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11. 发明公开

EP1895123A2 De-icing of turbine engine inlet and cooling of lubricant 有权
标题翻译：涡轮发动机入口的除冰和润滑剂的冷却
公开(公告)号：EP1895123A2
公开(公告)日：2008-03-05
申请号：EP07114905.8
申请日：2007-08-24
申请人： GENERAL ELECTRIC COMPANY (a New York Corporation)
发明人： Venkataramani, Kattalaicheri Srinivasan , Moniz, Thomas Ory , Stephenson, Justin Paul , Bailey, William Andrew
IPC分类号： F02C7/047 , F02C7/14
CPC分类号： F02C7/047 , F02C7/14 , F05D2260/208 , Y02T50/672 , Y02T50/675
摘要： A heat transfer system is provided for a turbine engine of the type including an annular inlet cowling (14). The heat transfer system includes at least one heat pipe (28) disposed in contact with an interior of the casing. The heat pipe is thermally coupled to a heat source, such that heat from the heat source can be transferred through the heat pipe (28) and into the inlet cowling (14).
摘要翻译：传热系统被提供用于这种类型的涡轮发动机，其包括环形入口罩（14）。传热系统包括布置成与壳体的内部接触的至少一个热管（28）。热管热耦合到热源，使得来自热源的热量可以通过热管（28）传递并进入入口罩（14）。

12. 发明公开

EP1884625A2 Heat transfer system and method for turbine engine using heat pipes 有权
标题翻译：用于热管的涡轮发动机的传热系统和方法
公开(公告)号：EP1884625A2
公开(公告)日：2008-02-06
申请号：EP07112981.1
申请日：2007-07-24
申请人： General Electric Company
发明人： Venkataramani, Kattalaicheri Srinivasan , Moniz, Thomas Ory , Stephenson, Justin Paul
IPC分类号： F01D9/06 , F01D5/08 , F01D5/18 , F01D25/12
CPC分类号： F02C7/047 , F01D9/065 , F01D25/02 , F01D25/125 , F02C7/14 , F05D2260/208 , F28D7/0008 , F28D15/0275 , Y02T50/672 , Y02T50/675
摘要： A heat transfer system is provided for a turbine engine of the type including an annular casing (14) with an array of generally radially-extending strut members (20) disposed therein. The heat transfer system includes at least one primary heat pipe (36) disposed at least partially inside a selected one of the strut members (20); at least one secondary heat pipe (48) disposed outside the fan casing (14) and thermally coupled to at least one primary heat pipe (36) and to a heat source. Heat from the heat source can be transferred through the secondary heat pipe (48) to the primary heat pipe (36) and to the selected strut member (20).
摘要翻译：提供了用于涡轮发动机的传热系统，该涡轮发动机包括环形壳体（14），环形壳体（14）具有设置在其中的大致径向延伸的支柱构件（20）的阵列。传热系统包括至少一个主热管（36），其至少部分地设置在支柱构件（20）中选定的一个内; 至少一个设置在风扇外壳（14）外部并与至少一个主热管（36）和热源热耦合的次热管（48）。来自热源的热量可通过次级热管（48）传递到主热管（36）并传递到选定的支柱构件（20）。

13. 发明公开

EP1471243A3 Rotating pulse detonation system for a gas turbine engine 审中-公开
标题翻译：燃气涡轮脉冲爆震系统
公开(公告)号：EP1471243A3
公开(公告)日：2007-09-05
申请号：EP04252347.2
申请日：2004-04-21
申请人： GENERAL ELECTRIC COMPANY
发明人： Venkataramani, Kattalaicheri Srinivasan , Butler, Lawrence , Lee, Ching-Pang , Maclin, Harvey Michael
IPC分类号： F02K7/075 , F02K7/02 , F02K7/00 , F02K3/06 , F02C5/04 , F02C5/06 , F01D1/32 , F02C3/16 , F02C7/22 , F23R3/56 , F23R7/00
CPC分类号： F02K3/06 , F02C5/11 , F02C5/12 , F02K7/02 , F05D2250/314 , F23R7/00
摘要： A pulse detonation system (40) for a gas turbine engine (10) having a longitudinal centerline axis (12) extending therethrough includes a rotatable cylindrical member (42) having a forward surface (44), an aft surface (46), and an outer circumferential surface (48), where a plurality of spaced detonation passages (52) are disposed therethrough. Each detonation passage (52) includes at least a portion having a longitudinal axis extending therethrough oriented at a circumferential angle to the longitudinal centerline axis (12). The pulse detonation system (40) further includes a shaft (36) rotatably connected to the cylindrical member (42) and a stator (62) configured in spaced arrangement with the forward surface (44) of the cylindrical member (42) and a portion of the shaft (36). The stator (62) has at least one group of ports formed therein alignable with the detonation passages (52) as the cylindrical member (42) rotates. In this way, detonation cycles are performed in the detonation passages (52) so that combustion gases exit the aft surface (46) of the cylindrical member (42) to create a torque which causes the cylindrical member (42) to rotate.

14. 发明授权

EP1632673B1 Pulse detonation system for a gas turbine engine having multiple spools 有权
标题翻译：一种用于具有多个轴的燃气涡轮脉冲爆轰系统
公开(公告)号：EP1632673B1
公开(公告)日：2007-07-25
申请号：EP05255345.0
申请日：2005-09-01
申请人： GENERAL ELECTRIC COMPANY
发明人： Venkataramani, Kattalaicheri Srinivasan , Davidson, James Paul , Butler, Lawrence
IPC分类号： F02K7/02 , F02K7/075 , F02K7/20 , F02K7/06
CPC分类号： F02K7/005 , Y02T50/671

15. 发明公开

EP1637711A2 High thrust gas turbine engine with modified core system 有权
标题翻译： Hohem Schub Gasturbine mit modifizierter气体发生器
公开(公告)号：EP1637711A2
公开(公告)日：2006-03-22
申请号：EP05255493.8
申请日：2005-09-08
申请人： GENERAL ELECTRIC COMPANY
发明人： Orlando, Robert Joseph , Venkataramani, Kattalaicheri Srinivasan , Lee, Ching-Pang , Moniz, Thomas Ory , Murrow, Kurt David
IPC分类号： F02C5/00
CPC分类号： F02C7/18 , F02C5/00 , F05D2260/20 , F05D2260/96 , F23R3/005 , F23R3/04 , F23R7/00 , F23R2900/03044 , F23R2900/03281 , Y02T50/676
摘要： A gas turbine engine (44) having a longitudinal centerline axis (12) therethrough, including: a fan section (16) at a forward end of the gas turbine engine (44) including at least a first fan blade row connected to a first drive shaft (40); a booster compressor (20) positioned downstream of and in at least partial flow communication with the fan section (16) including a plurality of stages, each stage including a stationary compressor blade row and a rotating compressor blade row connected to a drive shaft (40/51) and interdigitated with the stationary compressor blade row; a core system (45) positioned downstream of the booster compressor (20), where the core system (45) further includes an intermediate compressor (47) positioned downstream of and in flow communication with the booster compressor (20), the intermediate compressor (47) being connected to a second drive shaft (51), and a combustion system (46) for producing pulses of gas having increased pressure and temperature from a fluid flow (52) provided to an inlet (54) thereof so as to produce a working fluid (48) at an outlet (50); and, a low pressure turbine (36) positioned downstream of and in flow communication with the core system (45), the low pressure turbine (36) being utilized to power the first drive shaft (40). The core system (46) may also include an intermediate turbine (49) positioned downstream of the combustion system (46) in flow communication with the working fluid (48), where the intermediate turbine (49) is utilized to power the second drive shaft (51). A first source (64) of compressed air (52) having a predetermined pressure is provided to the combustion system inlet (50) and a second source (66) of compressed air (65) having a pressure greater than the first source (64) of compressed air (52) is provided to cool the combustion system (46).
摘要翻译：一种燃气涡轮发动机（44），其具有穿过其的纵向中心线轴线（12），包括：在燃气涡轮发动机（44）的前端处的风扇部分（16），包括至少第一风扇叶片排，其连接到第一驱动轴（40）; 位于与包括多个级的风扇部分（16）的下游并且至少部分流动连通的增压压缩机（20），每个级包括固定压缩机叶片排和连接到驱动轴（40）的旋转压缩机叶片排 / 51）并与固定压缩机叶片排相互指向; 位于所述增压压缩机（20）下游的核心系统（45），其中所述核心系统（45）还包括位于所述增压压缩机（20）下游并与所述增压压缩机（20）流动连通的中间压缩机（47） 47）连接到第二驱动轴（51）和用于从设置到其入口（54）的流体流（52））产生具有增加的压力和温度的气体脉冲的燃烧系统（46），以产生在出口（50）处的工作流体（48）; 以及位于所述核心系统（45）下游并与所述核心系统（45）流动连通的低压涡轮机（36），所述低压涡轮机（36）用于为所述第一驱动轴（40）供电。核心系统（46）还可以包括位于燃烧系统（46）下游的与工作流体（48）流动连通的中间涡轮机（49），其中中间涡轮机（49）用于为第二驱动轴（51）。具有预定压力的压缩空气（52）的第一源（64）被提供给燃烧系统入口（50）和具有大于第一源（64）的压力的压缩空气（65）的第二源（66）提供压缩空气（52）以冷却燃烧系统（46）。

16. 发明公开

EP1455065A2 Pulse detonation system for a gas turbine engine 有权
标题翻译： Pulsiertes DetonationssystemfürGasturbinen
公开(公告)号：EP1455065A2
公开(公告)日：2004-09-08
申请号：EP04251220.2
申请日：2004-03-03
申请人： GENERAL ELECTRIC COMPANY
发明人： Venkataramani, Kattalaicheri Srinivasan , Butler, Lawrence , Bailey, William Andrew
IPC分类号： F02C5/06 , F02K7/02
CPC分类号： F02C3/165 , F02K3/06 , F02K7/02 , Y02T50/671
摘要： A pulse detonation system for a gas turbine engine having a longitudinal centerline axis (12) extending therethrough, where the pulse detonation system includes an air inlet duct (48) in flow communication with a source of compressed air, the air inlet duct (48) including at least one port (50) formed therein for permitting compressed air to flow therethrough, a fuel injector (52) mounted to the air inlet duct (48) in circumferentially spaced relation to each port (50), and a device mounted to the air inlet duct (48) in circumferentially spaced relation to each fuel injector (52) for initiating a detonation wave. A rotatable ring member (56) is also positioned in coaxial relation around a portion of the air inlet duct (48), with the ring member (56) including at least one stage of detonation (58/60) disposed therein. Accordingly, a detonation wave is produced in each detonation stage (58,60) and combustion gases following each detonation wave create a torque which causes the ring member (56) to rotate. Each detonation stage (58,60) in the ring member (56) further includes a plurality of circumferentially spaced detonation ducts (66) extending tangentially from an inner surface (74) of the ring member (56), wherein the detonation ducts (66) are aligned with each port (50), the fuel injector (52) and the initiation device (54) in a predetermined timing and sequence so that detonation waves are produced therein.
摘要翻译：一种用于具有延伸穿过其中的纵向中心线轴线（12）的燃气涡轮发动机的脉冲爆震系统，其中所述脉冲爆炸系统包括与压缩空气源流动连通的进气管道（48），所述进气管道（48）包括在其中形成的用于允许压缩空气流过其中的至少一个端口（50），与每个端口（50）周向间隔开地安装到空气入口管道（48）的燃料喷射器（52），以及安装到空气入口管道（48）与每个燃料喷射器（52）周向间隔开，用于引发爆震波。旋转环构件（56）也围绕空气入口管道（48）的一部分以同轴的关系定位，环形构件（56）包括设置在其中的至少一个爆震级（58/60）。因此，在每个爆震级（58,60）中产生爆震波，并且在每个爆震波之后的燃烧气体产生使得环件（56）旋转的扭矩。环形构件（56）中的每个爆震级（58,60）还包括从环形构件（56）的内表面（74）切向延伸的多个周向间隔开的爆震导管（66），其中引爆管道（66 ）以预定的定时和顺序与每个端口（50），燃料喷射器（52）和启动装置（54）对准，使得在其中产生爆震波。

17. 发明授权

EP1884625B1 Heat transfer system and method for turbine engine using heat pipes 有权
公开(公告)号：EP1884625B1
公开(公告)日：2017-09-20
申请号：EP07112981.1
申请日：2007-07-24
申请人： GENERAL ELECTRIC COMPANY
发明人： Venkataramani, Kattalaicheri Srinivasan , Moniz, Thomas Ory , Stephenson, Justin Paul
IPC分类号： F01D9/06 , F01D5/08 , F01D5/18 , F01D25/12
CPC分类号： F02C7/047 , F01D9/065 , F01D25/02 , F01D25/125 , F02C7/14 , F05D2260/208 , F28D7/0008 , F28D15/0275 , Y02T50/672 , Y02T50/675

18. 发明授权

EP1942249B1 Heat transfer system for turbine engine using heat pipes 有权
标题翻译：用于与热管的涡轮发动机的传热系统
公开(公告)号：EP1942249B1
公开(公告)日：2015-10-28
申请号：EP07123431.4
申请日：2007-12-18
申请人： GENERAL ELECTRIC COMPANY
发明人： Stephenson, Justin P. , Moniz, Thomas Ory , Venkataramani, Kattalaicheri Srinivasan
IPC分类号： F01D5/04 , F01D5/08 , F01D25/08 , F01D25/10 , F02C7/047 , F01D25/02
CPC分类号： F01D5/046 , F01D5/08 , F01D25/02 , F01D25/08 , F01D25/10 , F02C7/047 , F05D2260/208 , F28D15/0275 , F28F2265/30 , Y02T50/671 , Y02T50/676

19. 发明公开

EP1884625A3 Heat transfer system and method for turbine engine using heat pipes 有权
标题翻译：用于涡轮发动机的过度的热管的热传递的系统和方法
公开(公告)号：EP1884625A3
公开(公告)日：2014-08-06
申请号：EP07112981.1
申请日：2007-07-24
申请人： GENERAL ELECTRIC COMPANY
发明人： Venkataramani, Kattalaicheri Srinivasan , Moniz, Thomas Ory , Stephenson, Justin Paul
IPC分类号： F01D9/06 , F01D5/08 , F01D5/18 , F01D25/12
CPC分类号： F02C7/047 , F01D9/065 , F01D25/02 , F01D25/125 , F02C7/14 , F05D2260/208 , F28D7/0008 , F28D15/0275 , Y02T50/672 , Y02T50/675
摘要： A heat transfer system is provided for a turbine engine of the type including an annular casing (14) with an array of generally radially-extending strut members (20) disposed therein. The heat transfer system includes at least one primary heat pipe (36) disposed at least partially inside a selected one of the strut members (20); at least one secondary heat pipe (48) disposed outside the fan casing (14) and thermally coupled to at least one primary heat pipe (36) and to a heat source. Heat from the heat source can be transferred through the secondary heat pipe (48) to the primary heat pipe (36) and to the selected strut member (20).

20. 发明公开

EP1777394A3 Gas turbine engine combustor hot streak control 审中-公开
标题翻译：控制燃气涡轮机燃烧器的热轧带钢的形成
公开(公告)号：EP1777394A3
公开(公告)日：2012-06-20
申请号：EP06255449.8
申请日：2006-10-23
申请人： GENERAL ELECTRIC COMPANY
发明人： Venkataramani, Kattalaicheri Srinivasan , Orlando, Robert Joseph , Lee, Ching-Pang , Myers, Jr., William Joseph , Cooker, Paul
IPC分类号： F02C9/26 , F23K5/00 , F23K5/06 , F23N1/00 , F23N5/02 , F23N5/24
CPC分类号： F02C9/263 , F05D2270/112 , F05D2270/3032 , F23K5/005 , F23K5/06 , F23K2203/105 , F23N1/00 , F23N1/002 , F23N5/02 , F23N5/022 , F23N5/24 , F23N5/242
摘要： A gas turbine engine combustion system (40) includes a plurality of fuel injectors (30) circumferentially disposed around a combustor (10) in a one to one fuel supply relationship with a plurality of fuel nozzle valves (48), and an electronic controller (76) for controlling the fuel nozzle valves (48) to eliminate and/or reduce hot streaking in response to sensed hot streak conditions. The fuel nozzle valves (48) may be modulating valves. The electronic controller (76) may be used to individually control the fuel nozzle valves (48). The hot streak conditions may be sensed with temperature sensors (55) such as temperature sensors operably mounted in the combustor (10). A program in the electronic controller (76) may be used for determining broken or malfunctioning sensors (55) by calculating a combustor temperature and comparing it to measured temperatures from the sensors (55) and comparing the measured fuel pressures in the individual fuel nozzle circuits (31) with the simulated or calculated fuel pressures.

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