公开(公告)号：US4858430A

公开(公告)日：1989-08-22

申请号：US222555

申请日：1988-07-21

申请人： Lionel A. Belbouche

发明人： Lionel A. Belbouche

IPC分类号： F02K1/70

CPC分类号： F02K1/70

摘要： The present invention relates to an improved thrust reverseer door structure having a deflector that will reduce the aerodynamic losses and thereby increase the operating efficiency of a turbofan engine. The deflector has a first portion that extends generally radially inwardly when the door is in its retracted position and a second portion extending in a downstream direction from the distal edge of the first portion. The downstream facing second portion is located adjacent the inner surface of a secondary-duct wall and serves to deflect the air passing through this annular space away from an inner, concave portion of the thrust reverser door. The deflector may also include aperatures in the first portion to allow passage of the thrust reversing gases when the door is in its extended position. A baffle may also be attached to the first portion so as to extend at an angle over the aperatures.

摘要翻译： 本发明涉及一种具有偏转器的改进的推力倒车门结构，其将减小空气动力学损失，从而提高涡轮风扇发动机的运行效率。 偏转器具有当门处于其缩回位置时大致径向向内延伸的第一部分和从第一部分的远侧边缘沿下游方向延伸的第二部分。 下游侧的第二部分位于次级管道壁的内表面附近，并且用于使通过该环形空间的空气偏离推力反向器门的内部凹入部分。 偏转器还可以包括第一部分中的温度，以便当门处于其延伸位置时允许推力反向气体通过。 挡板也可以附接到第一部分，以便以一定的角度在温度上延伸。

公开(公告)号：US4844694A

公开(公告)日：1989-07-04

申请号：US127398

申请日：1987-12-02

申请人： Jacky Naudet

发明人： Jacky Naudet

IPC分类号： F01D5/06 ,  F01D5/08 ,  F16B35/04

CPC分类号： F01D5/066 ,  F16B35/041

摘要： The present invention relates to a fastening spindle and a method of attaching the rotor elements together utilizing the spindle. The system according to the invention reliably permits the visual inspection of the rotor assembly and to determine if it is properly tightened without the need for any additional post assembly inspection. The fastening spindle according to the invention has a central portion having a generally oblong cross-section with a first, major transverse dimension d.sub.1 which is greater than a second, minor transverse dimension d.sub.2 ; a first cylindrical portion which extends from the central portion in a first direction, the first cylindrical portion having a threaded distal end and a diameter d.sub.3 such the d.sub.3 is less than d.sub.2 ; and a second cylindrical portion extending from the central portion in a second direction, the second cylindrical portion having a threaded distal end and a diameter d.sub.4 such that d.sub.4 is less than d.sub.2. A transverse surface defined between one end of the central portion and the first cylindrical portion bears against one of the rotary elements to assure the proper axial positioning of the fastening spindle. The invention also comprises a system and a method for fastening a plurality of rotor elements together.

摘要翻译： 本发明涉及一种紧固主轴和使用该主轴将转子元件连接在一起的方法。 根据本发明的系统可靠地允许对转子组件的目视检查，并且确定其是否被适当地紧固，而不需要任何额外的后装配检查。 根据本发明的紧固心轴具有中心部分，该中心部分具有大致椭圆形的横截面，其具有大于第二较小横向尺寸d2的第一主要横向尺寸d1; 第一圆柱形部分，其从中心部分沿第一方向延伸，第一圆柱形部分具有螺纹远端，直径d3如d3小于d2; 以及从第二方向从中心部分延伸的第二圆柱形部分，第二圆柱形部分具有螺纹远端和直径d4，使得d4小于d2。 限定在中心部分的一端和第一圆柱形部分之间的横向表面承载着一个旋转元件，以确保紧固心轴的适当的轴向定位。 本发明还包括用于将多个转子元件紧固在一起的系统和方法。

公开(公告)号：US4778109A

公开(公告)日：1988-10-18

申请号：US133886

申请日：1987-12-16

申请人： Gerard E. A. Jourdain ,  Marc G. Loubet ,  Jean-Michel Payen

发明人： Gerard E. A. Jourdain ,  Marc G. Loubet ,  Jean-Michel Payen

IPC分类号： B64D33/04 ,  F02K1/00 ,  F02K1/11 ,  F02K1/12 ,  F02K1/62 ,  B63H11/10

CPC分类号： F02K1/006 ,  F02K1/1223 ,  F02K1/1292 ,  F02K1/62

摘要： An adjustable two-dimensional nozzle is disclosed in which simplified control means are located away from the flow of gasses through the nozzle. The nozzle includes a movable frame located outside of fixed sidewalls and has pivotally attached thereto a pair of upstream or converging nozzle flaps. Upstream edges of the upstream flaps are attached to the movable frame such that the flaps pivot about axes extending substantially perpendicular to the longitudinal axis of the nozzle. Downstream or diverging flaps are attached to the downstream edges of the upstream flaps such that these flaps also pivot about axes extending substantially perpendicular to the longitudinal axis of the nozzle. A cam member extends between each of the movable frames and each downstream flap to control the angular variations of the flaps during movement of the frame. The flap arrangements are symmetrically arranged with respect to a plane passing through the longitudinal axis of the nozzle, such that translational movement of the frames will alter the cross-section of the nozzle in a symmetrical manner with respect to the plane. If the frame is rotated about its pivot attachment, the nozzle flaps will be asymmetrically adjusted and may be utilized to vector the thrust of the gasses emanating from the nozzle.

摘要翻译： 公开了一种可调节的二维喷嘴，其中简化的控制装置位于远离气体流经喷嘴的位置。 喷嘴包括位于固定侧壁外侧的可移动框架，并且可旋转地附接有一对上游或会聚的喷嘴襟翼。 上游翼片的上游边缘附接到可移动框架，使得翼片围绕基本上垂直于喷嘴的纵向轴线延伸的轴线枢转。 下游或发散的翼片附接到上游翼片的下游边缘，使得这些翼片也围绕基本上垂直于喷嘴的纵向轴线延伸的轴线枢转。 凸轮构件在每个可移动框架和每个下游翼片之间延伸以在框架移动期间控制翼片的角度变化。 翼片装置相对于穿过喷嘴的纵向轴线的平面对称地布置，使得框架的平移运动将相对于平面以对称的方式改变喷嘴的横截面。 如果框架绕其枢轴附件旋转，则喷嘴挡板将被不对称地调节，并且可以用于对从喷嘴发出的气体的推力进行矢量化。

公开(公告)号：US4747263A

公开(公告)日：1988-05-31

申请号：US922932

申请日：1986-10-24

申请人： Pierre M. H. Gerard ,  Pierre M. Geyer ,  Christian A. F. Parisel

发明人： Pierre M. H. Gerard ,  Pierre M. Geyer ,  Christian A. F. Parisel

IPC分类号： F02C9/28 ,  F02C9/26 ,  F02C9/36 ,  F02C9/46

CPC分类号： F02C9/26

摘要： An electrical control system for a fuel circuit including a low pressure pump, a high pressure pump, a throttle valve and a pressurizing valve connected in series between a fuel reservoir and the fuel injectors of a gas turbine engine includes a first device including a first solenoid controlled valve capable of interruption of the connection between the outlet of the throttle valve and an inlet to a pressure drop detector which is normally connected across the throttle valve. The output of the pressure drop detector controls a control valve which can by-pass high pressure fuel output from the high pressure pump back to the pump inlet. The first device includes two, identical, parallel control channels each provided with its own independent power supply, a control first switch with two positions each leading to a respective processing circuit which has its output connected to one terminal of a respective solenoid winding of the bistable first solenoid controlled valve. In the "start" position of the first switch each channel independently causes operation of its respective first solenoid controlled valve to make the fuel circuit between the output of the throttle valve and the input of the pressure drop detector allowing fuel to be supplied to the start-up injectors and then the main injectors of the jet engine. In the "stop" position the signal is processed to operate the bistable valves to "break" the fuel circuit between the output of the supply regulator and the input to the pressure detector. This causes the by-pass valve to by-pass the fuel from the outlet to the inlet of the high pressure pump, cutting off the fuel supply to the injectors and stopping the engine. A second device acts directly in the by-pass valve to supply the fuel reservoir pressure instead of the outlet from the pressure drop detector to the control input of the by-pass valve so as to cause the by-pass valve to open so that fuel is recirculated from the high pressure pump to its input. This second device acts as a safety cut-off device in the event of failure of the first device.

公开(公告)号：US4742975A

公开(公告)日：1988-05-10

申请号：US60026

申请日：1987-06-09

申请人： Guy R. Pachomoff ,  Raymond M. L. Rolinat

发明人： Guy R. Pachomoff ,  Raymond M. L. Rolinat

IPC分类号： B64D27/26 ,  B64D27/12

CPC分类号： B64D27/26 ,  B64D2027/266

摘要： An engine mounting structure for a turbojet engine is disclosed which incorporates a safety rod in addition to the normal support rods used to attach a turbojet engine to a mounting structure. Under normal conditions, the safety rod is unstressed and supports none of the engine's weight. Upon rupture of one of the support rods, a tensile or compressive force exerted on the safety rod will move it into an active position so as to assume support of the engine's weight. A locking structure is also disclosed which will securely lock the rod in its active position such that it assumes the portion of the engine weight normally undertaken by the ruptured support rod.

摘要翻译： 公开了一种用于涡轮喷气发动机的发动机安装结构，其包括除了用于将涡轮喷气发动机附接到安装结构的普通支撑杆之外的安全杆。 在正常情况下，安全杆不受应力，并且不支持发动机的重量。 在一个支撑杆断裂时，施加在安全杆上的拉伸或压缩力将使其移动到主动位置，以承受发动机重量的支撑。 还公开了一种锁定结构，其可以将杆牢固地锁定在其主动位置，使得其承受通常由破裂的支撑杆承受的发动机重量的部分。

公开(公告)号：US20020006524A1

公开(公告)日：2002-01-17

申请号：US09729972

申请日：2000-12-06

申请人： SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION "SNECMA"

发明人： Yann Jaslier ,  Alexandre Alperine Serge ,  Louis Leger Jacques

IPC分类号： B32B015/04 ,  C25D005/50

CPC分类号： C23C28/321 ,  C23C28/3455 ,  C23C30/00 ,  C23F11/16 ,  C23F11/165 ,  Y10T428/12611 ,  Y10T428/12875 ,  Y10T428/12931

摘要： A method of improving the oxidation and corrosion resistance of a superalloy article comprises providing a superalloy substrate having a sulphur content which is less than 0.8 ppm by weight, and depositing on the substrate a protective antioxidation coating having a sulphur content also less than 0.8 ppm by weight. A heat barrier layer may also be provided by depositing on the protective anti-oxidation coating a ceramic coating of columnar structure.

摘要翻译： 提高超合金制品的耐氧化和耐腐蚀性的方法包括提供硫含量小于0.8重量ppm的超级合金基材，并且在基材上沉积具有小于0.8ppm硫含量的保护性抗氧化涂层 重量。 还可以通过在保护性抗氧化涂层上沉积柱状结构的陶瓷涂层来提供阻热层。

公开(公告)号：US06164563A

公开(公告)日：2000-12-26

申请号：US356321

申请日：1999-07-16

申请人： Philippe Pierre Vincent Bouiller ,  Pierre-Yves Bourquin ,  Fabrice Michel Olivier Cot ,  Daniel Kettler ,  Jean-Pierre Ruis

发明人： Philippe Pierre Vincent Bouiller ,  Pierre-Yves Bourquin ,  Fabrice Michel Olivier Cot ,  Daniel Kettler ,  Jean-Pierre Ruis

IPC分类号： F02K1/11 ,  F02K1/82 ,  B05B12/00

CPC分类号： F02K1/11 ,  F02K1/825 ,  F05D2250/323 ,  F05D2250/34

摘要： A gas-flow exhaust assembly for a jet propulsion system of an aircraft in which a converging exhaust nozzle (4) is fitted with translating cold flaps (21, 22). The primary exhaust nozzle (4) comprises two hot-flaps (5, 6) situated beyond a primary duct (1) enclosed by an aircraft fairing (2). The fairing (2) is extended by a secondary exhaust nozzle (20) which is supported by the primary duct (1) and which is translatable by a control mechanism (27a, 27b). The secondary exhaust nozzle (20) comprises cold flaps (21, 22) which are driven by another control mechanism (29a, 29b) independently of the angular positions of the hot flaps (5, 6). Preferably, there are two eyelid-shaped cold-flaps (21, 22) hinging and supported on horizontal transverse shafts (23a, 23b). The shafts (23a, 23b) are preferably affixed on two lateral slides (24a, 24b) which slide on the primary duct (1) and are displaceable by the control mechanism (27a, 27b) which translates the secondary exhaust nozzle (20).

摘要翻译： 一种用于飞行器的喷射推进系统的气体流动排气组件，其中会聚的排气喷嘴（4）装配有平移的冷襟翼（21,22）。 主排气喷嘴（4）包括位于由飞行器整流罩（2）包围的主管道（1）之外的两个热襟翼（5,6）。 整流罩（2）由辅助排气喷嘴（20）延伸，二次排气喷嘴（20）由主管道（1）支撑，并可由控制机构（27a，27b）平移。 二次排气喷嘴（20）包括与另一个控制机构（29a，29b）驱动的冷襟翼（21,22），独立于热襟翼（5,6）的角位置。 优选地，在水平横向轴（23a，23b）上铰接并支撑有两个眼睑形冷舌片（21,22）。 轴（23a，23b）优选地固定在两个横向滑动件（24a，24b）上，滑动件（24a，24b）在主导管（1）上滑动，并可通过使辅助排气喷嘴（20）平移的控制机构（27a，27b）移动。

公开(公告)号：US06135712A

公开(公告)日：2000-10-24

申请号：US227879

申请日：1999-01-11

申请人： Alain Louis Andre Chevrollier ,  Philippe Charles Alain Lebiez ,  Claude Marcel Mons ,  Pierre Etienne Mosser

发明人： Alain Louis Andre Chevrollier ,  Philippe Charles Alain Lebiez ,  Claude Marcel Mons ,  Pierre Etienne Mosser

IPC分类号： F02C7/36 ,  F01D21/04 ,  F16C3/00 ,  F16C17/20 ,  F16C17/24 ,  F01D25/00

CPC分类号： F01D21/045 ,  F16C17/20 ,  F16C17/24 ,  F05B2260/3011 ,  Y02T50/67 ,  Y02T50/671

摘要： A coating (22) with a high coefficient of friction and low thermal conductivity covers a turbomachine low pressure shaft (12) in the vicinity (17) of a concentric high pressure shaft (11), in the area at which high friction contact between the two shafts could occur if a bearing (13) on the low pressure shaft (12) breaks following a failure causing the appearance of an out-of-balance mass. Friction would also more quickly equalize shaft speeds and reduce overheating in them.

摘要翻译： 具有高摩擦系数和低热导率的涂层（22）覆盖同心高压轴（11）附近（17）处的涡轮机低压轴（12），在该区域内 如果低压轴（12）上的轴承（13）发生故障，导致出现不平衡质量，则可能会发生两个轴。 摩擦力也将更快地平衡轴速度并减少其中的过热。

公开(公告)号：US6129512A

公开(公告)日：2000-10-10

申请号：US252821

申请日：1999-02-19

申请人： Daniel Andre Agram ,  Anne-Cecile Christine Marlin

发明人： Daniel Andre Agram ,  Anne-Cecile Christine Marlin

IPC分类号： F01D9/04 ,  F01D17/16

CPC分类号： F01D17/162 ,  F04D29/563 ,  F05D2250/141

摘要： A rectifier vane stage is connected to a stator that is supported at the internal end thereof by a connecting ring which includes a support ring and a stiffening ring, a retaining lip of which is inserted into the support ring and similarly into the recesses of the ends of the vanes. The possibility of the vane accidentally coming loose following breakage of said vane is therefore eliminated.

摘要翻译： 整流器叶片级连接到定子，该定子在其内端由连接环支撑，该连接环包括支撑环和加强环，其保持唇被插入到支撑环中并且类似地插入到端部的凹部中 的叶片。 因此，消除了叶片在破坏叶片之后意外松动的可能性。

公开(公告)号：US06082669A

公开(公告)日：2000-07-04

申请号：US71157

申请日：1998-05-04

申请人： Thierry Pascal Bardagi ,  Gerard Ernest Andre Jourdain

发明人： Thierry Pascal Bardagi ,  Gerard Ernest Andre Jourdain

IPC分类号： F02C7/042 ,  F02K3/06 ,  B64B1/24

CPC分类号： F02C7/042

摘要： The system (13) for admitting external air (12) into a working section (11) of a gas turbine engine through a jacket (10) of the working section is characterised by the combination of doors (15) sliding towards the front (ramps) and rotating doors (14). The ramps (15) are fitted with grooved lateral arms (30) in which run wheels mounted on the doors (14). When they reach an ascending part (33) of the grooves (31) after sufficient movement of the ramps (15) towards the front, they are caused to rise, which opens the doors (14). This system can be used on double flow gas turbine engines for supersonic aircraft.

摘要翻译： 用于通过工作部分的护套（10）将外部空气（12）进入燃气涡轮发动机的工作部分（11）的系统（13）的特征在于门（15）朝向前部（斜坡） ）和旋转门（14）。 坡道（15）装有开槽的侧臂（30），其中安装在门（14）上的跑轮。 当坡道（15）向前方充分移动之后，当它们到达凹槽（31）的上升部分（33）时，它们被升高，这就打开门（14）。 该系统可用于超音速飞机的双流燃气涡轮发动机。