公开(公告)号：US20060266016A1

公开(公告)日：2006-11-30

申请号：US11140667

申请日：2005-05-27

申请人： Curtis Cowan ,  Stephen Paul ,  Meggan Harris ,  Paul Attridge

发明人： Curtis Cowan ,  Stephen Paul ,  Meggan Harris ,  Paul Attridge

IPC分类号： F02K11/00

CPC分类号： F02K1/1223 ,  F02K1/805 ,  F02K1/822 ,  F05D2260/202 ,  F05D2260/205 ,  Y02T50/675

摘要： An axisymmetric nozzle for a gas turbine engine has divergent flaps and seals disposed about a central longitudinal axis thereof. The divergent flaps and seals each have an inner surface defining cooling air inlet holes at an upstream portion, cooling air exit holes at a downstream portion, and cooling air channels disposed within the divergent flap and seal, and communicating at a first end with the inlet holes and at a second end with the exit holes for conducting cooling air therethrough. Some of the exit holes of the divergent flap are disposed along lateral edge regions thereof. The divergent seals are interposed between adjacent divergent flaps, and each include lateral edge regions extending laterally beyond the exit holes. The lateral edge regions of each divergent seal have an outer surface overlying at least a portion of the exit holes of an adjacent divergent flap.

摘要翻译： 用于燃气涡轮发动机的轴对称喷嘴具有围绕其中心纵向轴线设置的发散的翼片和密封件。 发散翼片和密封件各自具有内表面，其限定在上游部分处的冷却空气入口孔，在下游部分处冷却空气出口孔，以及设置在发散片和密封件内的冷却空气通道，并且在第一端与入口 并且在第二端具有用于传导冷却空气的出口孔。 发散翼片的一些出口孔沿其侧边缘区域设置。 发散的密封件插入在相邻的发散片之间，并且每个都包括侧向延伸超出出口的侧边缘区域。 每个发散密封件的横向边缘区域具有覆盖相邻发散片的至少一部分出口孔的外表面。

公开(公告)号：US20050161527A1

公开(公告)日：2005-07-28

申请号：US10766398

申请日：2004-01-28

申请人： Michael Murphy ,  Curtis Cowan ,  Stephen Paul ,  James Allore ,  Meggan Harris

发明人： Michael Murphy ,  Curtis Cowan ,  Stephen Paul ,  James Allore ,  Meggan Harris

IPC分类号： B05B1/24 ,  B05B7/16 ,  B05C1/00 ,  F02K1/12 ,  F02K1/82

CPC分类号： F02K1/1223 ,  F02K1/822 ,  Y02T50/675

摘要： A nozzle system includes a multiple of circumferentially distributed convergent flaps, divergent flaps and inter-flap seals which circumscribe an engine centerline and define the radial outer boundary of a gas path. Each divergent flap includes a multiple of cooling channels with respective intakes and outlets. As the nozzle transitions between positions, the divergent flap seals move relative a divergent flap longitudinal axis to modulate the cooling airflow which enters the separate intakes.

摘要翻译： 喷嘴系统包括多个周向分布的会聚翼片，发散翼片和翼片间密封件，其围绕发动机中心线并限定气体路径的径向外部边界。 每个发散片包括多个具有各自的入口和出口的冷却通道。 当喷嘴在位置之间转换时，发散翼片密封件相对于发散的翼片纵向轴线移动，以调节进入分开的进气口的冷却气流。

公开(公告)号：US07377099B2

公开(公告)日：2008-05-27

申请号：US11140667

申请日：2005-05-27

申请人： Curtis C. Cowan ,  Stephen A. Paul ,  Meggan Harris ,  Paul Attridge

发明人： Curtis C. Cowan ,  Stephen A. Paul ,  Meggan Harris ,  Paul Attridge

IPC分类号： F02K11/00

CPC分类号： F02K1/1223 ,  F02K1/805 ,  F02K1/822 ,  F05D2260/202 ,  F05D2260/205 ,  Y02T50/675

摘要： An axisymmetric nozzle for a gas turbine engine has divergent flaps and seals disposed about a central longitudinal axis thereof. The divergent flaps and seals each have an inner surface defining cooling air inlet holes at an upstream portion, cooling air exit holes at a downstream portion, and cooling air channels disposed within the divergent flap and seal, and communicating at a first end with the inlet holes and at a second end with the exit holes for conducting cooling air therethrough. Some of the exit holes of the divergent flap are disposed along lateral edge regions thereof. The divergent seals are interposed between adjacent divergent flaps, and each include lateral edge regions extending laterally beyond the exit holes. The lateral edge regions of each divergent seal have an outer surface overlying at least a portion of the exit holes of an adjacent divergent flap.

摘要翻译： 用于燃气涡轮发动机的轴对称喷嘴具有围绕其中心纵向轴线设置的发散的翼片和密封件。 发散翼片和密封件各自具有内表面，其限定在上游部分处的冷却空气入口孔，在下游部分处冷却空气出口孔，以及设置在发散片和密封件内的冷却空气通道，并且在第一端与入口 并且在第二端具有用于传导冷却空气的出口孔。 发散翼片的一些出口孔沿其侧边缘区域设置。 发散的密封件插入在相邻的发散片之间，并且每个都包括侧向延伸超出出口的侧边缘区域。 每个发散密封件的横向边缘区域具有覆盖相邻发散片的至少一部分出口孔的外表面。

公开(公告)号：US09028205B2

公开(公告)日：2015-05-12

申请号：US13495454

申请日：2012-06-13

申请人： Meggan Harris

发明人： Meggan Harris

IPC分类号： F01D11/22 ,  F02C9/16

CPC分类号： F01D11/22 ,  F01D17/08 ,  F01D17/085 ,  F01D17/143 ,  F02C9/16 ,  F05D2240/11 ,  F05D2250/38 ,  F05D2260/57 ,  F05D2270/20 ,  F05D2270/301 ,  F05D2270/303 ,  F05D2270/44

摘要： A system for a turbofan has a variable outer air seal, an actuator coupled to the variable outer air seal, a sensor positioned inside the turbofan for sensing an engine parameter, and a flight controller connected to the turbofan for receiving the parameter from the sensor. The flight controller directs the actuator to regulate the position of the actuator based on the flight condition resulting form the received parameter.

摘要翻译： 用于涡轮风扇的系统具有可变的外部空气密封件，联接到可变外部空气密封件的致动器，位于涡轮风扇内部以用于感测发动机参数的传感器，以及连接到涡轮风扇以用于从传感器接收参数的飞行控制器。 飞行控制器根据从接收到的参数形成的飞行条件，引导执行机构调节执行机构的位置。

公开(公告)号：US20060213198A1

公开(公告)日：2006-09-28

申请号：US11091120

申请日：2005-03-28

申请人： Jaime Arbona ,  Meggan Harris ,  James Allore ,  Steven Laporte

发明人： Jaime Arbona ,  Meggan Harris ,  James Allore ,  Steven Laporte

IPC分类号： F02K1/06

CPC分类号： F02K1/1207 ,  F02K1/805

摘要： An exhaust nozzle assembly includes a plurality of interfitting flap assemblies that are moveable between a maximum area ratio and a minimum area ratio. Each of the pluralities of flap assemblies includes a slot and a wing. The wing fits within an adjacent slot of an adjacent flap assembly. Each of the flap assemblies includes a divergent element that provides a specific geometric shape forming the trailing edge surfaces. The flap element is attached to the divergent element and extends to a static structure. The flap element and the divergent element combine to form a continuous faceted outer surface of the exhaust nozzle assembly substantially void of gaps throughout the range of motion between the maximum and minimum area ratios.

公开(公告)号：US07578133B2

公开(公告)日：2009-08-25

申请号：US11091120

申请日：2005-03-28

申请人： Jaime A. Arbona ,  Meggan Harris ,  James Allore ,  Steven Laporte

发明人： Jaime A. Arbona ,  Meggan Harris ,  James Allore ,  Steven Laporte

IPC分类号： F02K1/00

CPC分类号： F02K1/1207 ,  F02K1/805

摘要： An exhaust nozzle assembly includes a plurality of interfitting flap assemblies that are moveable between a maximum area ratio and a minimum area ratio. Each of the pluralities of flap assemblies includes a slot and a wing. The wing fits within an adjacent slot of an adjacent flap assembly. Each of the flap assemblies includes a divergent element that provides a specific geometric shape forming the trailing edge surfaces. The flap element is attached to the divergent element and extends to a static structure. The flap element and the divergent element combine to form a continuous faceted outer surface of the exhaust nozzle assembly substantially void of gaps throughout the range of motion between the maximum and minimum area ratios.

摘要翻译： 排气喷嘴组件包括可在最大面积比和最小面积比之间移动的多个配合翼片组件。 多个翼片组件中的每一个包括槽和翼。 机翼装配在相邻的皮瓣组件的相邻狭槽内。 每个翼片组件包括提供形成后缘表面的特定几何形状的发散元件。 翼片元件附接到发散元件并延伸到静态结构。 翼片元件和发散元件组合以形成排气喷嘴组件的连续刻面的外表面，其在最大和最小面积比之间的运动范围内基本上无间隙。

公开(公告)号：US20070028621A1

公开(公告)日：2007-02-08

申请号：US11174378

申请日：2005-06-30

申请人： Marc Muldoon ,  Tor Sherwood ,  Meggan Harris ,  Robert Brooks

发明人： Marc Muldoon ,  Tor Sherwood ,  Meggan Harris ,  Robert Brooks

IPC分类号： F02K3/10

CPC分类号： F23R3/28 ,  F23R3/60

摘要： A gas turbine engine augmentor has a centerbody within a gas flowpath from upstream to downstream. The augmentor has upstream and downstream shell sections, a downstream rim of the upstream shell section meeting an upstream rim of the downstream shell section shell section. A plurality of vanes are positioned in the gas flowpath outboard of the centerbody. An augmentor spray bar fuel conduit extends through the centerbody and a first of the vanes to deliver fuel to the centerbody. A seal is mounted to the spray bar and positioned in a recess extending from at least one of the downstream rim of the upstream shell section and upstream rim of the downstream shell section shell section. The seal has a first portion and a second portion engaging the first portion in a backlocked interfitting.

摘要翻译： 燃气涡轮发动机增压器具有从上游到下游的气体流动路径内的中心体。 增压器具有上游和下游壳体部分，上游壳体部分的下游边缘满足下游壳体部分壳体部分的上游边缘。 多个叶片位于中心体外侧的气体流路中。 增强喷雾棒燃料导管延伸穿过中心体和第一叶片以将燃料输送到中心体。 密封件安装到喷杆上并且定位在从上游壳体部分的下游边缘和下游壳体部分壳部分的上游边缘中的至少一个延伸的凹部中。 密封件具有第一部分和第二部分，该第一部分和第二部分接合在后锁合配合件中的第一部分。

公开(公告)号：US20070006590A1

公开(公告)日：2007-01-11

申请号：US11174278

申请日：2005-06-30

申请人： Marc Muldoon ,  Tor Sherwood ,  Meggan Harris ,  Robert Brooks

发明人： Marc Muldoon ,  Tor Sherwood ,  Meggan Harris ,  Robert Brooks

IPC分类号： F02K3/10

CPC分类号： F23R3/20 ,  F23D2211/00

摘要： A gas turbine engine fueling system includes a number of spray bars having conduits extending through associated vanes. A number of fuel injector nozzles are along each conduit. Each of the nozzles are positioned to discharge an associated fuel stream from one of the sides of the associated vane. A number of wear members are each mounted relative to the associated one of the nozzles for a range of motion relative thereto. The wear members movably cooperate with the associated vane to accommodate operating deflection and/or tolerances of the spray bars and vanes.

摘要翻译： 燃气涡轮发动机加油系统包括多个具有延伸穿过相关叶片的导管的喷杆。 沿着每个管道的多个燃料喷射器喷嘴。 每个喷嘴被定位成从相关叶片的一侧的一侧排出相关联的燃料流。 相对于相关联的一个喷嘴，多个磨损构件相对于其相对运动的范围分别安装。 磨损构件与相关联的叶片可移动地协作以适应喷雾杆和叶片的操作偏转和/或公差。

公开(公告)号：US09482115B2

公开(公告)日：2016-11-01

申请号：US13592391

申请日：2012-08-23

申请人： Meggan Harris ,  Jorge I. Farah ,  Christopher Treat ,  Timothy Dale

发明人： Meggan Harris ,  Jorge I. Farah ,  Christopher Treat ,  Timothy Dale

IPC分类号： F01D25/28 ,  F01D25/16 ,  F16B9/02

CPC分类号： F01D25/28 ,  F01D25/162 ,  F16B9/023 ,  Y10T29/49323

摘要： A turbine engine includes multiple tierod supports. Each of the tierod supports is connected to an inner frame case of the turbine engine via multiple fasteners and at least one self anti-rotating bushing component.

摘要翻译： 涡轮发动机包括多个层架支架。 每个层架支撑件通过多个紧固件和至少一个自反向旋转衬套部件连接到涡轮发动机的内框架壳体。

公开(公告)号：US20070220892A1

公开(公告)日：2007-09-27

申请号：US11386305

申请日：2006-03-22

申请人： Meggan Harris ,  Claude Barnett

发明人： Meggan Harris ,  Claude Barnett

IPC分类号： F02K3/10

CPC分类号： F23R3/20

摘要： A turbine engine trailing edge box utilizes a metering plate for creating a pressure differential across the trailing edge box and to support the trailing edge box. The metering plate creates a pressure drop from the front to the rear of the trailing edge box resulting in a film of cooling air on the surface of a flameholder. Slots for receiving the metering plate are located in corrugations formed on the trailing edge box. Once within the slots, force is applied to the metering plate as a result of airflow through the engine to maintain the metering plate within the slots.

摘要翻译： 涡轮发动机后缘箱利用计量板在后缘箱上产生压差并支撑后缘箱。 计量板从后缘盒的前部到后部产生压降，导致在火焰稳定器表面上形成一层冷却空气。 用于接收计量板的槽位于形成在后缘箱上的波纹中。 一旦在槽内，由于通过发动机的气流，将计量盘施加到计量盘上，以将计量盘保持在槽内。