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71. 发明申请

US20060226290A1 Vane assembly with metal trailing edge segment 有权
公开(公告)号：US20060226290A1
公开(公告)日：2006-10-12
申请号：US11101255
申请日：2005-04-07
申请人： Christian Campbell
发明人： Christian Campbell
IPC分类号： B64C3/00 , B64C21/04
CPC分类号： F01D5/147 , F01D5/146 , F05D2240/301 , F05D2240/57 , F05D2260/20 , F05D2260/221 , F05D2300/21 , F05D2300/603
摘要： Embodiments of the invention relate to a vane assembly formed by a forward airfoil segment and an aft airfoil segment. The aft segment is made of metal and can define the trailing edge of the vane assembly. The forward segment can be made of ceramic, CMC or metal. The forward and aft segments cannot be directly joined to each other because of differences in their rates of thermal expansion and contraction. The forward and aft segments can be positioned substantially proximate to each other so as to form a gap therebetween. In one embodiment, the gap can be substantially sealed by providing a coupling insert or leaf springs in the gap. A separate metal aft segment can take advantage of the beneficial thermal properties of the metal to improve cooling efficiency at the trailing edge without limiting the rest of the vane to being made out of metal.

72. 发明申请

US20050109011A1 De-icing device for turbojet inlet guide wheel vane, vane provided with such a de-icing device, and aircraft engine equipped with such vanes 有权
标题翻译：用于涡轮喷气进口导向轮叶片的除冰装置，具有这种除冰装置的叶片，以及配备有这种叶片的飞机发动机
公开(公告)号：US20050109011A1
公开(公告)日：2005-05-26
申请号：US10883699
申请日：2004-07-06
申请人： Yannick Courtot , Francois Marlin , Jean Danielo
发明人： Yannick Courtot , Francois Marlin , Jean Danielo
IPC分类号： F01D5/14 , F01D17/16 , F02C7/047 , F02G3/00
CPC分类号： F01D5/146 , F01D17/162 , F02C7/047 , Y02T50/672 , Y02T50/673
摘要： The de-icing device is intended for the vane (10) of the inlet guide wheel (4) of a turbojet (2), comprising a fixed part (12) arranged on the upstream side and a mobile flap (18) arranged on the downstream side, in which said fixed part (12) comprises a trailing edge (16) substantially in the shape of a “U”, with one of the branches (162) being located on the intrados side (I) and the other branch (164) being located on the extrados side (E). It comprises at least one emission window (202), oriented substantially along an upstream-downstream direction, and arranged along the branch (162) of the “U” located on the intrados side (I) of the trailing edge (16). The inlet guide wheel (4) vane (10) is equipped with at least such a de-icing device. The aircraft engine (2) comprises at least one vane (10) equipped with such a de-icing device.
摘要翻译：除冰装置用于涡轮喷气发动机（2）的入口引导轮（4）的叶片（10），包括设置在上游侧的固定部分（12）和布置在上游侧的活动挡板（18）下游侧，其中所述固定部分（12）包括基本上为“U”形的后缘（16），其中一个分支（162）位于内侧（I）和另一分支 164）位于引渡侧（E）上。它包括基本上沿着上游 - 下游方向定向并且沿着位于后缘（16）的内侧（I）的“U”的分支（162）布置的至少一个发射窗口（202）。入口导向轮（4）叶片（10）至少装有这样的除冰装置。飞机发动机（2）包括配备有这样的除冰装置的至少一个叶片（10）。

73. 发明申请

US20030033813A1 Cycle gas turbine engine 有权
标题翻译：循环燃气涡轮发动机
公开(公告)号：US20030033813A1
公开(公告)日：2003-02-20
申请号：US10206770
申请日：2002-07-29
发明人： Richard J. Flatman , Christopher Freeman
IPC分类号： F02C007/00
CPC分类号： F01D17/167 , F01D5/146 , F01D9/041 , F02C9/22 , Y02T50/673
摘要： A variable cycle gas turbine engine (10) includes first and second compressors (18,16), combustion apparatus (20) and first and second turbines (22,24) operable to drive the first and second compressors (18,16) respectively via interconnecting shafts. The capacity of one of the turbines (24) may be varied, for example by means of guide vanes (32) which can be adjusted to reduce or increase a throat area (40) through which air leaves the guide vanes to impact the turbine. The capacity of the turbine may be increased at low engine speeds, to reduce the pressure ratio across the turbine and across the compressor (16) which it drives, thereby improving the surge margin of the compressor.
摘要翻译：可变循环燃气涡轮发动机（10）包括第一和第二压缩机（18,16），燃烧装置（20）和第一和第二涡轮机（22,24），其可操作以分别驱动第一和第二压缩机（18,16），经由互连轴。涡轮机（24）中的一个的容量可以例如通过导向叶片（32）而变化，导向叶片（32）可以被调节以减小或增加喉部区域（40），空气离开导叶以冲击涡轮。涡轮机的容量可以在低发动机转速下增加，以减小跨越涡轮机和跨越其驱动的压缩机（16）的压力比，由此提高压缩机的喘振裕度。

74. 发明申请

US20020020168A1 Turbojet power plant with heat exchanger 失效
标题翻译：涡轮喷气发电厂带热交换器
公开(公告)号：US20020020168A1
公开(公告)日：2002-02-21
申请号：US09878913
申请日：2001-06-13
发明人： Alexander Boeck
IPC分类号： F02C007/12
CPC分类号： F02C7/08 , F01D5/146 , F01D5/18 , F01D9/065 , F28D21/0003 , F28D2021/0021 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： Turbojet powerplant with at least one compressor (1), at least one combustion chamber (2), a high-pressure turbine (3) and a low-pressure turbine (4), characterised in that a heat exchanger (5) is arranged between the compressor (1) and the combustion chamber (2), in that at least one hot-gas line (6) branches off from an area downstream of the high-pressure turbine (3) and is connected to the heat exchanger (5), and in that at least one cold-gas line (7) connects the heat exchanger (5) with an area upstream of the low-pressure turbine (4).
摘要翻译：具有至少一个压缩机（1），至少一个燃烧室（2），高压涡轮机（3）和低压涡轮机（4）的涡轮喷气发动机，其特征在于，热交换器（5）布置在压缩机（1）和燃烧室（2），其特征在于，至少一个热气管线（6）从高压涡轮机（3）的下游区域分支并连接到热交换器（5）并且至少一条冷气管线（7）将热交换器（5）与低压涡轮机（4）的上游区域连接。

75. 发明授权

US5236307A Variable geometry rotors for turbo machines 失效
标题翻译：涡轮机可变几何转子
公开(公告)号：US5236307A
公开(公告)日：1993-08-17
申请号：US912746
申请日：1992-07-13
申请人： Dik H. Ng , Robert G. Marshall
发明人： Dik H. Ng , Robert G. Marshall
IPC分类号： F01D5/14 , F04D27/02 , F04D29/32
CPC分类号： F04D27/0246 , F01D5/146 , F01D5/148 , F04D29/324 , Y02T50/673
摘要： There is provided a rotor arrangement comprising primary blades 16 mounted on a support disc 15 and secondary blades 18 mounted on a support disc 17. The secondary blades are disposed between respective primary blades with some axial overlap. The set of secondary blades is movable relative to the set of primary blades so that each secondary blade can be moved between end positions abutting the associated pair of primary blades.
摘要翻译：提供了一种转子装置，其包括安装在支撑盘15上的主叶片16和安装在支撑盘17上的副叶片18.次叶片设置在相应的主叶片之间，具有一些轴向重叠。所述次级叶片组可相对于一组主叶片移动，使得每个次叶片可以在邻接相关联的一对主叶片的端部位置之间移动。

76. 发明授权

US4652208A Actuating lever for variable stator vanes 失效
标题翻译：可变定子叶片的驱动杆
公开(公告)号：US4652208A
公开(公告)日：1987-03-24
申请号：US740619
申请日：1985-06-03
申请人： Robert P. Tameo
发明人： Robert P. Tameo
IPC分类号： F01D5/14 , F01D17/16 , F04D29/36
CPC分类号： F01D5/146 , F01D17/162 , F04D29/563 , Y10S416/50
摘要： According to the present invention, there is provided an actuating lever for effecting concurrent vane rotation in tandem rows of variable stator vanes in a gas turbine engine. The actuating lever is interconnected between and operates to activate one vane in each of two axially adjacent vane rows with one free end of the lever being rotatably attached to an actuation ring and the other free end being secured to one of the vane spindles. The second vane spindle is attached at an intermediate position of the lever, and a flexible link section of the lever is provided between the two spindles to accommodate differential movements in the lever experienced during movement of the actuation ring.
摘要翻译：根据本发明，提供了一种用于在燃气涡轮发动机中实现串联排列的可变定子叶片中的同时叶片旋转的致动杆。致动杠杆在两个轴向相邻的叶片排中的每一个中相互连接并起作用，以使一个杠杆的一个自由端可旋转地附接到致动环上，而另一个自由端固定在一个叶片主轴上。第二叶片主轴安装在杠杆的中间位置处，并且杠杆的柔性连接部分设置在两个主轴之间，以适应在致动环运动期间所经受的杆中的差动运动。

77. 发明授权

US3692425A Compressor for handling gases at velocities exceeding a sonic value 失效
标题翻译：用于处理超过声码的速度的压缩机
公开(公告)号：US3692425A
公开(公告)日：1972-09-19
申请号：US3692425D
申请日：1969-01-02
申请人： GEN ELECTRIC
发明人： ERWIN JOHN R
IPC分类号： F01D5/14 , F04D21/00 , F04D29/32 , F04D29/58 , F04D29/38
CPC分类号： F04D29/321 , F01D5/146 , F04D21/00 , F04D29/324 , F05D2240/302 , Y02T50/673 , Y10S415/914 , Y10S416/50
摘要： In the fan portion of a turbofan engine, rotor blades comprise a primary cambered airfoil and an auxiliary airfoil. Where air flow exceeds a sonic velocity relative to the blades, the throat section between adjacent blades positions the normal air shock wave on the auxiliary airfoil. Each auxiliary airfoil forms a nozzle in combination with the pressure surface of its adjacent primary airfoil. This minimizes energy losses normally associated with such normal shock waves riding on the suction surfaces of cambered airfoils in regions of relatively thick boundary layer air. Lateral struts projecting from the primary airfoil, and used to position the auxiliary airfoil, create oblique shock waves which weaken the normal shock wave and minimize energy losses associated with a normal shock wave''s effect of distributing boundary layer air on an airfoil surface. These features are also effective in reducing the generation of noise.
摘要翻译：在涡扇发动机的风扇部分中，转子叶片包括初级弧形翼型件和辅助翼型件。当空气流相对于叶片超过声速时，相邻叶片之间的喉部将正常的空气冲击波定位在辅助翼型上。每个辅助翼型件与其相邻的主翼面的压力表面组合形成喷嘴。这最大限度地减少了在相对厚的边界层空气的区域中骑乘在弧形翼型件的吸力表面上的正常冲击波通常相关联的能量损失。从主翼面突出并用于定位辅助翼型的横向支柱产生倾斜的冲击波，这削弱了正常的冲击波，并使与正常冲击波在翼型表面上分配边界层空气的效果相关联的能量损失最小化。这些功能也有效减少了噪音的产生。

78. 发明授权

US2938662A Turbo compressor 失效
标题翻译：涡轮压缩机
公开(公告)号：US2938662A
公开(公告)日：1960-05-31
申请号：US41663654
申请日：1954-03-16
申请人： DAIMLER BENZ AG
发明人： BRUNO ECKERT , HEINRICH KUHL
IPC分类号： F04D29/32 , F04D29/68
CPC分类号： F04D29/324 , F01D5/146 , F04D29/681 , Y10S415/914

79. 发明授权

US2935246A Shock wave compressors, especially for use in connection with continuous flow engines for aircraft 失效
标题翻译：冲击波压缩机，特别适用于飞机连续流量发动机
公开(公告)号：US2935246A
公开(公告)日：1960-05-03
申请号：US16541050
申请日：1950-06-01
申请人： ONERA (OFF NAT AEROSPATIALE)
发明人： MAURICE ROY
IPC分类号： F01D5/14 , F04D19/02 , F04D21/00 , F04D29/68
CPC分类号： F04D21/00 , F01D5/146 , F04D19/024 , F04D29/682 , F04D29/684 , F05D2240/302 , F05D2250/70 , Y02T50/673

80. 发明授权

US2699319A Power conversion machine 失效
标题翻译：电力转换机
公开(公告)号：US2699319A
公开(公告)日：1955-01-11
申请号：US13073249
申请日：1949-12-02
申请人： CHRYSLER CORP
发明人： HUEBNER JR GEORGE J , BORDEN DAVID M
IPC分类号： F01D5/14
CPC分类号： F01D5/146 , F01D5/142

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