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31. 发明申请

WO2014158283A1 A SUBSONIC SHOCK STRUT 审中-公开
标题翻译：一个SUBSONIC SHOCK STRUT
公开(公告)号：WO2014158283A1
公开(公告)日：2014-10-02
申请号：PCT/US2013/078403
申请日：2013-12-31
申请人： POWER, Bronwyn
发明人： POWER, Bronwyn
IPC分类号： F01D25/28 , F02C7/20 , F01D9/02 , F01D25/16
CPC分类号： F01D9/02 , F01D25/28 , F05D2240/124 , F05D2250/70 , F05D2250/713
摘要： A gas turbine engine strut is disclosed as having a will forebody positioned upstream of a point of maximum thickness and an aft body positioned downstream of the point of maximum thickness. The aft body includes a discontinuity in a curvature distribution which provides for a "subsonic shock." The discontinuity in curvature distribution can include in inflection point that marks a transition from a curvature associated with an upstream portion of the aft body to a second curvature associated with a downstream portion of the aft body. In some forms, the aft body can additionally include boundary layer aspiration. The gas turbine engine strut can be symmetrical about a centerline.
摘要翻译：公开了一种燃气涡轮发动机支柱，其具有将位于最大厚度点上游的预定位置和位于最大厚度点下游的后部主体。后身体包括提供“亚音速冲击”的曲率分布中的不连续性。曲率分布的不连续性可以包括标记从与后身的上游部分相关联的曲率到与后身的下游部分相关联的第二曲率的转变的拐点。在一些形式中，后身体还可以包括边界层抽吸。燃气涡轮发动机支柱可以关于中心线对称。

32. 发明申请

WO2014151673A1 AERODYNAMIC TRACK FAIRING FOR A GAS TURBINE ENGINE FAN NACELLE 审中-公开
标题翻译：气动涡轮发动机风扇的航空跟踪公路
公开(公告)号：WO2014151673A1
公开(公告)日：2014-09-25
申请号：PCT/US2014/026223
申请日：2014-03-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ZSURKA, Mark
IPC分类号： F02C7/04 , F02C7/20 , F02C9/16
CPC分类号： F02K1/70 , B64D29/00 , B64D29/02 , B64D29/06 , B64D33/04 , F01D5/141 , F01D5/143 , F01D9/02 , F01D25/24 , F05D2220/323 , F05D2240/10 , F05D2240/11 , F05D2240/14 , F05D2250/712 , F05D2260/602 , Y02T50/673
摘要： A gas turbine engine includes an aerodynamic track fairing adjacent to a convergent- divergent nozzle, the aerodynamic track fairing including a localized curvature along an outside edge. The aerodynamic track fairing is configured to offset a circumferential pressure gradient otherwise introduced in part by a transition between the convergent-divergent nozzle with the aerodynamic track fairing.
摘要翻译：燃气涡轮发动机包括邻近会聚发散喷嘴的空气动力轨道整流罩，空气动力轨道整流罩包括沿着外边缘的局部曲率。空气动力轨道整流罩被构造成抵消由收敛发散喷嘴与气动轨道整流罩之间的过渡部分地引入的圆周压力梯度。

33. 发明申请

WO2014105232A3 MODEL BASED ENGINE INLET CONDITION ESTIMATION 审中-公开
标题翻译：基于模型的发动机进气条件估计
公开(公告)号：WO2014105232A3
公开(公告)日：2014-09-18
申请号：PCT/US2013061640
申请日：2013-09-25
申请人： UNITED TECHNOLOGIES CORP
发明人： MEISNER RICHARD P , BRITTEN ALEXANDRA I , POTH STEFAN M , KARPMAN BORIS
IPC分类号： F02C9/00 , F01D25/00 , F02C7/20 , G01K13/00 , G01L11/00
CPC分类号： G01M15/14 , G05B23/0254 , G05B23/0297
摘要： A gas turbine engine inlet sensor fault detection and accommodation system comprises an engine model, an engine parameter comparison block, an inlet condition estimator, control laws, and a fault detection and accommodation system. The engine model produces a real-time model-based estimate of engine parameters. The engine parameter comparison block produces residuals indicating the difference between the real-time model-based estimate of engine parameters and sensed values of the engine parameters. The inlet condition estimator iteratively adjusts an estimate of inlet conditions based on the residuals. The control laws produce engine control parameters for control of gas turbine engine actuators based on the inlet conditions. The fault detection and accommodation system detects faults in inlet condition sensors, selects sensed inlet conditions for use by the control laws in the event of no fault, and selects estimated inlet conditions for use by the control laws in the event of inlet condition sensor fault.
摘要翻译：燃气涡轮发动机入口传感器故障检测和调节系统包括发动机模型，发动机参数比较块，入口状况估计器，控制法则以及故障检测和调节系统。发动机模型产生一个基于实时模型的发动机参数估计。发动机参数比较模块产生指示发动机参数的实时基于模型的估计与发动机参数的感测值之间的差异的残差。入口状况估计器基于残差迭代地调整入口状况的估计。控制律根据入口条件产生用于控制燃气涡轮发动机致动器的发动机控制参数。故障检测和调节系统检测入口状态传感器中的故障，选择在没有故障的情况下由控制法则使用的感测入口状态，并且选择在入口状态传感器故障时由控制法则使用的估计入口状况。

34. 发明申请

WO2014105224A3 ELECTRICAL GROUNDING FOR BLADE SHEATH 审中-公开
标题翻译：叶片电气接地
公开(公告)号：WO2014105224A3
公开(公告)日：2014-09-18
申请号：PCT/US2013057972
申请日：2013-09-04
申请人： UNITED TECHNOLOGIES CORP
发明人： MURDOCK JAMES R
IPC分类号： F01D5/14 , F02C7/20
CPC分类号： F01D5/28 , F04D29/324 , F05D2220/36 , F05D2240/30 , F05D2240/303 , F05D2300/121 , F05D2300/50 , Y02T50/671
摘要： A blade for use in a gas turbine engine has an airfoil including a leading edge and a trailing edge. A sheath is positioned at the leading edge and secured to the airfoil by a first adhesive formed of a first material. The sheath is formed of a second material that is distinct from said first material. The first material is less electrically conductive than the second material. A grounding element is in contact with the sheath. The grounding element is in contact with a portion of the airfoil formed of a third material that is more electrically conductive than the first material. The grounding element and the portion of the airfoil together form a ground path from the sheath into the airfoil.
摘要翻译：用于燃气涡轮发动机的叶片具有包括前缘和后缘的翼型件。护套定位在前缘，并通过由第一材料形成的第一粘合剂固定到翼型件上。护套由与第一材料不同的第二材料形成。第一材料比第二材料导电性差。接地元件与护套接触。接地元件与由比第一材料更导电的第三材料形成的翼型的一部分接触。接地元件和翼型件的一部分一起形成从护套到翼型件的接地路径。

35. 发明申请

WO2014133649A3 COMPONENT RETENTION WITH PROBE 审中-公开
公开(公告)号：WO2014133649A3
公开(公告)日：2014-09-04
申请号：PCT/US2013/075446
申请日：2013-12-16
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： CHUONG, Conway , BUDNICK, Matthew
IPC分类号： F02C7/20 , F01D25/00 , F01D25/28 , F01D9/04 , G01K13/00
摘要： A gas turbine engine includes a casing, a probe, and a fairing. The probe extends through the casing and the fairing is disposed within the casing. The fairing is engaged by the probe to prevent circumferential movement of the fairing relative to the casing.

36. 发明申请

WO2014105604A1 ANGLED CUT TO DIRECT RADIATIVE HEAT LOAD 审中-公开
标题翻译：直接切换到直接热负荷
公开(公告)号：WO2014105604A1
公开(公告)日：2014-07-03
申请号：PCT/US2013/076394
申请日：2013-12-19
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SCOTT, Jonathan, A. , CHUONG, Conway
IPC分类号： F02C7/20 , F01D25/24
CPC分类号： F01D25/14 , F01D9/065 , F01D25/24 , F01D25/243
摘要： A fairing (118) comprises an inner platform (122), an outer platform (120), a plurality of vane bodies (124), and a flange (126). The inner and outer rings define radially inner and outer boundaries of an airflow path. The vane bodies extend radially from the inner platform to the outer platform. The flange extends radially outward from the outer platform, and is defined by a frustoconical surface (S) extending radially inward and axially aft from a substantially radial upstream surface.
摘要翻译：整流罩（118）包括内平台（122），外平台（120），多个叶片体（124）和凸缘（126）。内环和外环限定了气流路径的径向内部和外部边界。叶片体从内平台径向延伸到外平台。凸缘从外平台径向向外延伸，并且由从基本上径向的上游表面径向向内和轴向延伸的截头圆锥形表面（S）限定。

37. 发明申请

WO2014100684A1 THERMALLY COMPLIANT DUAL WALL LINER FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：适用于燃气涡轮发动机的热合双壁炉
公开(公告)号：WO2014100684A1
公开(公告)日：2014-06-26
申请号：PCT/US2013/077130
申请日：2013-12-20
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： PETERS, Donald, W.
IPC分类号： F02K1/82 , F02K1/78 , F02C7/20 , F02C7/00
CPC分类号： F02C7/24 , F01D25/12 , F02K1/822 , F02K3/10 , F05D2220/80 , F05D2230/54 , F05D2230/642 , F05D2240/15 , F05D2250/12 , F05D2250/14 , F05D2250/313 , F05D2260/202 , F05D2300/501 , Y02T50/675
摘要： A stiffener for a liner assembly of a gas turbine engine includes a second resilient member arranged on a first resilient member at substantially ninety (90) degree orientation.
摘要翻译：用于燃气涡轮发动机的衬套组件的加强件包括以基本上九十（90）度取向布置在第一弹性构件上的第二弹性构件。

38. 发明申请

WO2014031198A3 VARIABLE BLADE OUTER AIR SEAL 审中-公开
标题翻译：可变叶片外部空气密封
公开(公告)号：WO2014031198A3
公开(公告)日：2014-05-08
申请号：PCT/US2013042447
申请日：2013-05-23
申请人： UNITED TECHNOLOGIES CORP
发明人： HARRIS MEGGAN
IPC分类号： F01D11/08 , F01D25/24 , F02C7/20
CPC分类号： F01D11/22 , F01D17/08 , F01D17/085 , F01D17/143 , F02C9/16 , F05D2240/11 , F05D2250/38 , F05D2260/57 , F05D2270/20 , F05D2270/301 , F05D2270/303 , F05D2270/44
摘要： A system for a turbofan has a variable outer air seal, an actuator coupled to the variable outer air seal, a sensor positioned inside the turbofan for sensing an engine parameter, and a flight controller connected to the turbofan for receiving the parameter from the sensor. The flight controller directs the actuator to regulate the position of the actuator based on the flight condition resulting form the received parameter.
摘要翻译：用于涡轮风扇的系统具有可变的外部空气密封件，与可变外部空气密封件耦合的致动器，定位在涡轮风扇内用于感测发动机参数的传感器以及连接到涡轮风扇用于接收来自传感器的参数的飞行控制器。飞行控制器根据从接收到的参数产生的飞行状况指示执行机构调节执行机构的位置。

39. 发明申请

WO2014052629A1 SUPPORT HANGER FOR FLEXIBLY CONNECTING A PLURALITY OF PANELS 审中-公开
标题翻译：支持灵活连接多面板的支持
公开(公告)号：WO2014052629A1
公开(公告)日：2014-04-03
申请号：PCT/US2013/061977
申请日：2013-09-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： MCALICE, Timothy J. , FIGUEROA, Carlos G.
IPC分类号： F02C7/20 , F02C7/00 , F02B77/00
CPC分类号： F01D25/24 , F01D25/14 , F01D25/28 , F01D25/30 , F02C7/20 , F02K1/822 , F05D2230/642 , F23R3/60 , Y02T50/675
摘要： A turbine engine case includes a first panel, a second panel and a support hanger. The second panel defines an aperture. The support hanger includes a strut that is connected to the first panel, and a base that is pivotally connected to the strut. The base includes a pivot member that is pivotally engaged with the second panel. The base extends away from the strut and through the aperture to the pivot member.
摘要翻译：涡轮发动机壳体包括第一面板，第二面板和支撑架。第二个面板定义一个光圈。支撑架包括连接到第一面板的支柱和枢轴连接到支柱的底座。底座包括与第二面板枢转接合的枢转构件。基座从支柱延伸并且穿过孔径延伸到枢转构件。

40. 发明申请

WO2014051658A1 SEAL ASSEMBLY FOR A STATIC STRUCTURE OF A GAS TURBINE ENGINE 审中-公开
标题翻译：用于气体涡轮发动机静态结构的密封组件
公开(公告)号：WO2014051658A1
公开(公告)日：2014-04-03
申请号：PCT/US2013/024071
申请日：2013-01-31
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SZYMANSKI, Grace E.
IPC分类号： F02C7/00 , F02C7/20 , F02C7/32
CPC分类号： F02C7/28 , F01D9/065 , F01D11/005 , F01D25/162 , F01D25/24 , F05D2240/58 , F05D2240/80 , F05D2260/36 , Y10T29/49826
摘要： A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an outer platform, an inner platform, an airfoil that extends between the outer platform and the inner platform, a service tube disposed at least partially through the airfoil, and a seal assembly that seals between the service tube and one of the outer platform and the inner platform.
摘要翻译：根据本公开的示例性方面的燃气涡轮发动机的静态结构包括外平台，内平台，在外平台和内平台之间延伸的翼型件，至少设置的工作管部分地通过翼型件，以及密封组件，其密封在服务管与外部平台和内部平台中的一个之间。

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