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1.发明申请TRANSITION SUPPORT SYSTEM FOR COMBUSTION TRANSITION DUCTS FOR TURBINE ENGINES 有权用于涡轮发动机燃烧过渡管的过渡支撑系统公开(公告)号：US20150128609A1
公开(公告)日：2015-05-14
申请号：US14074911
申请日：2013-11-08
申请人： Keith W. Piersall , Yevgeniy Shteyman , Robert Angel , Ashley N. Girdich , Robert T. Brooks , James Alfonso , James Marshall
发明人： Keith W. Piersall , Yevgeniy Shteyman , Robert Angel , Ashley N. Girdich , Robert T. Brooks , James Alfonso , James Marshall
CPC分类号： F02C7/20 , F01D9/023 , F01D25/04 , F02C9/16 , F05D2260/30 , F05D2260/96 , F23R3/46 , F23R3/60 , F23R2900/00014
摘要： An adjustable transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The adjustable transition duct support system includes an adjustable forward transition flexible support assembly in contact with a transition duct body, whereby the forward transition flexible support assembly may be formed from a base extending toward the transition duct body and first and second side support arms extending from the base to the transition duct body. The first and second side support arms may be formed from a plurality of flex plates spaced from each other with spacers that provide rigidity in circumferential and radial directions and flexibility in an axial direction. The number of flex plates used may be varied to accommodate different turbine engines. The adjustable transition duct support system may have natural frequencies for circumferential and radial modes above two engine orders.
摘要翻译： 用于过渡管道的可调节的过渡管道支撑系统，其将来自燃烧器出口的热气体引导到涡轮发动机的燃气涡轮机入口。 可调节的过渡管道支撑系统包括与过渡管道本体接触的可调节的向前过渡的柔性支撑组件，由此前向过渡的柔性支撑组件可由朝向过渡管道本体延伸的基部形成，并且第一和第二侧支撑臂从 基座到过渡管体。 第一侧支撑臂和第二侧支撑臂可以由多个彼此间隔开的柔性板形成，间隔件在周向和径向方向上提供刚性并且在轴向方向上具有柔性。 所使用的柔性板的数量可以变化以适应不同的涡轮发动机。 可调节的过渡管道支撑系统可以具有高于两个发动机顺序的周向和径向模式的固有频率。
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2.发明授权Transition support system for combustion transition ducts for turbine engines 有权用于涡轮发动机燃烧过渡管道的过渡支撑系统公开(公告)号：US09328664B2
公开(公告)日：2016-05-03
申请号：US14074911
申请日：2013-11-08
申请人： Keith W. Piersall , Yevgeniy Shteyman , Robert Angel , Ashley N. Girdich , Robert T. Brooks , James Alfonso , James Marshall
发明人： Keith W. Piersall , Yevgeniy Shteyman , Robert Angel , Ashley N. Girdich , Robert T. Brooks , James Alfonso , James Marshall
CPC分类号： F02C7/20 , F01D9/023 , F01D25/04 , F02C9/16 , F05D2260/30 , F05D2260/96 , F23R3/46 , F23R3/60 , F23R2900/00014
摘要： An adjustable transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The adjustable transition duct support system includes an adjustable forward transition flexible support assembly in contact with a transition duct body, whereby the forward transition flexible support assembly may be formed from a base extending toward the transition duct body and first and second side support arms extending from the base to the transition duct body. The first and second side support arms may be formed from a plurality of flex plates spaced from each other with spacers that provide rigidity in circumferential and radial directions and flexibility in an axial direction. The number of flex plates used may be varied to accommodate different turbine engines. The adjustable transition duct support system may have natural frequencies for circumferential and radial modes above two engine orders.
摘要翻译： 用于过渡管道的可调节的过渡管道支撑系统，其将来自燃烧器出口的热气体引导到涡轮发动机的燃气涡轮机入口。 可调节的过渡管道支撑系统包括与过渡管道本体接触的可调节的向前过渡的柔性支撑组件，由此前向过渡的柔性支撑组件可由朝向过渡管道本体延伸的基部形成，并且第一和第二侧支撑臂从 基座到过渡管体。 第一侧支撑臂和第二侧支撑臂可以由多个彼此间隔开的柔性板形成，间隔件在周向和径向方向上提供刚性并且在轴向方向上具有柔性。 所使用的柔性板的数量可以变化以适应不同的涡轮发动机。 可调节的过渡管道支撑系统可以具有高于两个发动机顺序的周向和径向模式的固有频率。
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公开(公告)号：US08721278B2
公开(公告)日：2014-05-13
申请号：US13045626
申请日：2011-03-11
申请人： Yevgeniy Shteyman , James Marshall , Brian Micklos , Jonathan Leagon , Christopher Scogin , Brian H. Terpos , Robert T. Brooks , Scott Smith , Robert W. Spitzer , David Wiebe
发明人： Yevgeniy Shteyman , James Marshall , Brian Micklos , Jonathan Leagon , Christopher Scogin , Brian H. Terpos , Robert T. Brooks , Scott Smith , Robert W. Spitzer , David Wiebe
IPC分类号： F01D25/24
CPC分类号： F01D25/243 , F01D25/30 , F05B2260/301 , F05D2260/37
摘要： A flange connection for an exhaust section of a gas turbine engine. The flange connection includes a stub flange attached to an exhaust manifold. The stub flange has a first axial face for engagement with the axial face of a cylinder flange extending radially from an exhaust cylinder. A plate structure attached to the cylinder flange is configured to provide axial retention of the stub flange to the axial face of the cylinder flange. The plate structure includes a resilient beam portion extending radially inwardly and engaging a second axial face of the stub flange. The stub flange is retained between the cylinder flange and the beam portion of the plate structure in an interference fit to provide three degrees of freedom of the stub flange relative to the exhaust cylinder.
摘要翻译： 一种用于燃气涡轮发动机的排气部分的法兰连接。 法兰连接包括连接到排气歧管的短管法兰。 短柱法兰具有第一轴向面，用于与从排气筒径向延伸的气缸凸缘的轴向面接合。 连接到气缸凸缘的板结构构造成使得短柱凸缘向轴向保持在气缸凸缘的轴向面上。 板结构包括径向向内延伸并接合短截线凸缘的第二轴向面的弹性梁部分。 短柱凸缘以过盈配合保持在气缸凸缘和板结构的梁部之间，以提供短柱法兰相对于排气缸的三个自由度。
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公开(公告)号：US20120023968A1
公开(公告)日：2012-02-02
申请号：US13045626
申请日：2011-03-11
申请人： Yevgeniy Shteyman , James Marshall , Brian Micklos , Jonathan Leagon , Christopher Scogin , Brian H. Terpos , Robert T. Brooks , Scott Smith , Robert W. Spitzer , David Wiebe
发明人： Yevgeniy Shteyman , James Marshall , Brian Micklos , Jonathan Leagon , Christopher Scogin , Brian H. Terpos , Robert T. Brooks , Scott Smith , Robert W. Spitzer , David Wiebe
IPC分类号： F02C7/20
CPC分类号： F01D25/243 , F01D25/30 , F05B2260/301 , F05D2260/37
摘要： A flange connection for an exhaust section of a gas turbine engine. The flange connection includes a stub flange attached to an exhaust manifold. The stub flange has a first axial face for engagement with the axial face of a cylinder flange extending radially from an exhaust cylinder. A plate structure attached to the cylinder flange is configured to provide axial retention of the stub flange to the axial face of the cylinder flange. The plate structure includes a resilient beam portion extending radially inwardly and engaging a second axial face of the stub flange. The stub flange is retained between the cylinder flange and the beam portion of the plate structure in an interference fit to provide three degrees of freedom of the stub flange relative to the exhaust cylinder.
摘要翻译： 一种用于燃气涡轮发动机的排气部分的法兰连接。 法兰连接包括连接到排气歧管的短管法兰。 短柱法兰具有第一轴向面，用于与从排气筒径向延伸的气缸凸缘的轴向面接合。 连接到气缸凸缘的板结构构造成使得短柱凸缘向轴向保持在气缸凸缘的轴向面上。 板结构包括径向向内延伸并接合短截线凸缘的第二轴向面的弹性梁部分。 短柱凸缘以过盈配合保持在气缸凸缘和板结构的梁部之间，以提供短柱法兰相对于排气缸的三个自由度。
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公开(公告)号：US20130269352A1
公开(公告)日：2013-10-17
申请号：US13715233
申请日：2012-12-14
申请人： Robert Angel , Drew Ehlert , Matthias Hase , Michael Huth , James Marshall , Yevgeniy Shteyman
发明人： Robert Angel , Drew Ehlert , Matthias Hase , Michael Huth , James Marshall , Yevgeniy Shteyman
IPC分类号： F23R3/14
CPC分类号： F23R3/14 , F23D2900/00008 , F23D2900/14701 , F23R3/286 , F23R3/343
摘要： A gas-turbine burner having a plurality of main swirl generators which each have an inlet flow opening formed by the main swirl generator edge is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.
摘要翻译： 本发明提供一种燃气轮机燃烧器，其具有多个主漩涡发生器，每个主漩涡发生器具有由主漩涡发生器边缘形成的入口流动开口。 为了实现燃烧空气通过主漩涡发生器的均匀流动，燃气轮机燃烧器具有入口流动引导装置，其具有从一个入口流动开口延伸到相邻入口流动开口的流动引导表面 形成入口流动开口的主漩涡发生器边缘连接到其上，并且流动引导表面从那里径向向上变宽。 主涡旋发生器围绕引燃燃烧器中心对称地布置，并且流动引导表面径向地在主漩涡发生器外部延伸。
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公开(公告)号：US08973369B2
公开(公告)日：2015-03-10
申请号：US13715233
申请日：2012-12-14
申请人： Robert Angel , Drew Ehlert , Matthias Hase , Michael Huth , James Marshall , Yevgeniy Shteyman
发明人： Robert Angel , Drew Ehlert , Matthias Hase , Michael Huth , James Marshall , Yevgeniy Shteyman
CPC分类号： F23R3/14 , F23D2900/00008 , F23D2900/14701 , F23R3/286 , F23R3/343
摘要： A gas-turbine burner having a plurality of main swirl generators which each have an inlet flow opening formed by the main swirl generator edge is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.
摘要翻译： 本发明提供一种燃气轮机燃烧器，其具有多个主漩涡发生器，每个主漩涡发生器具有由主漩涡发生器边缘形成的入口流动开口。 为了实现燃烧空气通过主漩涡发生器的均匀流动，燃气轮机燃烧器具有入口流动引导装置，其具有从一个入口流动开口延伸到相邻入口流动开口的流动引导表面 形成入口流动开口的主漩涡发生器边缘连接到其上，并且流动引导表面从那里径向向上变宽。 主涡旋发生器围绕引燃燃烧器中心对称地布置，并且流动引导表面径向地在主漩涡发生器外部延伸。
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公开(公告)号：US20100275605A1
公开(公告)日：2010-11-04
申请号：US12668121
申请日：2008-07-02
申请人： Matthias Hase , Michael Huth , Robert Angel , Drew Ehlert , James Marshall , Yevgeniy Shteyman
发明人： Matthias Hase , Michael Huth , Robert Angel , Drew Ehlert , James Marshall , Yevgeniy Shteyman
IPC分类号： F02C7/22
CPC分类号： F23R3/14 , F23D2900/00008 , F23D2900/14701 , F23R3/286 , F23R3/343
摘要： A gas-turbine burner having a plurality of main swirl generators, each having an inlet flow opening formed by the main swirl generator edge, is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.
摘要翻译： 一种具有多个主旋流发生器的燃气轮机燃烧器，其具有由主涡流发生器边缘形成的入口流动开口。 为了实现燃烧空气通过主漩涡发生器的均匀流动，燃气轮机燃烧器具有入口流动引导装置，其具有从一个入口流动开口延伸到相邻入口流动开口的流动引导表面 形成入口流动开口的主漩涡发生器边缘连接到其上，并且流动引导表面从那里径向向上变宽。 主涡旋发生器围绕引燃燃烧器中心对称地布置，并且流动引导表面径向地在主漩涡发生器外部延伸。
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公开(公告)号：US08387394B2
公开(公告)日：2013-03-05
申请号：US12668121
申请日：2008-07-02
申请人： Matthias Hase , Michael Huth , Robert Angel , Drew Ehlert , James Marshall , Yevgeniy Shteyman
发明人： Matthias Hase , Michael Huth , Robert Angel , Drew Ehlert , James Marshall , Yevgeniy Shteyman
CPC分类号： F23R3/14 , F23D2900/00008 , F23D2900/14701 , F23R3/286 , F23R3/343
摘要： A gas-turbine burner having a plurality of main swirl generators, each having an inlet flow opening formed by the main swirl generator edge, is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.
摘要翻译： 一种具有多个主旋流发生器的燃气轮机燃烧器，其具有由主涡流发生器边缘形成的入口流动开口。 为了实现燃烧空气通过主漩涡发生器的均匀流动，燃气轮机燃烧器具有入口流动引导装置，其具有从一个入口流动开口延伸到相邻入口流动开口的流动引导表面 形成入口流动开口的主漩涡发生器边缘连接到其上，并且流动引导表面从那里径向向上变宽。 主涡旋发生器围绕引燃燃烧器中心对称地布置，并且流动引导表面径向地在主漩涡发生器外部延伸。
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公开(公告)号：US09664062B2
公开(公告)日：2017-05-30
申请号：US13746423
申请日：2013-01-22
申请人： Mrinal Munshi , John W. Finneran , Yevgeniy Shteyman , Daryl J. Graber , Matthew R. Porter , Jonathan M. Leagon
发明人： Mrinal Munshi , John W. Finneran , Yevgeniy Shteyman , Daryl J. Graber , Matthew R. Porter , Jonathan M. Leagon
摘要： An attachment system for attaching at least one exhaust diffuser downstream from a turbine assembly in a gas turbine engine is disclosed. The attachment system may include at least one attachment flange extending from a downstream edge and attached to a spring plate diffuser support structure and at least one attachment flange extending from side edges of the exhaust diffuser to couple sections of the exhaust diffuser together. The diffuser may also include a thermal barrier/cooling system for controlling a temperature of an outer case of the gas turbine engine. The thermal barrier/cooling system may form a flow path for an ambient air flow cooling.
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公开(公告)号：US09598981B2
公开(公告)日：2017-03-21
申请号：US14087042
申请日：2013-11-22
申请人： Anil L. Salunkhe , John A. Orosa , Yevgeniy Shteyman , Lijuan Han , Matthew J. Delisa, III , Daniel F. Riveros
发明人： Anil L. Salunkhe , John A. Orosa , Yevgeniy Shteyman , Lijuan Han , Matthew J. Delisa, III , Daniel F. Riveros
IPC分类号： F01D25/30 , F02K1/78 , F02K1/80 , F02K1/82 , F01D9/04 , F01D11/00 , F01D25/16 , F01D25/24 , F01D5/14
CPC分类号： F01D25/30 , F01D5/143 , F01D9/041 , F01D11/001 , F01D25/162 , F01D25/243 , F02K1/78 , F02K1/80 , F02K1/82 , F05D2250/15
摘要： 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.
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