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1. 发明申请

US20130004331A1 TURBINE BLADE OR VANE WITH SEPARATE ENDWALL 有权
标题翻译：涡轮叶片或带独立端口的风扇
公开(公告)号：US20130004331A1
公开(公告)日：2013-01-03
申请号：US13171678
申请日：2011-06-29
申请人： Alexander R. Beeck
发明人： Alexander R. Beeck
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/18 , F01D5/143 , F01D5/145 , F01D5/147 , F05D2240/80
摘要： A turbine engine airfoil structure including an airfoil adapted to be supported to extend across a gas passage for a hot working gas in a turbine engine. The airfoil structure further includes a platform structure located at one end of the airfoil and positioned at a location forming a boundary of the gas passage. The platform structure includes a platform member including a gas side surface extending generally perpendicular from the airfoil at a junction with the airfoil, and providing a structural connection to the airfoil. The platform structure further includes a separately formed platform cover attached to the platform member at the gas side surface. The platform cover extends from a location adjacent to one of the sidewalls of the airfoil, and includes an outer surface located for contact with the hot working gas passing through the gas path.
摘要翻译：一种涡轮发动机翼型结构，其包括适于被支撑以延伸穿过涡轮发动机中的热工作气体的气体通道的翼型件。翼型结构还包括位于翼型件的一端处并定位在形成气体通道的边界的位置处的平台结构。平台结构包括平台构件，该平台构件包括在与翼型的连接处大体上垂直于翼型延伸的气体侧表面，并且提供与翼型的结构连接。平台结构还包括在气体侧表面处附接到平台构件的单独形成的平台盖。平台盖从与翼型件的一个侧壁相邻的位置延伸，并且包括位于与通过气体路径的热作业气体接触的外表面。

2. 发明授权

US08313286B2 Diffuser apparatus in a turbomachine 有权
标题翻译：涡轮机中的扩散器装置
公开(公告)号：US08313286B2
公开(公告)日：2012-11-20
申请号：US12393555
申请日：2009-02-26
申请人： Alexander R. Beeck
发明人： Alexander R. Beeck
IPC分类号： F03D11/00 , F04D29/44 , F04D29/54 , F03B1/00 , F03B11/02
CPC分类号： F01D5/143 , F01D5/145 , F01D25/30
摘要： A diffuser apparatus in a turbomachine is provided comprising a diffuser structure and stabilizing structure. The diffuser structure includes inner and outer walls defining a flow passageway through which gases flow and diffuse such that kinetic energy is reduced and pressure is increased in the gases as they move through the passageway. The stabilizing structure stabilizes a separated gas recirculation zone.
摘要翻译：提供了一种涡轮机中的扩散装置，其包括扩散器结构和稳定结构。扩散器结构包括限定流动通道的内壁和外壁，气体通过该通道流动并扩散，使得动能减小，并且当气体移动通过通道时气体中的压力增加。稳定结构稳定了分离的气体再循环区域。

3. 发明申请

US20120076653A1 TURBINE BLADE TIP WITH VORTEX GENERATORS 失效
标题翻译：涡轮叶片带VORTEX发电机
公开(公告)号：US20120076653A1
公开(公告)日：2012-03-29
申请号：US12892515
申请日：2010-09-28
申请人： Alexander R. Beeck , Glenn E. Brown
发明人： Alexander R. Beeck , Glenn E. Brown
IPC分类号： F01D5/08
CPC分类号： F01D5/20 , F01D5/187 , F05D2210/33 , F05D2240/127 , F05D2250/21 , F05D2260/2212
摘要： A turbine blade for a turbine engine having a tip with one or more vortex generators for reducing tip leakage during operation of the turbine engine. The vortex generators may extend radially outward from the radially outer surface of the tip wall. The vortex generator may be positioned between a rib extending radially outward from the radially outer surface of the tip wall and an intersection between the outer surface of the tip wall and an outer surface on the pressure side. The vortex generators may include a base and three sides forming a triangular point with a first side having a larger surface are than second and third sides. One or more film cooling holes may be formed in the tip wall to provide cooling air to the tip. In one embodiment, film cooling holes may be positioned in one or more vortex generators.
摘要翻译：一种用于涡轮发动机的涡轮叶片，其具有具有一个或多个涡流发生器的尖端，用于在涡轮发动机的运行期间减少尖端泄漏。涡流发生器可以从尖端壁的径向外表面径向向外延伸。涡流发生器可以位于从尖端壁的径向外表面径向向外延伸的肋与尖端壁的外表面与压力侧的外表面之间的交叉点之间。涡流发生器可以包括基部，并且形成具有比第二和第三侧更大表面的第一侧的三角形点的三个边。可以在尖端壁中形成一个或多个薄膜冷却孔，以向尖端提供冷却空气。在一个实施例中，膜冷却孔可以定位在一个或多个涡流发生器中。

4. 发明申请

US20100290897A1 Tip Shrouded Turbine Blade 有权
标题翻译：尖头罩罩涡轮叶片
公开(公告)号：US20100290897A1
公开(公告)日：2010-11-18
申请号：US12464492
申请日：2009-05-12
申请人： Alexander R. Beeck , Sankar Nellian
发明人： Alexander R. Beeck , Sankar Nellian
IPC分类号： F01D11/08 , F01D5/22
CPC分类号： F01D11/08 , F01D5/225
摘要： A turbine blade is provided comprising: an airfoil including upper and lower ends; a root coupled to the airfoil lower end; a shroud coupled to the airfoil upper end; and at least one sealing rail extending radially outwardly from an upper surface of the shroud and extending generally along a circumferential length of the shroud. The sealing rail may comprise a mid-section, opposing end sections and at least one intermediate section located between the mid-section and one of the opposing end sections. An axial thickness of the rail may vary.
摘要翻译：提供一种涡轮叶片，其包括：包括上端和下端的翼型件; 与翼型件下端相连的根部; 联接到翼型件上端的护罩; 以及至少一个密封轨道，其从护罩的上表面径向向外延伸并且大致沿着护罩的圆周长度延伸。密封轨道可以包括中间部分，相对的端部部分和位于中间部分和相对的端部部分之一之间的至少一个中间部分。轨道的轴向厚度可以变化。

5. 发明申请

US20100021291A1 Diffuser Apparatus in a Turbomachine 有权
标题翻译：涡轮机中的扩散器
公开(公告)号：US20100021291A1
公开(公告)日：2010-01-28
申请号：US12393555
申请日：2009-02-26
申请人： Alexander R. Beeck
发明人： Alexander R. Beeck
IPC分类号： F01D25/24
CPC分类号： F01D5/143 , F01D5/145 , F01D25/30
摘要： A diffuser apparatus in a turbomachine is provided comprising a diffuser structure and stabilizing structure. The diffuser structure includes inner and outer walls defining a flow passageway through which gases flow and diffuse such that kinetic energy is reduced and pressure is increased in the gases as they move through the passageway. The stabilizing structure stabilizes a separated gas recirculation zone.
摘要翻译：提供了一种涡轮机中的扩散装置，其包括扩散器结构和稳定结构。扩散器结构包括限定流动通道的内壁和外壁，气体通过该通道流动并扩散，使得动能减小，并且当气体移动通过通道时气体中的压力增加。稳定结构稳定了分离的气体再循环区域。

6. 发明申请

US20150167986A1 SWIRLING MIDFRAME FLOW FOR GAS TURBINE ENGINE HAVING ADVANCED TRANSITIONS 有权
标题翻译：用于具有高级过渡的气体涡轮发动机的旋转中间流
公开(公告)号：US20150167986A1
公开(公告)日：2015-06-18
申请号：US14105313
申请日：2013-12-13
申请人： Matthew D. Montgomery , Richard C. Charron , Jose L. Rodriguez , Bernhard W. Küsters , Jay A. Morrison , Alexander R. Beeck
发明人： Matthew D. Montgomery , Richard C. Charron , Jose L. Rodriguez , Bernhard W. Küsters , Jay A. Morrison , Alexander R. Beeck
IPC分类号： F23R3/46
CPC分类号： F23R3/46 , F04D29/542 , F04D29/545 , F04D29/547 , F23R3/02 , F23R3/04 , F23R3/425
摘要： A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.
摘要翻译：一种燃气涡轮发动机罐环式燃烧装置（10），包括：轴向压缩机（82），其可操作以沿旋转方向（60）旋转; 构造成从所述轴向压缩机接收压缩空气（16）的扩散器（100,110）; 配置成从扩散器接收压缩空气的增压室（22）多个燃烧器罐（12）各自具有与所述气室流体连通的燃烧器入口（38），其中每个燃烧室可以被切向地定向，使得相应的燃烧器入口在与旋转相反的方向上与相应的燃烧室出口周向偏移方向; 以及气流引导装置（80），其构造成沿着与旋转方向相反的方向对所述增压室中的压缩空气施加周向运动。

7. 发明授权

US09017030B2 Turbine component including airfoil with contour 有权
标题翻译：涡轮机组件包括具有轮廓的翼型
公开(公告)号：US09017030B2
公开(公告)日：2015-04-28
申请号：US13280440
申请日：2011-10-25
申请人： Alexander R. Beeck
发明人： Alexander R. Beeck
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D5/145 , F05D2240/127 , F05D2250/184 , F05D2250/294
摘要： A turbine engine airfoil structure including an airfoil adapted to extend across a gas passage, and a platform structure defining an endwall located at one end of the airfoil and positioned at a location forming a boundary of the gas passage. A saddle portion is associated with at least one airfoil surface of the airfoil, the saddle portion defining a contour having a first radially outer edge located on the at least one airfoil surface and a second radially inner edge located radially inwardly from the radially outer edge. The contour includes a curvature in a plane extending generally perpendicular to the at least one airfoil surface and passing through the saddle portion, the curvature being radially spaced from the endwall and defining an apex located between the radially outer and inner edges of the saddle portion.
摘要翻译：包括适于延伸穿过气体通道的翼型件的涡轮发动机翼型结构以及限定位于所述翼型件的一端并位于形成所述气体通道的边界的位置处的端壁的平台结构。鞍座部分与翼型件的至少一个翼型件表面相关联，鞍形部分限定轮廓，该轮廓具有位于至少一个翼型表面上的第一径向外边缘和从径向外边缘径向向内定位的第二径向内边缘。轮廓包括在大致垂直于至少一个翼面表面延伸并穿过鞍座部分的平面中的曲率，该曲率与端壁径向间隔开并限定位于鞍部的径向外边缘和内边缘之间的顶点。

8. 发明授权

US08690536B2 Turbine blade tip with vortex generators 失效
标题翻译：涡轮叶片尖端与涡流发生器
公开(公告)号：US08690536B2
公开(公告)日：2014-04-08
申请号：US12892515
申请日：2010-09-28
申请人： Alexander R. Beeck , Glenn E. Brown
发明人： Alexander R. Beeck , Glenn E. Brown
IPC分类号： F01D5/20 , F01D5/08
CPC分类号： F01D5/20 , F01D5/187 , F05D2210/33 , F05D2240/127 , F05D2250/21 , F05D2260/2212
摘要： A turbine blade for a turbine engine having a tip with one or more vortex generators for reducing tip leakage during operation of the turbine engine. The vortex generators may extend radially outward from the radially outer surface of the tip wall. The vortex generator may be positioned between a rib extending radially outward from the radially outer surface of the tip wall and an intersection between the outer surface of the tip wall and an outer surface on the pressure side. The vortex generators may include a base and three sides forming a triangular point with a first side having a larger surface are than second and third sides. One or more film cooling holes may be formed in the tip wall to provide cooling air to the tip. In one embodiment, film cooling holes may be positioned in one or more vortex generators.
摘要翻译：一种用于涡轮发动机的涡轮叶片，其具有具有一个或多个涡流发生器的尖端，用于在涡轮发动机的运行期间减少尖端泄漏。涡流发生器可以从尖端壁的径向外表面径向向外延伸。涡流发生器可以位于从尖端壁的径向外表面径向向外延伸的肋与尖端壁的外表面与压力侧的外表面之间的交叉点之间。涡流发生器可以包括基部，并且形成具有比第二和第三侧更大表面的第一侧的三角形点的三个边。可以在尖端壁中形成一个或多个薄膜冷却孔，以向尖端提供冷却空气。在一个实施例中，膜冷却孔可以定位在一个或多个涡流发生器中。

9. 发明申请

US20130199038A1 METHOD OF ASSEMBLING A GAS TURBINE ENGINE 失效
标题翻译：组装气体涡轮发动机的方法
公开(公告)号：US20130199038A1
公开(公告)日：2013-08-08
申请号：US13367750
申请日：2012-02-07
申请人： Alexander R. Beeck
发明人： Alexander R. Beeck
IPC分类号： B23P11/00
CPC分类号： F01D25/285 , F01D11/00 , F02C7/28 , F05D2230/60
摘要： A method of assembling a seal in a horizontal split plane gas turbine engine including providing a rotor assembly including a turbine blade assembly defining a forward face and a seal ring extending axially from the forward face. The rotor assembly is positioned extending through a lower compressor casing and a lower turbine casing, the positioning including tilting the rotor assembly at an angle relative to the longitudinal axis for the engine. An upper turbine casing is positioned over the tilted rotor assembly, and the upper and lower turbine casings define a circumferentially extending seal groove. The rotor assembly is moved in an axially forward direction to position the seal ring in axially overlapping relation within the seal groove. The longitudinal axis of the rotor assembly is then aligned with the longitudinal axis of the turbine engine to further position the seal ring within the seal groove.
摘要翻译：一种在水平分裂平面燃气涡轮发动机中组装密封件的方法，包括提供转子组件，转子组件包括限定前表面的涡轮叶片组件和从前表面轴向延伸的密封环。转子组件定位成延伸穿过下压缩机壳体和下涡轮机壳体，该定位包括使转子组件相对于发动机的纵向轴线成一定角度倾斜。上涡轮机壳体位于倾斜的转子组件上方，并且上涡轮机壳体和下涡轮机壳体限定周向延伸的密封槽。转子组件沿轴向向前移动以将密封环定位在密封槽内的轴向重叠关系。然后转子组件的纵向轴线与涡轮发动机的纵向轴线对齐，以将密封环进一步定位在密封槽内。

10. 发明申请

US20130004315A1 MATEFACE GAP CONFIGURATION FOR GAS TURBINE ENGINE 有权
标题翻译：燃气轮机发动机功率谱配置
公开(公告)号：US20130004315A1
公开(公告)日：2013-01-03
申请号：US13171691
申请日：2011-06-29
申请人： Alexander R. Beeck , Shantanu P. Mhetras
发明人： Alexander R. Beeck , Shantanu P. Mhetras
IPC分类号： F01D5/22
CPC分类号： F01D5/143 , F01D5/22 , F01D11/003
摘要： In a gas turbine engine, adjoining pairs of airfoil structures include airfoils mounted to respective platforms. The platforms have side edges defining matefaces that form a mateface gap extending from an upstream edge of the platforms to a downstream edge of the platforms. A flow field of working gas adjacent to endwalls of the platform comprises streamlines extending generally transverse to the axial direction from a first airfoil toward an adjacent second airfoil. To achieve improved aerodynamic performance, the mateface gap has portions oriented transverse to the streamlines and oriented aligned with the streamlines. A step in elevation of the side edges at the transverse portion can include injected cooling flow in a direction that enhances attachment of the flow at a downstream side.
摘要翻译：在燃气涡轮发动机中，相邻的翼型结构对包括安装到相应平台的翼型件。平台具有侧边缘，其限定了形成从平台的上游边缘延伸到平台的下游边缘的面对间隙的面。与平台的端壁相邻的工作气体的流场包括从第一翼面朝向相邻的第二翼面大致横向于轴向方向延伸的流线。为了实现改进的空气动力学性能，配合间隙具有横向于流线并且与流线对准的部分。在横向部分处的侧边缘的升高台阶可以包括在增强下游侧的流动的附着方向的注入的冷却流。

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