公开(公告)号：WO1996017156A1

公开(公告)日：1996-06-06

申请号：PCT/US1995012493

申请日：1995-09-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  MARTIN, Anthony, N.

IPC: F01D11/08

CPC classification number: F01D11/22 ,  Y02T50/672

Abstract: The blades and the outer case of an encased engine, such as a turbo engine or the like will expand and contract during periods of operation. Blade expansion and contraction can result from operating temperature changes, rotational velocity changes, or the like. The engine casing includes a segmented seal (10) which is properly spaced apart from the engine blade tips so as to provide optimum operation of the engine. Proximity sensors mounted on the engine detect the radial clearance of the engine blades to the seal segments at all times. The seal segments are mounted on a corrugated piezoelectric support (12) which is electrically stimulated so as to properly adjust the seal segments relative to the blade tips to provide the proper spacing as the blades and case expand and contract. Appropriate stimulation of the piezoelectric support will move the seal segments toward or away from the blade tips as needed.

Abstract translation: 诸如涡轮发动机等的封装发动机的叶片和外壳将在操作期间膨胀和收缩。 刀片膨胀和收缩可能是由于工作温度变化，转速变化等引起的。 发动机壳体包括与发动机叶片尖端适当间隔开的分段密封件（10），以便提供发动机的最佳操作。 安装在发动机上的接近传感器始终检测发动机叶片到密封段的径向间隙。 密封段安装在波纹状压电支座（12）上，该压电支架电动刺激，以便相对于叶片尖端适当地调节密封段，以在叶片和壳体膨胀和收缩时提供适当的间距。 压电支架的适当刺激将根据需要将密封段朝向或远离叶片尖端移动。

公开(公告)号：WO1996015940A1

公开(公告)日：1996-05-30

申请号：PCT/US1995014544

申请日：1995-11-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  DELMONTE, Berardino ,  BARONE, Ralph, P.

IPC: B64C25/58

CPC classification number: B64C25/60

Abstract: A shock strut assembly (10) for an aircraft landing gear includes a trunnion fitting (12), a compressible oleo strut subassembly (14), a wheel subassembly (16), an energy dissipating subassembly (50), and a mechanical fuze subassembly (60). The oleo strut subassembly (14) includes a cylinder member (24) having an upper end mounted in combination with the trunnion fitting (12) by means of the mechanical fuze subassembly (60). The energy dissipating subassembly (50) includes a cylindrical cutter member (52) secured in combination with the cylinder member (24) and the trunnion fitting (12) and a frangible tube member (58) mounted in concentric combination with the cylinder member (24). The mechanical fuze subassembly (60) includes a shear ring (62). During normal landings, the shear ring (62) prevents movement of the cylinder member (24) with respect to the trunion fitting (12) in a crash landing, the shear flanges (66) shear at a predetermined axial load failure limit, which allows the cylinder member (24) to be displaced relative to the trunnion fitting (12). Displacement of the cylinder member (24) causes the frangible tube member (58) to interact with the cutter member (58) to interact with the cutter member (52), causing fracturing of the frangible tube member (58) for crash landing energy dissipation.

Abstract translation: 用于飞机起落架的冲击支柱组件（10）包括耳轴接头（12），可压缩的油支柱子组件（14），轮子组件（16），消能子组件（50）和机械引信子组件 60）。 油支柱子组件（14）包括具有通过机械引燃子组件（60）与耳轴配件（12）组合安装的上端的圆筒构件（24）。 能量消散子组件（50）包括与圆筒构件（24）和耳轴配件（12）组合固定的圆柱形切割器构件（52）和与圆柱体构件（24）同心组合安装的易碎管构件（58） ）。 机械引信子组件（60）包括剪切环（62）。 在正常着陆期间，剪切环（62）防止气缸构件（24）在碰撞着陆中相对于弹簧配件（12）移动，剪切凸缘（66）在预定的轴向负载故障极限下剪切，这允许 所述气缸构件（24）相对于所述耳轴接头（12）移位。 气缸构件（24）的位移导致易碎管构件（58）与切割构件（58）相互作用以与切割构件（52）相互作用，从而导致易碎管构件（58）的破裂，用于碰撞着陆能量耗散 。

公开(公告)号：WO1996015029A2

公开(公告)日：1996-05-23

申请号：PCT/US1995013156

申请日：1995-10-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  SCHMALING, David, N. ,  BYRNES, Francis, E.

IPC: B64C27/00

CPC classification number: B64C27/51 ,  B64C27/35 ,  B64C27/605

Abstract: A pitch adjustment assembly (100) for a bearingless rotor assembly (20) which includes a torque tube member (36) enveloping a flexbeam connector (22). The pitch adjustment assembly (100) includes a centering bearing (70) for centering an inboard end (38) of the torque tube member (36) relative to the flexbeam connector (22), wherein the centering bearing (70) defines a torque tube pivot point (110) about which the torque tube member (36) is rotationally displaced relative to the flexbeam connector (22), a pitch control rod (48) mechanically connecting to a pitch control arm (46) for imparting pitch control inputs to the torque tube member (36); wherein the pitch control rod and arm (46, 48) define an input pivot point (116) and, a displacement mechanism (102 or 140), in combination with the centering bearing (70), for effecting translational displacement of the geometric center (120) of the torque tube member (36) relative to the torque tube and input pivot points (110, 116). Adjustment shims (102) or a jacking arrangement (140) is used to effect the translational displacement of the torque tube member (36).

Abstract translation: 一种用于无轴承转子组件（20）的桨距调节组件（100），其包括包围柔性梁连接器（22）的扭矩管构件（36）。 螺距调节组件（100）包括定心轴承（70），用于相对于挠性连接器（22）定心转矩管构件（36）的内侧端部（38），其中定心轴承（70）限定扭矩管 枢转点（110），扭矩管构件（36）相对于挠性束连接器（22）旋转地移位;螺距控制杆（48），机械地连接到俯仰控制臂（46），用于将俯仰控制输入 扭矩管构件（36）; 其中所述俯仰控制杆和臂（46,48）限定输入枢轴点（116）和与所述定心轴承（70）组合的位移机构（102或140），用于实现所述几何中心的平移位移 扭矩管构件（36）相对于扭矩管和输入枢转点（110,116）的距离。 使用调整垫片（102）或顶起装置（140）来实现扭矩管构件（36）的平移位移。

公开(公告)号：WO1996012991A1

公开(公告)日：1996-05-02

申请号：PCT/US1995013500

申请日：1995-10-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  VEILLEUX, Leo, J., Jr. ,  ANZULEWICZ, David, T. ,  DYER, Gerald, P.

IPC: G05B19/414

CPC classification number: F15B21/08 ,  G05B19/4144 ,  G05B2219/34238 ,  Y10T137/87201 ,  Y10T137/87209

Abstract: A hydraulic control system for a jet aircraft engine has an electronic control that commands a pair of torque motors to ultimately control the position of each one of a plurality of two-position, "latching" hydraulic actuator valves. A first torque motor is operable with a three-position, on/off hydraulic valve. The second torque motor operates in conjuction with a second valve to control the linear position of the spool of a multiplexer selector valve. The multiplexer selector valve has a plurality of positions that the spool can be linear translatable to. At each position is located a pair of control ports to which are ultimately connected one side of each of a pair of corresponding hydraulic actuator valves. The actuator valves may comprise fuel or air valves. A selected fuel or air actuator valve is translated between one of its two positions by translating the spool of the multiplexer selector valve to the appropriate position and then porting high pressure hydraulic fluid to that actuator valve for a predetermined period of time. The control system can asynchronously choose any fuel or air actuator valve to translate, as necessary, at any point in time.

Abstract translation: 用于喷气式飞机发动机的液压控制系统具有电子控制器，其命令一对扭矩电动机最终控制多个两位置“锁定”液压致动器阀中的每一个的位置。 第一扭矩电动机可与三位置的开/关液压阀一起操作。 第二扭矩电动机与第二阀结合操作以控制多路复用器选择阀的线轴的线性位置。 多路复用器选择阀具有多个位置，该线轴可以被直线地平移。 在每个位置处设置有一对控制端口，最终连接到一对相应的液压致动器阀的每一个的一侧。 致动器阀可以包括燃料或空气阀。 所选择的燃料或空气致动器阀通过将多路复用器选择阀的阀芯平移到合适的位置，然后将高压液压流体移动到该致动器阀门一段预定的时间段而在其两个位置中的一个之间平移。 控制系统可以根据需要在任何时间点异步地选择任何燃料或空气致动器阀门进行平移。

公开(公告)号：WO1996012881A1

公开(公告)日：1996-05-02

申请号：PCT/US1995011818

申请日：1995-09-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  DUESLER, Paul, W. ,  LOFREDO, Constantino, V. ,  PROSSER, Harold, T., Jr.

IPC: F02K01/09

CPC classification number: F02K1/09 ,  F02K1/72 ,  F02K3/06

Abstract: A gas turbine engine (10) includes a translating sleeve (38) disposed within a downstream portion of an outer nacelle (20). A variable area fan exhaust nozzle (30) is defined between the trailing edge (32) of the translating sleeve (38) and a conical core cowl (26) disposed radially inward of the outer nacelle (20) and spaced apart therefrom. The translating sleeve (38) translates downstream to cooperate with the decreasing diameter of the core cowl (26) to increase the area of the fan exhaust nozzle (30).

Abstract translation: 燃气涡轮发动机（10）包括设置在外部机舱（20）的下游部分内的平移套管（38）。 可变区域风扇排气喷嘴（30）被限定在平移套筒（38）​​的后缘（32）和设置在外部机舱（20）的径向内侧并与其间隔开的锥形芯罩（26）之间。 平移套筒（38）​​在下游平移以配合核心罩（26）的直径减小，以增加风扇排气喷嘴（30）的面积。

公开(公告)号：WO1996010839A1

公开(公告)日：1996-04-11

申请号：PCT/US1995011921

申请日：1995-09-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  JEROME, Rick, C. ,  POST, Ian, R., C.

IPC: H01L21/331

CPC classification number: H01L29/66272 ,  H01L21/2257 ,  H01L21/8228 ,  Y10S148/01 ,  Y10S148/011

Abstract: The present invention teaches a method for fabricating a bipolar junction transistor ("BJT") from a semiconductor substrate having a base region, wherein the BJT comprises an increased Early voltage. The method initially comprises the step of forming a patterned interlevel dielectric layer superjacent the substrate such that a segment of the substrate is exposed. Subsequently, a contact comprising a material having a grain size smaller than polycrystalline silicon is formed superjacent the patterned interlevel dielectric layer and the segment of the substrate exposed. The contact is then implanted with a dopant. Once implanted, the substrate is annealed to enable the dopant to diffuse from the contact into the base region impeded by the grain size to form an emitter region and thereby increase the Early voltage of the bipolar junction transistor.

Abstract translation: 本发明教导了一种从具有基极区域的半导体衬底制造双极结型晶体管（“BJT”）的方法，其中BJT包括增加的早期电压。 该方法最初包括以下步骤：在衬底之上形成图案化的层间电介质层，使得衬底的一部分被暴露。 随后，包含具有小于多晶硅的晶粒尺寸的材料的触点形成在图案化的层间电介质层的上方，并且衬底的部分被暴露。 然后用掺杂剂注入接触。 一旦被植入，衬底被退火以使掺杂剂从接触扩散到由晶粒尺寸阻挡的基极区域中，以形成发射极区域，从而增加双极结型晶体管的早期电压。

公开(公告)号：WO1996006776A1

公开(公告)日：1996-03-07

申请号：PCT/US1994009967

申请日：1994-08-31

Applicant: UNITED TECHNOLOGIES CORPORATION ,  REINFELDER, William, C. ,  JONES, Corey, D. ,  DEGNAN, William ,  KOVALSKY, David, A. ,  PURSE, Jeffry, C.

Inventor： UNITED TECHNOLOGIES CORPORATION

IPC: B64C27/473

CPC classification number: B64C27/473 ,  B29C70/446 ,  B29D99/0025 ,  B29L2031/082 ,  B64C2027/4736 ,  Y10T29/49336

Abstract: A composite spar for a helicopter rotor blade includes upper and lower sidewall regions (40, 42) and forward and aft conic regions (45, 47) wherein the conic regions further define transition and closure subregions (50, 52). Constant width crossplies (62) and unidirectional plies (72) are stacked and arranged to form crossply and unidirectional laminates (60, 70). The crossply laminates (60) form the upper and lower sidewall regions (40, 42) and end portions thereof extend into the forward and aft conic regions (45, 47) to form a staggered distribution of structural joints (68) and slip plane interfaces (66) therein. The crossply laminates are comprised of high modulus fibers which are oriented within a range of +/- 42 DEG to about +/- 38 DEG relative to the longitudinal axis (25) of the composite spar (10). The unidirectional laminates (70) form the upper and lower sidewall regions (40, 42) and have end portions (72e) extending into the transition subregions (50). The unidirectional laminates (70) are interposed between the crossply laminates (60) and comprised of a mix of high and low modulus fibers which are oriented substantially parallel to the longitudinal axis (25). Furthermore, plies of reinforcing fabric (80) having low modulus fibers oriented above about 80 DEG relative to the longitudinal axis (25) may be disposed between the unidirectional plies (72) of the unidirectional laminate (70). The composite spar is manufactured in molds.

Abstract translation: 用于直升机转子叶片的复合翼梁包括上侧壁区域和下侧壁区域（40,42）以及向前和向后的圆锥区域（45,47），其中圆锥区域进一步限定过渡和闭合子区域（50,52）。 恒定宽度交叉（62）和单向层（72）被堆叠并布置成形成横向和单向层压板（60,70）。 横向层压板（60）形成上侧壁区域（40）和下侧壁区域（42），并且其端部延伸到前后的锥形区域（45,47）中以形成结构接头（68）和滑动平面界面 （66）。 交叉层压板由相对于复合翼梁（10）的纵向轴线（25）定向在+/- 42°至约+38°范围内的高模量纤维组成。 单向层压板（70）形成上侧壁区域（40）和下侧壁区域（42），并且具有延伸到过渡区域（50）中的端部部分（72e）。 单向层压板（70）插入在交替层压板（60）之间，并且由基本上平行于纵向轴线（25）定向的高模量和低模量纤维的混合物组成。 此外，可以在单向层压体（70）的单向层（72）之间设置具有相对于纵向轴线（25）高于约80°的低模量纤维的增强织物（80）的层。 复合钢筋是用模具制造的。

公开(公告)号：WO1996002417A2

公开(公告)日：1996-02-01

申请号：PCT/US1995007935

申请日：1995-06-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  LEAHY, Kevin, Patrick ,  JONES, Corey, D.

IPC: B64C27/473

CPC classification number: B29D99/0028 ,  B29C70/446 ,  B29C70/78 ,  B29C70/86 ,  B29L2031/082 ,  B64C27/473 ,  B64C2027/4736 ,  Y10T29/37 ,  Y10T29/49332 ,  Y10T29/53026 ,  Y10T29/53539 ,  Y10T29/5397

Abstract: Apparatus and methods for fabricating a helicopter main rotor blade (100) include a compaction fixture (10) for assembling and compacting blade subassembly components and a sheath spreading/insertion apparatus (50) for spreading and inserting a leading-edge sheath (120) onto the blade subassembly during the compaction process. The compaction fixture includes a lower assembly (12) having a contoured upper airfoil nest (14) mounted in combination with a support structure and an upper assembly (30) having a pressure bag (32) affixed in sealed combination to a contoured backplate affixed in combination to a structural support truss (36). With the upper and lower assemblies in locked combination, the pressure bag is pressurized to compact the assembled blade subassembly components. The sheath spreading/insertion apparatus (50) includes a movable stanchion (52), upper (60U) and lower (60L) elongate carriage members mounted in synchronized movable combination with the stanchion, and a row of suction cups (66) mounted in combination with each carriage member. A vacuum source (68) is pneumatically interconnected to the suction cups (66) to generate suction forces to cause the leading-edge sheath to be spread apart. Movement of the movable stanchion causes the spread-apart leading-edge sheath to be inserted onto the blade subassembly during compaction thereof.

Abstract translation: 用于制造直升机主转子叶片（100）的装置和方法包括用于组装和压实叶片子组件部件的压实夹具（10）和用于将前缘护套（120）扩展和插入到其中的护套扩展/插入装置（50） 在压实过程中刀片子组件。 压实夹具包括下部组件（12），其具有与支撑结构组合安装的轮廓上部翼型套筒（14）和具有与密封组合固定到轮廓背板上的压力袋（32）的上部组件（30） 组合到结构支撑桁架（36）。 通过将上部和下部组件锁定组合，压力袋被加压以压缩组装的叶片子组件部件。 护套扩展/插入装置（50）包括可移动支柱（52），与支柱同步移动的组合安装的上部（60U）和下部（60L）细长的托架构件，以及一排安装在一起的吸盘（66） 与每个托架成员。 真空源（68）被气动地互连到吸盘（66）以产生吸力，以使前缘护套分开。 活动支柱的运动导致扩展的前缘护套在其压实期间插入到叶片子组件上。

公开(公告)号：WO1996002416A1

公开(公告)日：1996-02-01

申请号：PCT/US1995007813

申请日：1995-06-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  SUCIC, Steve ,  JONES, Corey, D.

IPC: B64C27/473

CPC classification number: B64C27/473 ,  B23Q35/102 ,  B64C2027/4736 ,  Y10T29/49332 ,  Y10T83/0341 ,  Y10T83/0363

Abstract: The described embodiment of an edge-of-part (EOP) scribe device (10) is operative to simultaneously scribe trim lines in an oversized, cured leading-edge sheath (120) mounted on a sheath mold assembly (160) so that the scribed, cured leading-edge sheath may be cut along the scribed trim lines to form a prefabricated leading-edge sheath having finished edges for a helicopter main rotor blade (100). Trim line templates (168) having profile edges (170) defining the profiles of the finished edges of the prefabricated leading-edge sheath are affixed to the sheath mold assembly. The EOP scribe device includes a primary carriage assembly (12) having V-groove rollers (14) secured thereto wherein the primary carriage assembly is translatable in a spanwise direction along side rails (166) secured to the sheath mold assembly, handles (16) for mounting and dismounting the EOP scribe (10) device in combination with the sheath mold assembly, opposed pairs of guide rails (18) affixed to the primary carriage assembly, and a secondary carriage assembly (20) mounted in movable combination with each pair of guide rails. Each secondary carriage assembly includes a spring-loaded scribe head (22) mounted in movable combination therewith, a positioning knob (24) secured in rigid combination with the scribe head and operative to allow the scribe head to be moved between a disengaged position for mounting/dismounting of the EOP scribe device and a scribe position for inscribing a trim line in the cured leading-edge sheath, a rigid follower linkage (26) secured to the secondary carriage assembly, and a follower slide roller (26) mounted in rotatable combination with the rigid follower linkage. The spring-loaded scribe head (22) includes a hardened scriber (30) for scribing the trim line and a tolerance roller (32) that interacts with the cured leading-edge sheath during the scribing operation to define the depth of the scribed trim line. With the EOP scribe device mounted in combination with the sheath mold assembly and the spring-loaded scribe heads in the scribe position, each follower slide roller interacts with the respective profiled edge (170). As the primary carriage assembly is subjected to spanwise translation along the sheath mold assembly, dimensional changes in the profiled edges induce vertical displacements in the follower slide rollers, the induced vertical displacements being coupled through the rigid follower linkages to cause corresponding vertical displacements in the secondary carriage assemblies and concomitantly, in the scribe heads. The vertical displacement of the hardened scribers matches the respective profiled edges such that the scribed trim lines correspond to the profiles of the finished edges of the prefabricated leading-edge sheath.

Abstract translation: 部分边缘（EOP）划线装置（10）的所描述的实施例可操作以在安装在护套模具组件（160）上的尺寸过大的固化前缘护套（120）中同时刻划修剪线，使得划线 可以沿着划线的修剪线切割固化的前缘护套，以形成具有用于直升机主转子叶片（100）的成品边缘的预制前缘护套。 具有限定预制前缘护套的成品边缘的轮廓的轮廓边缘（170）的修剪线模板（168）被固定到护套模具组件。 EOP划线装置包括具有固定到其上的V形槽辊（14）的主托架组件（12），其中主支架组件可沿着固定到护套模具组件的侧轨（166）在翼展方向上平移，手柄（16） 用于将EOP划片（10）装置与护套模具组件组合安装和拆卸，固定到主支架组件上的相对的导轨对（18）和与每一对可移动组合安装的辅助滑架组件（20） 导轨。 每个辅助托架组件包括安装成与其可移动组合的弹簧加载划线头（22），定位旋钮（24），其与划线头刚性组合固定并且可操作以允许划线头在分离位置之间移动以用于安装 EOP划片装置的拆卸和用于在固化的前缘护套中刻划修剪线的划线位置，固定到第二托架组件的刚性从动件联动装置（26）和安装成可旋转组合的从动滑动辊（26） 与刚性从动联动。 弹簧加载的划线头（22）包括用于划线修剪线的硬化划线机（30）和在划线操作期间与固化的前缘护套相互作用的公差辊（32），以限定划线的修剪线的深度 。 通过将EOP划片装置与护套模具组件和在划片位置上的弹簧加载划线头组合安装，每个从动滑动辊与相应的成形边缘（170）相互作用。 当主滑架组件沿着护套模具组件进行横向平移时，成型边缘中的尺寸变化引起从动滑动辊中的垂直位移，感应的垂直位移通过刚性从动联轴器联接，从而在次级 支架组件，伴随着，在划痕头。 硬化划线机的垂直位移与相应的成型边缘相匹配，使得划线的修剪线对应于预制的前缘护套的成品边缘的轮廓。

公开(公告)号：WO1996000841A1

公开(公告)日：1996-01-11

申请号：PCT/US1994007301

申请日：1994-06-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  SPEAR, David, Alan ,  BIEDERMAN, Bruce, Philip

IPC: F01D05/14

CPC classification number: F01D5/143 ,  F01D5/145 ,  F01D9/02 ,  F04D29/321 ,  F04D29/526 ,  F04D29/681 ,  Y02T50/673 ,  Y10S415/914

Abstract: An inner and/or outer cylindrical wall limiting the working fluid flow path of an axial compressor radially has an ondulating contour. At the intersection with the leading edge of an airfoil the wall shows a convex contour (54) followed by a concave contour (58) in the region of the airfoils maximum thickness while at the intersection with the trailing edge of the airfoil the contour (56) is convex again. The airfoil can either be a rotor blade or a stator vane.

Abstract translation: 径向限制轴向压缩机的工作流体流动路径的内部和/或外部圆柱形壁具有开口轮廓。 在与翼型的前缘相交处，壁在翼型最大厚度的区域中呈现凸形轮廓（54），随后是凹形轮廓（58），而在与翼型件的后缘相交处的轮廓（56 ）再次凸起。 翼型件可以是转子叶片或定子叶片。