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1. 发明申请

WO2011018072A3 FASTENING ELEMENT FOR A GUIDE BLADE RING OF A TURBOMACHINE 审中-公开
标题翻译：固定元件FOR A叶片环的涡轮机
公开(公告)号：WO2011018072A3
公开(公告)日：2011-09-15
申请号：PCT/DE2010000927
申请日：2010-08-05
申请人： MTU AERO ENGINES GMBH , WEIDMANN WILFRIED
发明人： WEIDMANN WILFRIED
IPC分类号： F01D25/24 , F01D9/04
CPC分类号： F01D5/225 , F01D9/042 , F01D25/246 , F05D2240/80 , F05D2260/30
摘要： The invention relates to a turbomachine (10), in particular a gas turbine, comprising a housing (22) and a guide blade ring (12), the outer shroud (16) of which is divided into segments (14) by joints, characterized in that the outer shroud (16) is fastened to the housing (22) by means of a first fastening element (30) for absorbing axial force and a second fastening element (24) independent of the first fastening element (30) for absorbing circumferential force, the first and the second fastening elements (24, 30) enabling play in the radial direction for the segments (14) of the outer shroud (16).
摘要翻译：是通过在所述部分（14）分离的关节分成一个涡轮机（10），特别是燃气涡轮机，具有外壳（22）和叶片环（12），所述外护罩（16），其特征在于，所述外条带（16）用于Umfangskraftaufhahme一个第一紧固元件（30），用于Axialkraftaumahme和第二，从所述第一紧固元件（30）的独立的紧固元件（24）的壳体（22）上是固定的，其中，第一和第二紧固元件（24，30）（对于节段14 ）使外护罩（16）具有在径向方向上的间隙。

2. 发明申请

WO2008141609A3 GAS TURBINE 审中-公开
标题翻译：燃气轮机
公开(公告)号：WO2008141609A3
公开(公告)日：2009-06-11
申请号：PCT/DE2008000758
申请日：2008-05-02
申请人： MTU AERO ENGINES GMBH , WEIDMANN WILFRIED , WIRTH MORITZ
发明人： WEIDMANN WILFRIED , WIRTH MORITZ
IPC分类号： F01D5/08 , F01D25/12
CPC分类号： F01D5/082 , F01D5/025 , F01D25/125
摘要： The invention relates to a gas turbine having a rotor comprising a turbine rotor (1), a shaft (11), and a compressor rotor, the turbine rotor having at least one washer disk (3, 4, 5) and a rotor cone (9) leading from the or a washer disk to the shaft, the downstream end of the shaft being supported rotatably in a bearing (13) having a bearing chamber (15), the interior (25) of the shaft being designed as a flow channel for bearing chamber sealing air, and the upstream space surrounding the rotor cone being designed as a flow space for cooling air (21). The shaft has an expansion (27) in the region of the rotor connection (33), on the upstream end of which openings (28) for the inlet of cooling air are present, and on the downstream end of which openings for the outlet of cooling air are present in the space (24) between the bearing chamber and the rotor cone, a wall (31) separating the flows of cooling air and sealing air (19) from one another in the interior of the shaft.
摘要翻译：与具有涡轮机转子（1）的转子燃气涡轮机包括一轴（11）和增稠chterrotor，其中，所述涡轮机转子具有至少一个转子盘（3,4,5），并从或一个转子盘至轴转子锥体的领先（ 9），其特征在于，所述轴的所述下游端（在一个轴承13）的轴承腔（15）可旋转地支撑，其中，所述轴为流动通道的内部（25）。被设计用于承载密封空气室，并且其中，所述转子锥形上游周围空间作为冷却空气（21）的流动空间被执行。所述轴具有在转子链路（33）的区域具有加宽（27）在其上游端的孔口（28），用于冷却空气的入口，并且在用于冷却的空气进入贮存室之间的空间（24）的出口处的下游端部开口和转子锥体都存在，其特征在于，壁（31）分隔开的冷却空气和在彼此内部的轴密封空气（19）的流动。

3. 发明专利

ES2347303T3 TURBINA DE GAS. 未知
公开(公告)号：ES2347303T3
公开(公告)日：2010-10-27
申请号：ES08758019
申请日：2008-05-02
申请人： MTU AERO ENGINES GMBH
发明人： WEIDMANN WILFRIED , WIRTH MORITZ
IPC分类号： F01D5/08 , F01D25/12
摘要： Turbina de gas, equipada con un rotor que se compone de un rotor de turbina (1), de un eje (11) así como de un rotor compresor y, al tratarse de una turbina de gas de ejes múltiples, este rotor forma parte integrante del sistema de baja tensión; en este caso, el rotor (1) de la turbina comprende por lo menos un disco de guía (3, 4, 5) con unos alabes así como un cono de rotor (9) que desde el disco de guía (5) o de uno de los discos de guía conduce hacia el eje (11); aquel extremo del eje (11), el cual está situado corriente abajo, se encuentra apoyado de manera giratoria en un cojinete (13) con cámara de alojamiento (15) y el espacio interior (25) del eje (11) está realizado como un canal de corriente para el aire de bloqueo (19), el cual conduce hacia la cámara de alojamiento (15), mientras que el espacio (23), que corriente arriba rodea el cono de rotor (9), está realizado como una cámara de corriente para el aire refrigerante (21) que es empleado para la refrigeración de los alabes; turbina de gas ésta que está caracterizada porque el eje (11) comprende -dentro de la zona de la fijación (33) del cono (9) del rotor- un ensanchamiento (27) con un mayor diámetro interior y con un mayor diámetro exterior y por aquél extremo de este ensanchamiento, el cual está situado corriente arriba, están previstas unas aberturas (28) para la entrada del aire refrigerante (21) al ensanchado espacio interior (26) de la cámara de alojamiento (15), mientras que por el extremo del ensanchamiento, el cual está situado corriente abajo, están previstas unas aberturas (29) para la salida del aire refrigerante (21) hacia el espacio (24), situado entre la cámara de alojamiento (15) y el cono (9) del rotor; así como caracterizada porque este ensanchado espacio interior (25) se encuentra estancado -en relación con el espacio interior continuo (25) del eje (11)- por medio de una pared (31) para la separación entre el aire refrigerante (21) y el aire de bloqueo (19).

4. 发明专利

CA2698283A1 MULTILAYER SHIELDING RING FOR A FLIGHT DRIVING MECHANISM 未知
公开(公告)号：CA2698283A1
公开(公告)日：2009-03-12
申请号：CA2698283
申请日：2008-08-27
申请人： MTU AERO ENGINES GMBH
发明人： WEIDMANN WILFRIED
IPC分类号： F01D21/04
摘要： A shielding (6) of a turbine housing (3) of a flight engine against the radial escape of blade debris, especially for a high-speed low-pressure turbine, is characterized in that the shielding (6) is constructed as a rigid ring-shaped component of several layers (8). By uncoupling the containment function from the design of the turbine exhaust gas channel, which is produced as a cast part, the disadvantages of the prior art are avoided. In particular, the turbine exhaust channel can be designed so as to optimize costs and weight.

5. 发明专利

DE102007042767A1 未知
公开(公告)号：DE102007042767A1
公开(公告)日：2009-03-12
申请号：DE102007042767
申请日：2007-09-07
申请人： MTU AERO ENGINES GMBH
发明人： WEIDMANN WILFRIED
IPC分类号： F01D25/06
摘要： A shielding (6) of a turbine housing (3) of an aircraft engine against radial escape of blade fragments, especially for a high-speed low-pressure turbine, is characterized in that the shielding (6) is embodied as a rigid ring-shaped component of several layers (8). Through the decoupling of the containment function from the design of the turbine exhaust gas channel, which is fabricated as a cast part, the disadvantages of the prior art are avoided. Particularly, the design of the turbine exhaust gas channel can be carried out in a cost- and weight-optimized manner.

6. 发明专利

DE102004016244B4 未知
公开(公告)号：DE102004016244B4
公开(公告)日：2007-08-23
申请号：DE102004016244
申请日：2004-04-02
申请人： MTU AERO ENGINES GMBH
发明人： FISCHER MARTIN , WEIDMANN WILFRIED , KNODEL EBERHARD
IPC分类号： F01D5/02 , B63H1/20 , F01D5/06 , F16B5/02
摘要： The invention relates to a rotor for a turbomachine, in particular a low-pressure turbine rotor for a gas turbine, having at least one stage, each stage comprising a rotor disk having rotor blades attached to the rotor disk, and the rotor disk of each stage being removably connected either to oppositely situated rotor disks of adjoining stages or to a rotor connection of a rotor shaft by at least one respective attachments. According to the invention, the, or each of the, attachment means extends through the rotor disk of at least one stage, whereby the, or each of the, attachment means is guided with radial play into at least one borehole passing through the respective rotor disk, so that an interior borehole surface is not subjected to load or force.

7. 发明专利

DE102009037620A1 Strömungsmaschine 未知
公开(公告)号：DE102009037620A1
公开(公告)日：2011-02-17
申请号：DE102009037620
申请日：2009-08-14
申请人： MTU AERO ENGINES GMBH
发明人： WEIDMANN WILFRIED
IPC分类号： F01D9/04
摘要： Eine Strömungsmaschine (10), insbesondere Gasturbine, mit einem Gehäuse (22) und einem Leitschaufelkranz (12), dessen äußeres Deckband (16) durch Trennfugen in Segmente (14) unterteilt ist, ist dadurch gekennzeichnet, dass das äußere Deckband (16) über ein erstes Befestigungselement (30) zur Axialkraftaufnahme und ein zweites, vom ersten Befestigungselement (30) unabhängiges Befestigungselement (24) zur Umfangskraftaufnahme am Gehäuse (22) befestigt ist, wobei das erste und das zweite Befestigungselement (24, 30) für die Segmente (14) des äußeren Deckbandes (16) ein Spiel in radialer Richtung ermöglichen.

8. 发明专利

DE102008048006A1 Shaft output engine, particularly for aircraft, has flange and disk body of rotor disk which forms transmitting space for screw head of screw element 未知
公开(公告)号：DE102008048006A1
公开(公告)日：2010-03-25
申请号：DE102008048006
申请日：2008-09-19
申请人： MTU AERO ENGINES GMBH
发明人： WEIDMANN WILFRIED , WIRTH MORITZ
IPC分类号： F01D5/02
摘要： The shaft output engine (12) has a flange and a disk body (20a) of a rotor disk (18a) which forms a transmitting space (26) for a screw head (28) of a screw element (30). The transmitting space is locked radially upward concerning to a shaft (16) and opened radially downward, and is adapted to a dimension of the screw head.

9. 发明专利

DE102005059084A1 未知
公开(公告)号：DE102005059084A1
公开(公告)日：2007-06-14
申请号：DE102005059084
申请日：2005-12-10
申请人： MTU AERO ENGINES GMBH
发明人： WEIDMANN WILFRIED , WIRTH MORITZ
IPC分类号： F01D5/32 , F01D11/00

10. 发明专利

DE102004016244A1 未知
公开(公告)号：DE102004016244A1
公开(公告)日：2005-10-27
申请号：DE102004016244
申请日：2004-04-02
申请人： MTU AERO ENGINES GMBH
发明人： FISCHER MARTIN , WEIDMANN WILFRIED , KNODEL EBERHARD
IPC分类号： B63H1/20 , F01D5/02 , F01D5/06 , F16B5/02
摘要： The invention relates to a rotor for a turbomachine, in particular a low-pressure turbine rotor for a gas turbine, having at least one stage, each stage comprising a rotor disk having rotor blades attached to the rotor disk, and the rotor disk of each stage being removably connected either to oppositely situated rotor disks of adjoining stages or to a rotor connection of a rotor shaft by at least one respective attachments. According to the invention, the, or each of the, attachment means extends through the rotor disk of at least one stage, whereby the, or each of the, attachment means is guided with radial play into at least one borehole passing through the respective rotor disk, so that an interior borehole surface is not subjected to load or force.

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