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1.发明公开Heat transfer system and method for turbine engine using heat pipes 有权Wärmeübertragungssystemund -verfahrenfürTurbinenmotorenüberWärmerohre
公开(公告)号：EP1884628A2
公开(公告)日：2008-02-06
申请号：EP07112983.7
申请日：2007-07-24
CPC分类号： F01D25/125 , F01D9/06 , F01D25/08 , F02C7/047 , F02K3/06 , F05C2201/0466 , F05D2260/207 , F05D2260/208 , F05D2300/11 , F05D2300/133 , Y02T50/671 , Y02T50/675
摘要： A heat transfer system is provided for a turbine engine of the type including an annular casing (10) with an array of thermally conductive, generally radially-extending strut members disposed therein. The heat transfer system includes at least one arcuate heat pipe (36) disposed in contact with an outer surface of the casing within fore-and-aft limits of the axial extent of the strut members. The heat pipe (36) is thermally coupled to a heat source, such that heat from the heat source can be transferred through the heat pipe (36) and the casing (10) to the strut members.
摘要翻译： 提供了一种用于这种类型的涡轮发动机的传热系统，该涡轮发动机包括具有布置在其中的导热的大致径向延伸的支柱构件阵列的环形壳体（10）。 传热系统包括至少一个弓形热管（36），其布置成与支柱构件的轴向范围的前后限制的壳体的外表面接触。 热管（36）热耦合到热源，使得来自热源的热量可以通过热管（36）和壳体（10）传递到支柱构件。
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2.发明公开De-icing of turbine engine inlet and cooling of lubricant 有权Turbineneinlassenteisungsvorrichtung和润滑剂的冷却装置
公开(公告)号：EP1895123A3
公开(公告)日：2015-05-06
申请号：EP07114905.8
申请日：2007-08-24
发明人： Venkataramani, Kattalaicheri Srinivasan , Moniz, Thomas Ory , Stephenson, Justin Paul , Bailey, William Andrew
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).
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3.发明公开
公开(公告)号：EP1884628A3
公开(公告)日：2014-08-06
申请号：EP07112983.7
申请日：2007-07-24
CPC分类号： F01D25/125 , F01D9/06 , F01D25/08 , F02C7/047 , F02K3/06 , F05C2201/0466 , F05D2260/207 , F05D2260/208 , F05D2300/11 , F05D2300/133 , Y02T50/671 , Y02T50/675
摘要： A heat transfer system is provided for a turbine engine of the type including an annular casing (10) with an array of thermally conductive, generally radially-extending strut members disposed therein. The heat transfer system includes at least one arcuate heat pipe (36) disposed in contact with an outer surface of the casing within fore-and-aft limits of the axial extent of the strut members. The heat pipe (36) is thermally coupled to a heat source, such that heat from the heat source can be transferred through the heat pipe (36) and the casing (10) to the strut members.
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4.发明公开Pulse detonation system for a gas turbine engine having multiple spools 有权Pulsierendes Detonationssystemfüreine Gasturbine mit mehreren Wellen
公开(公告)号：EP1632673A1
公开(公告)日：2006-03-08
申请号：EP05255345.0
申请日：2005-09-01
CPC分类号： F02K7/005 , Y02T50/671
摘要： A gas turbine engine (10) having a longitudinal centerline axis (12) therethrough, including: a fan section (20) at a forward end of the gas turbine engine (10) including at least a first fan blade row connected to a first drive shaft (32); a booster compressor (28) positioned downstream of the fan section (20), the booster compressor (28) including a first compressor blade row and a second compressor blade row connected to a second drive shaft (33) and interdigitated with the first compressor blade row; and, a pulse detonation system (46) for powering the first and second drive shafts (32, 33). The pulse detonation system (46) powers only the second drive shaft (33) during a first designated condition of the gas turbine engine (10) and both the first drive shaft (32) and the second drive shaft (33) during a second designated condition of the gas turbine engine (10). The first and second drive shafts (32, 33) are powered independently of each other by the pulse detonation system (46).
摘要翻译： 一种具有穿过其中的纵向中心线轴线（12）的燃气涡轮发动机（10），包括：在燃气涡轮发动机（10）的前端处的风扇部分（20），至少包括连接到第一驱动 轴（32）; 位于所述风扇部分（20）下游的增压压缩机（28），所述增压压缩机（28）包括与第二驱动轴（33）连接的第一压缩机叶片排和第二压缩机叶片排，并与第一压缩机叶片 行; 以及用于为第一和第二驱动轴（32,33）供电的脉冲爆震系统（46）。 脉冲爆震系统（46）在燃气涡轮发动机（10）的第一指定状态期间仅驱动第二驱动轴（33），并且在第二指定期间在第一驱动轴（32）和第二驱动轴（33） 燃气涡轮发动机（10）的状态。 第一和第二驱动轴（32,33）由脉冲爆震系统（46）彼此独立地供电。
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5.发明授权
公开(公告)号：EP1884628B1
公开(公告)日：2016-11-09
申请号：EP07112983.7
申请日：2007-07-24
CPC分类号： F01D25/125 , F01D9/06 , F01D25/08 , F02C7/047 , F02K3/06 , F05C2201/0466 , F05D2260/207 , F05D2260/208 , F05D2300/11 , F05D2300/133 , Y02T50/671 , Y02T50/675
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公开(公告)号：EP1637711B1
公开(公告)日：2014-05-21
申请号：EP05255493.8
申请日：2005-09-08
发明人： Orlando, Robert Joseph , Venkataramani, Kattalaicheri Srinivasan , Lee, Ching-Pang , Moniz, Thomas Ory , Murrow, Kurt David
CPC分类号： F02C7/18 , F02C5/00 , F05D2260/20 , F05D2260/96 , F23R3/005 , F23R3/04 , F23R7/00 , F23R2900/03044 , F23R2900/03281 , Y02T50/676
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公开(公告)号：EP1637711A3
公开(公告)日：2012-10-17
申请号：EP05255493.8
申请日：2005-09-08
发明人： Orlando, Robert Joseph , Venkataramani, Kattalaicheri Srinivasan , Lee, Ching-Pang , Moniz, Thomas Ory , Murrow, Kurt David
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).
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公开(公告)号：EP1455065B1
公开(公告)日：2006-05-31
申请号：EP04251220.2
申请日：2004-03-03
CPC分类号： F02C3/165 , F02K3/06 , F02K7/02 , Y02T50/671
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公开(公告)号：EP1471243A2
公开(公告)日：2004-10-27
申请号：EP04252347.2
申请日：2004-04-21
发明人： Venkataramani, Kattalaicheri Srinivasan , Butler, Lawrence , Lee, Ching-Pang , Maclin, Harvey Michael
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.
摘要翻译： 可旋转的圆柱形构件（42）具有间隔开的引爆通道，在其中进行爆震循环，使得燃烧气体离开构件的后表面以产生使构件旋转的扭矩。
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公开(公告)号：EP1895123B1
公开(公告)日：2017-06-28
申请号：EP07114905.8
申请日：2007-08-24
发明人： Venkataramani, Kattalaicheri Srinivasan , Moniz, Thomas Ory , Stephenson, Justin Paul , Bailey, William Andrew
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).
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