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1. 发明授权

US08376697B2 Gas turbine sealing apparatus 有权
标题翻译：燃气轮机密封装置
公开(公告)号：US08376697B2
公开(公告)日：2013-02-19
申请号：US12611241
申请日：2009-11-03
申请人： David J. Wiebe , Brian J. Wessell , Todd Ebert , Alexander Beeck , George Liang , Walter H. Marussich
发明人： David J. Wiebe , Brian J. Wessell , Todd Ebert , Alexander Beeck , George Liang , Walter H. Marussich
IPC分类号： F02C7/28
CPC分类号： F01D11/001 , F01D11/005
摘要： A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine.
摘要翻译：燃气轮机包括可旋转叶片的前排和后排，在可旋转叶片的前排和后排之间的一排固定叶片，环形中间盘和密封件收纳装置。可旋转刀片的前排和后排被联接到盘/转子组件的相应的第一和第二部分。环形中间盘联接到盘/转子组件，以在燃气轮机的运行期间与盘/转子组件一起旋转。环形中间盘包括联接到盘/转子组件的第一部分的前侧和联接到盘/转子组件的第二部分的后侧。密封壳体装置联接到环形中间盘，以在燃气轮机的操作期间与环形中间盘和盘/转子组件一起旋转。

2. 发明申请

US20100074731A1 Gas Turbine Sealing Apparatus 有权
标题翻译：燃气轮机封口机
公开(公告)号：US20100074731A1
公开(公告)日：2010-03-25
申请号：US12611241
申请日：2009-11-03
申请人： David J. Wiebe , Brian J. Wessell , Todd Ebert , Alexander Beeck , George Liang , Walter H. Marussich
发明人： David J. Wiebe , Brian J. Wessell , Todd Ebert , Alexander Beeck , George Liang , Walter H. Marussich
IPC分类号： F02C7/28
CPC分类号： F01D11/001 , F01D11/005
摘要： A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine.
摘要翻译：燃气轮机包括可旋转叶片的前排和后排，在可旋转叶片的前排和后排之间的一排固定叶片，环形中间盘和密封件收纳装置。可旋转刀片的前排和后排被联接到盘/转子组件的相应的第一和第二部分。环形中间盘联接到盘/转子组件，以在燃气轮机的运行期间与盘/转子组件一起旋转。环形中间盘包括联接到盘/转子组件的第一部分的前侧和联接到盘/转子组件的第二部分的后侧。密封壳体装置联接到环形中间盘，以在燃气轮机的操作期间与环形中间盘和盘/转子组件一起旋转。

3. 发明授权

US08770924B2 Gas turbine engine with angled and radial supports 有权
标题翻译：具有角度和径向支撑的燃气涡轮发动机
公开(公告)号：US08770924B2
公开(公告)日：2014-07-08
申请号：US13177701
申请日：2011-07-07
申请人： Alexander Beeck , Malberto Gonzalez , Jerome H. Katy , David J. Wiebe
发明人： Alexander Beeck , Malberto Gonzalez , Jerome H. Katy , David J. Wiebe
IPC分类号： F01D25/16
CPC分类号： F01D25/28 , F01D25/30 , F05D2250/314
摘要： A support structure in a gas turbine engine including an inner annular wall and an outer annular wall defining an annular flow path, a casing housing the structure defining the flow path, and a bearing compartment housing a rotor shaft bearing located radially inwardly from the inner annular wall. The support structure includes a plurality of circumferentially spaced radial support members extending radially inwardly from an outer mount connection at the casing to an inner mount connection at the bearing compartment housing. The radial support members provide structural support for radial bearing loads on the rotor shaft bearing. A plurality of circumferentially spaced axial support members extend radially and axially inwardly from an outer mount connection at the casing to an inner mount connection located on an annular structure extending radially between connection locations at the bearing compartment housing and the inner annular wall.
摘要翻译：一种燃气涡轮发动机中的支撑结构，包括内环形壁和限定环形流路的外环形壁，容纳限定流路的结构的壳体和容纳从内环径向向内定位的转子轴轴承的轴承室壁。支撑结构包括多个周向间隔开的径向支撑构件，其从壳体处的外部安装连接件径向向内延伸到轴承隔室壳体处的内部安装连接。径向支撑构件为转子轴承上的径向轴承负载提供结构支撑。多个周向间隔开的轴向支撑构件从壳体处的外部安装连接件径向和轴向向内延伸到位于在轴承隔室壳体和内部环形壁处的连接位置之间径向延伸的环形结构上的内部安装连接件。

4. 发明申请

US20130011242A1 GAS TURBINE ENGINE WITH ANGLED AND RADIAL SUPPORTS 有权
标题翻译：气体涡轮发动机带有光束和径向支撑
公开(公告)号：US20130011242A1
公开(公告)日：2013-01-10
申请号：US13177701
申请日：2011-07-07
申请人： Alexander Beeck , Malberto Gonzalez , Jerome H. Katy , David J. Wiebe
发明人： Alexander Beeck , Malberto Gonzalez , Jerome H. Katy , David J. Wiebe
IPC分类号： F01D25/16
CPC分类号： F01D25/28 , F01D25/30 , F05D2250/314
摘要： A support structure in a gas turbine engine including an inner annular wall and an outer annular wall defining an annular flow path, a casing housing the structure defining the flow path, and a bearing compartment housing a rotor shaft bearing located radially inwardly from the inner annular wall. The support structure includes a plurality of circumferentially spaced radial support members extending radially inwardly from an outer mount connection at the casing to an inner mount connection at the bearing compartment housing. The radial support members provide structural support for radial bearing loads on the rotor shaft bearing. A plurality of circumferentially spaced axial support members extend radially and axially inwardly from an outer mount connection at the casing to an inner mount connection located on an annular structure extending radially between connection locations at the bearing compartment housing and the inner annular wall.
摘要翻译：一种燃气涡轮发动机中的支撑结构，包括内环形壁和限定环形流路的外环形壁，容纳限定流路的结构的壳体和容纳从内环径向向内定位的转子轴轴承的轴承室壁。支撑结构包括多个周向间隔开的径向支撑构件，其从壳体处的外部安装连接件径向向内延伸到轴承隔室壳体处的内部安装连接。径向支撑构件为转子轴承上的径向轴承负载提供结构支撑。多个周向间隔开的轴向支撑构件从壳体处的外部安装连接件径向和轴向向内延伸到位于在轴承隔室壳体和内部环形壁处的连接位置之间径向延伸的环形结构上的内部安装连接件。

5. 发明申请

US20150000283A1 COMBUSTOR APPARATUS IN A GAS TURBINE ENGINE 有权
标题翻译：燃气涡轮发动机中的燃烧器装置
公开(公告)号：US20150000283A1
公开(公告)日：2015-01-01
申请号：US13928476
申请日：2013-06-27
申请人： Stephen A. Ramier , David J. Wiebe , Lawrence P. Budnick , Mark L. Adamson , Daniel W. Garan , Robert H. Bartley , Yadollah Naghian
发明人： Stephen A. Ramier , David J. Wiebe , Lawrence P. Budnick , Mark L. Adamson , Daniel W. Garan , Robert H. Bartley , Yadollah Naghian
IPC分类号： F23R3/28
CPC分类号： F23R3/283 , F16L19/061 , F23R3/286 , F23R3/34 , F23R3/346 , F23R3/54 , F23R3/60
摘要： A combustor apparatus defining a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus comprises an outer wall including a fuel inlet opening for receiving a fuel feed pipe. A coupling assembly is engaged with the fuel feed pipe at the fuel inlet opening to attach the fuel feed pipe to the outer wall. A fuel injection system is located in the interior volume of the outer wall and comprises fuel supply structure including a fuel feed block having a fuel intake passage aligned with the outlet portion of the fuel feed pipe. A coupling fastener is engaged against an exterior outer face of the fuel feed block to create a sealed coupling for containing fuel passing from the fuel feed pipe into the fuel feed block, and to secure the fuel feed block relative to the coupling assembly.
摘要翻译：一种限定燃烧区域的燃烧器装置，其中燃烧空气和燃料以产生高温燃烧产物。燃烧器装置包括外壁，其包括用于接收燃料供给管的燃料入口。联接组件在燃料入口处与燃料供给管接合以将燃料供给管附接到外壁。燃料喷射系统位于外壁的内部容积中，并且包括燃料供给结构，其包括具有与燃料供给管的出口部分对准的燃料进入通道的燃料供给块。联接紧固件抵靠燃料供给块的外部外表面接合以产生密封联接件，用于容纳从燃料供给管道进入燃料供给块的燃料，并且相对于联接组件固定燃料供给块。

6. 发明授权

US08668454B2 Turbine airfoil fillet cooling system 失效
标题翻译：涡轮机翼角冷却系统
公开(公告)号：US08668454B2
公开(公告)日：2014-03-11
申请号：US12716548
申请日：2010-03-03
申请人： David J. Wiebe
发明人： David J. Wiebe
IPC分类号： F01D5/18
CPC分类号： F01D5/18
摘要： A cooling system for the fillet of a turbine blade is provided. The blade includes an airfoil transitioning to a platform having a flow path surface. The transition region is defined by a fillet. A cooling passage is formed in the platform and extends about at least a portion of the periphery of the airfoil. The cooling passage is located proximate to the flow path surface and is substantially aligned with at least a portion of the fillet. Coolant is delivered to the passage by a supply hole, which can reduce the temperature in the fillet region. As a result, thermal gradients in the fillet region can be minimized, which can reduce thermal stresses. An exhaust hole extends between the passage and the flow path surface of the platform. Thus, coolant discharged from the exhaust holes enters the flow path of the turbine.
摘要翻译：提供了一种用于涡轮叶片的圆角的冷却系统。叶片包括转变到具有流动路径表面的平台的翼型件。过渡区域由圆角定义。冷却通道形成在平台中并围绕翼型的周边的至少一部分延伸。冷却通道位于流路表面附近，并且基本上与圆角的至少一部分对齐。冷却液通过供应孔输送到通道，这可以降低圆角区域的温度。因此，可以最小化圆角区域的热梯度，这可以降低热应力。排气孔在平台的通道和流动通道表面之间延伸。因此，从排气孔排出的冷却剂进入涡轮机的流路。

7. 发明申请

US20130219921A1 MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE WITH A COOLING SYSTEM FOR THE TRANSITION 有权
标题翻译：具有用于过渡的冷却系统的CAN-ANNULAR气体涡轮发动机的中间部分
公开(公告)号：US20130219921A1
公开(公告)日：2013-08-29
申请号：US13408061
申请日：2012-02-29
申请人： David J. Wiebe , Jose L. Rodrigez
发明人： David J. Wiebe , Jose L. Rodrigez
IPC分类号： F02C6/08
CPC分类号： F01D9/023 , F01D25/12 , F02C3/14 , F05D2250/314 , F23R3/52 , F23R3/58
摘要： A cooling system is provided for a transition (420) of a gas turbine engine (410). The cooling system includes a cowling (460) configured to receive an air flow (111) from an outlet of a compressor section of the gas turbine engine (410). The cowling (460) is positioned adjacent to a region of the transition (420) to cool the transition region upon circulation of the air flow within the cowling (460). The cooling system further includes a manifold (121) to directly couple the air flow (111) from the compressor section outlet to an inlet (462) of the cowling (460). The cowling (460) is configured to circulate the air flow (111) within an interior space (426) of the cowling (460) that extends radially outward from an inner diameter (423) of the cowling to an outer diameter (424) of the cowling at an outer surface.
摘要翻译：为燃气涡轮发动机（410）的过渡（420）提供冷却系统。冷却系统包括构造成从燃气涡轮发动机（410）的压缩机部分的出口接收空气流（111）的整流罩（460）。整流罩（460）定位成邻近过渡区域（420），以在气流（460）内的空气流循环时冷却过渡区域。冷却系统还包括将空气流（111）从压缩机部分出口直接联接到整流罩（460）的入口（462）的歧管（121）。整流罩（460）构造成使得空气流（111）在整流罩（460）的内部空间（426）内循环，该整流罩（460）从整流罩的内径（423）径向向外延伸到外壳在外表面的整流罩。

8. 发明申请

US20130081407A1 AERO-DERIVATIVE GAS TURBINE ENGINE WITH AN ADVANCED TRANSITION DUCT COMBUSTION ASSEMBLY 审中-公开
标题翻译：具有先进过渡式燃煤组件的AERO-DERIVATIVE GAS TURBINE发动机
公开(公告)号：US20130081407A1
公开(公告)日：2013-04-04
申请号：US13252348
申请日：2011-10-04
申请人： David J. Wiebe
发明人： David J. Wiebe
IPC分类号： F02C3/04 , B23P17/00
CPC分类号： F23R3/46 , F01D9/023 , F02C3/04 , F02C3/14 , F05D2230/80 , F05D2250/314 , Y10T29/49229
摘要： An aero-derivative can annular gas turbine engine having: an aero gas turbine engine core including an aero high pressure compressor (65) interconnected with an aero high pressure turbine (73) by an aero high pressure shaft (142) in a geometric arrangement appropriate for association with an aero annular combustor (84), but with the aero annular combustor (84) and a first row of turbine vanes (38) of the aero high pressure turbine (73) absent; and a can annular combustor assembly (122) assembled with the aero gas turbine engine core and configured to receive compressed air from the aero high pressure compressor (65) and to accelerate and orient combustion gasses directly onto a first row of blades of the aero high pressure turbine (73).
摘要翻译：一种航空衍生罐环形燃气涡轮发动机，其具有：航空燃气涡轮发动机核心，其包括通过航空高压轴（142）以航空高压涡轮机（142）以几何布置适当的方式与航空高压涡轮机（73）互连的航空高压压缩机（65）用于与航空环形燃烧器（84）相关联，但是与空气环形燃烧器（84）和空气高压涡轮机（73）的第一排涡轮机叶片（38）不相关; 以及与所述航空燃气涡轮发动机芯组装的并且被配置为从所述航空高压压缩机（65）接收压缩空气并且将燃烧气体直接加速并定向到所述航空高压压缩机（65）的第一排叶片上的罐环形燃烧器组件（122）压力涡轮机（73）。

9. 发明授权

US08281594B2 Fuel injector for use in a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的燃油喷射器
公开(公告)号：US08281594B2
公开(公告)日：2012-10-09
申请号：US12555134
申请日：2009-09-08
申请人： David J. Wiebe
发明人： David J. Wiebe
IPC分类号： F02C1/00
CPC分类号： F23D11/36 , F23R3/283
摘要： A fuel injector in a combustor apparatus of a gas turbine engine. An outer wall of the injector defines an interior volume in which an intermediate wall is disposed. A first gap is formed between the outer wall and the intermediate wall. The intermediate wall defines an internal volume in which an inner wall is disposed. A second gap is formed between the intermediate wall and the inner wall. The second gap receives cooling fluid that cools the injector. The cooling fluid provides convective cooling to the intermediate wall as it flows within the second gap. The cooling fluid also flows through apertures in the intermediate wall into the first gap where it provides impingement cooling to the outer wall and provides convective cooling to the outer wall. The inner wall defines a passageway that delivers fuel into a liner downstream from a main combustion zone.
摘要翻译：燃气涡轮发动机的燃烧器装置中的燃料喷射器。注射器的外壁限定内部容积，其中设置中间壁。在外壁和中间壁之间形成第一间隙。中间壁限定了内壁的内部容积。在中间壁和内壁之间形成第二间隙。第二间隙接收冷却喷射器的冷却流体。冷却流体在第二间隙内流动时向中间壁提供对流冷却。冷却流体还通过中间壁中的孔流入第一间隙，在第一间隙中，其向外壁提供冲击冷却并向外壁提供对流冷却。内壁限定了将燃料输送到主燃烧区下游的衬套的通道。

10. 发明申请

US20100071377A1 Combustor Apparatus for Use in a Gas Turbine Engine 审中-公开
标题翻译：用于燃气轮机发动机的燃烧器装置
公开(公告)号：US20100071377A1
公开(公告)日：2010-03-25
申请号：US12477397
申请日：2009-06-03
申请人： Timothy A. Fox , David J. Wiebe
发明人： Timothy A. Fox , David J. Wiebe
IPC分类号： F02C7/22 , F02C5/02
CPC分类号： F23R3/16 , F23R3/283 , F23R3/346 , F23R2900/00005
摘要： A combustor apparatus for use in a gas turbine engine. The combustor apparatus includes a liner, a flow sleeve, and a fuel injection system. The liner includes an inner volume, wherein a portion of the inner volume defines a main combustion zone. The flow sleeve receives compressed air, is positioned radially outward from the liner, and includes a forward end and an aft end. The fuel injection system is coupled to the flow sleeve and provides fuel into the inner volume of the liner downstream from the main combustion zone. The fuel injection system includes a fuel manifold and a fuel dispensing structure. The fuel manifold is coupled to the flow sleeve and includes a cavity for receiving fuel. The fuel dispensing structure is associated with the cavity and distributes fuel from the cavity to the liner inner volume.
摘要翻译：一种用于燃气涡轮发动机的燃烧器装置。燃烧器装置包括衬套，流动套筒和燃料喷射系统。内衬包括内部容积，其中内部容积的一部分限定主燃烧区。流动套筒容纳压缩空气，从衬套径向向外定位，并且包括前端和后端。燃料喷射系统联接到流动套筒并且将燃料提供到主燃烧区下游的衬套的内部容积中。燃料喷射系统包括燃料歧管和燃料分配结构。燃料歧管联接到流动套管并且包括用于接收燃料的空腔。燃料分配结构与空腔相关联，并将燃料从空腔分配到衬里内部容积。

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