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1. 发明授权

US08632300B2 Energy absorbing apparatus in a gas turbine engine 有权
标题翻译：燃气涡轮发动机中的能量吸收装置
公开(公告)号：US08632300B2
公开(公告)日：2014-01-21
申请号：US12841291
申请日：2010-07-22
申请人： Friedrich Rogers , Yevgeniy Shteyman
发明人： Friedrich Rogers , Yevgeniy Shteyman
IPC分类号： F01D5/10
CPC分类号： F04D27/0292 , F01D5/26 , F01D9/041 , F01D25/06 , F01D25/246 , F04D29/522 , F05D2260/96
摘要： A gas turbine includes a casing, a first diaphragm assembly, a second diaphragm assembly, and first energy absorbing apparatus. The casing has a radially outer surface and a radially inner surface including an annular slot extending circumferentially therein. The first diaphragm assembly includes a first inner structure, a first outer structure and a plurality of airfoils extending between the first inner and outer structures. The second diaphragm assembly includes a second inner structure, a second outer structure and a plurality of airfoils extending between the second inner and outer structures. The first energy absorbing apparatus engages a first end portion of the first outer structure so as to absorb at least portions of unsteady aerodynamic loads and steady rotational loads generated by the first diaphragm assembly.
摘要翻译：燃气轮机包括壳体，第一膜片组件，第二膜片组件和第一能量吸收装置。壳体具有径向外表面和径向内表面，其包括在其中周向延伸的环形槽。第一隔膜组件包括第一内部结构，第一外部结构和在第一内部和外部结构之间延伸的多个翼型件。第二隔膜组件包括第二内部结构，第二外部结构以及在第二内部和外部结构之间延伸的多个翼型件。第一能量吸收装置接合第一外部结构的第一端部，以便吸收至少部分不稳定的空气动力学负载和由第一隔膜组件产生的稳定的转动负载。

2. 发明申请

US20070160475A1 Tilted turbine vane with impingement cooling 审中-公开
标题翻译：倾斜涡轮叶片与冲击冷却
公开(公告)号：US20070160475A1
公开(公告)日：2007-07-12
申请号：US11330598
申请日：2006-01-12
申请人： Friedrich Rogers , Kenneth Landis
发明人： Friedrich Rogers , Kenneth Landis
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/188 , F05D2250/314 , F05D2260/201
摘要： A turbine airfoil having enhanced cooling capabilities. The turbine vane may be configured such that when a generally elongated airfoil of the turbine vane is attached to a turbine engine, a longitudinal axis of the generally elongated airfoil may be positioned nonparallel relative to a radial axis of the turbine engine in which the turbine vane is mounted. In this position, cooling orifices may be positioned in a region that is typically a dead zone in a conventional turbine vane where no cooling occurs. In one embodiment, a plurality of cooling orifices in an inner shroud of the turbine vane may be positioned between an outer edge of the inner shroud in closest proximity to a suction side of the airfoil near a leading edge of the airfoil and an intersection between the suction side and the inner shroud.
摘要翻译：具有增强的冷却能力的涡轮机翼型。涡轮叶片可以构造成使得当涡轮叶片的大致细长的翼型件连接到涡轮发动机时，大致细长的翼型件的纵向轴线可以相对于涡轮发动机的径向轴线不平行地定位，在涡轮机叶片被安装。在这个位置上，冷却孔可以定位在传统的涡轮叶片中通常是死区的区域中，其中不发生冷却。在一个实施例中，涡轮叶片的内护罩中的多个冷却孔可以位于最靠近翼型件的吸入侧的靠近翼型件的前缘的内护罩的外边缘之间，吸力侧和内护罩。

3. 发明申请

US20070258814A1 Turbine airfoil with integral chordal support ribs 审中-公开
标题翻译：具有整体弦支撑肋的涡轮翼型
公开(公告)号：US20070258814A1
公开(公告)日：2007-11-08
申请号：US11415597
申请日：2006-05-02
申请人： Joseph Metrisin , Friedrich Rogers , Christopher Rawlings , Kenneth Landis , Jae Um
发明人： Joseph Metrisin , Friedrich Rogers , Christopher Rawlings , Kenneth Landis , Jae Um
IPC分类号： F01D5/18
CPC分类号： F01D5/147 , F01D5/187 , F05D2260/2212 , F05D2260/22141
摘要： A turbine airfoil including a structural support system formed from chordal ribs within an internal cooling system in the airfoil. The chordal ribs forming the structural support system may be positioned in a cooling fluid supply channel in the hollow airfoil that is positioned proximate to a trailing edge cooling channel. The trailing edge cooling channel may include a plurality of pin fins forming a pin fin bank extending between inner surfaces of the pressure side wall and suction side wall. The chordal ribs may protrude from an inner surface of the outer wall of the hollow airfoil and extend in a general chordwise direction from a mid-chord region of the hollow airfoil to the trailing edge and into the pin fin bank. The structural support system reduces stresses proximate to the pin fins in the pin fin bank closest to the mid-chord region of the airfoil.
摘要翻译：一种涡轮机翼型，其包括在翼型内的内部冷却系统内由弦肋形成的结构支撑系统。形成结构支撑系统的弦肋可以定位在靠近后缘冷却通道定位的中空翼型件中的冷却流体供应通道中。后缘冷却通道可以包括多个销翅片，其形成在压力侧壁和吸力侧壁的内表面之间延伸的销翅片组。弦杆可以从中空翼型件的外壁的内表面突出，并且从中空翼型的中弦区域延伸到大致的弦向方向延伸到后缘并进入销翼片组。结构支撑系统降低了最接近翼型中弦区域的销翅片组中靠近销翅片的应力。

4. 发明授权

US06851924B2 Crack-resistance vane segment member 有权
标题翻译：抗裂叶片段构件
公开(公告)号：US06851924B2
公开(公告)日：2005-02-08
申请号：US10259869
申请日：2002-09-27
申请人： Stefan Mazzola , Keith L. Nickols , Friedrich Rogers , W. David Day , Kelly M. Flannery
发明人： Stefan Mazzola , Keith L. Nickols , Friedrich Rogers , W. David Day , Kelly M. Flannery
IPC分类号： F01D5/14 , F01D5/18 , F01D9/06
CPC分类号： F01D5/187 , F01D5/145 , F05D2260/202
摘要： A crack-resistant vane segment assembly member for an industrial turbine engine is disclosed. The vane segment includes at least one internally-cooled body portion and inner and outer shroud portions. The body portions include end regions characterized by blending and transition zones that ensure heat is transferred at a non-crack-inducing rate from the shroud portions to the body portions. The vane segment assembly also includes a cooling arrangement that reduces the impact of thermal gradient-induced stresses acting at the interface between the body portions and shroud portions. The cooling arrangement cooperates with the transition and blending zones to produce synergistically-enhanced crack resistance properties.
摘要翻译：公开了一种用于工业涡轮发动机的抗裂性叶片段组件。叶片段包括至少一个内部冷却主体部分和内部和外部护罩部分。主体部分包括以混合和过渡区为特征的端部区域，其确保热量以非裂纹诱导速率从护罩部分转移到主体部分。叶片段组件还包括冷却装置，其减少作用在主体部分和护罩部分之间的界面处的热梯度引起的应力的冲击。冷却装置与过渡和混合区配合以产生协同增强的抗裂性。

5. 发明授权

US08684662B2 Ring segment with impingement and convective cooling 有权
标题翻译：环形区段具有冲击和对流冷却
公开(公告)号：US08684662B2
公开(公告)日：2014-04-01
申请号：US12875224
申请日：2010-09-03
申请人： Nan Jiang , Samuel R. Miller, Jr. , Friedrich Rogers , Hubert Paprotna
发明人： Nan Jiang , Samuel R. Miller, Jr. , Friedrich Rogers , Hubert Paprotna
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F05D2240/11 , F05D2260/201
摘要： A ring segment for a gas turbine engine includes an outer panel defining a structural body for the ring segment. An outer side of an inner panel is attached to an inner side of the outer panel at an interface, and an inner side of the inner panel defines a portion of a hot gas path through the gas turbine engine. An outer side of the outer panel, opposite from the interface, is in communication with a source of cooling air. A plurality of impingement holes extend through the outer panel from the outer side to the inner side of the outer panel for directing impingement air to the outer side of the inner panel. The outer and inner panels define a plurality of flow channels at the interface for effecting convective cooling of the outer panel along the flow channels between the outer and inner panels.
摘要翻译：用于燃气涡轮发动机的环段包括限定用于环段的结构体的外板。内板的外侧在界面处附接到外板的内侧，并且内板的内侧限定通过燃气涡轮发动机的热气路径的一部分。外部面板的与界面相对的外侧与冷却空气源连通。多个冲击孔从外板的外侧到内侧延伸穿过外板，用于将冲击空气引导到内板的外侧。外板和内板在界面处限定多个流动通道，用于沿着外板和内板之间的流动通道进行外板的对流冷却。

6. 发明申请

US20120057969A1 RING SEGMENT WITH IMPINGEMENT AND CONVECTIVE COOLING 有权
标题翻译：带有侵入和对流冷却的环形部分
公开(公告)号：US20120057969A1
公开(公告)日：2012-03-08
申请号：US12875224
申请日：2010-09-03
申请人： Nan Jiang , Samuel R. Miller, JR. , Friedrich Rogers , Hubert Paprotna
发明人： Nan Jiang , Samuel R. Miller, JR. , Friedrich Rogers , Hubert Paprotna
IPC分类号： F01D5/08
CPC分类号： F01D11/08 , F05D2240/11 , F05D2260/201
摘要： A ring segment for a gas turbine engine includes an outer panel defining a structural body for the ring segment. An outer side of an inner panel is attached to an inner side of the outer panel at an interface, and an inner side of the inner panel defines a portion of a hot gas path through the gas turbine engine. An outer side of the outer panel, opposite from the interface, is in communication with a source of cooling air. A plurality of impingement holes extend through the outer panel from the outer side to the inner side of the outer panel for directing impingement air to the outer side of the inner panel. The outer and inner panels define a plurality of flow channels at the interface for effecting convective cooling of the outer panel along the flow channels between the outer and inner panels.
摘要翻译：用于燃气涡轮发动机的环段包括限定用于环段的结构体的外板。内板的外侧在界面处附接到外板的内侧，并且内板的内侧限定通过燃气涡轮发动机的热气路径的一部分。外部面板的与界面相对的外侧与冷却空气源连通。多个冲击孔从外板的外侧到内侧延伸穿过外板，用于将冲击空气引导到内板的外侧。外板和内板在界面处限定多个流动通道，用于沿着外板和内板之间的流动通道进行外板的对流冷却。

7. 发明申请

US20120020770A1 ENERGY ABSORBING APPARATUS IN A GAS TURBINE ENGINE 有权
标题翻译：能源吸收装置在燃气涡轮发动机
公开(公告)号：US20120020770A1
公开(公告)日：2012-01-26
申请号：US12841291
申请日：2010-07-22
申请人： Friedrich Rogers , Yevgeniy Shteyman
发明人： Friedrich Rogers , Yevgeniy Shteyman
IPC分类号： F04D29/66
CPC分类号： F04D27/0292 , F01D5/26 , F01D9/041 , F01D25/06 , F01D25/246 , F04D29/522 , F05D2260/96
摘要： A gas turbine includes a casing, a first diaphragm assembly, a second diaphragm assembly, and first energy absorbing apparatus. The casing has a radially outer surface and a radially inner surface including an annular slot extending circumferentially therein. The first diaphragm assembly includes a first inner structure, a first outer structure and a plurality of airfoils extending between the first inner and outer structures. The second diaphragm assembly includes a second inner structure, a second outer structure and a plurality of airfoils extending between the second inner and outer structures. The first energy absorbing apparatus engages a first end portion of the first outer structure so as to absorb at least portions of unsteady aerodynamic loads and steady rotational loads generated by the first diaphragm assembly.
摘要翻译：燃气轮机包括壳体，第一膜片组件，第二膜片组件和第一能量吸收装置。壳体具有径向外表面和径向内表面，其包括在其中周向延伸的环形槽。第一隔膜组件包括第一内部结构，第一外部结构和在第一内部和外部结构之间延伸的多个翼型件。第二隔膜组件包括第二内部结构，第二外部结构以及在第二内部和外部结构之间延伸的多个翼型件。第一能量吸收装置接合第一外部结构的第一端部，以便吸收至少部分不稳定的空气动力学负载和由第一隔膜组件产生的稳定的转动负载。

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