公开(公告)号：US20170022905A1

公开(公告)日：2017-01-26

申请号：US15137280

申请日：2016-04-25

Applicant: John A. Orosa ,  Joseph D. Brostmeyer ,  Justin T. Cejka ,  Russell B. Jones

Inventor： John A. Orosa ,  Joseph D. Brostmeyer ,  Justin T. Cejka ,  Russell B. Jones

IPC: F02C9/18 ,  F02C7/18 ,  F02C3/04

CPC classification number: F02C9/18 ,  F02C3/04 ,  F02C6/08 ,  F02C7/18 ,  F05D2220/32 ,  F05D2260/205 ,  F05D2260/213

Abstract: An industrial gas turbine engine with a high spool and a low spool in which low pressure compressed air is supplied to the high pressure compressor, and where a portion of the low pressure compressed air is bled off for use as cooling air for hot parts in the high pressure turbine of the engine. Annular bleed off channels are located in the LPC diffuser. The bleed channels bleed off around 15% of the core flow and pass the bleed off air into a cooling flow channel that then flows into the cooling circuits in the turbine hot parts.

Abstract translation: 一种具有高阀芯和低阀芯的工业燃气涡轮发动机，其中低压压缩空气被供应到高压压缩机，并且其中一部分低压压缩空气被排出以用作冷却空气中的热部件 发动机的高压汽轮机。 环形泄放通道位于LPC扩散器中。 排放通道泄漏约15％的核心流量，并将排出的空气通入冷却流道，然后流入涡轮机热部分的冷却回路。

公开(公告)号：US20150143815A1

公开(公告)日：2015-05-28

申请号：US14087060

申请日：2013-11-22

Applicant: Anil L. Salunkhe ,  John A. Orosa ,  Yevgeniy Shteyman ,  Matthew R. Porter ,  Lijuan Han ,  Matthew J. Delisa, III ,  Daniel F. Riveros

Inventor： Anil L. Salunkhe ,  John A. Orosa ,  Yevgeniy Shteyman ,  Matthew R. Porter ,  Lijuan Han ,  Matthew J. Delisa, III ,  Daniel F. Riveros

IPC: F01D25/30

CPC classification number: F01D25/30 ,  F01D25/28 ,  F02C7/20 ,  Y10T29/49231

Abstract: An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

Abstract translation: 具有模块化结构的集成单件式排气系统（SPEX），有助于设计更改，提高空气动力学，结构完整性或可维护性。 SPEX定义了花键或弯曲的排气路径表面，例如模拟曲线的一系列圆柱形和截头圆锥形截面。 构造的部分可以包括：（i）由圆锥形部分制造的尾锥组件，其锥形下游到减小的直径; 或（ii）与一排或多排涡轮支架轴向对准的面积划线的横截面; 或两个功能。 模块化的内径和外径入口唇缘增强了最后一排叶片和SPEX之间的过渡流，并增强了结构完整性。 模块化支柱套环在SPEX环形内径和外径流动表面之间具有大的半径分布，用于增强气流和恒定厚度的壁，以实现均匀的热传递和热膨胀。 扇形安装法兰增强了结构的完整性和使用寿命。

公开(公告)号：US20150143814A1

公开(公告)日：2015-05-28

申请号：US14087050

申请日：2013-11-22

Applicant: John A. Orosa ,  Angelina Hinklein

Inventor： John A. Orosa ,  Angelina Hinklein

IPC: F01D25/30

CPC classification number: F01D25/30 ,  F01D5/143 ,  F01D9/041 ,  F01D11/001 ,  F01D25/162 ,  F01D25/243 ,  F05D2250/15 ,  Y10T29/49234

Abstract: An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

Abstract translation: 具有模块化结构的集成单件式排气系统（SPEX），有助于设计更改，提高空气动力学，结构完整性或可维护性。 SPEX定义了花键或弯曲的排气路径表面，例如模拟曲线的一系列圆柱形和截头圆锥形截面。 构造的部分可以包括：（i）由圆锥形部分制造的尾锥组件，其锥形下游到减小的直径; 或（ii）与一排或多排涡轮支架轴向对准的面积划线的横截面; 或两个功能。 模块化的内径和外径入口唇缘增强了最后一排叶片和SPEX之间的过渡流，并增强了结构完整性。 模块化支柱套环在SPEX环形内径和外径流动表面之间具有大的半径分布，用于增强气流和恒定厚度的壁，以实现均匀的热传递和热膨胀。 扇形安装法兰增强了结构的完整性和使用寿命。

公开(公告)号：US09032721B2

公开(公告)日：2015-05-19

申请号：US13325178

申请日：2011-12-14

Applicant: John A. Orosa ,  Pawel Matys

Inventor： John A. Orosa ,  Pawel Matys

IPC: F02K1/38 ,  F01D25/30

CPC classification number: F01D25/305 ,  F02K1/38 ,  F02K1/386 ,  F05D2240/122 ,  F05D2270/173

Abstract: A flow passage defined between an inner and an outer boundary for guiding a fluid flow in an axial direction. A flow control vane is supported at a radial location between the inner and outer boundaries. A fluid discharge opening is provided for discharging a flow of the compressed fluid from a trailing edge of the vane, and a fluid control surface is provided adjacent to the fluid discharge opening and extends in the axial direction at the trailing edge of the vane. The fluid control surface has a curved trailing edge forming a Coanda surface. The fluid discharge opening is selectively provided with a compressed fluid to produce a Coanda effect along the control surface. The Coanda effect has a component in the radial direction effecting a turning of the fluid flow in the flow path radially inward or outward toward one of the inner and outer boundaries.

Abstract translation: 限定在用于在轴向方向上引导流体流动的内边界和外边界之间的流动通道。 流量控制叶片在内边界和外边界之间的径向位置处被支撑。 提供流体排出口，用于排出来自叶片后缘的压缩流体的流动，并且流体控制表面邻近流体排放口设置并在叶片的后缘沿轴向方向延伸。 流体控制表面具有形成柯恩达表面的弯曲后缘。 流体排出口选择性地设置有压缩流体，以沿着控制表面产生柯恩达效应。 柯恩达效应具有在径向方向上的分量，从而使流路中的流体流向径向向内或向外转向内边界和外边界之一。

公开(公告)号：US06471482B2

公开(公告)日：2002-10-29

申请号：US09728238

申请日：2000-11-30

Applicant: Matthew Montgomery ,  Marc Samit ,  John A. Orosa

Inventor： Matthew Montgomery ,  Marc Samit ,  John A. Orosa

IPC: F01D510

CPC classification number: F04D29/668 ,  F01D5/10 ,  F01D5/16 ,  F01D25/06 ,  F04D29/666 ,  F05D2260/96 ,  F05D2260/961 ,  Y02T50/671 ,  Y02T50/673 ,  Y10S416/50

Abstract: The present invention relates to an array of flow directing elements having increased flutter stability for use in turbomachinery devices. The array comprises at least one high frequency flow directing element and at least one low frequency flow directing element. In a preferred embodiment, the array comprises a plurality of alternating high frequency and low frequency flow directing elements. Each high frequency flow directing element has its three lowest frequency vibratory modes at least 2.0% higher in frequency than the three lowest frequency vibratory modes of each low frequency flow directing element. The array of the present invention has particular utility in a turbomachinery device as part of a rotor stage.

Abstract translation: 本发明涉及一种用于涡轮机械装置的具有增加的振动稳定性的导流元件阵列。 阵列包括至少一个高频流动引导元件和至少一个低频流动引导元件。 在优选实施例中，该阵列包括多个交替的高频和低频流动引导元件。 每个高频流动引导元件具有三个最低频率的振动模式，其频率比每个低频流动引导元件的三个最低频率振动模式高至少2.0％。 本发明的阵列在作为转子级的一部分的涡轮机械装置中具有特别的用途。

公开(公告)号：US20170022901A1

公开(公告)日：2017-01-26

申请号：US15131110

申请日：2016-04-18

Applicant: John A. Orosa

Inventor： John A. Orosa

IPC: F02C7/18 ,  F02C3/04

CPC classification number: F02C3/14 ,  F01D5/081 ,  F05D2240/35 ,  F05D2260/14 ,  F05D2260/205 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine with an air cooled turbine component in which spent cooling air from the turbine component is routed through a rotor disk and into a static vaned diffuser on a static part of the engine so that the spent cooling air can be discharged into the combustor instead of into the turbine hot gas stream. The static vaned diffuser includes de-swirling vanes that de-swirl the flow coming off of the rotor and then diffuses the de-swirled air to increase a pressure for discharge into the combustor.

Abstract translation: 具有空气冷却涡轮机部件的燃气涡轮发动机，其中来自涡轮机部件的废冷却空气通过转子盘被引导到发动机的静止部分上的静态叶片扩散器中，使得废的冷却空气可以排放到燃烧器 而不是进入涡轮机热气流。 静态叶片式扩散器包括去旋转叶片，其使来自转子的流动脱离，然后扩散去除的空气以增加用于排放到燃烧器中的压力。

公开(公告)号：US09115602B2

公开(公告)日：2015-08-25

申请号：US14053642

申请日：2013-10-15

Applicant: Anthony J. Malandra ,  John A. Orosa

Inventor： Anthony J. Malandra ,  John A. Orosa

IPC: F02K1/78 ,  B63H11/10 ,  F01D25/30

CPC classification number: F01D25/30 ,  F05D2240/127

Abstract: A turbine exhaust diffuser for a gas turbine engine. The diffuser includes a flow ramp positioned on an ID flowpath boundary within a flowpath of the diffuser. The flow ramp extends circumferentially about the hub and includes a downstream, radially outward point that extends radially outward further from the ID flowpath boundary than an upstream, radially outward point that is positioned upstream from the downstream, radially outward point. A wavy portion is located at the downstream, radially outward point of the flow ramp. The wavy portion includes a circumferentially extending, undulating surface defined by alternating axially extending crests and troughs.

Abstract translation: 一种用于燃气涡轮发动机的涡轮机排气扩散器。 扩散器包括位于扩散器的流路内的ID流路边界上的流动斜坡。 所述流动斜坡围绕所述轮毂周向延伸，并且包括从位于所述ID流路边界的径向向外延伸的下游径向外部点，所述下游径向向外点位于比所述下游径向向外点的上游位置的上游径向向外点。 波纹部分位于流动斜坡的下游径向向外的点。 波浪形部分包括由交替的轴向延伸的波峰和波谷限定的周向延伸的起伏的表面。

公开(公告)号：US20150167488A1

公开(公告)日：2015-06-18

申请号：US14132024

申请日：2013-12-18

Applicant: John A. Orosa

Inventor： John A. Orosa

IPC: F01D11/22

CPC classification number: F01D11/22 ,  F05D2220/3215 ,  F05D2240/55 ,  F05D2250/283

Abstract: An airfoil system for use in a gas turbine engine having an adjustable clearance control system including an axially adjustable ring segment releasably coupled to the stationary turbine component whereby the axially adjustable ring segment may be controlled independently of other airfoil stages is disclosed The adjustable clearance control system may thus control the flow of hot gases passing one particular airfoil stage while the flow passing other airfoil stages within the component of the turbine engine remains unchanged The adjustable clearance control system may control the size of the gap between the axially adjustable ring segment and the tip of an airfoil through axial movement of the axially adjustable ring segment. The axially adjustable ring segment may include a radially inward contact surface that is positioned nonparallel and nonorthogonal relative to a direction of movement of the axial adjustable ring segment.

Abstract translation: 一种用于具有可调节间隙控制系统的燃气涡轮发动机的翼型系统，其包括可释放地联接到固定涡轮机部件的可轴向调节的环形部分，从而可以独立于其它翼型段来控制可轴向调节的环形部分。可调间隙控制系统 因此可以控制通过一个特定翼型段的热气流，同时通过涡轮发动机部件内的其它翼型段的流量保持不变。可调节间隙控制系统可以控制可轴向调节的环段和尖端之间的间隙的尺寸 通过可轴向调节的环段的轴向移动。 可轴向调节的环段可以包括径向向内的接触表面，其相对于轴向可调节环段的运动方向定位成不平行和非正交。

公开(公告)号：US20150143816A1

公开(公告)日：2015-05-28

申请号：US14087086

申请日：2013-11-22

Applicant: Anil L. Salunkhe ,  John A. Orosa ,  Yevgeniy Shteyman ,  Matthew R. Porter ,  Lijuan Han ,  Matthew J. Delisa, III ,  Daniel F. Riveros

Inventor： Anil L. Salunkhe ,  John A. Orosa ,  Yevgeniy Shteyman ,  Matthew R. Porter ,  Lijuan Han ,  Matthew J. Delisa, III ,  Daniel F. Riveros

IPC: F01D25/30

CPC classification number: F01D25/30 ,  F01D9/041 ,  F01D25/162 ,  F01D25/243 ,  F02K1/04 ,  F02K1/80 ,  F05D2230/51 ,  F05D2250/232

Abstract: An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

Abstract translation: 具有模块化结构的集成单件式排气系统（SPEX），有助于设计更改，提高空气动力学，结构完整性或可维护性。 SPEX定义了花键或弯曲的排气路径表面，例如模拟曲线的一系列圆柱形和截头圆锥形截面。 构造的部分可以包括：（i）由圆锥形部分制造的尾锥组件，其锥形下游到减小的直径; 或（ii）与一排或多排涡轮支架轴向对准的面积划线的横截面; 或两个功能。 模块化的内径和外径入口唇缘增强了最后一排叶片和SPEX之间的过渡流，并增强了结构完整性。 模块化支柱套环在SPEX环形内径和外径流动表面之间具有大的半径分布，用于增强气流和恒定厚度的壁，以实现均匀的热传递和热膨胀。 扇形安装法兰增强了结构的完整性和使用寿命。

公开(公告)号：US20150143813A1

公开(公告)日：2015-05-28

申请号：US14087040

申请日：2013-11-22

Applicant: Anil L. Salunkhe ,  John A. Orosa ,  Yevgeniy Shteyman ,  Matthew R. Porter ,  Lijuan Han ,  Matthew J. Delisa, III

Inventor： Anil L. Salunkhe ,  John A. Orosa ,  Yevgeniy Shteyman ,  Matthew R. Porter ,  Lijuan Han ,  Matthew J. Delisa, III

IPC: F01D25/30

CPC classification number: F01D25/30 ,  F01D5/143 ,  F01D9/041 ,  F01D11/001 ,  F01D25/162 ,  F01D25/243 ,  F05D2250/15

Abstract: An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

Abstract translation: 具有模块化结构的集成单件式排气系统（SPEX），有助于设计更改，提高空气动力学，结构完整性或可维护性。 SPEX定义了花键或弯曲的排气路径表面，例如模拟曲线的一系列圆柱形和截头圆锥形截面。 构造的部分可以包括：（i）由圆锥形部分制造的尾锥组件，其锥形下游到减小的直径; 或（ii）与一排或多排涡轮支架轴向对准的面积划线的横截面; 或两个功能。 模块化的内径和外径入口唇缘增强了最后一排叶片和SPEX之间的过渡流，并增强了结构完整性。 模块化支柱套环在SPEX环形内径和外径流动表面之间具有大的半径分布，用于增强气流和恒定厚度的壁，以实现均匀的热传递和热膨胀。 扇形安装法兰增强了结构的完整性和使用寿命。