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81. 发明专利

JP2003148164A EXHAUST DEVICE IN DOUBLE FLOW TURBOJET ENGINE 审中-公开
公开(公告)号：JP2003148164A
公开(公告)日：2003-05-21
申请号：JP2002315790
申请日：2002-10-30
申请人： SNECMA MOTEURS
发明人： BEUTIN BRUNO , BRAULT MICHEL GILBERT ROLAND , GERVAIS PASCAL GERARD , THORE MONIQUE
IPC分类号： F02C7/04 , F01D9/06 , F01D17/10 , F02K3/075 , F04D29/54 , F04D29/56
摘要： PROBLEM TO BE SOLVED: To simplify an intermediate cowling. SOLUTION: This device includes an intermediate cowling 9 arranged in an axial direction between a low pressure compressor 5 and a high pressure compressor 7, and an exhaust means capable of deflecting one part of gas flow transferred from the low pressure compressor 5 to a second flow pipe 3 between a first flow pipe 2 and the second flow pipe 3. The intermediate cowling 9 has a plurality of support arms 13 with a platform defining the second flow pipe 3 from the inside in the periphery thereof. The exhaust means includes means 16, 19 for taking the air through the first flow pipe 2 arranged upstream of the intermediate cowling 9, and a means for exhausting the intake air to the second flow pipe downstream of the support arm. These means include a passage 28 arranged around the intermediate cowling 9 below a platform 12.

82. 发明专利

JP2003074304A Cooling circuit for gas turbine blade 有权
标题翻译：用于气体涡轮叶片的冷却电路
公开(公告)号：JP2003074304A
公开(公告)日：2003-03-12
申请号：JP2002241495
申请日：2002-08-22
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： ENEAU PATRICE , PICOT PHILIPPE
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2260/2212 , Y02T50/676
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine blade for aircraft engine in which a cooling circuit is improved. SOLUTION: At least a first center cooling circuit A is provided at a center part. The first cooling circuit comprises: first and second cavities 2, 4 extending in a radial direction to a recess side 1a of the blade 1; at least one cavity 6 extending to a projection side 1b of the blade; an intake opening 8 at one radial direction end of the first cavity 2 at the recess side for supplying a cooling air to the first center cooling circuit A; a first passage 10 for making the other radial direction end of the first cavity 2 at the recess side communicate with a radial direction end adjacent to the cavity 6 at the projection side; a second passage 12 for making the other radial direction end of the cavity at the projection side communicate with a radial direction end adjacent to the second cavity 4 at the recess side; and an outlet orifice opening to the second cavity at the recess side via a recess surface 1a of the blade.
摘要翻译：要解决的问题：提供一种用于飞机发动机的燃气轮机叶片，其中冷却回路得到改善。解决方案：至少第一中心冷却回路A设置在中心部分。第一冷却回路包括：沿半径方向延伸到叶片1的凹入侧1a的第一和第二空腔2,4; 至少一个延伸到叶片的突出侧1b的空腔6; 在第一空腔2的一个径向端部处的凹部侧的进气口8，用于向第一中心冷却回路A供给冷却空气; 用于使第一空腔2的另一个径向端在凹槽侧的第一通道10与在突出侧与空腔6相邻的径向端连通; 在凹部侧使空腔的另一个径向端部的第二通道12与凹部侧的与第二空腔4相邻的径向端部连通; 以及通过所述叶片的凹部表面1a在所述凹部侧通向所述第二腔的出口孔。

83. 发明专利

JP2003065155A Variable-cycle propulsion system having gas branching means for supersonic aircraft and operation method thereof 有权
标题翻译：具有用于超级飞机的气体分配装置的可变循环推进系统及其运行方法
公开(公告)号：JP2003065155A
公开(公告)日：2003-03-05
申请号：JP2002170960
申请日：2002-06-12
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： FRANCHET MICHEL , LAUGIER YANN , LOISY JEAN
IPC分类号： B64C30/00 , F02C3/10 , F02C7/36 , F02K1/12 , F02K3/02 , F02K3/075 , F02K3/12
CPC分类号： F02K3/075 , F02K3/025 , F02K3/12 , Y02T50/671
摘要： PROBLEM TO BE SOLVED: To provide a variable-cycle propulsion system for a supersonic aircraft with a subsonic construction and a supersonic construction that are fully separated. SOLUTION: This system includes a means for generating exhaust gas, at least one engine 1 having a gas exhaust nozzle, at least one separate auxiliary propulsion assembly 14 that is separated from the engine and has no gas generator and further gas flow branching means. The gas flow branching means branches at least a part of the exhaust gas generated by the engine, supplies the branched part of the exhaust gas to the propulsion assembly and is disposed movably between a position for enabling generation of thrust for take-off, landing and subsonic cruising flight and a position for sending gas generated by the engine 1 only to an engine nozzle for supersonic cruising freight.
摘要翻译：要解决的问题：为具有亚音速构造和完全分离的超音速构造的超音速飞机提供可变循环推进系统。解决方案：该系统包括用于产生废气的装置，至少一个具有排气喷嘴的发动机1，与发动机分离并且没有气体发生器和另外的气体流量分支装置的至少一个单独的辅助推进组件14。气流分支装置分支由发动机产生的废气的至少一部分，将排气的分支部分供给推进组件，并且可移动地设置在用于产生用于起飞和着陆的推力的位置和亚音速巡航飞行和将发动机1产生的气体仅发送到用于超音速巡航运输的发动机喷嘴的位置。

84. 发明专利

JP2003021334A Resilient mount for cmc combustion chamber of turbomachine in metal casing 有权
标题翻译：用于金属铸造中的涡轮机的CMC燃烧室的回收装置
公开(公告)号：JP2003021334A
公开(公告)日：2003-01-24
申请号：JP2002161063
申请日：2002-06-03
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： CAMY PIERRE , CARRERE BENOIT , CONETE ERIC , FORESTIER ALEXANDRE , HABAROU GEORGES , HERNANDEZ DIDIER
IPC分类号： F02C7/00 , F02C7/20 , F23R3/00 , F23R3/42 , F23R3/60
CPC分类号： F23R3/60 , F05B2230/606 , F23R3/007
摘要： PROBLEM TO BE SOLVED: To provide a resilient mount for absorbing displacement caused by different coefficients of expansion of parts in mounting a combustion chamber to a casing.
SOLUTION: The combustion chamber is held in position in an annular metal shell by a plurality of flexible metal tongues 58, 60. Each of the flexible metal tongues comprises three branches connected in a star configuration. The ends 62a, 62b; 64a, 64b of two of the three branches are securely fixed to a downstream end 68, 70 of the combustion chamber via respective first and second fixing means 72a, 74a and 72b, 74b, while the end 76, 78 of the third branch thereof is securely fixed to the annular metal shell 12, 14 by the third fixing means 80, 82.
COPYRIGHT: (C)2003,JPO
摘要翻译：要解决的问题：提供一种弹性安装座，用于在将燃烧室安装到壳体上时吸收由不同的部件膨胀系数引起的位移。解决方案：燃烧室通过多个柔性金属舌片58,60保持在环形金属壳体中的适当位置。每个柔性金属舌片包括以星形结构连接的三个分支。端部62a，62b; 三个分支中的两个分支的64a，64b经由相应的第一和第二固定装置72a，74a和72b，74b牢固地固定到燃烧室的下游端68,70，而其第三分支的端部76,78 通过第三固定装置80,82牢固地固定到环形金属壳12,14。

85. 发明专利

JP2003014234A Mounting of cmc combustion chamber in turbo machine using brazed tub 有权
标题翻译：使用BRAZED TUB在涡轮机中安装CMC燃烧室
公开(公告)号：JP2003014234A
公开(公告)日：2003-01-15
申请号：JP2002161064
申请日：2002-06-03
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： CALVEZ GWENAELLE , HERNANDEZ DIDIER , FORESTIER ALEXANDRE , CONETE ERIC
IPC分类号： F23R3/42 , F23R3/00 , F23R3/60
CPC分类号： F23R3/60 , F05B2230/606 , F23R3/007
摘要： PROBLEM TO BE SOLVED: To propose a mounting capable of absorbing a displacement caused by various expansion coefficients of parts when a combustion chamber is mounted in a casing.
SOLUTION: A combustion chamber is held at a predetermined position between inside and outside metallic annular shells with a plurality of flexible metal tabs 58, 60. First ends 62, 64 of the flexible metal tabs 58, 60 are coupled with each other by metal rings 66a, 66b securely anchored to respective annular shells 66a, 66b by first anchoring means 52, 66, and second ends 70, 72 are fixed to rings 78a, 78b of a composite material securely anchored to the foregoing composite material combustion chambers 26, 28 by second fixing means 74, 76. Flexibility of the metal tongued substance causes free radial expansion at high temperature between the composite material combustion chamber and the metallic annular shells.
COPYRIGHT: (C)2003,JPO
摘要翻译：要解决的问题：当燃烧室安装在壳体中时，提出能够吸收由各种膨胀系数引起的位移的安装。解决方案：燃烧室被保持在内外金属环形壳体之间的预定位置处，具有多个柔性金属片58,60。柔性金属片58,60的第一端62,64通过金属环彼此连接 66a，66b通过第一锚固装置52,66牢固地锚定到相应的环形壳体66a，66b，并且第二端部70,72被固定到复合材料的环78a，78b上，该复合材料通过固定在上述复合材料燃烧室26,28上的环78a，78b被第二固定装置74,76。金属舌物质的柔韧性在复合材料燃烧室和金属环形壳体之间导致高温下的自由径向膨胀。

86. 发明专利

JP2002364850A MOUNTING OF CMC(CERAMIC MATRIX COMPOSITE) COMBUSTION CHAMBER IN TURBO MACHINE USING DILUTION HOLE 有权
公开(公告)号：JP2002364850A
公开(公告)日：2002-12-18
申请号：JP2002158745
申请日：2002-05-31
申请人： SNECMA MOTEURS
发明人： HERNANDEZ DIDIER , CALVEZ GWENAELLE , FORESTIER ALEXANDRE
IPC分类号： F23R3/42 , F02C7/00 , F23R3/00 , F23R3/06 , F23R3/44 , F23R3/60
摘要： PROBLEM TO BE SOLVED: To provide a mounting capable of absorbing a displacement caused by an expansion coefficient of different parts upon mounting a combustion chamber inside a casing. SOLUTION: The combustion chamber is held with a plurality of flexible metal tongue-shaped members 58, 60 at a fixed position between inside and outside annular metal shells. The foregoing flexible metal tongue members 58, 60 have first ends 62, 64 connected by metal rings 66a, 66b fixed securely to inner and outer annular shells 12, 14 by first fixing means 52, 66 and second ends 70, 72 securely fixed to an air supply opening of a composite material combustion chamber by second fixing means 72, 74.

87. 发明专利

JP2002146555A METHOD FOR DEPOSITING ALUMINIDE COATING WITH REACTIVE- ELEMENT ADDED ON METALLIC SUBSTRATE 审中-公开
公开(公告)号：JP2002146555A
公开(公告)日：2002-05-22
申请号：JP2001256423
申请日：2001-08-27
申请人： SNECMA MOTEURS
发明人： JASLIER YANN , MARTINEZ ALAIN , NTSAMA ETOUNDI MARIE-CHRISTINE , OBERLAENDER GUILLAUME
IPC分类号： F01D5/28 , C23C10/02 , C23C10/52 , C23C24/08 , F02C7/00
摘要： PROBLEM TO BE SOLVED: To easily and economically deposit an aluminide coating with a reactive-element added on a metallic supporting body for improving the corrosive oxidation resistance of parts in the high temperature part such as a turbomet engine. SOLUTION: The oxide powder of a reactive-element such as zirconium and the powder of an aluminum alloy (generally, a chromium-aluminum alloy) are mixed, e.g. with a resin. This mixture is, e.g. applied on the surface of a metallic supporting body and is introduced into the surface of the metallic supporting body. After that, heating is performed to cause thermochemical reaction, so that the aluminide coating is deposited thereon.

88. 发明专利

JP2001012396A STATOR OF HIGH PRESSURE COMPRESSOR 失效
公开(公告)号：JP2001012396A
公开(公告)日：2001-01-16
申请号：JP2000154077
申请日：2000-05-25
申请人： SNECMA MOTEURS
发明人： GERVAIS PASCAL GERARD , LEJEUNE PASCAL MICHEL DANIEL , MIRAUCOURT CARMEN , NAUDET JACKY SERGE , SUET PATRICE , THORE MONIQUE ANDREE
IPC分类号： F04D29/02 , F01D11/18 , F04D29/54
摘要： PROBLEM TO BE SOLVED: To provide a stator suitable for the high pressure compressor of a gas turbine engine which can dissolve the problem caused by an ununiform ventilation. SOLUTION: A stator is provided with two ventilations 17, 18 with a different temperature. The upstream side section of the stator is constituted by a casing 10 and shroud 11, and it is recommended that these both have no notch over an entire periphery and are formed by a material with a low thermal expansion rate. But, at the downstream side, the shroud users plural arc shape sectors consisting of a material with high thermal expansion rate.

89. 发明专利

JP2000310159A ORIENTATIVE, AXISYMMETRICAL CONTRACTION-DIFFUSION EXHAUST NOZZLE 失效
公开(公告)号：JP2000310159A
公开(公告)日：2000-11-07
申请号：JP2000113009
申请日：2000-04-14
申请人： SNECMA MOTEURS
发明人： FEDER DIDIER GEORGES , LAPERGUE GUY JEAN-LOUIS , MONVILLE BERTRAND PIERRE RENAU , SALPERWYCK LAURENT CLAUDE P
IPC分类号： F02K1/78 , F02K1/00 , F02K1/12 , F02K1/15
摘要： PROBLEM TO BE SOLVED: To provide an orientative, axisymmetrical contraction-diffusion exhaust nozzle for an improved turbojet engine. SOLUTION: A contractive flap 3 is actuated by a control ring 7 moving in an axial direction, and a diffusive flap 15 is joined into a rotating ring 21, being toggle-jointedly fitted to a spherical portion 30 to be joined into a fixed structure 13, by a rod 20. In this modified embodiment form, the portion 30 is fitted to the structure 13 by slide joining, and is made non-rotative with the axis X of a turbojet engine as the center by a rotation preventive mechanism 33.

90. 发明专利

JP2000274309A AXISYMMETRICAL FULL ORIENTATION TYPE EXHAUST GAS NOZZLE OF TURBOJET ENGINE 失效
公开(公告)号：JP2000274309A
公开(公告)日：2000-10-03
申请号：JP2000064391
申请日：2000-03-09
申请人： SNECMA MOTEURS
发明人： BOUILLER PHILIPPE PIERRE V , CHARIER GILLES ALAIN M , JOURDAIN GERARD ERNEST ANDRE , KETTLER DANIEL GERMAIN ALEXIS , MANDET GERARD MARCEL FRANCOIS , PROUTEAU JACKIE RAYMOND JULIEN
IPC分类号： F02K1/78 , F02K1/00 , F02K1/06 , F02K1/12 , F02K1/15 , F02K1/30
摘要： PROBLEM TO BE SOLVED: To provide an axisymmetrical full orientation type exhaust gas nozzle of a turbojet engine in which the structure is simplified and the full body is made in a small size, by executing the orientation function and the cross section regulation function of a nozzle according to the flying condition, by a single control. SOLUTION: A single control ring operated by a jack 30 can control the cross section of a nozzle. A convergence flap 7 is guided by a spherical surface wall 5 at the upstream side, and supported by a control lever 13 at the downstream side. The control lever 13 is connected to the control ring, and supported by the outer surface 16 of the spherical surface wall 5 at the upstream side. A divergence flap 10 is connected to the convergence flap 7 and a low temperature flap 11, and the convergence flap and the low temperature flap are connected to the control ring by themselves. A synchronous device connects the upstream side end of the control lever 13 to the control rink, and aligns the nozzle and the control ring automatically.

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