公开(公告)号：WO1996011842A1

公开(公告)日：1996-04-25

申请号：PCT/US1995013382

申请日：1995-10-10

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: B64C27/35

CPC classification number: B64C27/35

Abstract: A mounting assembly (100) is provided for securing a helicopter snubber bearing (70) to a bearingless rotor assembly (10) which includes a flexbeam connector (22) mounted to a torque drive hub member (18). The mounting assembly (100) includes a retainer fixture (102) for mounting a retainer (104) which engages an inner bearing race portion (88) of the snubber bearing (70). The retainer fixture (102) is mounted to the flexbeam connector (22) and includes an inboard end portion (112), a restraint portion (114) extending radially outboard thereof, and a seat portion (116) disposed therebetween. The retainer (104) is disposed in register with, and is compliantly bonded to, the seat portion (116) of the retainer fixture (102), and furthermore abuts the restraint portion (114) which provides redundant retention therefor. Furthermore, the seat portion (116) of the retainer fixture (102) is reduced in width dimension to reduce flap and pitch induced shear stresses.

Abstract translation: 提供一种安装组件（100），用于将直升机缓冲支承件（70）固定到一个无轴承的转子组件（10）上，该转子组件包括一个安装在扭矩驱动轮毂部件（18）上的挠性连接器（22）。 安装组件（100）包括用于安装与缓冲轴承（70）的内部轴承座圈部分（88）接合的保持器（104）的保持器固定件（102）。 保持器固定件（102）安装到柔性连接器（22）上，并包括内侧端部（112），径向向外延伸的约束部分（114）和设置在其间的座部（116）。 保持器（104）设置成与保持器固定装置（102）的座部（116）对准并且顺从地结合到保持器固定装置（102）的座部（116）上，并且还邻接限制部分（114），其提供冗余保持。 此外，保持器固定件（102）的座部（116）的宽度尺寸减小，以减小翼片和俯仰引起的剪切应力。

公开(公告)号：WO1996011288A1

公开(公告)日：1996-04-18

申请号：PCT/US1995012771

申请日：1995-10-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  MULLIN, Richard, S. ,  ALLEN, William, P. ,  GELL, Maurice, L. ,  BARKALOW, Richard, H. ,  NOETZEL, Allan, A. ,  APPLEBY, John, W. ,  KHAN, Abdus, S.

IPC: C23C14/08

CPC classification number: C23C14/568 ,  B82Y30/00 ,  C23C14/081 ,  C23C14/083 ,  C23C28/04 ,  F01D5/288 ,  Y10T428/24975

Abstract: A thermal barrier coating for high temperature applications has improved resistance to heat flow. The coating comprises a large number of these (nanometer scale) layers separated by interfaces which are effective in retarding heat flow. The coating material will typically be oxide based ceramics and the coating has particular applications in gas turbine engines.

Abstract translation: 用于高温应用的热障涂层具有改善的耐热流动性。 该涂层包括大量这些（纳米级）层，其通过界面分离，这些界面有效地延缓热流。 涂层材料通常是基于氧化物的陶瓷，并且该涂层在燃气涡轮发动机中具有特别的应用。

公开(公告)号：WO1996010143A1

公开(公告)日：1996-04-04

申请号：PCT/US1995012148

申请日：1995-09-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  SNYDER, James, G. ,  GERNHARDT, Gregory, H.

IPC: F16J15/32

CPC classification number: F01D11/00 ,  F16J15/3288

Abstract: A brush seal assembly (42) includes a tab (84) extending outward and engageable with a brush retainer (64). Various construction details are disclosed that provide a tab (84) that prevents rotation of the brush seal during use and also prevents reverse installation of the brush seal assembly (42). In a particular embodiment, a brush seal assembly (42) for installation within a carrier (58) includes a tab (84) that fits radially within a cut-out (92) in a retaining means (64). Engagement with the cut-out (92) prevents rotation. The tab (84) extends outward from the low pressured side of the brush seal assembly (42). If installed in a reverse orientation, the tab (84) engages the carrier (58) to block installation of the retaining means (64).

Abstract translation: 刷密封组件（42）包括向外延伸并可与刷保持器（64）接合的突片（84）。 公开了各种构造细节，其提供在使用期间防止刷密封旋转的突片（84），并且还防止刷密封组件（42）的反向安装。 在一个具体实施例中，用于安装在承载件（58）内的刷密封组件（42）包括在保持装置（64）中径向配合在切口（92）内的突片（84）。 与切口（92）配合防止旋转。 突片（84）从刷密封组件（42）的低压侧向外延伸。 如果以相反方向安装，则突片（84）接合载体（58）以阻止固定装置（64）的安装。

公开(公告)号：WO1996007106A2

公开(公告)日：1996-03-07

申请号：PCT/US1995010968

申请日：1995-08-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  SLABINSKI, Robert, J. ,  FILIPKOWSKI, Richard, C.

IPC: G01P05/00

CPC classification number: G01P13/02 ,  G01P5/14

Abstract: Static pressure sensing and free airstream temperature sensing is obviated in a method for determining aircraft velocity relative to an airmass by utilizing a static pressure and temperature component present in pressure variations sensed by a total pressure sensor located on a rotating arm mounted on the fuselage of an aircraft. A harmonic analysis of a quasi-sinusoidal total pressure variation includes a determination of steady state and both first and second harmonic components. These harmonic components are used to determine the static pressure, the free airstream temperature and the aircraft airspeed without separately sensing these parameters.

Abstract translation: 在通过利用位于安装在机身上的旋转臂上的总压力传感器感测到的压力变化中存在的静态压力和温度分量来确定相对于空气质量的飞行器速度的方法中，静止压力感测和自由气流温度感测被消除 飞机。 准正弦总压力变化的谐波分析包括稳态和第一和第二谐波分量的确定。 这些谐波分量用于确定静态压力，自由气流温度和飞机空速，而无需分别感测这些参数。

公开(公告)号：WO1996006775A1

公开(公告)日：1996-03-07

申请号：PCT/US1995010070

申请日：1995-08-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  REINFELDER, William, C. ,  LEAHY, Kevin, P. ,  JONES, Corey, D. ,  KOVALSKY, David, A.

IPC: B64C27/00

CPC classification number: B64C27/008 ,  G01M1/12

Abstract: The rotor blades of a helicopter are balanced both in the chordal direction and in the spanwise direction in a static balancing assembly. The assembly includes a support surface (4) on which there are four weighing scales (8). The scales (8) are positioned in close proximity with the four corners of the rotor blade (2). The scales (8) provide four cooperating pairs of blade spanwise and chordwise balancing reference data. The scales (8) are operably connected to a microprocessor which is preprogrammed with desired balance data for the blades being tested. Deviations from the desired balance data detected by the scales and the microprocessor are corrected by selectively adding or subtracting weight on the blades at appropriate locations of the surfaces thereof.

Abstract translation: 直升机的转子叶片在静平衡组件中在弦方向和翼展方向上平衡。 组件包括支撑表面（4），其上有四个称重秤（8）。 秤（8）定位成紧邻转子叶片（2）的四个角。 标尺（8）提供了四个协作的叶片翼展和对平衡参考数据对。 秤（8）可操作地连接到微处理器，该微处理器对所测试的刀片的所需平衡数据进行预编程。 通过在其表面的适当位置选择性地增加或减少叶片上的重量来校正由秤和微处理器检测到的期望平衡数据的偏差。

公开(公告)号：WO1996006267A1

公开(公告)日：1996-02-29

申请号：PCT/US1995010474

申请日：1995-08-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  PETERS, Gary, P. ,  STIRT, Robert, Gerard, Johannus

IPC: F01D11/02

CPC classification number: F01D11/02 ,  F05D2250/00 ,  Y02T50/671

Abstract: A rotatable seal element (38) is formed of at least two circumferentially continuous rings (48, 50). The rings have decreased thickness (T2, T3) in the outward direction. Various construction details are developed which effect the level of cyclic fatigue life. In one particular embodiment, the seal element has a flat surface (74) extending inwardly from the sides at the interface between the rings.

Abstract translation: 可旋转的密封元件（38）由至少两个周向连续的环（48,50）形成。 这些环在向外的方向上具有减小的厚度（T2，T3）。 开发了影响循环疲劳寿命水平的各种结构细节。 在一个具体实施例中，密封元件具有从环之间的界面处的侧面向内延伸的平坦表面（74）。

公开(公告)号：WO1995034745A1

公开(公告)日：1995-12-21

申请号：PCT/US1995006582

申请日：1995-05-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  MAZZAWY, Robert, S.

IPC: F01D11/08

CPC classification number: F01D11/02 ,  F01D11/08 ,  F04D29/526 ,  F04D29/685

Abstract: A stator structure such as the fan casing (34) of a gas turbine engine extending circumferentially about an array of rotor blades is disclosed. Various construction details which increase the surge margin of the construction with a minimal impact on aerodynamic efficiency are developed. In one particular embodiment, the fan casing has a groove region (62) which extends radially outwardly of the mid-chord region (58) of the blades. The groove region has a plurality of circumferentially extending grooves (38) which are interrupted in a circumferential direction by a plurality of dams (42).

Abstract translation: 公开了一种定子结构，例如围绕转子叶片阵列周向延伸的燃气涡轮发动机的风扇壳体（34）。 开发了各种结构细节，其增加了对空气动力效率的最小影响的施工浪涌裕度。 在一个特定的实施例中，风扇壳体具有一个沿着叶片的中和弦区域（58）径向向外延伸的槽区域（62）。 槽区域具有多个周向延伸的槽（38），它们通过多个坝（42）在圆周方向上被间隔开。

公开(公告)号：WO1995030779A1

公开(公告)日：1995-11-16

申请号：PCT/US1995005429

申请日：1995-05-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  KHAN, Abdus, S. ,  FENTON, Richard, J. ,  MURPHY, Kenneth, S.

IPC: C22C19/05

CPC classification number: C23C10/50 ,  C22C19/057

Abstract: Higher oxidation resistance and high-temperature life result when from 0.01 to 0.30 weight percent of an additive selected from the group consisting of zirconium, yttrium, and mixtures thereof is present in a nickel-base superalloy substrate bearing a diffusion aluminide coating.

Abstract translation: 当在含有扩散铝化物涂层的镍基超级合金基材中存在0.01至0.30重量％的选自锆，钇及其混合物的添加剂时，具有更高的抗氧化性和高温寿命。

公开(公告)号：WO1995030575A1

公开(公告)日：1995-11-16

申请号：PCT/US1995005198

申请日：1995-04-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  MCGONIGLE, Kevin, P. ,  FERRARO, John ,  CYCON, James, P.

IPC: B64C39/02

CPC classification number: B64D47/08 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162

Abstract: An unmanned arerial vehicle (UAV) has a toroidal fuselage and a rotor assembly having a pair of counter-rotating rotors secured in fixed coaxial combination with the toroidal fuselage to provide a vertical takeoff and landing (VTOL) capability for the UAV. One embodiment of the VTOL UAV is especially configured for ground surveillance missions by the inclusion of an externally mounted, remotely controllable stowable sensor subsystem (250) that provides an azimuthal scanning capability and a predetermined elevation/depression scanning capability to accomplish the ground surveillance mission and a foldable landing gear subsystem (300) to facilitate landing of the VTOL UAV at unprepared ground surveillance sites. The foldable landing gear subsystem includes a plurality of legs (302), one end of each leg being detachably secured in combination with the toroidal fuselage, a foot that includes a pad member (312) pivotally attached to the other end of each leg, and a non-structural hinge secured to each leg and the toroidal fuselage. The non-structural hinges (306) provide the capability to fold the landing gear subsystem to a stowage configuration wherein each leg, pivoting foot combination is folded within the envelope of the toroidal fuselage.

Abstract translation: 无人驾驶的车辆（UAV）具有环形机身和转子组件，其具有与环形机身固定的固定同轴组合的一对反向旋转转子，以为无人机提供垂直起飞和着陆（VTOL）能力。 VTOL UAV的一个实施例被特别地配置用于地面监视任务，包括外部安装的远程可控的可收缩传感器子系统（250），其提供方位扫描能力和预定的仰角/凹陷扫描能力以完成地面监视任务， 一个可折叠的起落架子系统（300），以便于在未准备的地面监视场所使VTOL无人机的着陆。 可折叠起落架子系统包括多个腿部（302），每个腿部的一端可与环形机身组合地可拆卸地固定，脚部包括枢转地附接到每个腿部的另一端的衬垫构件（312），以及 固定在每个支腿和环形机身上的非结构铰链。 非结构铰链（306）提供将起落架子系统折叠到存储构造的能力，其中每个腿，枢转脚组合在环形机身的包络内折叠。

公开(公告)号：WO1995030115A1

公开(公告)日：1995-11-09

申请号：PCT/US1995003672

申请日：1995-03-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  BUTLER, Aaron ,  COMEAU, Roger, J. ,  DAVIS, Franklin, John ,  HARDERS, James, R. ,  MALITSKY, Thomas, J. ,  McKINNLEY, Randy ,  PFEIFFER, Gordon

IPC: F23R03/28

CPC classification number: F23R3/10 ,  F05B2260/20 ,  F23R3/283 ,  Y02T50/675

Abstract: An assembly of a bulkhead (48) and fuel nozzle guide (62) for a fuel nozzle (46) disposed in a combustion chamber (24) is disclosed. Various construction details which provide for convection cooling of the various components of the assembly are developed. In one detailed embodiment, the nozzle fuel guide (62) is spaced from the bulkhead (48) to form an annular gap (G1) which is divided by a heat shield (72) into annular orifices (108, 112) for supplying to cooling air passages (126, 128) bounded by the heat shield (72).

Abstract translation: 公开了一种用于设置在燃烧室（24）中的燃料喷嘴（46）的隔板（48）和燃料喷嘴引导件（62）的组件。 开发了提供组件的各种部件的对流冷却的各种构造细节。 在一个详细的实施例中，喷嘴燃料引导件（62）与隔板（48）间隔开以形成环形间隙（G1），该间隙由隔热罩（72）分成环形孔口（108,112） 由隔热罩（72）限定的空气通道（126,128）。