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1. 发明申请

WO2016032506A1 CONTROLLED CONVERGENCE COMPRESSOR FLOWPATH FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：用于气体涡轮发动机的控制压缩机流量控制
公开(公告)号：WO2016032506A1
公开(公告)日：2016-03-03
申请号：PCT/US2014/053345
申请日：2014-08-29
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： OROSA, John A.
IPC分类号： F01D5/14 , F04D29/54 , F04D29/68
CPC分类号： F04D29/547 , F01D5/143 , F04D19/02 , F04D19/028 , F04D29/324 , F04D29/542
摘要： A controlled convergence compressor flowpath (10) configured to better distribute the limited flowpath (10) within compressors (12) in turbine engines (14) is disclosed. The compressor (12) may have a flowpath (10) defined by circumferentially extending inner and outer boundaries (16, 18) that have portions in which the rate of convergence changes to better distribute fluid flow therethrough. The rate of convergence may increase at surfaces (20, 22) adjacent to roots (24) of airfoils (26) and reduce convergence in the axial gaps (28) between airfoil rows (30). In at least one embodiment, the compressor flowpath (10) between leading and trailing edges (44, 46) of a first compressor blade (42) may increase convergence moving downstream to a trailing edge (46) of the first compressor blade (42) due to increased convergence of the inner compressor surface (22). The compressor flowpath (10) between leading and trailing edges (32, 34) of a first compressor vane (36) immediately downstream from the first compressor blade (42) may increase convergence moving downstream due to increased convergence of the outer compressor surface (20).
摘要翻译：公开了一种被配置为在涡轮发动机（14）内的压缩机（12）内更好地分配有限流路（10）的受控会聚压缩机流路（10）。压缩机（12）可以具有由周向延伸的内边界和外边界（16,18）限定的流路（10），所述内边界和外边界具有其中会聚速率变化的部分以更好地分布流体流动。在与翼型件26的根部（24）相邻的表面（20,22）处，会聚的速度可能增加，并减小翼型件列（30）之间的轴向间隙（28）的会聚。在至少一个实施例中，第一压缩机叶片（42）的前缘和后缘（44,46）之间的压缩机流动路径（10）可增加下游到第一压缩机叶片（42）的后缘（46）的收敛，由于内部压缩机表面（22）的会聚增加。在紧邻第一压缩机叶片（42）的下游的第一压缩机叶片（36）的前缘和后缘（32,34）之间的压缩机流动路径（10）可以增加由于外部压缩机表面（20 ）。

2. 发明申请

WO2015094990A1 ADJUSTABLE CLEARANCE CONTROL SYSTEM FOR AIRFOIL TIP IN GAS TURBINE ENGINE 审中-公开
标题翻译：用于气体涡轮发动机中空气的可调节间隙控制系统
公开(公告)号：WO2015094990A1
公开(公告)日：2015-06-25
申请号：PCT/US2014/070190
申请日：2014-12-13
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： OROSA, John A.
IPC分类号： F01D11/22
CPC分类号： F01D11/22 , F05D2220/3215 , F05D2240/55 , F05D2250/283
摘要： An airfoil system (10) for use in a gas turbine engine (12) having an adjustable clearance control system (14) including an axially adjustable ring segment (16) releasably coupled to the stationary turbine component (36) whereby the axially adjustable ring segment (16) may be controlled independently of other airfoil stages (18) is disclosed. The adjustable clearance control system (14) may thus control the flow of hot gases passing one particular airfoil stage (20) while the flow passing other airfoil stages (18) within the component of the turbine engine (12) remains unchanged. The adjustable clearance control system (14) may control the size of the gap (22) between the axially adjustable ring segment (16) and the tip (24) of an airfoil (26) through axial movement of the axially adjustable ring segment (16). The axially adjustable ring segment (16) may include a radially inward contact surface (28) that is positioned nonparallel and nonorthogonal relative to a direction of movement of the axial adjustable ring segment (16).
摘要翻译：一种在具有可调间隙控制系统（14）的燃气涡轮发动机（12）中使用的翼型系统（10），其包括可释放地联接到固定涡轮机部件（36）的可轴向调节的环段（16），由此可轴向调节的环段（16）可以独立于其它翼型段（18）进行控制。因此，可调间隙控制系统（14）可以控制通过一个特定翼型段（20）的热气流，同时通过涡轮发动机（12）的部件内的其它翼型段（18）的流量保持不变。可调间隙控制系统（14）可以通过轴向可调节环段（16）的轴向运动来控制可轴向调节的环段（16）和翼型件（26）的尖端（24）之间的间隙（22）的尺寸）。可轴向调节的环形段（16）可以包括径向向内的接触表面（28），其相对于轴向可调节环段（16）的运动方向定位成非平行且非正交。

3. 发明申请

WO2016167769A1 EXHAUST DIFFUSER STRUT APPARATUS 审中-公开
标题翻译：排气歧管装置
公开(公告)号：WO2016167769A1
公开(公告)日：2016-10-20
申请号：PCT/US2015/026130
申请日：2015-04-16
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： OROSA, John A. , BROOKS, Stephen
IPC分类号： F01D25/16 , F01D25/30 , F04D29/54 , F04D29/68
CPC分类号： F01D25/162 , F01D25/30 , F04D29/544 , F04D29/681 , F05D2260/96
摘要： A wall diffusion apparatus for an exhaust diffuser strut and a method for reducing diffusion includes a material having an upper side aft of a strut airfoil maximum thickness point of the strut, a trailing edge flush with an end of the strut, and a lower side, wherein the apparatus is attached to the strut.
摘要翻译：用于排气扩散器支柱的壁扩散装置和减小扩散的方法包括具有支柱的支柱翼型件最大厚度点的上侧后部的材料，与支柱的端部齐平的后缘以及下侧，其中所述装置附接到所述支柱。

4. 发明申请

WO2016068862A1 GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机
公开(公告)号：WO2016068862A1
公开(公告)日：2016-05-06
申请号：PCT/US2014/062536
申请日：2014-10-28
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： OROSA, John A.
IPC分类号： F01D5/14 , F01D25/16 , F01D25/30
CPC分类号： F01D25/30 , F01D5/145 , F01D25/162 , F05D2240/122 , F05D2240/127 , F05D2250/292 , F05D2250/38 , F05D2260/941 , F05D2260/96
摘要： A gas turbine exhaust section having a pair of concentrically spaced rings including an outer ring (48) and an inner ring (46), and a plurality of strut structures (64) extending radially between the rings (46, 48), interconnecting and supporting the rings (46, 48). The strut structures (64) include a main body portion (68 B ) and a trailing edge flap (80) located at the downstream end of each main body portion (68 B ). Each trailing edge flap (80) has a forward edge (86) affixed to the downstream end (76) of a respective main body portion (68 B ), and each trailing edge flap (80) has a radial end (87) affixed to one of the outer and inner rings (46, 48) in axially spaced relation from the downstream end (76) a respective main body portion (68 B ).
摘要翻译：一种燃气涡轮机排气部分，具有一对同心间隔的环，包括一个外环（48）和一个内环（46），以及多个在环（46,48）之间径向延伸的支柱结构（64），互连和支撑环（46,48）。支柱结构（64）包括位于每个主体部分（68B）的下游端的主体部分（68B）和后缘片（80）。每个后缘翼片（80）具有固定到相应主体部分（68B）的下游端（76）的前边缘（86），并且每个后缘翼片（80）具有固定到一个的外环和内环（46,48）与下游端（76）轴向间隔开相应的主体部分（68B）。

5. 发明申请

WO2019027661A1 GAS TURBINE EXHAUST DIFFUSER HAVING FLOW GUIDING ELEMENTS 审中-公开
公开(公告)号：WO2019027661A1
公开(公告)日：2019-02-07
申请号：PCT/US2018/042203
申请日：2018-07-16
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： OROSA, John A. , WALTKE, Ulrich
IPC分类号： F01D25/30 , F01D5/14 , F01D9/04
CPC分类号： F01D25/30 , F01D5/145 , F01D5/146 , F01D9/041
摘要： A gas turbine (10) includes a turbine section (24), and a diffuser (30) located downstream of a row of turbine blades (26) of the turbine section (24). The diffuser (30) includes an annular duct (34) extending axially along a diffuser axis (32). The annular duct (34) is delimited radially by an outer wall (36) and an inner wall (38) which respectively define outer and inner boundaries of an exhaust flowpath. A number of diffuser struts (40) are circumferentially distributed within the annular duct (34). Each diffuser strut (40) extends from the outer wall (36) to the inner wall (38). A plurality of flow guiding elements (50) are circumferentially distributed within the annular duct (34). The flow guiding elements (50) are positioned on the inner wall (38) and extend radially therefrom into the exhaust flowpath. The flow guiding elements (50) have an axial location downstream of the row of turbine blades (26) and upstream of the diffuser struts (40). The number of flow guiding elements (50) is larger than the number of diffuser struts (40).

6. 发明授权

EP3186484B1 GAS TURBINE ENGINE 有权转让
公开(公告)号：EP3186484B1
公开(公告)日：2019-06-05
申请号：EP14843216.4
申请日：2014-08-29
申请人： Siemens Aktiengesellschaft
发明人： OROSA, John A.
IPC分类号： F01D5/14 , F04D29/54 , F04D29/68

7. 发明公开

EP3186484A1 CONTROLLED CONVERGENCE COMPRESSOR FLOWPATH FOR A GAS TURBINE ENGINE 有权转让
标题翻译：气体涡轮发动机的受控收敛压气机流道
公开(公告)号：EP3186484A1
公开(公告)日：2017-07-05
申请号：EP14843216.4
申请日：2014-08-29
申请人： Siemens Aktiengesellschaft
发明人： OROSA, John A.
IPC分类号： F01D5/14 , F04D29/54 , F04D29/68
CPC分类号： F04D29/547 , F01D5/143 , F04D19/02 , F04D19/028 , F04D29/324 , F04D29/542
摘要： A controlled convergence compressor flowpath (10) configured to better distribute the limited flowpath (10) convergence within compressors (12) in turbine engines (14) is disclosed. The compressor (12) may have a flowpath (10) defined by circumferentially extending inner and outer boundaries (16, 18) that having portions in which the rate of convergence changes to better distribute fluid flow therethrough. The rate of convergence may increase at surfaces (20, 22) adjacent to roots (24) of airfoils (26) and decrease near airfoil tips (68) and in the axial gaps (28) between airfoil rows (30). In at least one embodiment, the compressor flowpath (10) between leading and trailing edges (44, 46) of a first compressor blade (42) may increase convergence moving downstream to a trailing edge (46) of the first compressor blade (42) due to increased convergence of the inner compressor surface (22). The compressor flowpath (10) between leading and trailing edges (32, 34) of a first compressor vane (36) immediately downstream from the first compressor blade (42) may increase convergence moving downstream due to increased convergence of the outer compressor surface (20).
摘要翻译：公开了一种控制的收敛压缩机流动路径（10），其配置为更好地将有限的流动路径（10）分布在涡轮发动机（14）中的压缩机（12）内。压缩机（12）可具有由周向延伸的内部和外部边界（16,18）限定的流动路径（10），所述流动路径具有会聚率变化以更好地分配流体流动通过的部分。收敛速度可以在与翼型件（26）的根部（24）相邻的表面（20,22）处增加，并且减小翼型件排（30）之间的轴向间隙（28）中的会聚。在至少一个实施例中，第一压缩机叶片（42）的前缘和后缘（44,46）之间的压缩机流动路径（10）可增加向下游移动到第一压缩机叶片（42）的后缘（46）由于内部压缩机表面（22）的收敛性增加。紧接在第一压缩机叶片（42）下游的第一压缩机叶片（36）的前缘和后缘（32,34）之间的压缩机流动路径（10）可以增加由于外部压缩机表面（20））。

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