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    PRESSURE VESSEL FUEL NOZZLE SUPPORT FOR AN INDUSTRIAL GAS TURBINE ENGINE
    211.
    发明申请
    PRESSURE VESSEL FUEL NOZZLE SUPPORT FOR AN INDUSTRIAL GAS TURBINE ENGINE 审中-公开
    工业燃气涡轮发动机的压力容器燃油喷嘴支持

    公开(公告)号：WO1996000345A1

    公开(公告)日：1996-01-04

    申请号：PCT/US1995007497

    申请日：1995-06-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  BUTLER, Aaron, S. ,  MADDEN, Thomas, J. ,  SODERQUIST, Robert, W. ,  SULLIVAN, Dennis, J.

    IPC: F02C07/22

    CPC classification number: F02C7/222 ,  F23R3/283

    Abstract: A support structure for a low NOx industrial gas turbine engine fuel nozzle includes a pressure vessel (38) which forms an interior cavity (50) such that the exterior of the pressure vessel is exposed to the high pressure and temperature of the compressor outlet while the interior cavity of the pressure vessel is exposed to ambient conditions. The fuel lines (46, 44) to the nozzle run through the interior cavity of the pressure vessel, isolated from the high temperatures and pressures at the compressor outlet. The pressure vessel housing and the ambient air within the housing acts as natural insulators which prevent the fuel lines from becoming too hot and choking. The support structure (60) also facilitates maintenance of the combustor section of the engine since the low NOx fuel nozzle and the annular combustor assembly of the engine are easily accessible for maintenance.

    Abstract translation: 用于低NOx工业燃气涡轮发动机燃料喷嘴的支撑结构包括形成内部空腔（50）的压力容器（38），使得压力容器的外部暴露于压缩机出口的高压和高温 压力容器的内腔暴露于环境条件。 到喷嘴的燃料管线（46,44）穿过压力容器的内腔，与压缩机出口处的高温和压力隔离。 压力容器外壳和外壳内的环境空气充当天然绝缘体，可防止燃油管路变得过热和阻塞。 由于低NOx燃料喷嘴和发动机的环形燃烧器组件易于维护，因此支撑结构（60）还有助于维护发动机的燃烧器部分。

    SELF-SCAVENGING, HYBRID LUBRICATION SUBSYSTEM
    212.
    发明申请
    SELF-SCAVENGING, HYBRID LUBRICATION SUBSYSTEM 审中-公开
    自吸，混合润滑子系统

    公开(公告)号：WO1995035455A1

    公开(公告)日：1995-12-28

    申请号：PCT/US1995006396

    申请日：1995-05-30

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  KISH, Jules, G. ,  SAMMATARO, Stephen, R. ,  ISABELLE, Charles, J.

    IPC: F16H57/04

    CPC classification number: F16N7/40 ,  B64C27/12 ,  F16H57/0434 ,  F16N7/18 ,  F16N2210/08 ,  F16N2210/12 ,  Y10T74/19991

    Abstract: A self-scavenging, hybrid lubrication subsystem for a main transmission gearbox includes a sump that is fabricated as an integral structural extension of the gearbox so that the dynamic fluid level of the lubricating medium in the sump is a predetermined distance above the bottom (18) of the gearbox. The radial discontinuity between the cylindrical (22) and throat segments (26) in combination define a nozzle inlet (28) that is operative to direct outflow of the lubricating medium collected in the bottom of the gearbox to another sump with higher fluid level by means of a nozzle (60). The interaction between the peripheral surface of the rotating annular planetary carrier plate and the structurally-modified side wall of the gearbox exerts a viscous pumping action on the lubricating medium in the flow channels causing the lubricating medium to flow therethrough and being transported through the nozzle (60) to a higher level.

    Abstract translation: 用于主传动齿轮箱的自清除混合润滑子系统包括：油箱，其被制造为齿轮箱的整体结构延伸部，使得油底壳中的润滑介质的动态流体液位在底部（18）上方预定的距离， 的变速箱。 圆柱形（22）和喉部段（26）之间的径向不连续性组合限定了喷嘴入口（28），该喷嘴入口（28）可操作以将收集在齿轮箱底部的润滑介质直接通过装置 的喷嘴（60）。 旋转的环形行星架的外周表面与变速箱的结构改性侧壁之间的相互作用对流动通道中的润滑介质施加粘性泵送作用，导致润滑介质流过并通过喷嘴（ 60）到更高的水平。

    TURN COORDINATION INHIBIT FOR ROTARY WING AIRCRAFT CONTROL SYSTEM
    213.
    发明申请
    TURN COORDINATION INHIBIT FOR ROTARY WING AIRCRAFT CONTROL SYSTEM 审中-公开
    转动旋转飞行控制系统的协调禁止

    公开(公告)号：WO1995030181A1

    公开(公告)日：1995-11-09

    申请号：PCT/US1995004517

    申请日：1995-04-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  GOLD, Phillip, J. ,  FOGLER, Donald, L., Jr. ,  SKONIECZNY, Joseph ,  KELLER, James, F.

    IPC: G05D01/08

    CPC classification number: G05D1/0858

    Abstract: A turn coordination inhibit system (150) inhibits a rotary winged aircraft control system from operating in an automatic turn coordination mode when a pilot desired to perform a sideslip maneuver, e.g., a flat turn. When automatic turn coordination is not engaged (132, 212, 215), e.g., the aircraft is not in a coordinated turn, and either aircraft bank angle (119) exceeds an inhibit threshold magnitude (210) or a pilot yaw command provided by a pilot sidearm controller (155) exceeds a minimum threshold value (243), e.g., the sidearm controller is out of detent in the yaw axis, automatic turn coordination is inhibited (152). Automatic turn coordination remains inhibited until both aircraft bank angle falls below a reset threshold magnitude (230) and the sidearm controller is back in the detent position for the yaw axis (243).

    Abstract translation: 转向协调禁止系统（150）当驾驶员期望执行侧滑操纵（例如平转）时，禁止旋转飞行的飞行器控制系统以自动转向协调模式操作。 当没有进行自动转向协调（132,212,215）时，例如飞行器不是协调的转弯，并且飞机倾斜角（119）超过禁止阈值幅值（210）或由 导频侧臂控制器（155）超过最小阈值（243），例如，侧臂控制器在偏航轴中不止于锁定，自动转向协调被禁止（152）。 自动转向协调保持禁止，直到两个飞行器组角度低于复位阈值大小（230），并且侧臂控制器返回到用于偏航轴（243）的制动位置。

    BRUSH SEAL SUPPORT AND VANE ASSEMBLY WINDAGE COVER
    215.
    发明申请
    BRUSH SEAL SUPPORT AND VANE ASSEMBLY WINDAGE COVER 审中-公开
    BRUSH密封支架和帆布组合罩盖

    公开(公告)号：WO1995030071A1

    公开(公告)日：1995-11-09

    申请号：PCT/US1995004359

    申请日：1995-04-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  BUTLER, Aaron, S. ,  GERNHARDT, Gregory, H.

    IPC: F01D11/00

    CPC classification number: F01D11/001 ,  F05D2220/32 ,  F05D2240/56 ,  F16J15/3288

    Abstract: A seal support for a brush seal used between a turbine nozzle assembly and a rotor assembly includes a cover plate portion and a support arm. Various construction details are developed that provide a lightweight support for a brush seal and a windage cover. In a particular embodiment, the seal support includes a cover plate portion having circumferentially continuous surfaces to reduce windage losses and a support arm extending inward over a brush seal. In the installed condition, the seal support is positioned to engage the turbine nozzle assembly in an interference fit to dampen the seal support. In another particular embodiment, the support arm has scalloped corners that mate with corners of adjacent seal supports to define an opening. The opening is located to permit cooling fluid to flow through a metering hole and into a cavity to purge the cavity of gas path fluid.

    Abstract translation: 用于在涡轮喷嘴组件和转子组件之间使用的刷子密封件的密封支撑件包括盖板部分和支撑臂。 开发了各种构造细节，其为刷子密封件和风挡盖提供轻质的支撑。 在特定实施例中，密封支撑件包括具有周向连续表面以减少风阻损失的盖板部分和在刷子密封件的内部延伸的支撑臂。 在安装状态下，密封支撑件定位成以过盈配合接合涡轮喷嘴组件以阻尼密封支撑。 在另一个具体实施例中，支撑臂具有与相邻密封支撑件的角部配合以形成开口的扇形拐角。 开口位于允许冷却流体流过计量孔并进入空腔以吹扫气体通道流体的空腔。

    MACHINE FAILURE ISOLATION USING QUALITATIVE PHYSICS
    216.
    发明申请
    MACHINE FAILURE ISOLATION USING QUALITATIVE PHYSICS 审中-公开
    使用定性物理学的机器故障分离

    公开(公告)号：WO1995029443A2

    公开(公告)日：1995-11-02

    申请号：PCT/US1995004174

    申请日：1995-04-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  CLARK, Robert, T. ,  HAMILTON, Thomas, P. ,  GALLO, Steven

    IPC: G06F11/22

    CPC classification number: G06F11/2257 ,  G06F11/22

    Abstract: The presence of particular faults in a machine is determined (58) using constraint suspension and a Qualitative Physics model of the machine. Received machine signals can be propagated (69) through the model and the implicants of values assigned to variables can be determined and other variables can be restricted (187) according to the union of the implicants. The user can be prompted to perform a machine test procedure (72) that causes a machine configuration change. Test performance time can be a factor in choosing (286) the optimum test for the user to perform. The Qualitative Physics model (310) of the machine can be constructed using graphical user interface (302) allowing selection and interconnection of machine components (306) for the model such that the user can define a landmark domain to provide definitions of qualitative value spaces of variables of the model. Generic test templates can also be used in developing the model.

    Abstract translation: 使用约束暂停和机器的定性物理模型来确定机器中特定故障的存在（58）。 可以通过模型传播接收的机器信号（69），并且可以确定分配给变量的值的含义，并且可以根据牵连的联合来限制其他变量（187）。 可以提示用户执行导致机器配置更改的机器测试程序（72）。 测试性能时间可能是选择（286）用户执行最佳测试的一个因素。 可以使用图形用户界面（302）来构建机器的定性物理模型（310），允许用于模型的机器组件（306）的选择和互连，使得用户可以定义界标域以提供定性值空间的定义 模型的变量。 通用测试模板也可用于开发模型。

    COOLED GAS TURBINE BLADE
    217.
    发明申请
    COOLED GAS TURBINE BLADE 审中-公开
    冷却气体涡轮叶片

    公开(公告)号：WO1995028243A1

    公开(公告)日：1995-10-26

    申请号：PCT/US1995004451

    申请日：1995-04-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  STURM, Shimon

    IPC: B22C09/10

    CPC classification number: B22C9/10 ,  B23P15/04 ,  F01D5/187 ,  F05D2260/2212

    Abstract: A hollow air cooled airfoil blade (10) castable with a single pull core and having internal trip strips (28) at the leading edge. Parallel ribs (16, 18) extend from the pressure side (12) of the blade to the suction side (14). A parting line (32) passes through the most forward point (34) of the airfoil, this being located on the suction side of the leading edge (36).

    Abstract translation: 一种中空的空气冷却翼型叶片（10），其可以用单个牵引芯铸造并且在前缘具有内部跳闸条（28）。 平行的肋（16,18）从叶片的压力侧（12）延伸到吸力侧（14）。 分型线（32）穿过机翼的最前进点（34），其位于前缘（36​​）的吸力侧。

    HIGH BRIGHTNESS COLD BURST SOLID STATE LASER OPERATION
    218.
    发明申请
    HIGH BRIGHTNESS COLD BURST SOLID STATE LASER OPERATION 审中-公开
    高亮度冷弯固体激光器操作

    公开(公告)号：WO1995023446A1

    公开(公告)日：1995-08-31

    申请号：PCT/US1994011141

    申请日：1994-09-30

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  GAGOSZ, Ronald

    IPC: H01S03/092

    CPC classification number: H01S3/092

    Abstract: A solid state laser having an elliptical chamber (22), a solid state laser rod (10), a flashtube (12) for optically pumping the rod (10), external mirrors (24, 26) providing an optical cavity, the flashlamp (12) being energized by a pulse generator (14) which generates electrical pulses across the flashlamp (12), is provided with cold burst pumping of the flashlamp (12) by a burst (120) of a predetermined number of pulses, e.g., 40 pulses, each having a predetermined pulse width, e.g., .650 msec, and the burst lasting a predetermined length of time, e.g., 200 msec, not to exceed 1/16 to 1/12 of the thermal time constant of the solid state laser rod (10). Cold burst pumping provides a substantially constant thermal rod profile which reduces divergence of the output beam (36) and increases beam brightness, thereby improving the productivity and precision of solid state lasers.

    Abstract translation: 一种固态激光器，具有椭圆形腔（22），固态激光棒（10），用于光学泵浦杆（10）的闪光管（12），提供光学腔的外部反射镜（24,26），闪光灯 12）由脉冲发生器（14）激励，脉冲发生器（14）产生跨过闪光灯（12）的电脉冲，通过预定数量脉冲的脉冲串（120）向闪光灯（12）进行冷脉冲泵浦，例如40 脉冲，每个具有预定的脉冲宽度，例如.650毫秒，并且脉冲串持续预定时间长度，例如200毫秒，不超过固态激光器的热时间常数的1/16至1/12 杆（10）。 冷脉冲泵送提供基本恒定的热棒轮廓，其减小输出光束（36）的发散度并增加光束亮度，从而提高固态激光器的生产率和精度。

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