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1.发明授权Device for blowing gases for regulating clearances in a gas turbine engine 失效用于吹送用于调节燃气涡轮发动机中的间隙的气体的装置
公开(公告)号：US5980201A
公开(公告)日：1999-11-09
申请号：US877903
申请日：1997-06-18
申请人： Josette Benoist , Guillaume Henri Chaput , Didier Desire Rene Pasquiet , Jean-Claude Christian Taillant , Guy Pierre Queneherve
发明人： Josette Benoist , Guillaume Henri Chaput , Didier Desire Rene Pasquiet , Jean-Claude Christian Taillant , Guy Pierre Queneherve
摘要： A gas mixer (8) which placed in a flow of gases upstream of a ring (3) that is to be heated or cooled, the gas mixer (8) including a succession of mbers (12, 14, 15) having communication or outlet orifices (16, 17, 18) in large numbers in order to render uniform a rate and temperature of the gas flow. The gas mixer (8) is applicable to gas turbine engines.
摘要翻译： 一种气体混合器（8），其放置在待加热或冷却的环（3）上游的气体流中，所述气体混合器（8）包括具有连通或出口的一系列腔室（12,14,15） 孔（16,17,18），以使气流的速率和温度均匀。 气体混合器（8）适用于燃气轮机。
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公开(公告)号：US5645398A
公开(公告)日：1997-07-08
申请号：US562597
申请日：1995-11-24
CPC分类号： F01D9/042 , F01D25/246 , F05D2230/642 , Y02T50/673
摘要： While remaining in one piece and unsectored, a nozzle permits a slight radial expansion of an assembly. The nozzle is formed by an inner platform mounted in a sliding manner with respect to a stator and an outer platform mounted in a free manner with respect to the case of the stator. Rods are fitted in a pivoting manner so as to radially guide and axially block upper parts of vanes, which are mounted in a sliding manner in the inner platform. The assembly is advantageously completed by gaskets. The nozzle can be used in high pressure turbines of turbojets.
摘要翻译： 虽然保持在一个单件中并且未被接合，但是喷嘴允许组件略微径向膨胀。 喷嘴由相对于定子滑动安装的内平台和相对于定子的壳体以自由方式安装的外平台形成。 杆以枢转的方式安装，以便径向地引导和轴向地阻挡叶片的上部，其以滑动方式安装在内平台中。 该组件有利地由垫圈完成。 喷嘴可用于涡轮喷气发动机的高压涡轮机。
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公开(公告)号：US5752804A
公开(公告)日：1998-05-19
申请号：US562598
申请日：1995-11-24
CPC分类号： F01D25/246 , F05D2230/642 , Y02T50/671
摘要： A nozzle of a turbine stator of a turbine engine, wherein at least two of the vanes are fixed to each inner platform and to opposite each outer platform, and a maintaining unit is configured to maintain each sector with respect to a case of the turbine stator and to connect sectors together and has a rotational maintaining element, a radial maintaining element and an axial maintaining element. The radial maintaining element is flexible so as to permit a radial expansion of each sector and is constituted by an elastic joint fixed to the case so as to surround the sectors.
摘要翻译： 涡轮发动机的涡轮机定子的喷嘴，其中至少两个叶片固定到每个内平台并且与每个外平台相对，并且保持单元构造成相对于涡轮机定子的壳体来维持每个扇区 并且将扇区连接在一起并具有旋转保持元件，径向保持元件和轴向保持元件。 径向保持元件是柔性的，以便允许每个扇区的径向膨胀，并且由固定到壳体上的弹性接头构成以围绕扇形部分。
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公开(公告)号：US5993156A
公开(公告)日：1999-11-30
申请号：US104200
申请日：1998-06-25
申请人： Yves Maurice Bailly , Xavier Gerard Andre Coudray , Mischael Francois Louis Derrien , jean-Michel Roger Fougeres , Philippe Christian Pellier , Jean-Claude Christian Taillant , Thierry Henri Marcel Tassin , Christophe Bernard Texier
发明人： Yves Maurice Bailly , Xavier Gerard Andre Coudray , Mischael Francois Louis Derrien , jean-Michel Roger Fougeres , Philippe Christian Pellier , Jean-Claude Christian Taillant , Thierry Henri Marcel Tassin , Christophe Bernard Texier
CPC分类号： F01D5/188 , F01D5/187 , F05D2250/15 , F05D2250/25
摘要： A turbine vane-system cooling system uses three internal cooling cavities 1, 12, 13) separated by two radial walls (9, 10). The upstream cavity (11) uses a helical ramp (30) and is fed through an intake (22) at the vane root (3). The middle cavity (12) also is fed at the vane root (3) and includes a compartmented, multi-perforated lining (40). The air is exhausted from each compartment through impact orifices and enters the succeeding compartment through slots (42) and then is finally exhausted through a vane-head orifice (21). The vane side walls opposite the downstream cavity (13) have double skins with bridging elements. The air passes through these double skins but circulates centrifugally in the upstream portion (15) of the downstream cavity (13) and enters this cavity's downstream portion (16) to be exhausted through slots (19) in the trailing edge (6). A third wall (14) divides the downstream cavity (13) into two parts (15, 16).
摘要翻译： 涡轮叶片系统冷却系统使用由两个径向壁（9,10）分开的三个内部冷却腔（11,12,13）。 上游腔（11）使用螺旋斜坡（30）并且通过叶片根部（3）处的进气口（22）进给。 中空腔（12）也在叶片根部（3）处进给，并且包括隔室，多孔衬里（40）。 空气从每个隔室通过冲击孔排出，并通过狭槽（42）进入后续隔间，然后最终通过叶片头孔（21）排出。 与下游腔（13）相对的叶片侧壁具有带有桥接元件的双面皮。 空气通过这些双面皮，但是在下游腔（13）的上游部分（15）中离心地循环，并且进入该空腔的下游部分（16）以通过后缘（6）中的狭槽（19）排出。 第三壁（14）将下游腔（13）分成两部分（15,16）。
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公开(公告)号：US08336317B2
公开(公告)日：2012-12-25
申请号：US12889791
申请日：2010-09-24
申请人： Stéphane Pierre Guillaume Blanchard , Patrick Claude Pasquis , Wilfried Lionel Schweblen , Jean-Claude Christian Taillant
发明人： Stéphane Pierre Guillaume Blanchard , Patrick Claude Pasquis , Wilfried Lionel Schweblen , Jean-Claude Christian Taillant
IPC分类号： F02C7/12
CPC分类号： F01D5/082 , F01D11/001 , F01D25/12 , F02C7/18 , Y02T50/671 , Y02T50/676
摘要： A turbine engine, including a final centrifugal compressor stage associated with a diffuser for supplying air to a combustion chamber, and a ventilation element for ventilating a high-pressure turbine wheel, is disclosed. The ventilation element includes an injection element for injecting air onto the wheel and a take-up element for taking up a flow for cooling the impeller of the compressor, where the take-up element has a labyrinth seal mounted at the outlet of the injection element, and the air outlet orifices are installed between the injection element and the labyrinth seal and leading upstream of the turbine wheel.
摘要翻译： 公开了一种涡轮发动机，包括与用于向燃烧室供应空气的扩散器相关联的最终离心压缩机台，以及用于使高压涡轮机叶轮通风的通风元件。 通风元件包括用于将空气喷射到轮上的注射元件和用于吸收用于冷却压缩机叶轮的流动的卷取元件，其中卷取元件具有安装在注射元件出口处的迷宫式密封件 并且空气出口孔安装在注射元件和迷宫式密封件之间并引导到涡轮机叶轮的上游。
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6.发明授权Low pressure turbine for an aircraft turbomachine, comprising a segmented nozzle with an improved design 有权用于飞机涡轮机的低压涡轮机，包括具有改进设计的分段喷嘴公开(公告)号：US08979489B2
公开(公告)日：2015-03-17
申请号：US13300981
申请日：2011-11-21
CPC分类号： F01D9/042 , F01D11/005 , F01D25/12 , Y02T50/675
摘要： The invention relates to a low pressure turbine (1) of a turbomachine comprising a nozzle (62) belonging to an upstream stage (20B) and a nozzle (162) belonging to a downstream stage (20C), the nozzle (62) forming segments (62a) having an external structure (66) comprising: a tab (76) bearing radially on a hook (79) fixed to the case, a tab (85) bearing radially on a reaming (87) in the case, the tabs (76, 85) delimiting an annular upstream cooling air circulation cavity (91), a contact surface (84) extending in the downstream direction from the tab (85) and lined with an abradable element (86) on the inside, the contact surface comprising a downstream end (92) bearing axially on the nozzle (162) and bearing radially on a stop (93) of the case, the contact surfaces (84) delimiting an annular downstream cooling air circulation cavity (94) communicating with cavity (91).
摘要翻译： 本发明涉及一种涡轮机的低压涡轮（1），其包括属于上游级（20B）的喷嘴（62）和属于下游级（20C）的喷嘴（162），所述喷嘴（62）形成段 （62a），其具有外部结构（66），所述外部结构（66）包括：径向地支撑在固定到所述壳体上的钩（79）上的突片（76），在所述壳体中的径向（87） 限定环形上游冷却空气循环空腔（91）;接触表面（84），其从所述突片（85）向下游方向延伸并且在内侧衬有可磨损元件（86），所述接触表面包括 位于所述喷嘴（162）上并且径向地支承在所述壳体的止动件（93）上的下游端（92），所述接触表面（84）限定与腔（91）连通的环形下游冷却空气循环腔（94） 。
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公开(公告)号：US5772398A
公开(公告)日：1998-06-30
申请号：US774636
申请日：1996-12-30
CPC分类号： F01D5/189 , F05D2240/81 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A cooled turbine guide vane comprises a hollow aerodynamic portion between inner and outer platforms. The interior of the aerodynamic portion is partitioned into a leading edge duct and a main cavity in which a perforated tubular member is disposed, being spaced from the intrados and extrados side walls of the vane by longitudinal ribs. The tubular member is divided by a partition into two cavities on the intrados and extrados sides of the partition. A first cooling circuit is constituted by the leading edge duct and the intrados cavity of the tubular member, and a second cooling circuit is constituted by the extrados cavity and a cooling system for the inner platform, both circuits being supplied with air by the same source from the outer platform. Cooling air from each circuit passes through the perforations of the tubular member to impinge on the inside face of the respective side wall of the vane and is then guided towards the trailing edge where it escapes through slits in the trailing edge.
摘要翻译： 冷却的涡轮引导叶片包括在内平台和外平台之间的中空空气动力部分。 空气动力部分的内部被分隔成前缘管道和主空腔，其中设置多孔管状构件，其通过纵向肋与叶片的内侧和外侧侧壁间隔开。 管状构件由分隔件分隔成分隔件的内侧和外侧两个空腔。 第一冷却回路由管状部件的前缘管道和内部空腔构成，第二冷却回路由外部空腔和内部平台的冷却系统构成，两个回路由相同的源供给空气 从外部平台。 来自每个电路的冷却空气通过管状构件的穿孔以撞击在叶片的相应侧壁的内表面上，然后被引导到后缘，在该后缘通过后缘中的狭缝逸出。
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公开(公告)号：US06334755B1
公开(公告)日：2002-01-01
申请号：US09506685
申请日：2000-02-18
申请人： Xavier Gérard André Coudray , Mischaël François Louis Derrien , Marc Roger Marchi , Philippe Christian Pellier , Jean-Claude Christian Taillant , Thierry Henri Marcel Tassin , Christophe Bernard Texier , Isabelle Marie Monique Valente
发明人： Xavier Gérard André Coudray , Mischaël François Louis Derrien , Marc Roger Marchi , Philippe Christian Pellier , Jean-Claude Christian Taillant , Thierry Henri Marcel Tassin , Christophe Bernard Texier , Isabelle Marie Monique Valente
IPC分类号： F01D514
CPC分类号： F02C7/185 , F01D5/088 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： The invention provides a turbomachine including a device for supplying pressurized gas, the gas being bled from the compressor of the turbomachine via a bleed orifice and cooled in a cooling cavity disposed within the compressor rotor upstream of the bleed orifice. This arrangement has the effect of cooling the bled gas by heat transfer through the outer wall of the compressor rotor to the gas stream which is being compressed by the compressor upstream of the bleed orifice, and has the result of reducing the drop in the performance of the compressor as a result of the gas being bled off.
摘要翻译： 本发明提供了一种涡轮机，其包括用于供应加压气体的装置，该气体经由泄放孔从涡轮机的压缩机中排出，并在设置在该排气口上游的压缩机转子内的冷却腔中冷却。 这种布置具有通过从压缩机转子的外壁传热到排出口压缩机压缩的气流而使排出气体冷却的效果，并且具有减少排气管的性能下降的结果 压缩机由于气体被排出。
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