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1. 发明公开

EP3249205A1 JET ENGINE 有权
标题翻译：喷气发动机
公开(公告)号：EP3249205A1
公开(公告)日：2017-11-29
申请号：EP15893346.5
申请日：2015-05-27
申请人： IHI Corporation
发明人： KIMURA, Takehiko , MUROOKA, Takeshi , KAMEI, Atsushi
IPC分类号： F02K3/06 , F02C7/00 , F02C7/042 , F02K1/16
CPC分类号： F02C9/20 , F01D17/162 , F02C3/04 , F02C7/042 , F02K1/16 , F02K1/165 , F02K3/06 , F05D2220/326 , F05D2220/327 , F05D2240/12 , F05D2270/02 , F05D2270/101 , Y02T50/671
摘要： A jet engine which includes: a fan (3, 31, 32, 33) provided with a plurality of stages of rotor blades (3b1, 3d1, 3g1, 3i1, 3k1); a compressor (4, 5) which compresses air which is sent from the fan (3, 31, 32, 33); a combustor (6) which generates combustion gas by using compressed air generated by the compressor (4, 5); a turbine (7, 8) which generates a driving force from the combustion gas; and a nozzle (11a) which discharges the combustion gas, the jet engine further includes: a variable guide vane (3f1, 3fa1, 3fb1, 3fc1) which is disposed upstream of the rotor blades (3d1, 3g1, 3i1, 3k1) of a second and later stage of the rotor blades (3b1, 3d1, 3g1, 3i1, 3k1) of the fan (3, 31, 32, 33) and which adjusts an inlet angle of air flow against the second and later stage of the rotor blades (3d1, 3g1, 3i1, 3k1); a fluid resistance adjusting device (11b) which adjusts a fluid resistance at the nozzle (11a); and a controller (12) which controls the variable guide vane (3f1, 3fa1, 3fb1, 3fc1) such that the inlet angle at the time of cruise flight is smaller than the inlet angle at the time of acceleration and controls the fluid resistance adjusting device (11b) such that increase in the fluid resistance, due to an increase in a volume flow at an outlet of the fan (3, 31, 32, 33) corresponding to a reduction in the inlet angle, is suppressed.
摘要翻译： 1。一种喷气发动机，其特征在于，具有：具有多级动叶片（3b1,3d1,3g1,3i1,3k1）的风扇（3,31,32,33）; 压缩机（4,5），压缩从风扇（3,31,32,33）送出的空气;压缩机燃烧器（6），其利用压缩机（4,5）产生的压缩空气产生燃烧气体; 从燃烧气体产生驱动力的涡轮机（7,8）和排出燃烧气体的喷嘴（11a），所述喷气发动机还包括：可变导向叶片（3f1,3fa1,3fb1,3fc1），所述可变导向叶片布置在所述转子叶片（3d1,3g1,3i1,3k1）风扇（3,31,32,33）的转子叶片（3b1,3d1,3g1,3i1,3k1）的第二级和后级，并且调节风扇相对于第二级和后级转子叶片的入口角度（3d1,3g1,3i1,3k1）; 调节喷嘴（11a）的流体阻力的流体阻力调节装置（11b）; 和控制器（12），其控制所述可变导向叶片（3f1,3fa1,3fb1,3fc1），使得巡航行驶时的入口角度小于加速时的入口角度，并且控制流体阻力调节装置（11b），使得由于风扇（3,31,32,33）的出口处的体积流量的增加而导致的流体阻力的增加被抑制，所述体积流量对应于入口角度的减小。

2. 发明授权

EP2098704B1 Fan flutter management system in a turbofan engine with variable area fan nozzle 有权
标题翻译： Einem Turbofan mit variablemFandüsenquerschnitt的管理系统
公开(公告)号：EP2098704B1
公开(公告)日：2016-05-04
申请号：EP09250625.2
申请日：2009-03-04
申请人： United Technologies Corporation
发明人： Grabowski, Zbigniew M. , Morris, Robert J.
IPC分类号： F02C9/16 , F02K1/16 , F02K3/06 , F04D29/66
CPC分类号： F02C9/16 , F02K1/16 , F02K3/06 , F04D29/563 , F04D29/667 , F05D2270/709

3. 发明公开

EP2561209A1 SYSTÈME DE COMMANDE DE TYPE HYDRAULIQUE POUR DISPOSITIF D'INVERSION DE POUSSÉE 有权转让
标题翻译：水力发电机组FÜREINEN SCHUBUMKEHRER
公开(公告)号：EP2561209A1
公开(公告)日：2013-02-27
申请号：EP11715589.5
申请日：2011-03-22
申请人： Aircelle
发明人： LE COQ, Vincent, Pierre, Germain
IPC分类号： F02K1/16 , F02K1/76
CPC分类号： F02K1/763 , F02K1/16 , F02K1/766 , F05D2270/64 , F15B15/26
摘要： The present invention relates to a hydraulic control system for a thrust reversal device installed on a jet engine nacelle and combined with a nozzle variation device, which includes at least one mobile cowl translated by a plurality of mutually synchronised single-action actuators (1d, 1g), said hydraulic control system including at least one unit (100d, 100g) for controlling the cylinders according to a variable nozzle mode, and at least one unit (200) for controlling the cylinders according to a thrust reversal mode, characterised in that the control system includes at least one additional regulation unit (400) hydraulically interconnecting the cylinders and including a plurality of control valves (401, 402).
摘要翻译：通过本公开提供了一种用于推力反转装置的液压式控制系统，其具有喷射发动机机舱并且与喷嘴变速装置相关联。控制系统包括至少一个附加控制单元，其将致动器液压连接在一起，其中来自控制单元的喷嘴模式的液压供应管路和来自控制单元的逆向模式然后能够彼此液压地连通。设置多个控制阀，使得当用于以喷嘴模式驱动致动器的单元有效时，相应的液压信号将控制单元的阀控制在使驱动器的致动器的液压供应管线根据反向模式的单位被切断。

4. 发明授权

EP2798183B8 GAS TURBINE ENGINE WITH LOW FAN PRESSURE RATIO 有权转让
公开(公告)号：EP2798183B8
公开(公告)日：2021-01-20
申请号：EP12872281.6
申请日：2012-12-28
发明人： SMITH, Peter G. , OCHS, Stuart S. , SCHWARZ, Frederick M.
IPC分类号： F02K1/00 , F02C3/10 , F02C6/00 , F02C1/06 , F02C3/00 , F02C7/275 , F01D5/14 , F01D17/16 , F02K1/09 , F02K1/16 , F02C7/36 , F02C9/20 , F04D29/56

5. 发明公开

EP3620634A1 VARIABLE CYCLE COMPENSATION IN A GAS TURBINE ENGINE 审中-实审转让
公开(公告)号：EP3620634A1
公开(公告)日：2020-03-11
申请号：EP19196054.1
申请日：2019-09-06
申请人： United Technologies Corporation
发明人： TERWILLIGER, Neil , BENGEA, Sorin
IPC分类号： F02C9/20 , F02C9/58 , F02K1/16 , F02K5/00
摘要： An aspect includes a variable cycle system (210) of a gas turbine engine (20). The variable cycle system (210) includes an actuation system (205), an electric component (212), and a controller (216). The actuation system (205) is configured to adjust a variable cycle of turbomachinery (202) of the gas turbine engine (20). The electric component (212) is operable to provide a shaft power supply or a load corresponding respectively to an adjustment of the turbomachinery (202). The controller (216) is operable to adjust an output of either or both of the actuation system (205) and the electric component (212) for separate control of thrust and cycle responses.

6. 发明授权

EP2561209B1 SYSTÈME DE COMMANDE DE TYPE HYDRAULIQUE POUR DISPOSITIF D'INVERSION DE POUSSÉE 有权转让
标题翻译： SYSTÈMEDE COMMANDE DE TYPE HYDRAULIQUE POUR DISPOSITIF D'INVERSION DEPOUSSÉE
公开(公告)号：EP2561209B1
公开(公告)日：2017-08-16
申请号：EP11715589.5
申请日：2011-03-22
申请人： Safran Nacelles
发明人： LE COQ, Vincent, Pierre, Germain
IPC分类号： F02K1/16 , F02K1/76
CPC分类号： F02K1/763 , F02K1/16 , F02K1/766 , F05D2270/64 , F15B15/26

7. 发明公开

EP3141730A1 TURBOFAN ENGINE OPERATION CONTROL 审中-公开
标题翻译：涡轮增压发动机运行控制
公开(公告)号：EP3141730A1
公开(公告)日：2017-03-15
申请号：EP16186992.0
申请日：2006-10-12
申请人： United Technologies Corporation
发明人： The designation of the inventor has not yet been filed
IPC分类号： F02K1/12 , F02K1/16 , F02K3/075
CPC分类号： F02K1/16 , F02K1/1207 , F02K3/075 , F05D2220/327
摘要： A turbofan engine (10) is provided that includes a spool (14). The spool (14) supports a turbine (18) and is housed within a core nacelle (12). A fan (20) is coupled to the spool (14) and includes a target operability line. The target operability line provides desired fuel consumption, engine performance, and/or fan operability margin. A fan nacelle (34) surrounds the fan (20) and core nacelle (12) to provide a bypass flow path (39) having a nozzle exit area (40). A controller (50) is programmed to command a flow control device (41) for changing the nozzle exit area (40). The change in nozzle exit area (40) achieves the target operability line in response to an engine operating condition that is a function of airspeed and throttle position. A change in the nozzle exit area (40) is used to move the operating line toward a fan stall or flutter boundary by manipulating the fan pressure ratio.
摘要翻译：提供涡扇发动机（10），其包括线轴（14）。阀芯（14）支撑涡轮机（18）并容纳在核心机舱（12）内。风扇（20）联接到阀芯（14）并且包括目标可操作性线。目标可操作性线提供期望的燃料消耗，发动机性能和/或风扇可操作性裕度。风扇机舱（34）围绕风扇（20）和核心机舱（12）以提供具有喷嘴出口区域（40）的旁路流动路径（39）。控制器（50）被编程以命令流量控制装置（41）改变喷嘴出口区域（40）。响应于作为空速和节气门位置的函数的发动机操作条件，喷嘴出口区域（40）的变化实现目标可操作性线。喷嘴出口区域（40）的变化被用于通过操纵风扇压力比将操作线朝向风扇失速或颤动边界移动。

8. 发明公开

EP2971726A2 THRUST EFFICIENT TURBOFAN ENGINE 审中-公开
标题翻译：高效率的涡轮喷气发动机
公开(公告)号：EP2971726A2
公开(公告)日：2016-01-20
申请号：EP14807688.8
申请日：2014-03-14
申请人： United Technologies Corporation
发明人： SABNIS, Jayant
IPC分类号： F02K1/15 , F02K1/16 , F02K3/06
CPC分类号： F02K3/06 , F02C7/36 , F05D2260/40311
摘要： A disclosed turbofan engine includes a gas generator section for generating a gas stream flow. A speed reduction device is driven by the power turbine. A propulsor section includes a fan driven by the power turbine through the speed reduction device at a second speed lower than the first speed for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The fan includes a tip diameter greater than about fifty (50) inches and an Engine Unit Thrust Parameter ("EUTP") defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is less than about 0.30 at a take-off condition.
摘要翻译：公开的涡轮风扇发动机包括用于产生气流流动的气体发生器部分。减速装置由动力涡轮机驱动。推进器部分包括由动力涡轮机通过减速装置以低于第一速度的第二速度驱动的风扇，用于产生推进推力作为通过旁路流动路径的空气的质量流率。风扇包括大于约五十（50）英寸的顶端直径和定义为净发动机推力的发动机单元推力参数（“EUTP”）除以通过旁路流动路径的空气的质量流率，顶端直径并且在起飞状态下动力涡轮的第一转速小于约0.30。

9. 发明公开

EP2074314A1 TURBOFAN ENGINE OPERATION CONTROL 审中-公开
标题翻译：控制涡扇发动机运行
公开(公告)号：EP2074314A1
公开(公告)日：2009-07-01
申请号：EP06851137.7
申请日：2006-10-12
申请人： United Technologies Corporation
发明人： MCVEY, William J.
IPC分类号： F02K1/12 , F02K1/16 , F02K3/075
CPC分类号： F02K1/16 , F02K1/1207 , F02K3/075 , F05D2220/327
摘要： A turbofan engine (10) is provided that includes a spool (14). The spool (14) supports a turbine (18) and is housed within a core nacelle (12). A fan (20) is coupled to the spool (14) and includes a target operability line. The target operability line provides desired fuel consumption, engine performance, and/or fan operability margin. A fan nacelle (34) surrounds the fan (20) and core nacelle (12) to provide a bypass flow path (39) having a nozzle exit area (40). A controller (50) is programmed to command a flow control device (41) for changing the nozzle exit area (40). The change in nozzle exit area (40) achieves the target operability line in response to an engine operating condition that is a function of airspeed and throttle position. A change in the nozzle exit area (40) is used to move the operating line toward a fan stall or flutter boundary by manipulating the fan pressure ratio.

10. 发明授权

EP3812570B1 GAS TURBINE ENGINE WITH LOW FAN PRESSURE RATIO 有权转让
公开(公告)号：EP3812570B1
公开(公告)日：2024-02-21
申请号：EP20210919.5
申请日：2012-12-28
发明人： SMITH, Peter G. , OCHS, Stuart S. , SCHWARZ, Frederick M.
IPC分类号： F02K1/00 , F02C3/10 , F02C6/00 , F02C1/06 , F02C3/00 , F02C7/275 , F01D5/14 , F01D17/16 , F02K1/09 , F02K1/16 , F02C7/36 , F02C9/20 , F04D29/56 , F02K3/075

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