔진(4)의고장의징후를탐지하는단계(10); 고장의징후가탐지되는경우상기정상작동하는엔진(5)의상기비상정지수단들을최대동력단발엔진상황에대응하는비상정지수단들로수정하는단계(11); 상기오작동하는엔진(4)의고장을확인하는단계(12); 고장이확인된경우상기정상작동하는엔진(5)의연료공급의유량의즉각적인증가를제어하는단계(13);를구비하는것을특징으로한다.
摘要翻译：本发明涉及一种用于检测双引擎直升机的称为故障发动机（4）的第一涡轮发动机的故障的方法，用于操作称为声音引擎（5）的第二涡轮发动机，每个发动机（4,5）包括由限定最大功率速度的调节装置调节的保护端止动件，其特征在于包括：检测所述故障发动机（4）的故障指数的步骤（10）; 在检测到故障指标的情况下，修改所述端部止挡件用于保护所述声音引擎（5）到对应于最大功率单引擎速度的保护端部停止的步骤（11）确定所述故障发动机（4）的故障的步骤（12）; 在确定故障的情况下，指示增加对所述声音引擎（5）的燃料供给速率的步骤（13）。

55. 发明公开

KR1020120055520A 다축 다단 제트엔진 无效
标题翻译：多轴/压缩喷气发动机
公开(公告)号：KR1020120055520A
公开(公告)日：2012-05-31
申请号：KR1020120049083
申请日：2012-05-09
申请人： 박병만
发明人： 박병만
IPC分类号： F02K3/12 , F02K7/14 , F02C6/20
摘要： PURPOSE: A multi-shaft and multi-stage jet engine is provided to obtain high thrust by increasing suction air amount and a compression ratio because compressed air cools a turbine with passing through the turbine and secondary compression and pre-heating are operated at the same time. CONSTITUTION: A multi-shaft and multi-stage jet engine comprises one or more compressors(4), turbines, shafts(3), and compressing/discharging/separating ducts(5). Air is inhaled from both sides of the jet engine. Types of the jet engine are one-stage, multi-stage, or combined compression methods. Cooling, preheating, and the compression process operate in the turbine.
摘要翻译：目的：提供多轴和多级喷气发动机，以通过增加吸入空气量和压缩比来获得高推力，因为压缩空气通过涡轮冷却涡轮，并且二次压缩和预热在同一运行时间。构造：多轴和多级喷气发动机包括一个或多个压缩机（4），涡轮机，轴（3）和压缩/排放/分离导管（5）。从喷气发动机的两侧吸入空气。喷气发动机的类型是一级，多级或组合式压缩方法。冷却，预热和压缩过程在涡轮机中运行。

56. 发明授权

KR102339468B1 쌍발 엔진 헬리콥터의 제 1 터빈 엔진의 고장을 탐지하는 것 및 제 2 터빈 엔진을 작동시키는 것을 위한 방법, 및 대응하는 장치 有权
公开(公告)号：KR102339468B1
公开(公告)日：2021-12-15
申请号：KR1020167027526
申请日：2015-03-20
IPC分类号： F02K3/12 , B64D31/12 , F02C3/10 , F02C9/46 , F02C9/56
摘要： 쌍발엔진헬리콥터의제 1 터빈엔진의고장을탐지하는것 및제 2 터빈엔진을제어하는것을위한방법, 및대응하는장치본 발명은쌍발엔진헬리콥터의오작동하는엔진(4)으로지칭되는제 1 터보샤프트엔진의기능장애를탐지하는것 및정상작동하는엔진(5)으로지칭되는제 2 터보샤프트엔진을제어하는것을위한방법에관한것이고, 각각의엔진(4, 5)은최대동력상황을정의하는조절장치에의해조절되는비상정지수단들을구비하고, 다음의단계들, 즉: 상기오작동하는엔진(4)의고장의징후를탐지하는단계(10); 고장의징후가탐지되는경우상기정상작동하는엔진(5)의상기비상정지수단들을최대동력단발엔진상황에대응하는비상정지수단들로수정하는단계(11); 상기오작동하는엔진(4)의고장을확인하는단계(12); 고장이확인된경우상기정상작동하는엔진(5)의연료공급의유량의즉각적인증가를제어하는단계(13);를구비하는것을특징으로한다.

57. 发明授权

US11781507B2 Multi-mode combined cycle propulsion engine 有权
公开(公告)号：US11781507B2
公开(公告)日：2023-10-10
申请号：US17853691
申请日：2022-06-29
申请人： ATRX, Inc.
发明人： John A Bossard , John L Bergmans
IPC分类号： F02K7/16 , F02K3/10 , F01D9/04 , F02K9/78 , F02K9/48 , F02K9/08 , F02K9/30 , F02K9/42 , F02K3/12 , F02K9/26 , F02K9/97 , F02K7/18 , F02K9/76
CPC分类号： F02K7/16 , F01D9/041 , F02K3/10 , F02K3/12 , F02K7/18 , F02K9/08 , F02K9/26 , F02K9/30 , F02K9/42 , F02K9/48 , F02K9/76 , F02K9/78 , F02K9/97 , F05D2220/74 , F05D2240/128 , F05D2240/35
摘要： A turbojet engine capable of operation in an Air Turbo Rocket (ATR) mode includes a compressor, a rotatable turbine wheel comprising turbine blades, a non-rotating guide vane ring comprising guide vanes, a turbine shaft configured to power said compressor, a combustor, a gas generator, and a main combustor. The main combustor is configured to combust hot, fuel rich gas from the gas generator in air compressed by the compressor. Hot, fuel rich gas from the gas generator is directed towards the turbine blades by a directing means.

58. 发明申请

US20220403774A1 GAS GENERATOR BIFURCATING EXHAUST DUCT TO FREE TURBINE 有权
公开(公告)号：US20220403774A1
公开(公告)日：2022-12-22
申请号：US17716290
申请日：2022-04-08
申请人： Raytheon Technologies Corporation
发明人： Jesse M. Chandler , Gabriel L. Suciu
IPC分类号： F02C3/10 , F02K3/062 , B64D27/10 , B64D33/02 , B64D33/04 , F01D25/30 , F02C7/36 , F02K3/12
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.

59. 发明授权

US11326555B2 Gear and gas turbine engine 有权
公开(公告)号：US11326555B2
公开(公告)日：2022-05-10
申请号：US16358189
申请日：2019-03-19
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Stephan Uhkoetter , Uwe Kracht
IPC分类号： F02K3/12 , F02C7/36 , F02C6/00 , F01D25/18 , F16H1/28 , F16H57/04
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°.

60. 发明授权

US10024235B2 Offset core engine architecture 有权
公开(公告)号：US10024235B2
公开(公告)日：2018-07-17
申请号：US14608227
申请日：2015-01-29
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , James D. Hill , Jesse M. Chandler
IPC分类号： F02C3/14 , F02C3/06 , F02C3/10 , F02C6/02 , F02C7/05 , F02K3/12
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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