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    TURBINE BYPASS WORKING FLUID ADMISSION
    352.
    发明申请
    TURBINE BYPASS WORKING FLUID ADMISSION 审中-公开
    涡轮机旁路工作流体入场

    公开(公告)号：WO1993019982A1

    公开(公告)日：1993-10-14

    申请号：PCT/US1992008931

    申请日：1992-10-19

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  MCAULIFFE, Christopher ,  MAHER, John, F, Jr.

    IPC: B64D13/08

    CPC classification number: B64D13/00 ,  F02C3/32

    Abstract: An air cycle machine (10) has a first stage turbine (60) mounted to a central portion of a common shaft (12), a compressor (50) mounted to the central portion of the shaft (12), a second stage turbine (30) mounted to a first end of the shaft (12), and a fan (40) mounted to a second end of the shaft (12), all for rotation therewith about a longitudinal axis (14). The first and second stage turbines (60, 30) are operative to extract energy from a flow of compressed air for driving the shaft (12), and the fan (40) and the compressor (50), in rotation about the axis (14). A bypass air discharge nozzle (20) is disposed coaxially with the turbine shroud (32) of the outboard turbine (30) at the outlet (134) thereof or downstream thereof at the discharge end (38) of the turbine diffuser (36) so as to receive in a central region the turbine exhaust (3) discharging from the turbine (30) and to define an annular flow inlet (28) through which a flow of bypass air (5) is directed into an outer circumferential region thereof to flow substantially parallel to and about the cooled expanded conditioning air exhaust flow (3) discharged from the turbine (30).

    IMPROVED COOLING FLUID EJECTOR
    354.
    发明申请
    IMPROVED COOLING FLUID EJECTOR 审中-公开
    改进的冷却流体喷射器

    公开(公告)号：WO1993016275A1

    公开(公告)日：1993-08-19

    申请号：PCT/US1993001081

    申请日：1993-02-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  ANTONELLIS, Stephen, M.

    IPC: F02C07/18

    CPC classification number: F01D11/001 ,  F01D11/025

    Abstract: A turbine section having a seal cavity with effectively continuous flow surfaces is disclosed. Various construction details are developed which disclose a fluid cooled stator assembly having a plurality of ejectors for flowing cooling fluid into the seal cavity. In one embodiment, the ejectors (114) include a wall (132) which have circumferentially spaced mating edges (134, 136) arranged in a cascade type configuration. The arrangement of the walls provides an effectively continuous flow surface for the radially flowing annulus of cooling fluid within a seal cavity (108). In an alternate embodiment, an opening (152) between adjacent mating edges (154, 156) provides access to mechanical fasteners (162) which retain a sealing shroud (164) to a stator assembly (150).

    Abstract translation: 公开了具有有效连续流动表面的密封腔的涡轮部分。 开发了各种结构细节，其公开了具有用于将冷却流体流入密封腔的多个喷射器的流体冷却的定子组件。 在一个实施例中，喷射器（114）包括壁（132），其具有以级联类型配置布置的周向间隔开的配合边缘（134,136）。 壁的布置为密封空腔（108）内的径向流动的冷却流体环提供有效连续的流动表面。 在替代实施例中，在相邻的配合边缘（154,156）之间的开口（152）提供了将密封罩（164）保持在定子组件（150）上的机械紧固件（162）的通路。

    LOW NOx COMBUSTION PILOTED BY LOW NOx PILOTS
    356.
    发明申请
    LOW NOx COMBUSTION PILOTED BY LOW NOx PILOTS 审中-公开
    低NO x PILOTS引起的低NOx燃烧

    公开(公告)号：WO1993010400A1

    公开(公告)日：1993-05-27

    申请号：PCT/US1992009808

    申请日：1992-11-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  COLKET, Meredith, B., III ,  SEERY, Daniel, J. ,  SANGIOVANNI, Joseph, J.

    IPC: F23D23/00

    CPC classification number: F23C13/00 ,  F23D23/00

    Abstract: An improved method of burning a hydrocarbon fuel in a combustion system includes burning the fuel in a main burner under fuel-lean conditions to produce a main flame and burning a low heating value fuel in a pilot burner to stabilize the main flame and limit the amount of NOx produced in the pilot burner. The pilot fuel can inherently have a low heating value, can be diluted high heating value fuel, or can be made by partially oxidizing a high heating value fuel. An improved combustion system for burning a hydrocarbon fuel with limited NOx emissions has a main burner (2), a pilot burner (10), and a partial oxidation stage (4) capable of converting a high heating value fuel to a low heating value fuel in a partial oxidation reaction. The system also has means for burning the low heating value fuel in the pilot burner. The system can include means (16) for removing heat from the partial oxidation stage or low heating value fuel to lower the temperature of the pilot flame.

    Abstract translation: 在燃烧系统中燃烧烃燃料的改进方法包括在燃料稀燃条件下燃烧主燃烧器中的燃料以产生主火焰并在引燃燃烧器中燃烧低热值燃料以稳定主火焰并限制该量 在导向燃烧器中产生的NOx。 引燃燃料本身可以具有低热值，可以稀释高热值燃料，或者可以通过部分氧化高热值燃料来制造。 用于燃烧具有有限NOx排放物的碳氢化合物燃料的改进的燃烧系统具有主燃烧器（2），引燃燃烧器（10）和能够将高热值燃料转化为低热值燃料的部分氧化级（4） 在部分氧化反应中。 该系统还具有燃烧引燃燃烧器中的低热值燃料的装置。 该系统可以包括用于从部分氧化阶段除去热量的装置（16）或低热值燃料以降低引燃火焰的温度。

    FIBER REINFORCED GLASS MATRIX COMPOSITES WITH SECONDARY MATRIX REINFORCEMENT
    357.
    发明申请
    FIBER REINFORCED GLASS MATRIX COMPOSITES WITH SECONDARY MATRIX REINFORCEMENT 审中-公开
    具有二次矩阵加固的纤维增强玻璃基体复合材料

    公开(公告)号：WO1993007097A1

    公开(公告)日：1993-04-15

    申请号：PCT/US1992008653

    申请日：1992-10-09

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  TREDWAY, William, K. ,  MUSSON, Craig, W. ,  CHEN, Otis, Y.

    IPC: C03C14/00

    CPC classification number: C03C14/004 ,  C03C14/002 ,  C03C2214/02 ,  C03C2214/04 ,  Y10T428/24124 ,  Y10T428/24942 ,  Y10T428/249928 ,  Y10T428/25 ,  Y10T428/30

    Abstract: A fiber reinforced glass matrix composite has a glass matrix and a plurality of primary and secondary reinforcing fibers dispersed in the matrix. The secondary reinforcing fibers are shorter than the primary fibers. The composite may be made by uniformly distributing the secondary reinforcing fibers in a dispersant. A glass powder is mixed in a carrier liquid to create a slurry and the secondary reinforcing fibers and dispersant are slowly added to the slurry so the fibers uniformly disperse as they are added. A binder is also added to the slurry. A continuous fiber is impregnated with the slurry and the impregnated fiber is dried to remove the carrier liquid. The impregnated yarn is cut to a suitable length and molded by a suitable molding method to form a fiber reinforced glass matrix composite.

    Abstract translation: 纤维增强玻璃基复合材料具有分散在基体中的玻璃基体和多个初级和次级增强纤维。 次级增强纤维比初级纤维短。 复合材料可以通过将二次增强纤维均匀分布在分散剂中而制成。 将玻璃粉末在载液中混合以产生浆料，并将第二增强纤维和分散剂缓慢加入到浆料中，使得纤维在添加时均匀分散。 还向浆料中加入粘合剂。 用浆料浸渍连续纤维，干燥浸渍的纤维以除去载液。 将浸渍的纱线切割成合适的长度并通过合适的模制方法模制以形成纤维增强的玻璃基质复合材料。

    METHOD AND APPARATUS TO INSTALL AND REMOVE HEAVY COMPONENTS
    358.
    发明申请
    METHOD AND APPARATUS TO INSTALL AND REMOVE HEAVY COMPONENTS 审中-公开
    安装和拆卸重型部件的方法和装置

    公开(公告)号：WO1993006343A1

    公开(公告)日：1993-04-01

    申请号：PCT/US1992007574

    申请日：1992-09-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  DUESLER, Paul, W. ,  MANNING, Frank, B.

    IPC: F01D25/28

    CPC classification number: F01D25/285 ,  F02C7/32 ,  Y02T50/671

    Abstract: A method and apparatus to install and remove heavy components mounted on a base structure is disclosed. Various construction details are developed which provide means for coupling the component and base structure in a manner permitting relative rotation and translation about an axis of rotation. In one embodiment, an aircraft engine component (18) has a pair of hooks (32) and an aircraft engine (10) has a pair of pins (46) which engage the hooks to couple the component and engine to permit rotational and translational motion of the component relative to the engine. For this embodiment, a method for relative motion between an installed and uninstalled condition is comprised of maneuvering the component and engine between a coupled and uncoupled position, moving the coupled component relative to the engine about the axis of rotation, and manipulating a fastener means between a secured and unsecured position.

    MANEUVER FEEL SYSTEM FOR A ROTARY WING AIRCRAFT
    359.
    发明申请
    MANEUVER FEEL SYSTEM FOR A ROTARY WING AIRCRAFT 审中-公开
    用于旋转飞行器的MANEUVER FEEL系统

    公开(公告)号：WO1993005464A1

    公开(公告)日：1993-03-18

    申请号：PCT/US1992007126

    申请日：1992-08-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  GOLD, Phillip, J. ,  WRIGHT, Stuart, C.

    IPC: G05D01/10

    CPC classification number: G05D1/0858 ,  G05D1/0061

    Abstract: A rotary wing aircraft flight control system (21) which receives signals indicative of aircraft pitch rate (88), pitch attitude (86), bank angle (87) and airspeed (66), and responds to a pitch command from a sidearm controller (29) to control the pitch of an aircraft comprises means for scheduling and providing a set point signal indicative of the desired aircraft pitch rate of change, means for computing the difference between the said point and the pitch rate signal, and for providing a pitch rate error signal indicative thereof, inverse model means (56) responsive to said set point signal for scheduling a feedforward command signal to drive the aircraft to respond in a manner which is essentially equal to said set point signal, means for providing maneuvering feel on the sidearm controller (29) when the bank angle of the aircraft exceeds a predetermined value by conditioning said set point signal, means for integrating over time said conditioned set point signal to provide a desired pitch attitude set point, for comparing said pitch attitude set point and the pitch attitude signal (86) and providing a pitch attitude error signal indicative of the difference, and means responsive to said pitch rate error signal, said feedforward command signal, and said pitch attitude error signal, for providing a pitch command signal to the main rotor of the aircraft.

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