公开(公告)号：WO1994017366A1

公开(公告)日：1994-08-04

申请号：PCT/US1994000967

申请日：1994-01-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  BALL, Gary, A. ,  MELTZ, Gerald ,  NEWMAN, Leon, A.

IPC: G01D05/26

CPC classification number: G01D5/35383 ,  G01J3/1895 ,  H01S3/0675

Abstract: A remote active multipoint fiber laser sensor includes a plurality of fiber lasers (12, 14, 16), each having a pair of Bragg gratings (18, 20), embedded in a fiber (10) and excited by a common pump light (30). The lasers (12, 14, 16) lase at different longitudinal modes (lasing wavelengths) and emit light (32, 34, 36), at their respective wavelengths ( lambda 1, lambda 2, lambda n). The lasing wavelength of each laser shifts due to perturbations, such as strain or temperature, applied thereto. The output light (32, 34, 36) is fed to a spectrum analyzer (50) where the wavelength shift is analyzed. A signal processor (54) reads the wavelength shift and provides a signal on lines (56) indicative of the perturbation at each of the lasers/sensors (12-16). Alternatively, a single laser may be used as a single sensor. Alternatively, birefringent fiber may be used as the fiber cavities (21) and the two polarizations are beat together to form a lower difference or ''beat'' frequency, thereby allowing lower frequency detection devices to be used.

Abstract translation: 远程有源多点光纤激光传感器包括多个光纤激光器（12,14,16），每个光纤激光器具有嵌入在光纤（10）中并由公共泵浦光（30）激发的一对布拉格光栅（18,20） ）。 激光器（12,14,16）以不同的纵向模式（激光波长）发射并在其各自的波长（λ1，λ2，λn）处发光（32,34,36）。 每个激光器的激光波长由于施加到其上的扰动（例如应变或温度）而移动。 输出光（32,34,36）被馈送到分析波长偏移的频谱分析器（50）。 信号处理器（54）读取波长偏移并且在线（56）上提供指示每个激光器/传感器（12-16）处的扰动的信号。 或者，单个激光器可以用作单个传感器。 或者，可以使用双折射光纤作为光纤腔（21），并且两个极化被一起击打以形成较低的差或“拍”频率，从而允许使用较低频率检测装置。

公开(公告)号：WO1994016200A1

公开(公告)日：1994-07-21

申请号：PCT/US1994000414

申请日：1994-01-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  GRANT, Parker, A. ,  HOYT, Stephen, D.

IPC: F01D05/08

CPC classification number: F01D5/3015 ,  F01D5/082 ,  F01D11/005

Abstract: A gas turbine engine having a turbine rotor assembly with a free standing sideplate assembly is disclosed. Various construction details are developed which provide a sideplate assembly which is not radially or axially supported by the web or rim of the adjacent disk. In one particular embodiment, a rotor assembly includes a rotor disk, having a rim, a web (44), and a bore (46) and a sideplate assembly, having a web (54) and a bore (52). The web of the sideplate is radially supported by the bore of the sideplate and includes a disk seal means (62, 86) and an aperture (66). The disk seal means (62, 86) is engaged with the rotor disk and has an axially directed seal force provided by an axially interfering fit between the sideplate and rotor disk. The aperture (68) provides means for fluid communication between a source of cooling fluid and the rotor disk.

Abstract translation: 公开了具有具有独立侧板组件的涡轮转子组件的燃气涡轮发动机。 开发出各种构造细节，其提供侧板组件，其不被相邻盘的腹板或边缘径向或轴向地支撑。 在一个具体实施例中，转子组件包括转子盘，其具有轮缘，腹板（44）和具有腹板（54）和孔（52）的孔（46）和侧板组件。 侧板的腹板由侧板的孔径向支撑，并且包括盘密封装置（62,86）和孔（66）。 圆盘密封装置（62,86）与转子盘接合并且具有通过侧板和转子盘之间的轴向干涉配合提供的轴向定向的密封力。 孔（68）提供用于冷却流体源和转子盘之间的流体连通的装置。

公开(公告)号：WO1994014650A1

公开(公告)日：1994-07-07

申请号：PCT/US1993011828

申请日：1993-12-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  REINFELDER, William, C. ,  PURSE, Jeffry, C.

IPC: B64C27/46

CPC classification number: B64C27/463 ,  Y10T29/49332 ,  Y10T29/49337 ,  Y10T156/11

Abstract: A replaceable tip portion (20) for a helicopter rotor blade (14) is selectively swept, tapered and anhedral. The tip portion is formed of an upper and lower composite tip skin layer (35), each tip skin layer having bonded thereto a honeycomb core (38). A channel (recess) (40) is formed in the honeycomb for receiving a rotor spar tip end (30), removably attached (60) to the rotor spar. The honeycomb core is attached to the upper and lower tip skin layers in halves, and is machined along the rotor blade chord plane (70) prior to assembly of the halves on the rotor spar. A composite tip cap (50) is fixed to the extreme tip end of the removable anhedral tip portion, the mating surface of the tip cap which is joined to the removable tip is machined to provide a precise joint.

Abstract translation: 用于直升机转子叶片（14）的可替换的尖端部分（20）被选择性地扫掠，渐缩和倾斜。 尖端部由上下复合顶端表皮层（35）形成，每个末端表层与蜂窝芯（38）结合。 在蜂窝中形成有用于接收转子翼尖末端（30）的通道（凹部）40，可拆卸地安装在转子翼梁上。 蜂窝芯体以上半部分和下部尖端皮肤层连接在一半上，并且在将半部分组装在转子翼梁上之前沿着转子叶片平面（70）加工。 复合顶盖（50）固定到可移除的双面尖端部分的最前端，加工结合到可拆卸顶端的顶盖的配合表面提供精确的接头。

公开(公告)号：WO1994014601A1

公开(公告)日：1994-07-07

申请号：PCT/US1993012343

申请日：1993-12-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  BOIVIN-IASSOGNA, Denise, L. ,  DIONIZIO, Richard, J. ,  SANTISO, Joseph, M., III

IPC: B29C67/14

CPC classification number: B29C70/086 ,  B29K2995/0022

Abstract: A method for manufacturing composite articles that have enhanced exterior surfaces, i.e, clean finished surfaces that present a cosmetically smooth visual appearance. The method includes a molding assembly preparation procedure, conventional lay-up and curing steps utilizing a conventional molding assembly, and an improved post-cure finishing procedure. The molding assembly preparation procedure prepares the molding assembly for the lay-up step, and includes the steps of laying-up and conforming surfacing film onto the molding surfaces of the molding assembly. The surfacing films are an integral part of the finished composite article, functioning as the outermost ply layer that defines the exterior surfaces of the cured composite article. The improved post-cure finishing procedure includes, in seriatim, a cleaning step to achieve exterior surfaces having a clean surface finish, a first sanding step to finely texturize the clean surfacing film layer of the exterior surfaces to facilitate the application of a single coat of conventional primer thereto, a testing step wherein the clean, texturized exterior surfaces are waterbreak tested for cleanliness, the sequential application of one or more coats of an environmentally safe, waterborne epoxy filler to the primer-coated exterior surfaces, a second sanding step to remove latent surface defects from the primer-filler coated exterior surfaces, the application of a primer coating to the primer-filler coated, sanded exterior surfaces, and lastly, the application of one or more coats of paint to the primer-coated, exterior surfaces to form a finished composite article having enhanced exterior surfaces.

Abstract translation: 一种用于制造具有增强的外表面的复合制品的方法，即，具有美观平滑视觉外观的清洁的成品表面。 该方法包括成型组件制备程序，利用常规成型组件的常规铺设和固化步骤以及改进的后固化整理程序。 成型组装准备程序准备了用于铺设步骤的模制组件，并且包括将表面覆膜放置并贴合到模制组件的模制表面上的步骤。 表面膜是成品复合制品的一个组成部分，用作限定固化复合制品外表面的最外层层。 改进的后固化整理程序包括清洁步骤，以实现具有干净表面光洁度的外表面，第一砂光步骤，以使外表面的清洁表面膜层精细地纹理化，以便于施加单面涂层 常规底漆，测试步骤，其中干净的，变形的外表面经过水洗试验以获得清洁度，将一种或多种环境安全的水性环氧树脂填料的涂层顺序施加到底漆涂覆的外表面，第二砂磨步骤以除​​去 来自底漆 - 填料涂布的外表面的潜在表面缺陷，将底漆涂料施用于底漆 - 涂料涂覆的砂磨外表面，最后，将一种或多种涂料涂料施用于底漆涂覆的外表面 形成具有增强的外表面的成品复合制品。

公开(公告)号：WO1994014600A1

公开(公告)日：1994-07-07

申请号：PCT/US1993011826

申请日：1993-12-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  DUBLINSKI, Alex, C. ,  CARSTENSEN, Thomas, A. ,  RAMEY, Philip, J.

IPC: B29C67/14

CPC classification number: B29D99/0089 ,  B29C33/38 ,  B29C33/405 ,  B29C33/76 ,  B29C43/3642 ,  B29C70/086 ,  B29C70/44 ,  B29C2043/3644 ,  B29D24/007 ,  B29K2705/02 ,  B29K2827/16 ,  B29K2877/10 ,  B29K2995/0046 ,  B29L2007/002 ,  B29L2024/00 ,  B29L2031/608 ,  Y10T83/0405 ,  Y10T156/1052 ,  Y10T156/1062 ,  Y10T428/236 ,  Y10T428/24149

Abstract: A composite molding apparatus (10) and method for high pressure co-cure molding of lightweight honeycomb core composite articles having ramped surfaces utilizing low total density, stabilized ramped honeycomb cores. The low total density, stabilized ramped honeycomb core is formed by net shaping stabilized honeycomb core material into a ramped honeycomb core, which is prepped for lay-up and co-cure by applying a layer of low areal weight film adhesive to the upper, lower and ramped surfaces thereof. The honeycomb core material is stabilized for the net shaping operation by a layer of the low areal weight film adhesive applied to the upper and lower surfaces of the material in a predetermined picture frame format. The composite molding apparatus is a semi-rigid molding assembly that includes a rigid base member (12) and a complementary semi-rigid mold (20) member that includes internal rigid reinforcement inserts (22) that provide symmetric pressure distribution over the ramped surfaces of the honeycomb core and the overlaid composite prepregs during the high pressure co-cure process. Composite prepregs and the ramped honeycomb core are laid-up in the semi-rigid molding assembly, which is vacuum bagged and disposed in an autoclave. The vacuum bag is evacuated, and the laid-up molding assembly is subjected to a two stage pressure, temperature cycle for high pressure co-cure. The autoclave is pressurized to a dwell pressure, and the temperature is then raised from ambient to a dwell temperature whereupon the autoclave is stabilized for a dwell period. Next, the autoclave pressure is increased to a high pressure, and the temperature is raised to a co-cure temperature whereupon the autoclave is stabilized for a co-cure period to effect curing of the lay-up. After curing is complete, the autoclave is cooled, and then depressurized for removal of the composite molding apparatus.

Abstract translation: 一种复合成型设备（10）和用于使用低总密度，稳定化的倾斜蜂窝芯的具有斜面的轻质蜂窝芯复合材料的高压共固化模塑的方法。 低总密度稳定化的蜂窝状蜂窝芯通过将网状成形稳定的蜂窝芯材料成形为斜面蜂窝芯体，其通过将一层低面积重量膜粘合剂施加到上部，下部 并且其斜坡表面。 通过以预定的相框格式施加到材料的上表面和下表面的低面积重量膜粘合剂层，蜂窝芯材料被稳定以进行净整形操作。 复合成型设备是半刚性模制组件，其包括刚性基部构件（12）和互补半刚性模具（20）构件，所述互补半刚性模具（20）构件包括内部刚性加强件插入件（22），其在 蜂窝芯和叠层复合预浸料在高压共固化过程中。 将复合预浸料坯和斜面蜂窝芯堆放在半刚性模制组件中，该组装件被真空包装并置于高压釜中。 真空袋被抽真空，并且成型组件经受两段压力，高压共固化的温度循环。 将高压釜加压至停留压力，然后将温度从环境升高至停留温度，随后将高压釜稳定一段停留时间。 接下来，将高压釜压力提高到高压，并且将温度升高到共固化温度，随后将高压釜稳定在共固化时间段以实现层压固化。 固化完成后，将高压釜冷却，然后减压除去复合成型装置。

公开(公告)号：WO1994014108A1

公开(公告)日：1994-06-23

申请号：PCT/US1993010871

申请日：1993-11-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  REED, Robert, W. ,  KARTSEN, Douglas, A. ,  AKERLEY, Stevan, W.

IPC: G05B19/18

CPC classification number: G05B19/402 ,  G01B17/00 ,  G01M1/16 ,  G05B2219/37197 ,  G05B2219/37269 ,  G05B2219/37398 ,  G05B2219/37492 ,  G05B2219/37525 ,  G05B2219/49113 ,  G05B2219/50055 ,  G05B2219/50152 ,  Y10S82/903 ,  Y10T82/10

Abstract: A computer (21) processes the time between ultrasonic echoes received at a transducer (19) indicative of the outer radius and wall thickness of a workpiece (10) by subtracting (69) the weighted average (80-90) wall thickness from the weighted average outer radius to generate an internal radius for a large number of points around a spiral slice of the workpiece. The internal radii and angles are converted (69) to x and y coordinates. The centroid (X, Y) of each slice of data indicating workpiece cavity internal radii is determined (71) as twice the summation of the x coordinates and twice the summation of the y coordinates of all of the datum points of the slice. The least squares fit (73) of the X coordinates of the centroids of all of the slices and the least squares fit (74) of the Y coordinates of the centroids of all of the slices are then used to determine the average axis of the cavity of the workpiece. The X &cir& NOt and Y &cir& NOt coordinates of the end points of the average axis of the cavity are then converted (75) to polar coordinates to permit offsetting the end points of the workpiece commensurate amounts, whereby further machining will cause the internal cavity of the workpiece to end up more nearly centrally located, on average.

Abstract translation: 计算机（21）通过从加权平均值（80-90）中减去（69）加权平均（80-90）壁厚来处理在换能器（19）处接收的指示工件（10）的外径和壁厚之间的超声波回波之间的时间 平均外半径以产生围绕工件的螺旋切片的大量点的内半径。 将内部半径和角度（69）转换为x和y坐标。 确定表示工件腔内半径的每个切片数据的重心（X，Y）（71）是x坐标的和的两倍，并且是切片的所有基准点的y坐标的和的两倍。 所有切片的质心的X坐标的最小二乘拟合（73）和所有切片的质心的Y坐标的最小二乘拟合（74）然后用于确定腔的平均轴 的工件。 然后将空腔平均轴的端点的X＆cir＆NOt和Y＆cir＆NOt坐标转换（75）到极坐标，以允许偏移工件的端点相应的量，从而进一步加工将导致内腔 平均来说，工件最终更靠近中心位置。

公开(公告)号：WO1994014031A1

公开(公告)日：1994-06-23

申请号：PCT/US1993010829

申请日：1993-11-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  REED, Robert, W.

IPC: G01B17/02

CPC classification number: G01M1/16 ,  B23B1/00 ,  G01B17/00 ,  G05B2219/37525 ,  Y10S82/903 ,  Y10T82/10

Abstract: A computer (21) processes the time between ultrasonic echoes received at a transducer (19) indicative of the outer radius and wall thickness of a workpiece (10) by subtracting (69) the weighted average (80-90) wall thickness from the weighted average outer radius to generate an internal radius for a large number of points around a spiral slice of the workpiece. The internal radii and angles are converted (69) to x and y coordinates. The centroid (X, Y) of each slice of data indicating workpiece cavity internal radii is determined (71) as twice the summation of the x coordinates and twice the summation of the y coordinates of all of the datum points of the slice. The least squares fit (73) of the X coordinates of the centroids of all of the slices and the least squares fit (74) of the Y coordinates of the centroids of all of the slices are then used to determine the average axis of the cavity of the workpiece. The X &cir& NOt and Y &cir& NOt coordinates of the end points of the average axis of the cavity are then converted (75) to polar coordinates to permit offsetting the end points of the workpiece commensurate amounts, whereby further machining will cause the internal cavity of the workpiece to end up more nearly centrally located, on average.

Abstract translation: 计算机（21）通过从加权平均值（80-90）中减去（69）加权平均（80-90）壁厚来处理在换能器（19）处接收的指示工件（10）的外径和壁厚之间的超声波回波之间的时间 平均外半径以产生围绕工件的螺旋切片的大量点的内半径。 将内部半径和角度（69）转换为x和y坐标。 确定表示工件腔内半径的每个切片数据的重心（X，Y）（71）是x坐标的和的两倍，并且是切片的所有基准点的y坐标的和的两倍。 所有切片的质心的X坐标的最小二乘拟合（73）和所有切片的质心的Y坐标的最小二乘拟合（74）然后用于确定腔的平均轴 的工件。 然后将空腔平均轴的端点的X＆cir＆NOt和Y＆cir＆NOt坐标转换（75）到极坐标，以允许偏移工件的端点相应的量，从而进一步加工将导致内腔 平均来说，工件最终更靠近中心位置。

公开(公告)号：WO1994013945A1

公开(公告)日：1994-06-23

申请号：PCT/US1993011675

申请日：1993-12-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  DYER, Gerald, P. ,  WIESNER, Charles, E. ,  DONNELLY, Brian, G.

IPC: F02C07/228

CPC classification number: F02C7/228 ,  Y10T137/2521

Abstract: A fuel delivery system (10) incorporates a fuel splitter valve assembly (30) including a first valve (40) having a selectively positionable spool (42) disposed therein for controllably metering fuel flow therethrough for delivery to a first combustion chamber (22) and a second valve (50) operative to pass a second portion of the fuel flow to a second combustion chamber (24) while maintaining at least a desired minimum pressure upstream of the first valve (40) whenever the second combustion chamber is in operation, and to shut-off fuel flow to the second combustion chamber whenever the second combustion chamber is not in operation.

Abstract translation: 燃料输送系统（10）包括燃料分配阀组件（30），燃料分配器阀组件（30）包括第一阀（40），第一阀（40）具有设置在其中的可选择性定位的阀芯（42），用于可控地计量通过其中的燃料流以输送到第一燃烧室（22） 第二阀（50），其操作以将燃料流的第二部分传递到第二燃烧室（24），同时在第二燃烧室运行时保持至少所述第一阀（40）上游的所需最小压力，以及 每当第二燃烧室不工作时，切断到第二燃烧室的燃料流。

公开(公告)号：WO1994013598A1

公开(公告)日：1994-06-23

申请号：PCT/US1993012104

申请日：1993-12-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  KMETZ, Michael, A. ,  LALIBERTE, John, M. ,  SUIB, Steven, L. ,  GALASSO, Francis, S.

IPC: C04B35/80

CPC classification number: C04B35/6286 ,  C04B35/563 ,  C04B35/565 ,  C04B35/62844 ,  C04B35/62868 ,  C04B35/62873 ,  C04B35/62897 ,  C04B35/806 ,  C04B2235/5228 ,  C04B2235/524 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2235/614 ,  C04B2235/96 ,  C04B2235/9684 ,  C23C16/32 ,  Y10T428/2918 ,  Y10T428/292

Abstract: A substrate can be coated with boron carbide by contacting the substrate with a reaction mixture of a boron source and a carbon source at a temperature of at least about 1050 DEG C such that the boron source and carbon source react with each other to produce a boron carbide coating on the substrate. The boron carbide coating comprises up to about 45 atomic percent boron.

Abstract translation: 通过在至少约1050℃的温度下使基底与硼源和碳源的反应混合物接触，使得硼源和碳源彼此反应以产生硼，可以用碳化硼涂覆基底 基材上的碳化物涂层。 碳化硼涂层包含至多约45原子百分比的硼。

公开(公告)号：WO1994012771A1

公开(公告)日：1994-06-09

申请号：PCT/US1993011254

申请日：1993-11-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  SYLVESTRO, Joseph, A. ,  LINASK, Indrik ,  BEABOUT, Brian, K.

IPC: F01D05/18

CPC classification number: F01D5/187 ,  Y02T50/676

Abstract: A turbine airfoil (32) having a cut-back trailing edge (62) and a plurality of diffusing flow dividers (68) upstream of the cut-back trailing edge (62) is disclosed. Various construction details are developed which provide ejection of a diffusing film of cooling fluid over a cut-back trailing edge (62). In one particular embodiment, a turbine airfoil (32) includes a plurality of radially spaced flow dividers (68) extending between a pressure wall (56) and a suction wall (58). Each flow divider (68) includes a rounded leading edge (74), a pair of parallel sidewalls (82) downstream of the leading edge (74), and a pair of converging sidewalls (86) downstream of the parallel sidewalls (82). Adjacent sidewalls of adjacent flow dividers form flow channels (72) having a constant area channel (76) and a diffusing section. The diffusing section includes a covered portion (94) upstream of the cut-back trailing edge (62) and an uncovered portion (96) extending over the cut-back trailing edge (62).

Abstract translation: 公开了一种具有切割后缘（62）和在切割后缘（62）上游的多个扩散分流器（68）的涡轮机翼型件（32）。 开发了各种构造细节，其提供冷却流体的扩散膜在切割后缘（62）上的喷射。 在一个特定实施例中，涡轮机翼片（32）包括在压力壁（56）和吸力壁（58）之间延伸的多个径向隔开的分流器（68）。 每个分流器（68）包括圆形前缘（74），在前缘（74）下游的一对平行侧壁（82）和平行侧壁（82）下游的一对会聚侧壁（86）。 相邻分流器的相邻侧壁形成具有恒定区域通道（76）和扩散部分的流动通道（72）。 扩散部分包括在切割后缘（62）上游的覆盖部分（94）和在切割后缘（62）上延伸的未覆盖部分（96）。