公开(公告)号：WO1996020108A1

公开(公告)日：1996-07-04

申请号：PCT/US1995016787

申请日：1995-12-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  EATON, Harry, E. ,  HOLOWCZACK, John, E. ,  REINFELDER, William, C.

IPC: B64C27/473

CPC classification number: B64C27/473 ,  B64C2027/4736

Abstract: An engineered ceramic component (10) for the leading edge of a rotor blade provides enhanced erosion protection therefor. In one embodiment, the engineered ceramic component (10) includes a strain isolator member (19), an aerodynamic ceramic member (14), a first adhesive bond layer (16), and a second adhesive bond layer (18). The strain isolator member (19), which is operative to minimize strain transfer between the rotor blade infrastructure and the aerodynamic ceramic member (14), is configured so that inner mold line surface thereof is complementary to outer mold line surface of the rotor blade infrastructure. The aerodynamic ceramic member (14), which is operative to provide enhanced erosion protection for the respective leading edge of the rotor blade, is configured so that the outer mold line surface thereof defines the aerodynamic configuration of the respective leading edge and the inner mold line surface is complementary to the outer mold line surface of the strain isolator member (19). The aerodynamic ceramic member (14) is fabricated from an engineered ceramic material, which are defined in the present context as ceramic materials having a hardness greater than 1200kg/mm2 and an average flexural strength equal to or greater than 40ksi. The first adhesive bond layer (16) is operative to bond the strain isolator (19) member to the rotor blade infrastructure (140) and the second adhesive bond layer (18) is operative to bond the aerodynamic ceramic member (14) to the strain isolator member (19). In another embodiment, the engineered ceramic member (10) includes the aerodynamic ceramic member (14) described hereinabove and a thick adhesive layer. The thick adhesive layer is operative to minimize strain transfer between the rotor blade infrastructure and the aerodynamic ceramic member and to bond the aerodynamic ceramic member in combination with the rotor blade infrastructure.

Abstract translation: 用于转子叶片的前缘的工程陶瓷部件（10）为其提供了增强的侵蚀保护。 在一个实施例中，工程陶瓷部件（10）包括应变隔离器构件（19），空气动力学陶瓷构件（14），第一粘合剂接合层（16）和第二粘合剂接合层（18）。 用于最小化转子叶片基础设施和空气动力学陶瓷构件（14）之间的应变传递的应变隔离器构件（19）构造成使得其内部模具线表面与转子叶片基础设施的外部模具线表面互补 。 可操作地为转子叶片的各个前缘提供增强的侵蚀保护的空气动力学陶瓷构件（14）构造成使得其外模线表面限定相应前缘和内模线的空气动力学结构 表面与应变隔离构件（19）的外模线表面互补。 空气动力陶瓷构件（14）由工程陶瓷材料制成，其在本上下文中被定义为具有大于1200kg / mm2的硬度和等于或大于40ksi的平均弯曲强度的陶瓷材料。 第一粘合剂层（16）可操作以将应变隔离器（19）构件结合到转子叶片基础设施（140），并且第二粘合剂粘结层（18）用于将空气动力学陶瓷构件（14）结合到应变 隔离器构件（19）。 在另一个实施例中，工程陶瓷构件（10）包括上述空气动力陶瓷构件（14）和厚粘合剂层。 厚粘合剂层可操作以最小化转子叶片基础设施和空气动力学陶瓷构件之间的应变传递，并将空气动力学陶瓷构件与转子叶片基础结构结合。

公开(公告)号：WO1996018853A1

公开(公告)日：1996-06-20

申请号：PCT/US1995015569

申请日：1995-11-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  JOHNSON, Thomas, E.

IPC: F23R03/10

CPC classification number: F23R3/283 ,  F23R3/10

Abstract: Fuel nozzle guide (24) is threaded to fuel nozzle retainer (26), entrapping bulkhead (14), bulkhead liner (30) and key washer (28). Internal tabs (74) lock within slot (76) in the threads of the fuel nozzle guide. External tabs (78) of the key washer are bent into slot (80) of the retainer (26), after the nozzle guide (24) and the retainer are threaded together.

Abstract translation: 燃料喷嘴引导件（24）被螺纹连接到燃料喷嘴保持器（26），截留隔板（14），隔板衬套（30）和钥匙垫圈（28）。 内部突片（74）锁定在燃料喷嘴引导件的螺纹中的槽（76）内。 在喷嘴引导件（24）和保持器拧在一起之后，钥匙圈的外部卡舌（78）弯曲到保持器（26）的槽（80）中。

公开(公告)号：WO1996016287A1

公开(公告)日：1996-05-30

申请号：PCT/US1995014851

申请日：1995-11-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  BOUCHARD, Joseph, Paul

IPC: F16J15/32

CPC classification number: A46D9/02 ,  F16J15/3288 ,  Y10S451/916 ,  Y10T29/49297 ,  Y10T83/04

Abstract: Excess length (20) of brush seal wires (14) is sheared off with a punch (30) and die (26). A true and accurate diameter (22) is formed. The wires can be ground to a final finish diameter (18) if desired.

Abstract translation: 电刷密封线（14）的多余长度（20）用冲头（30）和模具（26）剪切。 形成真实且准确的直径（22）。 如果需要，电线可以研磨成最终精加工直径（18）。

公开(公告)号：WO1996014494A2

公开(公告)日：1996-05-17

申请号：PCT/US1995013402

申请日：1995-10-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  SHARMA, Om, P. ,  STAUBACH, Joseph, Brent ,  STETSON, Gary

IPC: F01D05/14

CPC classification number: F01D5/20 ,  F01D5/141 ,  F01D5/145

Abstract: A rotor blade (24) for a gas turbine engine includes a bowed surface (43) on a tip region (40) of the suction side (32) thereof. The curvature of the bowed surface (43) progressively increases toward the tip (36) of the blade (24). The bowed surface (43) results in a reduction of tip leakage through a tip clearance (50) from the pressure side (30) to the suction side (32) of the blade (24) and reduces mixing loss due to tip leakage.

Abstract translation: 用于燃气涡轮发动机的转子叶片（24）包括在其吸力侧（32）的尖端区域（40）上的弯曲表面（43）。 弯曲表面（43）的曲率朝着刀片（24）的尖端（36）逐渐增加。 弯曲表面（43）导致通过尖端间隙（50）从叶片（24）的压力侧（30）到吸力侧（32）的尖端泄漏减少，并且减少由于尖端泄漏引起的混合损失。

公开(公告)号：WO1996012873A1

公开(公告)日：1996-05-02

申请号：PCT/US1995011820

申请日：1995-09-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  OWENS, James, L.

IPC: F01D05/00

CPC classification number: B23P6/002 ,  F01D5/005 ,  F01D21/003

Abstract: A system for repairing damaged airfoils (28, 30) for gas turbine engines (10) includes a borescope with a plurality of rigid attachment tools (52). Each attachment tool (52) is individually shaped to access a leading edge (32) of the damaged airfoil (28) of a particular stage of the gas turbine engine (10). The attachment tools (52) enable repair of the damaged airfoils (28) without disassembling of the gas turbine engine (10).

Abstract translation: 用于修理用于燃气涡轮发动机（10）的受损翼型件（28,30）的系统包括具有多个刚性附接工具（52）的管道镜。 每个附接工具（52）被单独成形以接近燃气涡轮发动机（10）的特定级的损坏的翼型件（28）的前缘（32）。 附接工具（52）能够在不拆卸燃气涡轮发动机（10）的情况下修理损坏的翼型件（28）。

公开(公告)号：WO1996009737A1

公开(公告)日：1996-03-28

申请号：PCT/US1995012152

申请日：1995-09-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  FRITZ, Daniel, J. ,  BAILEY, Timothy, J. ,  BALL, Gary, A.

IPC: H04Q11/00

CPC classification number: G02B6/351 ,  G02B6/2932 ,  G02B6/29322 ,  G02B6/3534 ,  G02B6/3546 ,  G02B6/356 ,  G02B6/3578 ,  H04Q11/0005 ,  H04Q2011/0009 ,  H04Q2011/0015 ,  H04Q2011/0022 ,  H04Q2011/0026 ,  H04Q2011/0039 ,  H04Q2011/0052

Abstract: An all fiber wavelength selective optical switch has one or more 1xN input optical couplers (20, 120), each having an input signal with a plurality of wavelengths ( lambda 1, lambda 2, lambda 3). The output signals from the couplers (20, 120) are connected to fibers (26, 32, 126, 158) having Bragg gratings impressed therein, each having a central reflection wavelength, and each having a tuner attached thereto for detuning a central reflection wavelength of the gratings from a base wavelength corresponding to a wavelength of the input signal. For a given grating to pass a particular wavelength of the input signal that grating must be detuned. The fibers (26, 32, 126, 158) are also connected to one or more Nx1 couplers (66, 98) to combine input signals from different input couplers. The switch allows any combination of input wavelengths from any input signal to be selectively switched to one or more output ports.

Abstract translation: 全光纤波长选择光开关具有一个或多个1xN输入光耦合器（20,120），每个具有多个波长（λ1，λ2，λ3）的输入信号。 来自耦合器（20,120）的输出信号被连接到其中印有布拉格光栅的光纤（26,32,126,158），每个具有中心反射波长，并且每个具有附接到其上的调谐器以使中心反射波长失谐 从与输入信号的波长相对应的基波长的光栅。 对于给定的光栅来传递光栅必须失谐的输入信号的特定波长。 光纤（26,32,126,158）也连接到一个或多个Nx1耦合器（66,98）以组合来自不同输入耦合器的输入信号。 开关允许来自任何输入信号的输入波长的任何组合被选择性地切换到一个或多个输出端口。

公开(公告)号：WO1996009703A1

公开(公告)日：1996-03-28

申请号：PCT/US1995012231

申请日：1995-09-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  BALL, Gary, A.

IPC: H04J14/02

CPC classification number: G02B6/2932 ,  G02B6/2938 ,  H04J14/0206 ,  H04J14/0209 ,  H04J14/0213 ,  H04J14/0219 ,  H04Q11/0003 ,  H04Q2011/0009 ,  H04Q2011/0015 ,  H04Q2011/0022 ,  H04Q2011/0026

Abstract: An efficient wavelength multiplexer/demultiplexer includes a plurality of 2x2 optical couplers (122, 180, 200, 220), each having a pair of matched gratings (130, 142; 182, 184; 202, 204; and 222, 224), having bandpass wavelengths ( lambda 1, lambda 2, lambda 3, lambda 4), respectively, attached to two of the ports. An input signal (116) enters a port (120) and is split and reflected off the gratings (130, 142) and then recombined so as to provide all the input signal (116) at an output port (150) and no reflection out of the port (120). Another input signal (154) is incident on the grating (142) which is passed by the grating (142) and is coupled onto the output port (150) with the signal (116) as a signal (160). A similar arrangement exists for the other couplers (180, 200, 220) connected in series, each of which adds another input wavelength. Alternatively, in a de-multiplexing application the signal (116) may be broadband and the signals (154, 190, 206, 230) would be separate output wavelengths.

Abstract translation: 有效的波长多路复用器/解复用器包括多个2x2光耦合器（122,180,200,200），每个具有一对匹配的光栅（130,142; 182,184; 202,204;和222,224），具有 分别连接到两个端口的带通波长（λ1，λ2，λ3，λ4）。 输入信号（116）进入端口（120）并被分离并从光栅（130,142）反射，然后再结合，以在输出端口（150）提供所有输入信号（116），并且不反射出 的端口（120）。 另一个输入信号（154）入射到由光栅（142）通过的光栅（142）上，并以信号（116）作为信号（160）耦合到输出端口（150）上。 对于串联连接的其他耦合器（180,200,200）存在类似的布置，每个耦合器增加了另一个输入波长。 或者，在解复用应用中，信号（116）可以是宽带的，并且信号（154,190,206,230）将是分离的输出波长。

公开(公告)号：WO1996007534A1

公开(公告)日：1996-03-14

申请号：PCT/US1995010413

申请日：1995-08-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  LEONI, Peter, B.

IPC: B29C70/44

CPC classification number: B29C70/342 ,  B29C44/12 ,  B29C70/865

Abstract: A two-stage co-cure method for fabricating a composite article having a box-beam cross-sectional configuration wherein an outer shell portion of the composite article is fabricated and configured in the first stage to function as the tooling for completing the fabrication of composite article in the second stage. The first stage (12) includes a molding assembly set-up, a prepreg lay-up step (16), a vacuum-bagging step (18), a curing step (20) to cure the prepreg plies to form the outer shell, a de-bagging step (22), an optional reconfiguration step (24) wherein the molding assembly is reconfigured as required so that the reconfigured molding assembly and the outer shell in combination define a foam injection cavity, a securing step (26) wherein cover plates are secured in combination with the reconfigured molding assembly to close the foam injection cavity, a foam injecting step (26) to form an outer shell, cured foam core stabilized combination that functions as the tooling for the second stage, and a disassembly step (30) wherein the reconfigured molding assembly is disassembled to expopse the outer shell, cured foam core stabilized combination. The second stage (40) includes an application step (42) wherein a film adhesive is applied to the outer shell, cured foam core stabilized combination, a lay-up step (44) wherein prepreg plies are layed-up onto the adhesive coated outer shell, a vacuum-bagging step (46), and a curing step (48) to form the inner shell, and to concomitantly cause the applied film adhesive to fuse wherein the inner cap and outer shell are adhesively bonded in combination to form the composite article having the box-beam cross-sectional configuration.

Abstract translation: 一种用于制造具有盒梁横截面构造的复合制品的两级共固化方法，其中复合制品的外壳部分被制造和构造在第一阶段中，用作完成复合材料制造的工具 第二阶段的文章。 第一阶段（12）包括模制组装设备，预浸料叠层步骤（16），真空包装步骤（18），固化预浸料层以形成外壳的固化步骤（20） 去包装步骤（22），可选的重新配置步骤（24），其中模制组件根据需要被重新配置，使得重新配置的模制组件和外壳组合限定泡沫喷射腔，固定步骤（26），其中盖 板与重新配置的模制组件结合以封闭泡沫注射腔，泡沫注射步骤（26）以形成外壳，用作第二阶段的模具的固化泡沫芯稳定组合以及拆卸步骤（ 30），其中重新配置的成型组件被拆卸以使外壳膨胀，固化的泡沫芯稳定组合。 第二阶段（40）包括施加步骤（42），其中将膜粘合剂施加到外壳上，固化的泡沫芯稳定组合，铺设步骤（44），其中将预浸料层铺在粘合剂涂覆的外部 壳体，真空包装步骤（46）和固化步骤（48）以形成内壳，并且伴随地引起涂覆的膜粘合剂熔合，其中内盖和外壳组合粘合地结合以形成复合材料 具有盒梁横截面构造的制品。

公开(公告)号：WO1996004125A1

公开(公告)日：1996-02-15

申请号：PCT/US1995009106

申请日：1995-07-19

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: B29C70/86

CPC classification number: B29D99/0025 ,  B29C70/44 ,  B29L2031/08 ,  Y10S425/044 ,  Y10T156/1028 ,  Y10T156/103

Abstract: A fiberglass or other material skin is applied to a composite airfoil structure (2) in a mold assembly (22) having a partially compliant caul plate component which defines the shape of the lower surface of the airfoil. The caul plate component includes a first portion (34) which is essentially rigid and which covers the leading edge (16) of the airfoil. The rigid portion of the caul plate component provides improved conformation of the airfoil skin to the leading edge of the airfoil. The caul plate component also includes a compliant portion (36) which covers and defines the shape of the trailing edge of the lower surface of the airfoil. The stiffness of the caul plate component also has a variable stiffness zone (38) which interconnects the rigid and compliant portions thereof. The use of rigid and compliant portions on the caul plate provides for a controlled conformance of the skin to the leading edge of the airfoil, while allowing the skin to accurately conform to the remainder of the airfoil in spite of variations in the dimensions of internal operating components of the airfoil.

Abstract translation: 将玻璃纤维或其它材料表皮施加到具有限定翼型件的下表面的形状的部分柔性挡板部件的模具组件（22）中的复合翼型结构（2）上。 刮板部件包括基本刚性并且覆盖翼型件的前缘（16）的第一部分（34）。 挡板部件的刚性部分提供了翼型皮肤到翼型的前缘的改进构造。 挡板部件还包括覆盖并限定翼型件的下表面的后缘的形状的柔顺部分（36）。 止动板部件的刚度还具有可变刚度区域38，其将刚性部分和柔性部分互连。 在挡板上使用刚性和柔顺部分提供了皮肤对翼型前缘的受控一致性，同时允许皮肤准确地符合翼型的其余部分，尽管内部操作的尺寸有变化 机翼的部件。

公开(公告)号：WO1995034029A1

公开(公告)日：1995-12-14

申请号：PCT/US1995005750

申请日：1995-05-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  GOLD, Phillip, J. ,  FOGLER, Donald, L., Jr. ,  DRYFOOS, James, B.

IPC: G05D01/10

CPC classification number: G05D1/0858

Abstract: A velocity command system is provided with a velocity stabilization mode wherein aircraft flight path referenced velocities are determined with respect to an inertial frame of reference, the flight path referenced velocities are held constant during pilot commanded yaw maneuvers so that the aircraft maintains a fixed inertial referenced flight path regardless of the pointing direction of the aircraft. Velocity control with respect to an inertial frame of reference is accomplished by controlling the aircraft flight path based on aircraft body referenced commanded lateral and longitudinal acceleration and based on aircraft body referenced lateral and longitudinal centrifugal acceleration. Operation in the velocity stabilization mode is provided in response to the manual activation of the velocity stabilization mode by the pilot, provided that the aircraft is already operating in the ground speed mode and the aircraft is not in a coordinated turn.

Abstract translation: 速度指令系统被提供有速度稳定模式，其中飞行器飞行路径参考速度相对于惯性参考系确定，飞行路径参考速度在飞行员指令的偏航操纵期间保持恒定，使得飞行器维持固定的惯性参考 飞行路径，无论飞机的指向方向如何。 相对于惯性参考框架的速度控制是通过基于飞行器体参考的指向横向和纵向加速度并且基于飞行器本体参考的横向和纵向离心加速度来控制飞行器飞行路径来实现的。 响应于飞行员手动启动速度稳定模式，提供速度稳定模式的操作，前提是飞机已经以地面速度模式运行，飞机不处于协调转弯状态。