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1. 发明专利

JP2005023936A Cooling gas turbine blade 有权
标题翻译：冷却气体涡轮叶片
公开(公告)号：JP2005023936A
公开(公告)日：2005-01-27
申请号：JP2004191192
申请日：2004-06-29
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： PABION PHILIPPE JEAN PIERRE , SOUPIZON JEAN-LUC , GUIMBARD JEAN-MICHEL BERNARD
IPC分类号： F01D9/02 , F01D5/18 , F02C7/00
CPC分类号： F01D5/189 , Y02T50/676
摘要： PROBLEM TO BE SOLVED: To reduce leakage of air in the slide of a cooling blade, especially a nozzle blade and more concretely a low-pressure nozzle blade.
SOLUTION: A cooling gas turbine blade is provided with a casting part(10) and a vertical sleeve(30). The casting part contains a vertical body provided with a vertical cavity(10C) having a first and a second openings at both ends. The sleeve is mounted by being welded at a wall of the first opening, and its end(30I) freely slides the second opening(10G). The end and the slide of the blade slide and touch against a surface formed by processing. According to an enforcement form, a sealing insert(30S) is arranged between the end of the sleeve and the wall of the second opening, and the insert is integral with the sleeve. An assembly of the gas turbine blade reduces a leakage rate of cool air between the sleeve and the opening forming a slide.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：为了减少冷却叶片，特别是喷嘴刀片的滑块中的空气泄漏，更具体地说，是低压喷嘴刀片。解决方案：冷却燃气轮机叶片设置有铸造部件（10）和垂直套筒（30）。铸造部件包括垂直主体，其设置有在两端具有第一和第二开口的垂直腔（10C）。通过焊接在第一开口的壁上来安装套筒，并且其端部（30I）自由地滑动第二开口（10G）。刀片的末端和滑块滑动并且接触由加工形成的表面。根据执行形式，密封插入件（30S）布置在套筒的端部和第二开口的壁之间，并且插入件与套筒成一体。燃气轮机叶片的组件降低了套筒和形成滑块的开口之间的冷空气的泄漏率。版权所有（C）2005，JPO＆NCIPI

2. 发明专利

JP2004245224A Device for cooling turbine disk 有权
公开(公告)号：JP2004245224A
公开(公告)日：2004-09-02
申请号：JP2004036047
申请日：2004-02-13
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： IMBOURG SEBASTIEN , SOUPIZON JEAN-LUC , PABION PHILIPPE
IPC分类号： F02C1/00 , F01D5/08 , F01D11/02 , F02C7/18 , F16J15/447
CPC分类号： F01D5/082
摘要： PROBLEM TO BE SOLVED: To provide a turbine disk cooling device particularly conformed to the shape of a swan neck nozzle and reducing head loss while maintaining excellent airtightness.
SOLUTION: The cooling device for cooling the disks of high-pressure and low-pressure turbines of a turbomachine is fed with cooling air from at least one air orifice formed passing through a bottom annular platform for supporting at least one fixed vane of the low-pressure turbine. The cooling device is disposed between an upstream flange and a downstream flange of the bottom platform, and provided with an upstream annular plate and a downstream annular plate. The upstream plate and downstream plate are formed with at least one annular cavity for cooling air in the longitudinal direction, and provided with a sealing device for closing the cooling air cavity in an airtight state, a holding means for holding the upstream plate and downstream plate, and a plurality of holes for jetting the cooling air.
COPYRIGHT: (C)2004,JPO&NCIPI

3. 发明专利

JP2004245223A Annular platform for nozzle of low-pressure turbine in turbomachine 有权
公开(公告)号：JP2004245223A
公开(公告)日：2004-09-02
申请号：JP2004036046
申请日：2004-02-13
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： IMBOURG SEBASTIEN , SOUPIZON JEAN-LUC , PABION PHILIPPE , GUIMBARD JEAN-MICHEL
IPC分类号： F01D9/04 , F01D1/00 , F01D5/18 , F01D9/02 , F02C7/18
CPC分类号： F01D5/187 , F05D2240/10 , F05D2240/128 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： PROBLEM TO BE SOLVED: To propose a nozzle platform capable of lengthening an aerodynamic channel for gas flow without lowering the mechanical behavior and efficiency of a nozzle.
SOLUTION: The annular platform is for the nozzle of the low-pressure turbine in the turbomachine. The nozzle has a longitudinal axis and at least one fixed vane disposed downstream of at least one moving blade of a high-pressure turbine. The annular platform comprises a downstream portion supporting the fixed vane radially defining an aerodynamic channel extending longitudinally between a leading edge of the fixed vane and a trailing edge of the moving blade. The annular platform further comprises an upstream portion extending longitudinally beyond the leading edge of the fixed vane toward the trailing edge of the moving blade to lengthen the aerodynamic channel.
COPYRIGHT: (C)2004,JPO&NCIPI

4. 发明专利

JP2005291204A Turbine casing which has heat resistant hooking and which is obtained through powder metallurgy processing 有权
标题翻译：通过粉末冶金加工获得耐热性的涡轮机
公开(公告)号：JP2005291204A
公开(公告)日：2005-10-20
申请号：JP2005087761
申请日：2005-03-25
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： IMBOURG SEBASTIEN ALAIN , MONS CLAUDE MARCEL , PABION PHILIPPE JEAN PIERRE , SOUPIZON JEAN-LUC
IPC分类号： B22F3/15 , B22F3/24 , B22F5/00 , B22F7/06 , B22F7/08 , F01D9/00 , F01D9/04 , F01D25/14 , F01D25/24 , F02C7/00
CPC分类号： B22F7/062 , B22F3/15 , F01D9/04 , F01D25/246 , Y10T29/4932
摘要： PROBLEM TO BE SOLVED: To provide an improved turbine casing to be fitted to a jacket through assembly means characterized by a simple structure in which a fastener displays considerable mechanical strength and is substantially resistant to heating. SOLUTION: This invention is a turbine stator casing, which is equipped with a jacket as well as fastener hooks 3a and 3b, which are designed to tighten a turbine distributor nozzle in an arrangement to protrude from the inner side face of the jacket. The jacket is made from the 1 st alloy based on hot isostatic compression that employs metal powder 5, while fastener hooks 3a and 3b are made from the 2 nd alloy, which is more heat resistant than the 1 st alloy and fitted to the jacket through diffusion welding during the isostatic compression. The casing is also equipped with an insert 20, which passes through fastener hooks 3a and 3b, and pierces through the jacket. COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供一种改进的涡轮机壳体，其通过组装装置装配到护套上，其特征在于其中紧固件显示相当大的机械强度并且基本上耐受加热的简单结构。解决方案：本发明是一种涡轮机定子外壳，其配备有护套以及紧固件钩3a和3b，其被设计成将涡轮分配器喷嘴紧固在从外壳的内侧面突出的布置。基于使用金属粉末5的热等静压，由夹套1＆lt; SP＆gt; st＆lt; / SP＆gt;合金制成，而紧固件钩3a和3b由2＆lt; SP＆比1 st 合金更耐热，并且在等静压压缩下通过扩散焊接装配到护套上。外壳还配有插入件20，插入件20穿过紧固件钩3a和3b，穿过夹套。版权所有（C）2006，JPO＆NCIPI

5. 发明专利

JP2005121021A Device for attaching movable blade to turbine rotor disk in turbomachine 有权
标题翻译：将可动叶片连接到涡轮机中的涡轮转子盘上的装置
公开(公告)号：JP2005121021A
公开(公告)日：2005-05-12
申请号：JP2004299644
申请日：2004-10-14
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： RODRIGUES PAUL , SOUPIZON JEAN-LUC
IPC分类号： F01D5/14 , F01D5/30
CPC分类号： F01D5/3007 , F01D5/14 , F01D5/141 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To reduce defects of a turbomachine by using an attachment device which enables the axis of a blade to be correctly perpendicular to the axis of rotation of a rotor during operation of the turbomachine.
SOLUTION: An attachment device for attaching the blade 12 to a turbine rotor disk 11 in the turbomachine, the blade root 30 forming a male portion engaged and held radially in a cavity 31 of complementary shape in the rotor disk 11, with means for preventing the blade root 30 from moving axially in the cavity 31, the blade axis 24 being inclined relative to a perpendicular to the axis 10 of rotation of the rotor, in a direction and at an angle that are designed to compensate at least in part for the displacement of the axis 24 of the blade caused by the mechanical and thermal stresses applied to the rotor during operation of the turbomachine.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：通过使用在涡轮机操作期间使叶片的轴线能够正确地垂直于转子的旋转轴线的附接装置来减少涡轮机的缺陷。解决方案：用于将叶片12附接到涡轮机中的涡轮机转子盘11的附接装置，叶片根部30形成接合并径向保持在转子盘11中的互补形状的空腔31中的凸形部分，为了防止叶片根部30在空腔31中轴向移动，叶片轴线24相对于垂直于转子的旋转轴线10的倾斜方向和角度被设计成至少部分地补偿用于在涡轮机操作期间由施加到转子的机械和热应力引起的叶片的轴线24的位移。版权所有（C）2005，JPO＆NCIPI

6. 发明专利

JP2005299662A Main shaft protecting system for engine with fusible bearing 有权
标题翻译：带有可靠轴承的发动机主轴保护系统
公开(公告)号：JP2005299662A
公开(公告)日：2005-10-27
申请号：JP2005113188
申请日：2005-04-11
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： BOURGET SEBASTIEN , DAMBRINE BRUNO , MONS CLAUDE , SOUPIZON JEAN-LUC
IPC分类号： F01D5/02 , F01D21/04 , F01D25/16 , F02C7/00 , F02C7/06 , F04D29/053 , F04D29/04
CPC分类号： F01D21/045 , Y02T50/67 , Y02T50/672
摘要： PROBLEM TO BE SOLVED: To prevent a risk of rupturing a first shaft by more effectively protecting the shaft.
SOLUTION: A turbo machine comprises, at least, a first rotating assembly having a first shaft 12, a stator 2, and bearings 13 fixed to the stator and adequate for supporting the first shaft. One of the bearings 13 is breakable when unbalance occurs in the rotating assembly. A covering 32 is applied to at least one segment 30 of the shaft. The covering 32 has a fabric impregnated with at least one piece of a resin, and it contacts a peripheral portion 11 of the turbo machine when the unbalance occurs, to protect the first shaft 12 and surely prevent a risk of rupturing the first shaft. The turbo machine is mainly used in aircraft applications, more specifically, for an aircraft turbo jet engine.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：为了防止通过更有效地保护轴来破裂第一轴的风险。解决方案：涡轮机至少包括具有第一轴12，定子2和固定到定子并足以支撑第一轴的轴承13的第一旋转组件。当在旋转组件中发生不平衡时，其中一个轴承13是可断裂的。覆盖物32施加到轴的至少一个段30。覆盖物32具有浸渍有至少一片树脂的织物，并且当发生不平衡时，其接触涡轮机的周边部分11，以保护第一轴12并且确保防止第一轴断裂的风险。涡轮机主要用于飞机应用，更具体地，用于飞机涡轮喷气发动机。版权所有（C）2006，JPO＆NCIPI

7. 发明专利

JP2005299651A Device for balancing rotary part, particularly, turbo jet rotor 有权
标题翻译：涡轮零件，特别是涡轮喷气机的平衡装置
公开(公告)号：JP2005299651A
公开(公告)日：2005-10-27
申请号：JP2005105697
申请日：2005-04-01
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： CHARRIER EMMANUEL BERNARD MARI , PABION PHILIPPE JEAN PIERRE , SOUPIZON JEAN-LUC
IPC分类号： F01D5/10 , F01D5/02 , F02C7/00 , F04D29/66 , F16F15/32 , F16F15/34
CPC分类号： F01D5/027 , F16F15/34 , Y02T50/671
摘要： PROBLEM TO BE SOLVED: To reduce the weight of a means for fixing a balancing weight to a rotary disc of a turbine or a turbo machine.
SOLUTION: This device is provided for balancing a rotary part, particularly, a turbine rotor of the turbo machine such as a turbo jet. The device comprises at least one balancing weight having an engaging means for engaging the balancing weight with an annular flange of the rotary part and a lock means to be joined to the balancing weight and the annular flange. The balancing weight is prevented from moving relative to the annular flange, and the lock means itself is prevented from rotationally moving and axially translating relative to the balancing weight.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：为了减轻用于将平衡重物固定到涡轮机或涡轮机的旋转盘的装置的重量。解决方案：该装置用于平衡涡轮机的旋转部件，特别是涡轮机的涡轮转子，例如涡轮喷射。所述装置包括至少一个平衡重物，其具有用于使所述平衡重与所述旋转部分的环形凸缘相接合的接合装置和与所述平衡重和所述环形凸缘接合的锁定装置。防止平衡重相对于环形凸缘移动，并且防止锁定装置本身相对于平衡重量的旋转移动和轴向平移。版权所有（C）2006，JPO＆NCIPI

8. 发明专利

JP2004245222A Method for manufacturing turbo machine turbine including blade insert having resonance frequency differently adjusted and for adjusting resonance frequency thereof 有权
公开(公告)号：JP2004245222A
公开(公告)日：2004-09-02
申请号：JP2004035174
申请日：2004-02-12
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： BALLERON CHARLES , BION CLAUDE , GIRARD PATRICK JOSEPH MARIE , LESCURE XAVIER FIRMIN CAMILLE , LOPEZ JOSE , POPINET HENRI CLAUDE DANIEL , ROSSET PATRICE JEAN-MARC , ROSSI PATRICK , SOUPIZON JEAN-LUC , TOURBIER SANDRINE
IPC分类号： F02C1/00 , F01D5/16 , F01D5/22 , F01D5/26 , F01D5/30 , F02C7/00
CPC分类号： F01D5/16 , F01D5/225 , F01D5/26 , Y02T50/671 , Y02T50/673 , Y10S416/50 , Y10T29/49318 , Y10T29/4932
摘要： PROBLEM TO BE SOLVED: To provide a method for manufacturing a turbine for a turbo machine capable of preventing generation of undesired vibration. SOLUTION: A blade insert is used for the each moving wheel of the turbine. Each insert is provided with at least two blades. The blades are mutually connected to a common outer platform and a common inner platform and sharing a common root. The inserts are provided with hollow roots formed in a recessed shape. Different shapes are intentionally given for the roots of inserts belonging to a same wheel and/or the roots of inserts belonging to two different wheels so that resonance frequency of the inserts is adjusted to extremely different value, and thereby, it is ensured that the inserts in a same wheel and/or between two different wheels are out of tune. COPYRIGHT: (C)2004,JPO&NCIPI

9. 发明专利

JP2006017121A Drain tube for low-pressure shaft of turbomachine 有权
标题翻译：排水管用于低压涡轮机轴
公开(公告)号：JP2006017121A
公开(公告)日：2006-01-19
申请号：JP2005186169
申请日：2005-06-27
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： DAMBRINE BRUNO , HUGONIE AYMERIC , MONS CLAUDE , SOUPIZON JEAN-LUC
IPC分类号： F01D25/18 , F01D5/08 , F01D25/00 , F01D25/20 , F02C7/06
CPC分类号： F01D5/085 , F01D25/20 , F02C7/06
摘要： PROBLEM TO BE SOLVED: To provide a drain tube which makes it possible to omit an intermediate support, while possessing excellent oil tightness and deformation by bending.
SOLUTION: The invention provides the drain tube 18 which is mounted coaxially inside a low-pressure shaft 2 of a turbomachine. The drain tube comprises a hollow metal tubular portion of length substantially identical to that of the shaft inside which the drain tube is to be mounted. The outside surface of the metal tubular portion of the drain tube is covered over at least a fraction of its length in a composite material based on fibers 20 oriented along a direction that is substantially longitudinal so as to confer bending strength to the tube.
COPYRIGHT: (C)2006,JPO&NCIPI

10. 发明专利

JP2005299661A Main shaft blocking system for engine with fusible bearing 有权
标题翻译：带有可靠轴承的发动机主轴阻塞系统
公开(公告)号：JP2005299661A
公开(公告)日：2005-10-27
申请号：JP2005113187
申请日：2005-04-11
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： HUGONIE AYMERIC , MONS CLAUDE , SOUPIZON JEAN-LUC
IPC分类号： B64D27/16 , F01D21/04 , F01D21/06 , F01D25/04 , F02C7/00
CPC分类号： F01D21/045 , F01D21/06 , Y02T50/67 , Y02T50/672
摘要： PROBLEM TO BE SOLVED: To remove vibration resulting from the wind mill condition of a fan by using a system having effective and simple construction.
SOLUTION: A turbo machine comprises, at least, a first rotating assembly having a first shaft, a stator, and bearings fixed to the stator and adequate for supporting the first shaft. One of the bearings is breakable when unbalance occurs in the first rotating assembly. The turbo machine has a braking means for braking the first shaft when the unbalance occurs and a joint means to be operated for joining part of the first shaft to a peripheral portion of the turbo machine at final braking operation. The turbo machine is mainly used in aircraft applications, more specifically, for an aircraft turbo jet engine.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：通过使用具有有效和简单结构的系统来消除风扇风机的振动。解决方案：涡轮机至少包括具有第一轴，定子和固定到定子上并足以支撑第一轴的轴承的第一旋转组件。当在第一旋转组件中发生不平衡时，其中一个轴承是可断裂的。涡轮机具有用于在不平衡发生时制动第一轴的制动装置和用于在最终制动操作时将第一轴的一部分连接到涡轮机的周边部分的联接装置。涡轮机主要用于飞机应用，更具体地，用于飞机涡轮喷气发动机。版权所有（C）2006，JPO＆NCIPI

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