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公开(公告)号：WO1995030077A1
公开(公告)日：1995-11-09
申请号：PCT/US1995004992
申请日：1995-04-24
Applicant: UNITED TECHNOLOGIES CORPORATION
IPC: F01D21/04
CPC classification number: F01D21/045 , F05D2220/327 , Y02T50/671
Abstract: Isogrid structure (20) forms case (14) surrounding the fan blades (12) of the turbofan. A ballistic fabric (22) surrounds the case. Containment zones (30, 32, 34) at the forward end have isogrid ribs (38) extending other than circumferentially. In the rear support zone, ribs (76) extend circumferentially stiffening the case against collapse.
Abstract translation: 等离子体结构（20）形成围绕涡轮风扇的风扇叶片（12）的壳体（14）。 弹道织物（22）围绕壳体。 位于前端的收容区（30,32,34）具有沿圆周方向延伸的异格子肋（38）。 在后支撑区域中，肋（76）在外壳周向加强以防止塌陷。
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公开(公告)号：WO1995030069A1
公开(公告)日：1995-11-09
申请号：PCT/US1995001167
申请日：1995-01-26
Applicant: UNITED TECHNOLOGIES CORPORATION
IPC: F01D05/18
CPC classification number: F01D5/187 , F05D2260/201 , Y02T50/676
Abstract: An airfoil (42) for a gas turbine engine (10) having an airfoil portion (52) with a leading and a trailing edge (60, 62) includes dual pressure source cooling. The trailing edge (62) of the airfoil (42) includes an internal trailing edge passage (78) and the leading edge (60) includes an internal leading edge passage (64). Compressor bleed air at higher pressure is channeled through the leading edge passage (64) whereas compressor bleed air at lower pressure is channeled through the trailing edge passage (78). The higher internal pressure in the leading edge (60) ensures that the inward flow of products of combustion does not occur.
Abstract translation: 用于具有具有前缘和后缘（60,62）的翼型部分（52）的燃气涡轮发动机（10）的翼型件（42）包括双重压力源冷却。 翼型件（42）的后缘（62）包括内部后缘通道（78），前缘（60）包括内部前缘通道（64）。 压缩机在较高压力下排出空气通过前缘通道（64）引导，而压力下降的空气通过后缘通道（78）引导。 前缘（60）中较高的内部压力确保不会发生燃烧产物的向内流动。
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公开(公告)号：WO1995030032A1
公开(公告)日：1995-11-09
申请号：PCT/US1995001620
申请日：1995-02-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： UNITED TECHNOLOGIES CORPORATION , CHEN, Otis, Y. , SEOW, Kim, Chong , LIM, Choo, Boon
IPC: C23G01/14
Abstract: A cleaning method for gas turbine engine airfoils (30) includes a step of autoclave process cleaning and a step of chelating agent solution cleaning. The cleaning method also includes water rinsing after the autoclave cleaning and after the chelating agent solution cleaning. A subsequent step of high pressure water jet spray removes the debris. The cleaning method of the present invention significantly reduces the number of cleaning cycles required to clean the airfoils (30).
Abstract translation: 燃气涡轮发动机翼型件（30）的清洁方法包括高压釜处理清洗步骤和螯合剂溶液清洗步骤。 清洗方法还包括高压釜清洗后和螯合剂溶液清洗后的水洗。 随后的高压喷水喷雾步骤除去碎屑。 本发明的清洁方法显着地减少了清洁翼型件（30）所需的清洁循环次数。
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公开(公告)号：WO1995029787A1
公开(公告)日：1995-11-09
申请号：PCT/US1995004990
申请日：1995-04-24
Applicant: UNITED TECHNOLOGIES CORPORATION
IPC: B23P15/04
CPC classification number: F01D5/147 , B23P15/04 , Y02T50/671 , Y10T29/49336 , Y10T29/49339 , Y10T29/49893
Abstract: Purge flow openings through chordwise ribs (14) are formed by making partial circular cuts at the rib edges before diffusion bonding the blade halves (10, 32). A full semi-circular is used on the pressure side, but only a segment on the suction side.
Abstract translation: 通过弦肋（14）吹扫流动开口通过在扩散结合叶片半部（10,32）之前在肋边缘处形成部分圆形切口而形成。 在压力侧使用全半圆形，但在吸力侧仅使用一段。
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公开(公告)号：WO1995027847A1
公开(公告)日：1995-10-19
申请号：PCT/US1995003347
申请日：1995-03-24
Applicant: UNITED TECHNOLOGIES CORPORATION
IPC: F02D41/08
CPC classification number: F02D41/083 , F02D31/001 , F02D31/007 , F02D2041/141
Abstract: An automatic engine speed hold control system (430) allows an engine (420) to quickly achieve a commanded engine speed and thereafter maintain a constant commanded engine speed regardless of changes in engine loading. An engine speed error signal (444) is computed as the difference between an operator commanded engine speed (440) and actual engine speed (434, 436). The engine speed error signal (444) is scaled based on an engine speed error gain (448), and the scaled engine speed error (452) is then provided via an integral path (456) and a proportional path (454) to a summing junction (478) where it is summed with load anticipation trim signals (474, 467) to provide a final trim signal (485). The load anticipation trim signals (474, 467) are feed forward signals which anticipate engine response to changes in commanded engine loading, the combined engine trim signal (452) and load anticipation trim signals (474, 467) provide an engine speed hold throttle position command (final trim signal) (485) to control fuel flow to the engine (420) and therefore control engine speed. The engine speed error gain (448) is determined based on engine loading (450), and the error gain is thereafter limited (451) based on current engine speed.
Abstract translation: 自动发动机速度保持控制系统（430）允许发动机（420）快速地实现指令的发动机转速，并且此后维持恒定的发动机转速指令，而与发动机负荷的变化无关。 发动机转速误差信号（444）被计算为操作者指令的发动机转速（440）与实际发动机转速（434,436）之差。 基于发动机速度误差增益（448）对发动机转速误差信号（444）进行缩放，然后经由积分路径（456）和比例路径（454）将缩放的发动机转速误差（452）提供给求和 （478），其中与负载预期调整信号（474,467）相加以提供最终的微调信号（485）。 负载预期微调信号（474,467）是预测发动机响应于指令的发动机负载变化的前馈信号，组合的发动机微调信号（452）和负载预期调整信号（474,467）提供发动机转速保持节气门位置 命令（最终微调信号）（485）以控制到发动机（420）的燃料流量，因此控制发动机转速。 基于发动机负载（450）确定发动机转速误差增益（448），然后根据当前发动机转速限制误差增益（451）。
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Patent Agency Ranking
公开(公告)号：WO1995027326A1
公开(公告)日：1995-10-12
申请号：PCT/US1995003619
申请日：1995-03-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： UNITED TECHNOLOGIES CORPORATION , MILLER, Robin, M.
IPC: H02K07/02
CPC classification number: H02K21/026 , B60L11/16 , H02K7/025 , H02K21/24 , H02K29/06 , Y02E60/16 , Y02T10/641 , Y02T10/7027 , Y02T10/7033
Abstract: A flywheel system having permanent magnets (20) embedded in a flywheel (10) rotating about a shaft (16) is provided with a stator (28) which is slidably mounted to the shaft (16) thereby allowing a gap g1 between the stator (28) and the rotor/flywheel (10) to be adjustable. When energy is being provided to (spin-up mode) or extracted from (spin-down mode) the flywheel (10), the stator (28) is positioned so the gap g1 is small to provide strong electromagnetic interaction between the stator (28) and the flywheel (10). Conversely, when the flywheel (10) is freewheeling, the stator (28) is positioned so the gap g1 is large enough to minimize electromagnetic drag on the flywheel (10).
Abstract translation: 具有埋置在围绕轴（16）旋转的飞轮（10）中的永磁体（20）的飞轮系统设置有可滑动地安装到轴（16）上的定子（28），从而允许定子 28）和转子/飞轮（10）可调节。 当从（旋转模式）提供能量或从（旋转降落模式）飞轮（10）提取能量时，定子（28）被定位成使得间隙g1小，以在定子（28）之间提供强电磁相互作用 ）和飞轮（10）。 相反，当飞轮（10）空转时，定子（28）被定位成使得间隙g1足够大以最小化飞轮（10）上的电磁阻力。
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公开(公告)号：WO1995027311A1
公开(公告)日：1995-10-12
申请号：PCT/US1995004053
申请日：1995-03-30
Applicant: UNITED TECHNOLOGIES CORPORATION
IPC: H01L27/118
CPC classification number: H01L27/11801
Abstract: A linear, bipolar-type application-specific integrated circuit includes a silicon substrate having a plurality of columns of device primitives or cells. Each cell comprises a plurality of identical NPN and PNP transistors flanking a centrally-located capacitor. Each transistor has dual emitters, bases and collectors. Open field areas are reserved on the silicon substrate on the sides of the columns of cells. Formed in these open field areas are precise thin film silicon chromium resistors. Power planes are also routed in these open field areas. A ground plane is routed in the vicinity of the centrally-located capacitor. Standard analog circuits are personalized using two layers of metallization interconnects.
Abstract translation: 线性双极型专用集成电路包括具有多列器件基元或单元的硅衬底。 每个单元包括位于中心位置的电容器两侧的多个相同的NPN和PNP晶体管。 每个晶体管具有双重发射器，基极和集电极。 开放场区域保留在单元格列侧面的硅衬底上。 在这些开放场地形成的是精密的薄膜硅铬电阻。 电力平面也可以在这些开阔的地区进行路由。 接地平面位于中心位置的电容器附近。 标准模拟电路使用两层金属化互连进行个性化。
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公开(公告)号：WO1995027124A1
公开(公告)日：1995-10-12
申请号：PCT/US1995003526
申请日：1995-03-20
Applicant: UNITED TECHNOLOGIES CORPORATION
IPC: F01D11/00
CPC classification number: F01D11/02 , F01D11/001 , F05D2260/231
Abstract: An airfoil for a gas turbine engine includes a platform having an integral heat shield extending over a seal. Various construction details are developed that disclose a heat shield that protects the seal structure from damage due to exposure to hot gases within the gas turbine engine. In a particular embodiment, a turbine vane includes a platform having a heat shield extending from the leading edge of the platform and a recess. The heat shield extends over the outward surface of a honeycomb seal that is disposed within the recess.
Abstract translation: 用于燃气涡轮发动机的翼型件包括具有在密封件上延伸的整体式热屏蔽的平台。 开发了各种结构细节，其公开了一种隔热罩，其保护密封结构免受由于暴露于燃气涡轮发动机内的热气体的损害。 在特定实施例中，涡轮叶片包括具有从平台的前缘延伸的隔热罩和凹槽的平台。 隔热罩在布置在凹槽内的蜂窝密封件的外表面上延伸。
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公开(公告)号：WO1995024339A1
公开(公告)日：1995-09-14
申请号：PCT/US1995002285
申请日：1995-02-23
Applicant: UNITED TECHNOLOGIES CORPORATION
IPC: B64C27/473
CPC classification number: B64C27/473
Abstract: An expandable spar filler block (10) device for use in combination with a spar member (108) of an articulated main rotor assembly of a helicopter. A preferred embodiment of the device includes first and second filler members (20, 22) and an expansion mechanism. Each filler member includes a spar engagement surface that is complementary to the inner mold line (IML) surfaces of the spar member and first and second tapered surfaces. The expansion mechanism for the preferred embodiment of the expandable spar filler block device is a pull shim (40) that includes a first segment and a constant tapered segment having tapered surfaces that are complementary to the first tapered surfaces of the filler members. The spar engagement surfaces and the tapered surfaces of the constant tapered segment are coated with a paste adhesive, and the expandable spar filler block device is inserted in the spar cavity of the spar member with the coated spar engagement surfaces adjacent the IML surfaces defining the spar cavity and the coated tapered surfaces of the pull shim adjacent the first tapered surfaces of the filler members. The constant thickness segment of the pull shim is manipulated to exert a motive force that causes the tapered surfaces thereof to slidingly interact with the first tapered surfaces of the filler members such that the spar engagement surfaces are displaced into abutting engagement with the IML surfaces of the spar member.
Abstract translation: 一种与直升机的铰接主转子组件的翼梁构件（108）组合使用的可膨胀翼梁填料块（10）装置。 装置的优选实施例包括第一和第二填料构件（20,22）和膨胀机构。 每个填充构件包括与翼梁构件和第一和第二锥形表面的内模线（IML）表面互补的翼梁接合表面。 用于可膨胀翼梁填料块装置的优选实施例的膨胀机构是包括第一段和具有与填充构件的第一锥形表面互补的锥形表面的恒定锥形段的牵引垫片（40）。 恒定锥形段的翼梁接合表面和锥形表面涂覆有糊状粘合剂，并且可膨胀翼梁填料块装置插入翼梁构件的翼梁腔中，涂覆的翼梁接合表面邻近限定翼梁的IML表面 并且所述拉动垫片的所述涂覆的锥形表面邻近所述填充件的所述第一锥形表面。 拉动垫片的恒定厚度段被操纵以产生使其锥形表面与填充构件的第一锥形表面滑动相互作用的动力，使得翼梁接合表面被移位成与其中的IML表面邻接接合 翼梁会员
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40.发明申请A PROCESS FOR THE ELECTROPHORETIC DEPOSITION OF DEFECT-FREE METALLIC OXIDE COATINGS 审中-公开无缺陷金属氧化物涂层的电沉积工艺
公开(公告)号：WO1995023246A1
公开(公告)日：1995-08-31
申请号：PCT/US1995002053
申请日：1995-02-17
Applicant: UNITED TECHNOLOGIES CORPORATION
IPC: C25D13/02
CPC classification number: C25D13/02
Abstract: A process for electrophoretically depositing a metal oxide coating onto a substrate (16) immersing an electrically conductive substrate (16) in a sol (10) that comprises metal hydrate particles suspended in a medium comprising an alcohol and water. A direct current potential is applied between the substrate (16) and an anode (26) immersed in the sol (10) to electrophoretically deposit metal hydrate particles from the sol (10) onto the substrate (16). Simultaneously, gas bubbles are passed over the substrate (16) to remove hydrogen that forms on the substrate (16) during electrophoretic deposition. The metal hydrate coated substrate (16) is then removed from the sol (10), and heated to dry the coating and transform the metal hydrate to its corresponding metal oxide.
Abstract translation: 一种用于将金属氧化物涂层电泳沉积到将导电基底（16）浸入溶胶（10）中的基底（16）上的方法，所述溶胶包括悬浮在包含醇和水的介质中的金属水合物颗粒。 在衬底（16）和浸入溶胶（10）中的阳极（26）之间施加直流电势，以将金属水合物颗粒从溶胶（10）电泳沉积到衬底（16）上。 同时，在电泳沉积期间，气泡通过衬底（16）以去除在衬底（16）上形成的氢。 然后从溶胶（10）中除去金属水合物涂覆的基材（16），并加热以干燥涂层并将金属水合物转化成其相应的金属氧化物。
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