公开(公告)号：WO1997023301A1

公开(公告)日：1997-07-03

申请号：PCT/US1996020130

申请日：1996-12-23

Applicant: UNITED TECHNOLOGIES CORPORATION ,  AEROSTAR COATINGS, S.L. ,  CHERNYSHOV, Alexandr Vladimirovich ,  BARYKIN, Gregory Yur'evich ,  KITSCHUK, Alexandr

Inventor： UNITED TECHNOLOGIES CORPORATION ,  AEROSTAR COATINGS, S.L.

IPC: B05B07/20

CPC classification number: B05B7/0006 ,  C23C4/126

Abstract: An energy bleed apparatus and method for a detonation gun (2) apparatus utilizing bleed to remove reflected energy from interfering with the detonation wave front (100). The energy bleed system is positioned in the downstream portion of the combustion chamber (12) of a detonation gun. The bleed apertures of the present invention extract energy from the combustion chamber (12) that would otherwise be reflected off the combustion chamber walls and collide with the detonation wave front. The bleeding off of this energy allows the detonation wave front to progress into a barrel (13) of a detonation relatively undisturbed and permits a maximum amount of energy to be transferred directly to the coating powder. The increase in energy available to be transferred from the detonation wave front (100) to the coating powder translates into better quality coatings and an associated increase in productivity of the overall coating process.

Abstract translation: 一种用于爆震枪（2）的能量泄放装置和方法，所述装置利用渗流以消除反射能量与所述爆震波前（100）的干扰。 能量泄放系统位于爆震枪的燃烧室（12）的下游部分。 本发明的排放孔口从燃烧室（12）提取能量，否则其将从燃烧室壁反射并与爆震波前面相撞。 这种能量的渗出允许爆炸波前沿相对不受干扰地进入爆炸的枪管（13），并允许最大量的能量直接转移到涂层粉末。 可从爆炸波前（100）转移到涂层粉末的能量的增加转化为更好质量的涂层和相关的整个涂覆过程的生产率的增加。

公开(公告)号：WO1997023299A1

公开(公告)日：1997-07-03

申请号：PCT/US1996020152

申请日：1996-12-23

Applicant: UNITED TECHNOLOGIES CORPORATION ,  AEROSTAR COATINGS, S.L. ,  CHERNYSHOV, Alexandr Vladimirovich

Inventor： UNITED TECHNOLOGIES CORPORATION ,  AEROSTAR COATINGS, S.L.

IPC: B05B07/00

CPC classification number: B05B7/0006

Abstract: A gas detonation apparatus and method for powder coating a workpiece. The present invention lies in the ability to preselect a discrete number of detonation cells and the judicious selection of a suitable barrel diameter. The present invention employs an energy bleed system positioned in the downstream end of a combustion chamber of a detonation gun to bleed off unwanted energy from the combustion chamber (12) leaving behind a discrete number of detonation cells. The detonation cells are then discharged into the barrel (13) of the detonation gun (2). The barrel (13) diameter is selected to match the total area of the discrete detonation cells selected. The effect is to discharge a discrete number of detonation cells into the barrel (13) to preclude energy loss to the detonation cells from interference with reflected energy within the barrel itself. The present invention substantially increases the productivity of the detonation coating process.

Abstract translation: 一种用于粉末涂覆工件的气体爆炸装置和方法。 本发明在于能够预先选择离散数量的引爆单元和明智地选择合适的筒直径。 本发明采用位于爆震枪的燃烧室的下游端的能量泄放系统，以从燃烧室（12）排出不需要的能量，留下离散数量的爆炸电池。 然后将引爆单元排放到爆震枪（2）的枪管（13）中。 选择桶（13）直径以匹配所选择的离散爆炸电池的总面积。 效果是将离散数量的引爆单元排放到筒体（13）中，以防止爆震单元的能量损失不受筒体本身内的反射能量的干扰。 本发明显着提高了爆轰涂覆工艺的生产率。

公开(公告)号：WO1997019325A1

公开(公告)日：1997-05-29

申请号：PCT/US1996018770

申请日：1996-11-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  DUNPHY, James, R. ,  RUKUS, Robert, M. ,  HA, Jong-Min

IPC: G01D05/353

CPC classification number: G01M11/086 ,  B29C35/0288 ,  B29C70/54 ,  B29K2105/108 ,  G01B11/18 ,  G01C19/56 ,  G01D5/35316 ,  G01H11/06 ,  G01N33/44 ,  G01P15/125

Abstract: Resin curing of a composite laminated structure is monitored using an optical fiber (20) having a grating sensor (28) embedded therein. The fiber (20) is surrounded by upper and lower buffer regions (12, 14) having a predetermined minimum number of layers (30) (or thickness) with uni-directional reinforcing filaments (32) and resin (34) therebetween. When the filaments (32) are oriented perpendicular to the longitudinal axis of the fiber (20), the buffer regions (12, 14) allow the sensor (28) to exhibit maximum sensitivity to detection of the minimum resin viscosity and the gelation point (i.e., the onset of a rapid cross-linking rate) of the resin (34). The buffer regions (12, 14) also have a minimum thickness which serves to isolate the sensor (28) from interfering stresses from arbitrarily angled filaments (32) in layers (30) of outer regions (10, 16) which surround the buffer regions (12, 14).

Abstract translation: 使用其中嵌入有光栅传感器（28）的光纤（20）监测复合层压结构的树脂固化。 纤维（20）由具有单向增强细丝（32）和树脂（34）的预定最小数量的层（30）（或厚度）的上缓冲区域和下缓冲区域（12,14）包围。 当长丝（32）垂直于纤维（20）的纵向轴线定向时，缓冲区域（12,14）允许传感器（28）对检测最小树脂粘度和凝胶化点（ 即快速交联速率的开始）的树脂（34）。 缓冲区域（12,14）也具有最小厚度，其用于将传感器（28）与包围缓冲区域（10,16）的层（30）中的任意成角度的细丝（32）的干扰应力隔离开， （12,14）。

公开(公告)号：WO1997002732A3

公开(公告)日：1997-01-30

申请号：PCT/US1996010670

申请日：1996-06-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  COLBY, Roy, S. ,  PIECH, Zbigniew

IPC: F16C30/06

公开(公告)号：WO1996034207A1

公开(公告)日：1996-10-31

申请号：PCT/US1996005309

申请日：1996-04-17

Applicant: UNITED TECHNOLOGIES CORPORATION ,  GERTZ, Jeffrey, B. ,  SHARMA, Om, Parkash ,  EVEKER, Kevin, M. ,  NETT, Carl, N. ,  GYSLING, Daniel, L. ,  FEULNER, Matthew, R.

Inventor： UNITED TECHNOLOGIES CORPORATION

IPC: F04D27/02

CPC classification number: F04D27/001 ,  F04D27/0223

Abstract: A pressure sensor (12) is located in the compressor stage of a gas turbine engine (10) to provide a pressure signal (PR1) that shows the compressor flow characteristics. The pressure signal (PR1) is applied to a bandpass filter (16) with roll-offs above and below N2. The difference between the filter output and a stored value for the pressure signal is integrated, and compressor bleed valves (18) are opened if the integral exceeds a stored threshold. The health of a compressor stage is determined by analyzing the magnitude of compressor pressure variations at N2 while accelerating the engine and by comparing the magnitude with values obtained from a compressor with a known stall margin.

Abstract translation: 压力传感器（12）位于燃气涡轮发动机（10）的压缩机级中，以提供示出压缩机流量特性的压力信号（PR1）。 压力信号（PR1）被施加到带通滤波器（16）上，在N2之上和之下滚降。 过滤器输出与压力信号的存储值之间的差异被集成，如果积分超过存储的阈值，压缩机排放阀（18）将被打开。 通过在加速发动机的同时分析N2处的压缩机压力变化的大小并通过将具有已知失速余量的压缩机的值与该值进行比较来确定压缩机级的健康。

公开(公告)号：WO1996034181A1

公开(公告)日：1996-10-31

申请号：PCT/US1996005889

申请日：1996-04-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  CARTER, David, B. ,  WEISSE, Michael, A.

IPC: F01D05/14

CPC classification number: F01D5/147 ,  B23P15/04 ,  F05D2200/23 ,  Y02T50/671 ,  Y10S416/02 ,  Y10T29/49339

Abstract: A hollow airfoil (10) for a gas turbine engine having a leading edge (12), a trailing edge (14), a pressure side (20), and a suction side (22) includes a plurality of internal spanwise stiffening ribs (31-35) that are arranged in a logarithmic pattern. The particular arrangement of internal ribs (31-35) optimizes stiffness of the airfoil (10) without significantly increasing the weight thereof.

Abstract translation: 一种用于具有前缘（12），后缘（14），压力侧（20）和吸力侧（22）的燃气涡轮发动机的中空翼片（10）包括多个内翼展加强筋 -35），它们以对数模式排列。 内部肋（31-35）的特定布置优化翼型件（10）的刚度而不显着地增加其重量。

公开(公告)号：WO1996028642A1

公开(公告)日：1996-09-19

申请号：PCT/US1996003410

申请日：1996-03-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  ANGUS, Todd, J.

IPC: F01D11/00

CPC classification number: F01D25/246 ,  F01D9/042 ,  F01D11/001 ,  F05D2230/642 ,  F05D2230/90

Abstract: An airseal assembly (54) for a gas turbine engine (10) includes an airseal body (62) with a forward rail (68) and a ring rail (58). Both rails extend radially outward from the airseal body (62) and are spaced apart from each other by a plurality of spacers (60) to define a space therebetween. The airseal assembly (54) is segmented in at least two portions so that the forward rail (68) and the ring rail (58) are detached from each other. Each rail (68, 58) includes a contact surface (70, 80) that can be sprayed with wear resistant coating prior to assembly of the airseal in order to reduce wear on the forward rail (68) and the ring rail (58).

Abstract translation: 用于燃气涡轮发动机（10）的气密组件（54）包括具有前导轨（68）和环形轨道（58）的气密体（62）。 两个轨道从气密体（62）径向向外延伸并且通过多个间隔物（60）彼此间隔开，以在它们之间形成一个空间。 气密组件（54）至少分成两部分，使得前导轨（68）和环形导轨（58）彼此分离。 每个轨道（68,58）包括接触表面（70,80），其可以在组装气密孔之前喷涂耐磨涂层，以减少前导轨（68）和环形轨道（58）上的磨损。

公开(公告)号：WO1996025329A1

公开(公告)日：1996-08-22

申请号：PCT/US1996001392

申请日：1996-02-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  ARMY, Donald, E., Jr. ,  WILMOT, George, E., Jr.

IPC: B64D13/06

CPC classification number: B64D13/00 ,  B64D2013/0688 ,  F24F13/04 ,  F24F13/22 ,  Y02T50/56

Abstract: An air mixer (10), with a water collector (46), is disclosed for supplying recirculated cabin air in aircraft. In the preferred embodiment: used cabin air flows over pipes of colder fresh air to cool the used air and condense out most of the moisture contained in it; the fresh air and used air are passed over opposite faces of a ring of stator vanes (36), thereby imparting swirls to both types of airstreams; and the streams meet at the trailing tips of the stator vanes, where they corkscrew together to throw remaining coalesced moisture against a collection trough (40), from where it is discharged. The airstreams can now be injected into the cabin without droplets raining down on the passengers, nor ice clogging any pipes for the fresh air, which is typically supplied at below-freezing temperature.

Abstract translation: 公开了一种具有集水器（46）的空气混合器（10），用于在飞行器中供应再循环的客舱空气。 在优选实施例中：用过的客舱空气流过较冷新鲜空气的管道，以冷却用过的空气并冷凝其中含有的大部分水分; 新鲜空气和用过的空气通过定子叶片（36）的环的相对面，从而对两种类型的气流产生漩涡; 并且流在定子叶片的尾端处相交，在那里它们一起开瓶以将剩余的聚结的水分抵靠在收集槽（40）上，从其排出。 气流现在可以注入舱内，而不会在乘客身上滴下液滴，也不会导致冰堵塞新鲜空气的管道，这些通常是在低于冰点的温度下供应的。

公开(公告)号：WO1996019656A1

公开(公告)日：1996-06-27

申请号：PCT/US1995011752

申请日：1995-09-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  NIKKANEN, John, P.

IPC: F02K01/62

CPC classification number: F02K1/625 ,  Y02T50/671

Abstract: A thrust reverser (30) of a gas turbine engine (10) includes a blocker door (36) and a plurality of cascades (38). The thrust reverser (30) and the blocker door (36) have a stowed position and a deployed position. In the deployed position the blocker door (36) "leaks" airflow therethrough without generating substantial forward thrust. The leaked airflow reduces the amount of total airflow that must be accommodated by the cascades (38) of the thrust reverser (30), thereby decreasing the overall size of the cascades (38) and of the associated thrust reverser hardware and subsequently reducing the overall weight thereof.

Abstract translation: 燃气涡轮发动机（10）的推力反向器（30）包括阻挡门（36）和多个级联（38）。 推力反向器（30）和阻挡门（36）具有收起位置和展开位置。 在展开位置，阻塞门（36）将气流“泄漏”而不产生实质的向前推力。 泄漏的气流减少了推力反向器（30）的级联（38）必须容纳的总气流量，从而减小级联（38）和相关联的推力反向器硬件的总体尺寸，并随后减小总体 重量。

公开(公告)号：WO1996018538A1

公开(公告)日：1996-06-20

申请号：PCT/US1995012451

申请日：1995-09-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  DUESLER, Paul, W. ,  LOFFREDO, Constantino, V. ,  POTZ, Stephen, E. ,  SARCICH, Stephen, A. ,  MARX, Jon, A.

IPC: B64D27/26

CPC classification number: B64D27/18 ,  B64D2027/264 ,  F02C7/20

Abstract: A mounting arrangement securing a gas turbine engine (10) onto a pylon (45) includes a front mount (48), a thrust mount (50), and a rear mount (52). The front mount (48) is disposed forward of a forward end of the thrust mount (50). The thrust mount (50) is angled to point onto an intersection line (L) between a vertical plane (Y) traversing the gas turbine engine (10) and passing through the front mount (48) and a horizontal plane (X) passing through a longitudinal center axis (20). The mounting arrangement of the present invention significantly reduces the bending moment resulting from aerodynamic loading and engine thrust.

Abstract translation: 将燃气涡轮发动机（10）固定到塔架（45）上的安装装置包括前安装件（48），推力安装件（50）和后安装件（52）。 前支架（48）设置在推力支架（50）的前端的前方。 推力安装件（50）成角度以指向穿过燃气涡轮发动机（10）并穿过前部安装座（48）的垂直平面（Y）和通过前部安装件（48）的水平面（X）之间的交叉线（L） 纵向中心轴线（20）。 本发明的安装结构显着降低了由空气动力学载荷和发动机推力引起的弯矩。