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。

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。

公开(公告)号：US20140205447A1

公开(公告)日：2014-07-24

申请号：US13746486

申请日：2013-01-22

申请人： Harry Patat ,  Cheryl A. Schopf ,  Jerome H. Katy ,  Adam Wallace ,  David J. Wiebe

发明人： Harry Patat ,  Cheryl A. Schopf ,  Jerome H. Katy ,  Adam Wallace ,  David J. Wiebe

IPC分类号： F02C7/18 ,  F01D25/16 ,  F02C6/08

CPC分类号： F02C7/18 ,  F01D9/02 ,  F01D9/065 ,  F01D25/12 ,  F01D25/125 ,  F01D25/162 ,  F01D25/30 ,  F02C6/08 ,  F05D2240/15

摘要： A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and radially inward from the gas path. A plurality of structural struts support the inner casing to the outer casing, and a fairing surrounds each of the struts in an area extending between the outer and inner flow path walls. A first purge air path extends through at least one of the struts for conducting purge cooling air radially inward to the inner casing, and a second purge air path extends through the strut for further conducting the purge cooling air radially outward to provide a flow of purge air to a location of the exhaust casing cavity radially outward from the outer flow path wall.

摘要翻译： 具有外壳，内壳，限定在外流路壁和内流路壁之间的环形排气通道的涡轮机排气外壳以及从气体路径径向向外和径向向内定位的涡轮排气壳体腔。 多个结构支柱将内壳支撑到外壳，并且整流罩围绕在外流路壁和内流路壁之间延伸的区域中的每个支柱。 第一吹扫空气路径延伸穿过支柱中的至少一个，用于将吹扫冷却空气径向向内引导到内部壳体，并且第二吹扫空气路径延伸穿过支柱，以进一步将吹扫冷却空气径向向外引导以提供吹扫流 空气从外部流路壁向径向外侧排出到排气套管腔的位置。

公开(公告)号：US09316153B2

公开(公告)日：2016-04-19

申请号：US13746486

申请日：2013-01-22

申请人： Harry Patat ,  Cheryl A. Schopf ,  Jerome H. Katy ,  Adam Wallace ,  David J. Wiebe

发明人： Harry Patat ,  Cheryl A. Schopf ,  Jerome H. Katy ,  Adam Wallace ,  David J. Wiebe

IPC分类号： F01D25/12 ,  F01D9/02 ,  F01D9/06 ,  F01D25/16 ,  F01D25/30 ,  F02C6/08 ,  F02C7/18

CPC分类号： F02C7/18 ,  F01D9/02 ,  F01D9/065 ,  F01D25/12 ,  F01D25/125 ,  F01D25/162 ,  F01D25/30 ,  F02C6/08 ,  F05D2240/15

摘要： A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and radially inward from the gas path. A plurality of structural struts support the inner casing to the outer casing, and a fairing surrounds each of the struts in an area extending between the outer and inner flow path walls. A first purge air path extends through at least one of the struts for conducting purge cooling air radially inward to the inner casing, and a second purge air path extends through the strut for further conducting the purge cooling air radially outward to provide a flow of purge air to a location of the exhaust casing cavity radially outward from the outer flow path wall.

摘要翻译： 具有外壳，内壳，限定在外流路壁和内流路壁之间的环形排气通道的涡轮机排气外壳以及从气体路径径向向外和径向向内定位的涡轮排气壳体腔。 多个结构支柱将内壳支撑到外壳，并且整流罩围绕在外流路壁和内流路壁之间延伸的区域中的每个支柱。 第一吹扫空气路径延伸穿过支柱中的至少一个，用于将吹扫冷却空气径向向内引导到内部壳体，并且第二吹扫空气路径延伸穿过支柱，以进一步将吹扫冷却空气径向向外引导以提供吹扫流 空气从外部流路壁向径向外侧排出到排气套管腔的位置。

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。

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。

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。

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。

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。

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）。