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1. 发明公开

EP3114409A1 CHAMBRE DE COMBUSTION ANNULAIRE DE TURBOMACHINE 有权
标题翻译： RINGFÖRMIGEBRENNKAMMERFÜREINEN TURBINENMOTOR
公开(公告)号：EP3114409A1
公开(公告)日：2017-01-11
申请号：EP15706859.4
申请日：2015-01-27
申请人： Safran Helicopter Engines
发明人： SAVARY, Nicolas , BERTEAU, Patrick , CARRERE, Bernard , DUBOURDIEU, Jean-Marc , NAUDOT, Ludovic
IPC分类号： F23R3/00 , F23R3/52 , F23R3/60
CPC分类号： F23R3/52 , F02C7/20 , F05D2230/50 , F05D2230/51 , F05D2230/64 , F05D2230/642 , F05D2240/35 , F05D2240/90 , F05D2260/30 , F23C5/02 , F23D11/103 , F23R3/002 , F23R3/007 , F23R3/28 , F23R3/283 , F23R3/42 , F23R3/425 , F23R3/46 , F23R3/48 , F23R3/50 , F23R3/54 , F23R3/56 , F23R3/58 , F23R3/60 , F23R2900/00005 , F23R2900/00017 , F23R2900/00018 , F23R2900/00019
摘要： The invention relates to an annular turbine engine combustion chamber having an axial direction (X), a radial direction, and an azimuthal direction. Said chamber includes a first annular wall (12) and a second annular wall (14). Each wall defines at least part of the enclosure of the annular combustion chamber. The first and second walls (12, 14) have complementary interlocking elements (12d, 14d). The first wall (12) has at least one first through-hole (12f), while the second wall (14) has at least one second through-hole (14f). The combustion chamber also includes at least one pin inserted into a pair of holes that include a first hole (12f) and a second hole (14f). Said pin (18) is formed by an injector and securely interlocks the first and second walls (12, 14).
摘要翻译：一种用于涡轮机（100）的环形燃烧室（10），所述燃烧室具有轴向方向（X），径向方向和方位方向，并且包括第一环形壁（12）和第二环形壁），限定所述环形燃烧室（10）的体积的至少一部分的每个壁，所述第一和第二壁（12,14）呈现互补的配合元件（12d，14d），所述第一壁（12）至少呈现一个第一通孔（12f），而第二壁（14）呈现至少一个第二通孔（14f），燃烧室（10）还具有接合在一对孔中的至少一个销（18）孔（12f）和第二孔（14f），所述销（18）锁定第一和第二壁（12,14）的配件。

2. 发明授权

EP2338002B1 CAN-ANNULAR GAS TURBINE ENGINE 有权
标题翻译：环罐式燃气轮机
公开(公告)号：EP2338002B1
公开(公告)日：2016-02-24
申请号：EP09789807.6
申请日：2009-06-12
申请人： Siemens Energy, Inc.
发明人： WILSON, Jody W. , NORDLUND, Raymond S. , CHARRON, Richard C.
IPC分类号： F01D9/02 , F23R3/42 , F23R3/46
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/121 , F05D2250/141 , F05D2250/322 , F05D2250/323 , F05D2250/324 , F23R3/425 , F23R3/46

3. 发明授权

EP2324206B1 Gas turbine transition duct with a canted outlet 有权
标题翻译：具有锥形出口燃气轮机入口管道
公开(公告)号：EP2324206B1
公开(公告)日：2013-03-27
申请号：EP09788709.5
申请日：2009-02-17
申请人： Siemens Energy, Inc.
发明人： CHARRON, Richard , MONTGOMERY, Matthew , SNYDER, Gary
IPC分类号： F01D9/02 , F23R3/42 , F23R3/46
CPC分类号： F01D9/023 , F05D2240/128 , F05D2250/25 , F23R3/425 , Y02T50/675

4. 发明公开

EP2530248A1 Linear transition duct for a gas turbine 审中-公开
标题翻译： Gasturbineneinlasskanal mit einem linearen Flusspfad
公开(公告)号：EP2530248A1
公开(公告)日：2012-12-05
申请号：EP12182481.7
申请日：2009-02-17
申请人： Siemens Energy, Inc.
发明人： Charron, Richard C , Montgomery, Matthew , Snyder, Gary D
IPC分类号： F01D9/02 , F23R3/42 , F23R3/46
CPC分类号： F01D9/023 , F05D2240/128 , F05D2250/25 , F23R3/425 , Y02T50/675
摘要： A combustion turbine subsystem that includes a first stage blade array having a plurality of blades extending in a radial direction from a rotor assembly for rotation in a circumferential direction, said circumferential direction having a tangential direction component, an axis of the rotor assembly defining a longitudinal direction, and at least one combustor located longitudinally upstream of the first stage blade array and located radially outboard of the first stage blade array, the combustion turbine subsystem including an annular array of transition ducts each for routing gas flow from a combustor to the first stage blade array, a first transition duct (94) of the annular array of transition ducts comprising a transition duct body (96) having an internal passage (102) extending between an inlet (98) and an outlet (100), the outlet (100) being offset from the inlet (98) in the longitudinal direction and the tangential direction, the transition duct body (96) having a throat (134) positioned therein having a cross-sectional area that is less than other aspects of the transition duct body (96), wherein an axis (130) of the transition duct body (96) downstream of the throat (134) is generally linear, wherein the outlet (100) is formed from a radially outer side (108) generally opposite to a radially inner side (110), the radially outer and inner sides (108, 110) being coupled together with opposed first and second outlet side walls (112, 114), wherein the first transition duct (94) has an axis (130) that is generally linear, wherein the inlet (98) is generally cylindrical and is adjacent to a conical midsection (132), wherein the conical midsection (132) is positioned between the inlet (98) and the throat (134), wherein the conical midsection (132) includes an ever decreasing cross-sectional area until the conical midsection (132) joins the adjacent throat (134).
摘要翻译：一种燃气轮机子系统，其包括具有多个叶片的第一级叶片阵列，所述第一级叶片阵列具有从转子组件在径向方向上沿圆周方向旋转的多个叶片，所述圆周方向具有切向方向分量，所述转子组件的轴线限定纵向并且至少一个燃烧器位于第一级叶片阵列的纵向上游并且位于第一级叶片阵列的径向外侧，燃气轮机子系统包括过渡管道的环形阵列，每个过渡管道用于将燃烧器的气流从燃料管路向第一阶段所述过渡管道的所述环形阵列的第一过渡管道（94）包括具有在入口（98）和出口（100）之间延伸的内部通道（102）的过渡管道本体（96），所述出口）沿纵向方向和切线方向偏离入口（98），过渡管体（96）具有喉部（134）定位在其中具有小于过渡管体（96）的其它方面的横截面面积，其中在喉部（134）下游的过渡管体（96）的轴线（130）大体上是线性的，其中出口（100）由大致与径向内侧（110）相反的径向外侧（108）形成，径向外侧和内侧（108,110）与相对的第一和第二出口侧壁（112， 114），其中所述第一过渡管道（94）具有大致线性的轴线（130），其中所述入口（98）通常为圆柱形并且与锥形中段（132）相邻，其中所述锥形中部（132）定位在入口（98）和喉部（134）之间，其中锥形中段（132）包括不断减小的横截面面积，直到圆锥形中部（132）连接相邻的喉部（134）。

5. 发明公开

EP1722069A1 Combustion turbine engine 审中-公开
标题翻译：燃气轮机
公开(公告)号：EP1722069A1
公开(公告)日：2006-11-15
申请号：EP05010540.2
申请日：2005-05-13
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： Bethke, Sven, Dr. , Krebs, Werner, Dr. , Sattinger, Stanley S.
IPC分类号： F01D9/02 , F02C3/14 , F23R3/42 , F23M13/00
CPC分类号： F23R3/425 , F01D9/023 , F02C3/14 , F05D2240/12 , F05D2240/35 , F05D2260/962
摘要： A combustion turbine engine includes a turbine section and a combustor section,
the combustor section comprising a combustor for producing a hot pressurized gas and a combustor transition being arranged between the combustor and the turbine section for leading the hot pressurized gas to the turbine section,
the turbine section comprising a rotatable turbine having an axial direction and a radial direction, wherein rotation may be imparted to the turbine by the hot pressurized gas being lead to the turbine section,
wherein the combustor transition comprises a hot pressurized gas outlet and wherein at least the hot pressurized gas outlet of the combustor transition is inclined with respect to the radial direction of the turbine such that hot pressurized gas leaving the hot pressurized gas outlet towards the turbine section receives a velocity component in the rotation direction of the turbine.
摘要翻译：燃气涡轮发动机包括涡轮部分和燃烧器部分，燃烧器部分包括用于产生热加压气体的燃烧器和设置在燃烧器和涡轮部分之间的燃烧器过渡部，用于将热的加压气体引导到涡轮部分，涡轮机部分包括具有轴向方向和径向方向的可旋转涡轮机，其中可以通过导致涡轮机部分的热加压气体将旋转赋予涡轮机，其中燃烧器过渡部分包括热加压气体出口，并且其中至少燃烧器过渡的热加压气体出口相对于涡轮机的径向倾斜，使得离开热加压气体出口的涡轮机部分的热压气体在涡轮机的旋转方向上接收速度分量。

6. 发明公开

EP0870990A1 Gasturbine mit toroidaler Brennkammer 失效
标题翻译： Gurburbine mit toroidaler Brennkammer
公开(公告)号：EP0870990A1
公开(公告)日：1998-10-14
申请号：EP97810167.3
申请日：1997-03-20
申请人： Asea Brown Boveri AG
发明人： Keller, Jakob, Prof. Dr. , Suter, Roger
IPC分类号： F23R3/52
CPC分类号： F23R3/425 , F23R3/52
摘要： Bei einer Brennkammer einer Gasturbogruppe weist der Innenraum (8) dieser Brennkammer (1) eine ringförmig toroidale Form auf. Auf den Umfang dieser Brennkammer sind eine Anzahl mit dem Innenraum in Wirkverbindung stehenden Brenner (5) angeordnet, welche eine Drallströmung (9) auslösen. Diese bildet dann ihrerseits einen Vortex-Kern (10), der die Stabilität der Flammenfront gewährleistet.
摘要翻译：燃烧室（1）具有至少一个围绕燃烧室的周边主动地连接到燃烧器（5）的环形环形内部（8）。环形内部具有沿周向分支的热气体管道（11），并位于放置在气体涡轮组之后的涡轮机（3）的流动平面上。热气体管道的端部具有与涡轮机协作的导向叶片（12）。环形环形内部封闭在其中形成有中间空间（14）中的冷却剂（15）的壳体（13）中。属于集气室（6）的燃烧空气（7）供给燃烧器。

7. 发明授权

EP0539636B1 Gas turbine engine 失效
标题翻译：燃气轮机
公开(公告)号：EP0539636B1
公开(公告)日：1996-06-05
申请号：EP91310104.4
申请日：1991-10-31
申请人： HONDA GIKEN KOGYO KABUSHIKI KAISHA
发明人： Inoue, Kazuo, c/o K.K. Honda Gijutsu Kenkyusho , Kishi, Noriyuki, c/o K.K. Honda Gijutsu Kenkyusho , Bannai, Takashi, c/o K.K. Honda Gijutsu Kenkyusho , Endoh, Tsuneo, c/o K.K. Honda Gijutsu Kenkyusho , Aoki, Hisayoshi, c/o K.K. Honda Gijutsu Kenkyusho
IPC分类号： F02C7/105 , F23R3/42
CPC分类号： F02C7/36 , F02C7/105 , F02G2254/30 , F23R3/425 , Y10S74/05

8. 发明授权

EP3204615B1 ARRANGEMENT FOR A GAS TURBINE COMBUSTION ENGINE 有权
公开(公告)号：EP3204615B1
公开(公告)日：2018-11-28
申请号：EP14786755.0
申请日：2014-10-07
申请人： Siemens Energy, Inc.
发明人： LITTLE, David A.
IPC分类号： F01D9/02
CPC分类号： F01D9/023 , F02C7/12 , F02C7/125 , F05D2240/12 , F05D2250/25 , F05D2260/201 , F05D2260/202 , F23R3/42 , F23R3/425 , F23R3/46 , F23R2900/03044
摘要： An arrangement (10) for delivering gases from combustors (15) to a first row of blades. The arrangement (10) includes at least an upstream flow path (60) including an aft first side wall (64) and a downstream flow path (62) including a forward second side wall (66). A convergence junction trailing edge (40) is defined at a downstream terminal edge (41) of the first side wall (64), and the second side wall (66) converges toward the first side wall (64) in the direction of the convergence junction trailing edge (40). An impingement sheet structure (78) is located between and provides impingement cooling air to the first and second side walls (64, 66). Openings (88) provide a cooling air passage between the first and second side walls (64, 66) and provide a flow of post impingement air into the gas path at the convergence junction trailing edge (40).

9. 发明授权

EP2430297B1 TURBINE ENGINE WITH A STRUCTURAL ATTACHMENT SYSTEM FOR TRANSITION DUCT OUTLET 有权
公开(公告)号：EP2430297B1
公开(公告)日：2018-07-11
申请号：EP10704856.3
申请日：2010-01-21
申请人： Siemens Energy, Inc.
发明人： CHARRON, Richard
IPC分类号： F02C3/14 , F23R3/42 , F01D9/02 , F23R3/60
CPC分类号： F01D9/023 , F02C3/14 , F05B2260/301 , F05D2260/94 , F05D2260/941 , F23R3/425 , F23R3/60 , F23R2900/00005
摘要： A structural attachment system for the outlet of a transition duct includes a structural attachment member that has a step over portion with an outer flange at one end thereof and an inner flange at the other end thereof. The step over portion can project away from the inner and outer flanges and can define an open area. The step over portion can have a cross-section that is generally u-shaped, v-shaped, c-shaped, semi-circular, semi-oval, parabolic, or bowed. A portion of the outlet of a transition duct is received within the step over portion of the structural attachment member. Because of such arrangement, the structural attachment member is not constrained circumferentially to fitting in between two neighboring transition ducts. The structural attachment member can manage the thermal displacements that can occur between the transitions, rotor shaft cover and first row of blades during transient engine operation.

10. 发明公开

EP3246631A1 TRANSITION DUCT ASSEMBLY WITH LATE INJECTION FEATURES 有权转让
标题翻译：过渡管道组件具有注射功能
公开(公告)号：EP3246631A1
公开(公告)日：2017-11-22
申请号：EP17161635.2
申请日：2017-03-17
申请人： General Electric Company
发明人： LEBEGUE, Jeffrey Scott , MCMAHAN, Kevin Weston , FLANAGAN, James Scott
IPC分类号： F23R3/46 , F23R3/34 , F23R3/42
CPC分类号： F23R3/346 , F23R3/425 , F23R3/46 , F23R2900/03041 , F23R2900/03044
摘要： A turbomachine 10 includes a plurality of transition ducts 50 disposed in a generally annular array. Each of the plurality of transition ducts 50 includes an inlet 52 an outlet 54, and a passage 56 defining an interior 57 and extending between the inlet 52 and the outlet 54 and defining a longitudinal axis 90, a radial axis 94, and a tangential axis 92. The outlet 54, of each of the plurality of transition ducts 50 is offset from the inlet 52 along the longitudinal axis 90 and the tangential axis 92. The turbomachine 10 includes a support ring assembly downstream of the plurality of transition ducts 50 along a hot gas path 104, and a plurality of mechanical fasteners 200 connecting at least one transition duct 50 of the plurality of transition ducts 50 to the support ring assembly. The turbomachine 10 includes a late injection assembly 210 providing fluid communication for an injection fluid to flow into the interior 57 downstream of the inlet 52 of at least one transition duct 50 of the plurality of transition ducts 50.
摘要翻译：涡轮机10包括布置成大致环形阵列的多个过渡管道50。多个过渡导管50中的每一个包括入口52和出口54以及限定内部57并且在入口52和出口54之间延伸并限定纵向轴线90，径向轴线94和切向轴线的通道56 92.多个过渡导管50中的每一个的出口54沿着纵向轴线90和切向轴线92偏离入口52.涡轮机10包括在多个过渡导管50下游的支撑环组件热气路径104以及将多个过渡导管50中的至少一个过渡导管50连接到支撑环组件的多个机械紧固件200。涡轮机10包括后注射组件210，其提供流体连通以使注射流体流入多个过渡导管50的至少一个过渡导管50的入口52下游的内部57中。

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