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1. 发明公开

EP2216510A3 Transition duct assemblies and gas turbine engine systems involving such assemblies 审中-公开
标题翻译：涡轮机入口通道的安排和燃气涡轮推进系统具有这样的安排
公开(公告)号：EP2216510A3
公开(公告)日：2014-03-05
申请号：EP10250216.8
申请日：2010-02-09
申请人： United Technologies Corporation
发明人： Fiqueroa, Carlos G. , Smith, Craig F.
IPC分类号： F01D9/02
CPC分类号： F01D9/023 , F05D2260/201
摘要： Transition duct assemblies and gas turbine engine systems involving such assemblies are provided. In this regard, a representative transition duct assembly (120) for a gas turbine engine (100) includes: an impingement sheet (124) having cooling holes (140) formed therethrough, an inlet end (142) and a non-flanged outlet end (144), the impingement sheet being operative to be positioned about an exterior of a transition duct (127;190) such that cooling air is directed to flow about the transition duct; the non-flanged outlet end of the impingement sheet being operative to attach the impingement sheet to the transition duct such that the inlet end is positioned adjacent to an intake end of the transition duct and the outlet end is positioned adjacent to an exhaust end of the transition duct.

2. 发明公开

EP2148140A2 Flow sleeve impingement cooling baffles 审中-公开
标题翻译： Muffenartiges Leitblech mitPrallkühlung
公开(公告)号：EP2148140A2
公开(公告)日：2010-01-27
申请号：EP09251001.5
申请日：2009-03-31
申请人： United Technologies Corporation
发明人： Chokshi, Jaisukhlal V. , Smith, Craig F. , Figueroa, Carlos G. , George, Larry C.
IPC分类号： F23R3/08
CPC分类号： F23R3/08 , F23R3/06 , F23R2900/03044
摘要： A combustor assembly (10) for a turbine engine includes a combustor liner (12), a flow sleeve (14) and a baffle ring (36). The flow sleeve surrounds the combustor liner. An annulus (26) is formed between the flow sleeve and the combustor liner. A plurality of rows of cooling holes (24) are formed in the flow sleeve. The baffle ring radially surrounds the combustor liner and is located in the annulus.
摘要翻译：用于涡轮发动机的燃烧器组件（10）包括燃烧器衬套（12），流动套筒（14）和挡板环（36）。流动套筒围绕燃烧器衬套。在流动套管和燃烧器衬套之间形成有环（26）。在流动套筒中形成有多排冷却孔（24）。挡板环径向包围燃烧器衬套并且位于环形空间中。

3. 发明公开

EP2148139A3 Flow sleeve impingement cooling using a plenum ring 有权
标题翻译：流动套筒冲击冷却用气室环
公开(公告)号：EP2148139A3
公开(公告)日：2013-09-11
申请号：EP09251000.7
申请日：2009-03-31
申请人： United Technologies Corporation
发明人： Chokshi, Jaisukhlal V. , Smith, Craig F. , Figueroa, Carlos G.
IPC分类号： F23R3/00 , F23R3/06 , F23R3/46 , F02K1/82
CPC分类号： F01D5/186 , F02K1/822 , F23R3/002 , F23R3/005 , F23R3/06 , F23R3/54 , F23R2900/03044 , Y02T50/675
摘要： A combustor assembly (10) for a turbine engine includes a combustor liner (12), a flow sleeve (14) and a plenum ring (36). The flow sleeve surrounds the combustor liner to form an annulus (26) radially between the combustor liner and the flow sleeve. The flow sleeve has a plurality of rows of cooling holes (24). The plenum ring radially surrounds the combustor liner in the annulus. The plenum ring has a plurality of bypass tubes (38) for directing axial air flow and radial flow chambers (40) for directing radial air flow.

4. 发明公开

EP2148140A3 Flow sleeve impingement cooling baffles 审中-公开
标题翻译：套筒状的具有挡板的冲击冷却
公开(公告)号：EP2148140A3
公开(公告)日：2013-03-20
申请号：EP09251001.5
申请日：2009-03-31
申请人： United Technologies Corporation
发明人： Chokshi, Jaisukhlal V. , Smith, Craig F. , Figueroa, Carlos G. , George, Larry C.
IPC分类号： F23R3/06 , F23R3/08
CPC分类号： F23R3/08 , F23R3/06 , F23R2900/03044
摘要： A combustor assembly (10) for a turbine engine includes a combustor liner (12), a flow sleeve (14) and a baffle ring (36). The flow sleeve surrounds the combustor liner. An annulus (26) is formed between the flow sleeve and the combustor liner. A plurality of rows of cooling holes (24) are formed in the flow sleeve. The baffle ring radially surrounds the combustor liner and is located in the annulus.

5. 发明公开

EP2144003A2 A combustion liner for a gas turbine engine 审中-公开
标题翻译： Brennkammerwandfüreinen Gasturbinenmotor
公开(公告)号：EP2144003A2
公开(公告)日：2010-01-13
申请号：EP09251009.8
申请日：2009-03-31
申请人： United Technologies Corporation
发明人： Tu, John S. , Chokshi, Jaisukhlal V. , Smith, Craig F.
IPC分类号： F23R3/60 , F23R3/00 , F23M5/08
CPC分类号： F23R3/60 , F01D9/023 , F05D2240/55 , F23M5/085 , F23R3/005 , F23R2900/00012
摘要： A combustion duct assembly (45) has a transition duct (52) and a combustion liner (48) having a hula seal (50) at a downstream end that is forced within an inner wall (55) of the transition duct (52). The combustion liner (48) is held within the transition duct (52) by the hula seal (50), but allowed to move relative to the transition duct (52). The combustion liner (48) is formed with heat transfer columns (60) adjacent the downstream end, and radially inwardly of the hula seal (50).
摘要翻译：燃烧管道组件（45）具有过渡管道（52）和燃烧衬套（48），该燃烧衬套在下游端具有压缩在过渡管道（52）的内壁（55）内的呼啦密封件（50）。燃烧衬套（48）通过呼啦密封件（50）保持在过渡管道（52）内，但允许其相对于过渡管道（52）移动。燃烧衬套（48）由邻近下游端的热传递柱（60）形成，并且在呼啦密封件（50）的径向向内形成。

6. 发明公开

EP2144003A3 A combustion liner for a gas turbine engine 审中-公开
标题翻译：燃烧器衬套用于燃气涡轮发动机
公开(公告)号：EP2144003A3
公开(公告)日：2014-02-12
申请号：EP09251009.8
申请日：2009-03-31
申请人： United Technologies Corporation
发明人： Tu, John S. , Chokshi, Jaisukhlal V. , Smith, Craig F.
IPC分类号： F23R3/60 , F23R3/00 , F23M5/08
CPC分类号： F23R3/60 , F01D9/023 , F05D2240/55 , F23M5/085 , F23R3/005 , F23R2900/00012
摘要： A combustion duct assembly (45) has a transition duct (52) and a combustion liner (48) having a hula seal (50) at a downstream end that is forced within an inner wall (55) of the transition duct (52). The combustion liner (48) is held within the transition duct (52) by the hula seal (50), but allowed to move relative to the transition duct (52). The combustion liner (48) is formed with heat transfer columns (60) adjacent the downstream end, and radially inwardly of the hula seal (50).

7. 发明公开

EP2131110A3 Combustor liner cap assembly 审中-公开
标题翻译：端面更换为燃烧室壁
公开(公告)号：EP2131110A3
公开(公告)日：2013-02-27
申请号：EP09250823.3
申请日：2009-03-24
申请人： United Technologies Corporation
发明人： Tuthill, Richard S. , Smith, Craig F.
IPC分类号： F23R3/60 , F23R3/00
CPC分类号： F23R3/60 , F23R3/002
摘要： A liner cap assembly (30) is disclosed for use in a gas turbine engine combustor (12). The assembly includes an outer ring (52) that extends along an axis. Multiple struts (44) are circumferentially arranged about an inner diameter of the outer ring (52) and extend radially inwardly therefrom. A plate (46) is supported by and axially aligned with the struts (44). The plate (46) includes multiple circumferential openings (66) that support a collar (38) and a premix tube (42) at each of the openings (66). The plate (46) is arranged between leading and trailing edges (80,82) of the struts (44) to provide a stiffened liner cap assembly (30) that is robust and resistant to the vibrations typically found in dry low NOx systems.

8. 发明公开

EP2141335A1 An inlet air heating system for a gas turbine engine 有权
标题翻译： Einlassluft-Heizsystemfüreinen Gasturbinenmotor
公开(公告)号：EP2141335A1
公开(公告)日：2010-01-06
申请号：EP09250925.6
申请日：2009-03-30
申请人： United Technologies Corporation
发明人： Smith, Craig F.
IPC分类号： F02C3/34 , F02C1/08
CPC分类号： F02C3/34 , F02C1/08 , F05D2270/082
摘要： A gas turbine engine (20) has an inlet (22) for delivering air into a compressor section (24). The compressor section (24) is connected to feed air into a combustion section (27), wherein the air mixes with fuel and combusts. The combustion section (27) is connected to turbine rotors (128, 130) such that products of combustion can pass over the turbine rotors (128, 130) to drive the turbine rotors (128, 130). An exhaust (32) communicates with the turbine rotors (128, 130) to receive the products of combustion. A bleed tap (34) communicates the exhaust (32) to the inlet (22). A control (43) controls the amount of exhaust gasses tapped into the inlet (22) to achieve desired operating conditions.
摘要翻译：燃气涡轮发动机（20）具有用于将空气输送到压缩机部分（24）中的入口（22）。压缩机部分24与进料空气连接到燃烧部分27中，其中空气与燃料混合燃烧。燃烧部分（27）连接到涡轮转子（128,130），使得燃烧产物可以通过涡轮转子（128,130）以驱动涡轮转子（128,130）。排气（32）与涡轮机转子（128,130）连通以接收燃烧产物。排放口（34）将排气（32）连通到入口（22）。控制器（43）控制抽吸入入口（22）中的废气量以达到所需的操作条件。

9. 发明公开

EP2131110A2 Combustor liner cap assembly 审中-公开
标题翻译： Stirnseitiger EinbaufürBrennkammerwand
公开(公告)号：EP2131110A2
公开(公告)日：2009-12-09
申请号：EP09250823.3
申请日：2009-03-24
申请人： United Technologies Corporation
发明人： Tuthill, Richard S. , Smith, Craig F.
IPC分类号： F23R3/60
CPC分类号： F23R3/60 , F23R3/002
摘要： A liner cap assembly (30) is disclosed for use in a gas turbine engine combustor (12). The assembly includes an outer ring (52) that extends along an axis. Multiple struts (44) are circumferentially arranged about an inner diameter of the outer ring (52) and extend radially inwardly therefrom. A plate (46) is supported by and axially aligned with the struts (44). The plate (46) includes multiple circumferential openings (66) that support a collar (38) and a premix tube (42) at each of the openings (66). The plate (46) is arranged between leading and trailing edges (80,82) of the struts (44) to provide a stiffened liner cap assembly (30) that is robust and resistant to the vibrations typically found in dry low NOx systems.
摘要翻译：公开了一种用于燃气涡轮发动机燃烧器（12）中的衬套盖组件（30）。组件包括沿轴线延伸的外环（52）。多个支柱（44）围绕外圈（52）的内径周向布置并从其径向向内延伸。板（46）由支柱（44）支撑并且与支柱（44）轴向对准。板（46）包括在每个开口（66）处支撑套环（38）和预混合管（42）的多个周向开口（66）。板（46）布置在支柱（44）的前缘和后缘（80,82）之间，以提供坚固的并且耐受通常在干燥的低NOx系统中发现的振动的加强的衬套帽组件（30）。

10. 发明授权

EP2141335B1 An inlet air heating system for a gas turbine engine 有权
标题翻译：一种用于燃气涡轮发动机的进气加热系统
公开(公告)号：EP2141335B1
公开(公告)日：2012-10-10
申请号：EP09250925.6
申请日：2009-03-30
申请人： United Technologies Corporation
发明人： Smith, Craig F.
IPC分类号： F02C3/34 , F02C1/08
CPC分类号： F02C3/34 , F02C1/08 , F05D2270/082

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