公开(公告)号：US07695241B2

公开(公告)日：2010-04-13

申请号：US11606853

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

Inventor： Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

IPC: F01D5/18 ,  F01D25/12 ,  F04D29/58

CPC classification number: F01D5/186 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2270/172 ,  F15D1/12 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/673 ,  Y02T50/676 ,  Y10S165/903 ,  Y10S415/914

Abstract: An downstream plasma boundary layer shielding system includes film cooling apertures disposed through a wall having cold and hot surfaces and angled in a downstream direction from a cold surface of the wall to an outer hot surface of the wall. A plasma generator located downstream of the film cooling apertures is used for producing a plasma extending downstream over the film cooling apertures. Each plasma generator includes inner and outer electrodes separated by a dielectric material disposed within a groove in the outer hot surface. The wall may be part of a hollow airfoil or an annular combustor or exhaust liner. A method for operating the downstream plasma boundary layer shielding system includes forming a plasma extending in the downstream direction over the film cooling apertures along the outer hot surface of the wall. The method may further include operating the plasma generator in steady state or unsteady modes.

Abstract translation: 下游等离子体边界层屏蔽系统包括薄膜冷却孔，该薄膜冷却孔通过具有冷和热表面的壁设置，并且在下游方向上从壁的冷表面到壁的外部热表面成角度。 位于膜冷却孔下游的等离子体发生器用于产生在膜冷却孔的下游延伸的等离子体。 每个等离子体发生器包括由设置在外部热表面中的凹槽内的电介质材料分开的内部和外部电极。 该壁可以是中空翼型件或环形燃烧器或排气衬套的一部分。 一种用于操作下游等离子体边界层屏蔽系统的方法包括形成沿着下游方向延伸的等离子体沿着壁的外部热表面的膜冷却孔。 该方法还可以包括以等稳态或不稳定模式操作等离子体发生器。

公开(公告)号：US07690885B2

公开(公告)日：2010-04-06

申请号：US11565472

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Daniel Vern Jones

Inventor： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Daniel Vern Jones

IPC: F01D25/12

CPC classification number: F01D11/08 ,  F01D11/10 ,  F05D2240/11 ,  F05D2260/202 ,  Y02T50/676

Abstract: A method for cooling a shroud segment of a gas turbine engine includes providing a turbine shroud assembly including a shroud segment having a leading edge defining a forward face. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face, wherein a lip formed on the aft face is positioned radially inwardly with respect to the gap and extends substantially axially downstream from the gap. Cooling air is directed into the gap. Cooling air exiting the gap impinges against the lip. Post impingement cooling air is directed at the forward face to facilitate forming a film cooling layer on the shroud segment. The film cooling layer is shielded from combustion gases flowing through the gas turbine engine.

Abstract translation: 一种用于冷却燃气涡轮发动机的护罩区段的方法包括提供一种涡轮机护罩组件，其包括具有限定前表面的前缘的护罩区段。 涡轮喷嘴联接到涡轮机护罩组件，使得在涡轮喷嘴的外带的前表面和前表面之间限定间隙，其中形成在后表面上的唇缘相对于间隙径向向内定位 并且从所述间隙基本轴向地延伸到下游。 冷却空气被引导到间隙中。 离开间隙的冷却空气撞击唇缘。 后冲击冷却空气指向前面，以便于在护罩段上形成薄膜冷却层。 膜冷却层与流过燃气涡轮发动机的燃烧气体屏蔽。

公开(公告)号：US20100047060A1

公开(公告)日：2010-02-25

申请号：US11966275

申请日：2007-12-28

Applicant: Aspi Rustom Wadia ,  David Scott Clark ,  Ching-Pang Lee ,  Andrew Breeze-Stringfellow ,  Gregory Scott McNulty

Inventor： Aspi Rustom Wadia ,  David Scott Clark ,  Ching-Pang Lee ,  Andrew Breeze-Stringfellow ,  Gregory Scott McNulty

IPC: F02C9/16

CPC classification number: F04D29/526 ,  F05D2270/101 ,  F05D2270/172 ,  F15D1/12

Abstract: A gas turbine engine is disclosed, comprising a compressor having a circumferential row of blades, a casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one plasma generator located on the casing. The plasma generator comprises a first electrode and a second electrode separated by a dielectric material. The gas turbine engine further comprises an engine control system which controls the operation of the plasma generator such that the stable operating range of the compressor is increased.

Abstract translation: 公开了一种燃气涡轮发动机，其包括具有周向排的叶片的压缩机，围绕叶片的尖端的壳体，位于与叶片的尖端径向分开的位置以及位于壳体上的至少一个等离子体发生器。 等离子体发生器包括由电介质材料隔开的第一电极和第二电极。 燃气涡轮发动机还包括发动机控制系统，其控制等离子体发生器的操作，使得压缩机的稳定工作范围增加。

公开(公告)号：US20100047056A1

公开(公告)日：2010-02-25

申请号：US11967479

申请日：2007-12-31

Applicant: Ching-Pang Lee ,  Robert Joseph Orlando

Inventor： Ching-Pang Lee ,  Robert Joseph Orlando

IPC: F02C7/12

CPC classification number: F01D25/12 ,  F01D9/041 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A duplex turbine nozzle includes a row of different first and second vanes alternating circumferentially between radially outer and inner bands in vane doublets having axial splitlines therebetween. The vanes have opposite pressure and suction sides spaced apart in each doublet to define an inboard flow passage therebetween, and corresponding outboard flow passages between doublets. The vanes have different patterns of film cooling holes with larger cooling flow density along the outboard passages than along the inboard passages.

Abstract translation: 双相涡轮喷嘴包括一排不同的第一和第二叶片，其在叶片双重体的径向外部和内部带之间周向交替，其间具有轴向分裂线。 叶片具有相反的压力和吸力侧面，每个双层间隔开，以在其间限定内侧流动通道，并且在双层之间具有相应的外侧流动通道。 叶片具有不同于薄膜冷却孔的图案，沿着外侧通道具有比沿内侧通道更大的冷却流动密度。

公开(公告)号：US20100034647A1

公开(公告)日：2010-02-11

申请号：US11635749

申请日：2006-12-07

Applicant: Ching-Pang Lee ,  Hsin-Pang Wang

Inventor： Ching-Pang Lee ,  Hsin-Pang Wang

IPC: F02C7/12 ,  B23K26/00

CPC classification number: F01D11/24 ,  B23K26/32 ,  B23K26/34 ,  B23K2101/001 ,  B23K2103/02 ,  B23K2103/04 ,  B23K2103/05 ,  B23K2103/08 ,  B23K2103/10 ,  B23K2103/14 ,  B23K2103/16 ,  B23K2103/26 ,  B23K2103/50 ,  B23K2103/52 ,  F05D2240/11 ,  F05D2260/22141

Abstract: A process for the formation of positive features on the surface of a turbine shroud component is described. The process involves applying a feature-forming material to a selected portion of the component surface with a laser consolidation apparatus, according to a pre-selected shape and size for the positive features. A gas turbine engine, comprising a shroud component which contains positive features formed according to embodiments of this process, represents another embodiment of this invention. Methods for modifying the shape of at least one positive feature on a surface of a shroud component are also described.

Abstract translation: 描述了在涡轮机护罩部件的表面上形成正特征的方法。 该方法包括根据用于阳性特征的预先选择的形状和尺寸，用激光整形装置将特征形成材料施加到部件表面的选定部分。 包括根据本方法的实施例形成的包含正特征的护罩部件的燃气涡轮发动机代表本发明的另一实施例。 还描述了用于修改护罩部件的表面上的至少一个正特征的形状的方法。

公开(公告)号：US07654734B2

公开(公告)日：2010-02-02

申请号：US11126793

申请日：2005-05-10

Applicant: Liang Jiang ,  Lawrence Bernard Kool ,  Melvin Robert Jackson ,  Canan Uslu Hardwicke ,  Ji-Cheng Zhao ,  Ann Melinda Ritter ,  Ching-Pang Lee

Inventor： Liang Jiang ,  Lawrence Bernard Kool ,  Melvin Robert Jackson ,  Canan Uslu Hardwicke ,  Ji-Cheng Zhao ,  Ann Melinda Ritter ,  Ching-Pang Lee

IPC: G01N25/72 ,  G01N17/00 ,  G01K3/00

CPC classification number: G01N17/00 ,  G01K7/02

Abstract: A method for evaluating the thermal exposure of a selected metal component which has been exposed to changing temperature conditions is described. The voltage distribution on a surface of the metal component, or on a metallic layer which lies over the component, is first obtained. The voltage distribution usually results from a compositional change in the metal component. The voltage distribution is then compared to a thermal exposure-voltage model which expresses voltage distribution as a function of exposure time and exposure temperature for a reference standard corresponding to the metal component. In this manner, the thermal exposure of the selected component can be obtained. A related device for evaluating the thermal exposure of a selected metal component is also described.

Abstract translation: 描述了已经暴露于变化的温度条件下的所选金属组分的热暴露评估方法。 首先获得金属部件的表面上或位于部件上的金属层上的电压分布。 电压分布通常由金属组分的组成变化引起。 然后将电压分布与表示与对应于金属组分的参考标准的曝光时间和曝光温度的函数的电压分布的热暴露电压模型进行比较。 以这种方式，可以获得所选择的部件的热曝光。 还描述了用于评估所选金属组分的热暴露的相关装置。

公开(公告)号：US07625174B2

公开(公告)日：2009-12-01

申请号：US11303884

申请日：2005-12-16

Applicant: Vincent Marion Drerup ,  Harold Ray Hansel ,  Ching-Pang Lee

Inventor： Vincent Marion Drerup ,  Harold Ray Hansel ,  Ching-Pang Lee

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D11/005 ,  F05D2240/57 ,  F05D2260/30 ,  F05D2260/33 ,  Y02T50/673

Abstract: A method for assembling a gas turbine engine is provided. The method comprises coupling a first turbine nozzle within the engine, coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and second turbine nozzles and providing at least one spline seal including a substantially planar body. The method also comprises forming at least one catch to extend outward from the body portion of the at least one spline seal, and inserting the at least one spline seal into a slot defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through said gap, such that a portion of the at least one spline seal is received within a recess defined within the turbine nozzle slot to facilitate retaining the at least one spline seal within the turbine nozzle slot.

Abstract translation: 提供一种用于组装燃气涡轮发动机的方法。 该方法包括将第一涡轮喷嘴联接在发动机内，将第二涡轮喷嘴与第一涡轮喷嘴周向相邻地连接，使得在第一涡轮喷嘴和第二涡轮喷嘴之间限定间隙，并提供包括基本上平面的主体的至少一个花键密封。 该方法还包括形成至少一个止动件以从至少一个花键密封件的本体部分向外延伸，以及将至少一个花键密封件插入到限定在第一和第二涡轮喷嘴中的至少一个中的狭槽中，以便减少 泄漏通过所述间隙，使得所述至少一个花键密封件的一部分被容纳在限定在所述涡轮喷嘴槽内的凹部内，以便于将所述至少一个花键密封件保持在所述涡轮喷嘴槽内。

公开(公告)号：US07611324B2

公开(公告)日：2009-11-03

申请号：US11565273

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Paul Hadley Vitt ,  Michael Elliot Wymore

Inventor： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Paul Hadley Vitt ,  Michael Elliot Wymore

IPC: F01D25/12

CPC classification number: F01D9/04 ,  F01D11/08 ,  F05D2240/11 ,  F05D2240/81 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T29/49346 ,  Y10T29/53443

Abstract: A method of assembling a gas turbine engine is provided. The method includes coupling at least one turbine nozzle segment within the gas turbine engine. The at least one turbine nozzle segment includes at least one airfoil vane extending between an inner band and an outer band that includes an aft flange and a radial inner surface. The method also includes coupling at least one turbine shroud segment downstream from the at least one turbine nozzle segment, wherein the at least one turbine shroud segment includes a leading edge and a radial inner surface, coupling a cooling fluid source in flow communication with the at least one turbine nozzle segment such that cooling fluid channeled to each turbine nozzle outer band aft flange is directed at an oblique discharge angle towards the leading edge of the at least one turbine shroud segment, and channeling the cooling fluid through at least a first group of cooling openings having a larger aggregate cross-sectional area and a second group of cooling openings having a smaller aggregate cross-sectional area to facilitate preferential cooling of the turbine shroud.

Abstract translation: 提供一种组装燃气涡轮发动机的方法。 该方法包括联接燃气涡轮发动机内的至少一个涡轮喷嘴段。 至少一个涡轮喷嘴段包括在内带和外带之间延伸的至少一个翼型叶片，其包括后翼缘和径向内表面。 该方法还包括将至少一个涡轮机护罩区段联接在至少一个涡轮喷嘴段的下游，其中至少一个涡轮机护罩段包括前缘和径向内表面，将与流体连通的冷却流体源 至少一个涡轮喷嘴段，使得被引导到每个涡轮喷嘴外带后缘的冷却流体朝向至少一个涡轮机护罩段的前缘以倾斜的排出角度引导，并且通过至少一个第一组 具有较大聚集体横截面面积的冷却开口和具有较小聚集体横截面积的第二组冷却开口，以便于涡轮机护罩的优先冷却。

公开(公告)号：US07594388B2

公开(公告)日：2009-09-29

申请号：US11145848

申请日：2005-06-06

Applicant: David Glenn Cherry ,  Robert John Beacock ,  William Larson Clifford ,  Robert Joseph Orlando ,  Thomas Ory Moniz ,  Ching-Pang Lee

Inventor： David Glenn Cherry ,  Robert John Beacock ,  William Larson Clifford ,  Robert Joseph Orlando ,  Thomas Ory Moniz ,  Ching-Pang Lee

IPC: F02C3/067 ,  F02K3/072

CPC classification number: F02C3/067 ,  F01D5/142 ,  F01D9/02 ,  F01D9/041 ,  F01D9/065 ,  F02K3/072 ,  F05D2240/127 ,  Y02T50/671 ,  Y02T50/673

Abstract: A turbofan engine includes a fan, compressor, combustor, high pressure turbine, and low pressure turbine joined in serial flow communication. The high pressure turbine includes two stages of rotor blades to effect corresponding exit swirl in the combustion gases discharged therefrom. A transition duct includes fairings extending between platforms for channeling the combustion gases to the low pressure turbine with corresponding swirl. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pressure turbine for counterrotation.

Abstract translation: 涡轮风扇发动机包括串联流动连接的风扇，压缩机，燃烧器，高压汽轮机和低压汽轮机。 高压涡轮机包括两级转子叶片，以在从其排出的燃烧气体中实现相应的出口涡流。 过渡管道包括在平台之间延伸的整流罩，用于将燃烧气体引导到具有相应涡流的低压涡轮机。 低压涡轮机中的第一级转子叶片与用于逆旋转的高压涡轮机中的转子叶片相反地定向。

公开(公告)号：US07588413B2

公开(公告)日：2009-09-15

申请号：US11606971

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

Inventor： Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

IPC: F01D25/12

CPC classification number: F01D5/186 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2270/172 ,  F15D1/12 ,  H05H1/2406 ,  Y02T50/673 ,  Y02T50/676 ,  Y10S415/914

Abstract: An upstream plasma boundary layer shielding system includes film cooling apertures disposed through a wall having cold and hot surfaces and angled in a downstream direction from a cold surface of the wall to an outer hot surface of the wall. A plasma generator located upstream of the film cooling apertures is used for producing a plasma extending downstream over the film cooling apertures. Each plasma generator includes inner and outer electrodes separated by a dielectric material disposed within a groove in the outer hot surface. The wall may be part of a hollow airfoil or an annular combustor or exhaust liner. A method for operating the upstream plasma boundary layer shielding system includes forming a plasma extending in the downstream direction over the film cooling apertures along the outer hot surface of the wall. The method may further include operating the plasma generator in steady state or unsteady modes.

Abstract translation: 上游等离子体边界层屏蔽系统包括通过具有冷和热表面的壁布置的薄膜冷却孔，并且在从壁的冷表面到壁的外部热表面的下游方向上成角度。 位于膜冷却孔的上游的等离子体发生器用于产生在膜冷却孔的下游延伸的等离子体。 每个等离子体发生器包括由设置在外部热表面中的凹槽内的电介质材料分开的内部和外部电极。 该壁可以是中空翼型件或环形燃烧器或排气衬套的一部分。 用于操作上游等离子体边界层屏蔽系统的方法包括形成沿着下游方向沿着壁的外部热表面在膜冷却孔上延伸的等离子体。 该方法还可以包括以等稳态或不稳定模式操作等离子体发生器。