公开(公告)号：EP1882827A3

公开(公告)日：2011-05-25

申请号：EP07252955.5

申请日：2007-07-26

Applicant: United Technologies Corporation

Inventor： Somanath, Nagendra ,  Kumar, Keshava B. ,  Sowa, William A.

IPC: F01D25/16

CPC classification number: F01D25/162 ,  F05D2250/241 ,  F05D2250/60 ,  Y02T50/671

Abstract: An engine casing (12) for a mid-turbine frame (14) having a plurality of radially extending struts (34) includes a ring structure (22) and at least one mount (30). The ring structure has an interior surface (24), an exterior surface (26), and a plurality of equally spaced dimples (28) along the exterior surface (26) and protruding from the interior surface (24). The ring structure (22) is connected to each of the plurality of struts (34) at the interior surface (24) at the dimples (28). The mount (34) is positioned within each of the dimples (28) and transfers load to the engine casing (12).

公开(公告)号：EP1930556A3

公开(公告)日：2011-03-16

申请号：EP07254706.0

申请日：2007-12-05

Applicant: United Technologies Corporation

Inventor： Somanath, Nagendra ,  Kumar, Keshava B. ,  Sowa, William A. ,  Dye, Christopher

IPC: F01D25/16 ,  F01D25/24

CPC classification number: F01D25/162 ,  F01D25/24 ,  Y02T50/671

Abstract: A mid-turbine frame (12) connected to at least one mount (16) of a gas turbine engine transfers a first load from a first bearing (18) and a second load from a second bearing (20) to the mount (16). The mid-turbine frame (12) includes a load transfer unit (22), a torque box (24) rotatably positioned within the load transfer unit (22), and a plurality of struts (26). The load transfer unit (22) has a first locking element (36,38) and combines the first load and the second load into a combined load. The torque box (24) has a second locking element (40,42) that is engagable with the first locking element (36,38) of the load transfer unit (22). The plurality of struts (26) are connected between the torque box (24) and the mount (16), and transfer the combined load from the torque box (24) to the mount (16). The first locking element (36,38) and the second locking element (40,42) are at least one of a rib or a groove.

公开(公告)号：EP0924463B1

公开(公告)日：2004-03-03

申请号：EP98310129.6

申请日：1998-12-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Snyder, Timothy S. ,  Sowa, William A. ,  Morford, Stephen A. ,  van Dyke, Kevin J.

IPC: F23D17/00 ,  F23C7/00 ,  F23R3/12 ,  F23R3/28

CPC classification number: F23D14/82 ,  F23C7/002 ,  F23C2900/07002 ,  F23D14/74 ,  F23D17/00 ,  F23D17/002 ,  F23D2206/10 ,  F23D2209/10 ,  F23D2209/20 ,  F23R3/12 ,  F23R3/286

公开(公告)号：EP0924463A2

公开(公告)日：1999-06-23

申请号：EP98310129.6

申请日：1998-12-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Snyder, Timothy S. ,  Sowa, William A. ,  Morford, Stephen A. ,  van Dyke, Kevin J.

IPC: F23D17/00 ,  F23C7/00 ,  F23R3/12 ,  F23R3/28

CPC classification number: F23D14/82 ,  F23C7/002 ,  F23C2900/07002 ,  F23D14/74 ,  F23D17/00 ,  F23D17/002 ,  F23D2206/10 ,  F23D2209/10 ,  F23D2209/20 ,  F23R3/12 ,  F23R3/286

Abstract: A tangential entry premixing fuel injector ( 10 ) for a gas turbine engine combustor includes a pair of offset scrolls ( 18 ) whose ends define a pair of entry slots ( 36 ) for admitting primary combustion air tangentially into a mixing chamber ( 28 ) bounded by the scrolls ( 18 ) and by longitudinally spaced endplates ( 14, 16 ). An array of fuel injection passages ( 42 ) extends along the length of the slots. The passage array is configured to inject a primary fuel nonuniformly along the length of the air entry slots and to control the fuel penetration depth d in proportion to slot height H . The injector also includes a flame disgorging centerbody ( 48 ) having a bluff tip ( 54 ) longitudinally aligned with the injector's discharge plane ( 22 ) and a secondary fuel conduit ( 80 ) extending through the centerbody for discharging a secondary combustible fluid, preferably gaseous fuel, through a series of fuel discharge openings ( 84 ) in the tip ( 54 ). The flame disgorging centerbody improves fuel injector durability by resisting ingestion of combustion flame into the mixing chamber ( 28 ) and reliably disgorging any flame that is ingested. The controlled fuel penetration depth reinforces the flame disgorging capability of the centerbody by preventing fuel from penetrating into the slowly moving boundary layer attached to the centerbody ( 48 ). The bluff character of the centerbody, in combination with its longitudinal alignment with the fuel injector discharge plane, makes the centerbody capable of anchoring the flame at the discharge plane so that combustion occurs aft of the discharge plane where the combustion flame is unlikely to damage the scrolls or centerbody. Introduction of fuel or fuel and air through the openings in the bluff tip encourage the flame to become anchored to the tip and therefore spatially stabilizes the flame, resulting in additional attenuation of acoustic oscillations and further improved combustor durability. The longitudinally nonuniform injection of primary fuel compensates for any mixing nonuniformities attributable to the flame disgorging centerbody and therefore augments flame stability. The injector and an associated method of premixing fuel and air prior to combustion suppress formation of nitrous oxides, and improve the durability of both the injector and the combustor.

Abstract translation: 用于燃气涡轮发动机燃烧器的切向入口预混合燃料喷射器（10）包括一对偏置涡卷（18），其一端限定一对入口槽（36），用于将初级燃烧空气切向地进入混合室（28） 涡卷（18）和纵向隔开的端板（14,16）。 燃料喷射通道（42）的阵列沿槽的长度延伸。 通道阵列被构造成沿着空气入口狭槽的长度不均匀地喷射一次燃料，并且与槽高度H成比例地控制燃料穿透深度D.喷射器还包括具有虚张出风口尖端的火焰释放中心体（48） 54），其与喷射器的排出平面（22）纵向对齐，以及延伸穿过中心体的次级燃料导管（80），用于通过尖端（54）中的一系列燃料排放开口（84）排出次级可燃液体，优选气体燃料 ）。 火焰喷射中心体通过阻止燃烧火焰进入混合室（28）并可靠地排除任何被摄入的火焰来提高燃料喷射器的耐久性。 受控的燃料穿透深度通过防止燃料渗透到附接到中心体（48）的缓慢移动的边界层中，加强了中心体的火焰排出能力。 中心体的虚张声势特征与其与燃料喷射器排放平面的纵向对准结合使得中心体能够将火焰锚定在排放平面处，使得燃烧发生在排放平面的后方，其中燃烧火焰不太可能损坏 卷轴或中心体。 燃料或燃料和空气通过虚张声光尖端的开口引入，促使火焰锚定到尖端，从而在空间上稳定火焰，从而进一步衰减声振荡并进一步提高燃烧器的耐久性。 主要燃料的纵向不均匀喷射补偿了归因于火焰排出中心体的任何混合不均匀性，因此增加了火焰稳定性。 喷射器和在燃烧之前预混合燃料和空气的相关方法抑制了一氧化二氮的形成，并提高了喷射器和燃烧器的耐久性。

公开(公告)号：EP0849529A3

公开(公告)日：1999-06-09

申请号：EP97310463.1

申请日：1997-12-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Snyder, Timothy S. ,  Sowa, William A. ,  Kramer, Stephen K.

IPC: F23C7/00 ,  F23D17/00

CPC classification number: F23D17/002 ,  F05B2250/322 ,  F23C7/002 ,  F23C2900/07002

Abstract: A method of reducing the tendency of the combustion flame to attach to the centerbody of a tangential entry nozzle 10 is disclosed which comprises mixing fuel and air in a mixing zone 28 within a fuel nozzle assembly, thereby producing a first fuel/air mixture, which is isolated from the combustion products by maintaining sufficiently high axial velocities throughout the mixing zone. The nozzle has a longitudinal axis 26 and two cylindrical-arc scrolls 22,24 with the centerline of each offset from that of the other. Overlapping ends of these scrolls form an air inlet slot therebetween for the introduction of an air/fuel mixture into the fuel nozzle. A combustor-end endplate 18 has a central opening 20 to permit air and fuel to exit into a combustor, while at the opposite end another endplate 16 blocks the nozzle flow area. The scrolls are secured between these endplates. A centerbody 12 is located between the scrolls coaxial with the axis. The centerbody 12 has a base 58 which includes at least one air supply port extending therethrough, and an internal passageway 64. It includes a frustum portion (54) and aerodynamic ramps theat prevent flow reversal and flame stabilisation between the endplates 16,18.

Abstract translation: 公开了一种降低燃烧火焰附着于切向入口喷嘴10的中心体的倾向的方法，其包括在燃料喷嘴组件内的混合区28中混合燃料和空气，由此产生第一燃料/空气混合物，其 通过在整个混合区保持足够高的轴向速度而与燃烧产物分离。 喷嘴具有纵向轴线26和两个圆柱弧形涡卷22,24，其中心线各自偏离另一个的中心线。 这些涡管的重叠端在其间形成用于将空气/燃料混合物引入燃料喷嘴中的空气入口槽。 燃烧器端部端板18具有中心开口20以允许空气和燃料排出到燃烧器中，而在另一端部处，另一端板16堵塞喷嘴流动区域。 卷轴被固定在这些端板之间。 中心体12位于与轴线同轴的涡卷之间。 中心体12具有基座58，基座58包括至少一个贯穿其中的空气供应端口和内部通路64.它包括平截头体部分（54）和空气动力学斜坡，防止端板16,18之间的流动反转和火焰稳定。

公开(公告)号：EP1845237B1

公开(公告)日：2017-08-02

申请号：EP07251453.2

申请日：2007-04-02

Applicant: United Technologies Corporation

Inventor： Kumar, Keshava B. ,  Sowa, William A. ,  Somanath, Nagendra

IPC: F01D25/16 ,  F01D25/24

CPC classification number: F01D25/162 ,  F01D25/24

公开(公告)号：EP2503245A3

公开(公告)日：2014-01-15

申请号：EP12160966.3

申请日：2010-11-24

Applicant: United Technologies Corporation

Inventor： Hoke, James B. ,  Cheung, Albert K. ,  Sowa, William A.

IPC: F23R3/50 ,  F23R3/06

CPC classification number: F23R3/50 ,  F23R3/06 ,  Y02T50/675

Abstract: An annular combustor (100) for a gas turbine has a combustion chamber having an interior volume that, in longitudinal section, includes a forward volume (V 1 ), an intermediate volume (V 2 ) and an aft volume (V 3 ). The forward volume (V 1 ) represents from about 30% to about 40% of the combustor interior volume, the intermediate volume (V 2 ) represents from about 10% to about 20% of the combustor interior volume, and the aft volume (V 3 ) represents from about 40% to about 60% of the combustor interior volume.

公开(公告)号：EP2148047A2

公开(公告)日：2010-01-27

申请号：EP09251859.6

申请日：2009-07-23

Applicant: United Technologies Corporation

Inventor： Somanath, Nagendra ,  Dye, Christopher M. ,  Kumar, Keshava B. ,  Sowa, William A.

IPC: F01D25/16 ,  F01D25/24

CPC classification number: F01D25/162 ,  F05D2240/14 ,  F05D2250/60 ,  Y02T50/671

Abstract: An engine casing assembly (12) includes a mid-turbine frame (14), a ring structure (22), a plurality of shell stiffening dimples (28), a cylindrical rail (50), a plurality of struts (34) and a plurality of rail fins (52). The ring structure has an interior surface and an exterior surface. The shell stiffening dimples are along the circumference of the ring structure for stiffening the ring structure. The shell stiffening dimples are formed in the ring structure so that protrusions are formed in the interior surface of the ring structure and indentions are formed in the exterior surface of the ring structure. The cylindrical rail (50) radially surrounds and extends from the exterior surface of the ring structure (22). The struts connect the ring structure to the mid-turbine frame. The rail fins extend from the rail.

Abstract translation: 发动机壳体组件（12）包括中涡轮机架（14），环形结构（22），多个壳体加强凹部（28），圆柱形轨道（50），多个支柱（34）和 多个导轨翅片（52）。 环形结构具有内表面和外表面。 壳体加强凹坑沿着环形结构的圆周，用于加强环形结构。 壳体加强凹坑形成在环形结构中，使得在环形结构的内表面中形成凸起，并且在环形结构的外表面中形成凹口。 圆柱形导轨（50）从环形结构（22）的外表面径向地包围并延伸。 支柱将环形结构连接到中涡轮机架。 导轨翅片从导轨延伸。

公开(公告)号：EP0849529B1

公开(公告)日：2004-03-03

申请号：EP97310463.1

申请日：1997-12-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Snyder, Timothy S. ,  Sowa, William A. ,  Kramer, Stephen K.

IPC: F23C7/00 ,  F23D17/00

CPC classification number: F23D17/002 ,  F05B2250/322 ,  F23C7/002 ,  F23C2900/07002

公开(公告)号：EP0849531A2

公开(公告)日：1998-06-24

申请号：EP97310465.6

申请日：1997-12-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Snyder, Timothy S. ,  Sowa, William A.

IPC: F23C7/00 ,  F23C9/00

CPC classification number: F23C9/006 ,  F23C7/002 ,  F23C2202/40 ,  F23C2900/07002 ,  F23D17/002 ,  F23D2206/10 ,  F23D2209/20 ,  F23D2210/00

Abstract: A method of reducing pressure fluctuations in the combustor of a gas turbine engine resulting from the combustion of fuel and air therein comprises combusting a fuel/air mixture in a combustor downstream of the exit plane of a fuel nozzle assembly such that such recirculation zones generated by the fuel nozzle assembly are in spaced relation to the exit plane at all operating conditions of the engine.

Abstract translation: 一种减少燃料涡轮发动机的燃烧器的燃烧器中由于燃料和空气的燃烧引起的压力波动的方法包括在燃料喷嘴组件的出口平面下游的燃烧器中燃烧燃料/空气混合物，使得由燃料喷嘴组件产生的这种再循环区域 在发动机的所有操作条件下，燃料喷嘴组件与出口平面间隔开。