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    Variable size bleed port for jet engines
    1.
    发明授权
    Variable size bleed port for jet engines 失效
    喷气发动机可变尺寸出油口

    公开(公告)号：US3909152A

    公开(公告)日：1975-09-30

    申请号：US40131173

    申请日：1973-09-27

    Applicant: UNITED AIRCRAFT CORP

    Inventor： RANNENBERG GEORGE C

    IPC: F04D27/02

    CPC classification number: F04D27/0215 ,  F04D27/023 ,  Y10T137/7753 ,  Y10T137/7848

    Abstract: A simple, substantially fail-safe jet engine bleed used for aircraft accessories is designed to have a small bleed port area for high power operating conditions of the engine and a larger bleed port area for lesser power operating conditions. The variable port can be made to vary its size in response to the power lever position, engine rpm, compressor bleed temperature or an engine pressure ratio.

    Abstract translation: 用于飞机附件的简单，基本上故障安全的喷气发动机排放设计为具有用于发动机的高功率操作条件的较小的排放口区域和用于较小功率运行条件的较大的排放口区域。 变量端口可以响应于动力杆位置，发动机转速，压缩机排放温度或发动机压力比来改变其尺寸。

    Novel fuel cell structure
    2.
    发明授权
    Novel fuel cell structure 失效
    新型燃料电池结构

    公开(公告)号：US3905832A

    公开(公告)日：1975-09-16

    申请号：US43344674

    申请日：1974-01-15

    Applicant: UNITED AIRCRAFT CORP

    Inventor： TROCCIOLA JOHN C

    IPC: H01M8/02 ,  H01M4/86 ,  H01M8/08 ,  H01M27/00

    CPC classification number: H01M8/08 ,  H01M4/86 ,  Y10T29/49108

    Abstract: A compact electrochemical cell comprising a pair of opposed electrodes; an electrolyte matrix containing an aqueous, ionconductive electrolyte between the opposed electrodes; and an electrolyte reservoir positioned behind and partially defined by at least one of said electrodes. The electrode partly defining the reservoir has a continuous hydrophobic surface and select hydrophilic areas substantially uniformly distributed within the boundaries of the electrode surface. The electrolyte volume of the cell is controlled by electrolyte movement between the electrolyte matrix of the cell and the reservoir through the select hydrophilic areas of the electrode, thereby stabilizing the electrochemical performance of the cell.

    Abstract translation: 一种紧凑的电化学电池，包括一对相对的电极; 在相对电极之间包含含水离子传导电解质的电解质基质; 以及位于所述电极中的至少一个之后并部分地限定的电解质储存器。 部分地限定储存器的电极具有连续的疏水表面，并且选择基本均匀分布在电极表面的边界内的亲水区域。 电池的电解质体积通过电极的电解质基质和储存器之间的电解质运动通过电极的选择的亲水区域来控制，从而稳定电池的电化学性能。

    Starting fuel control system for gas turbine engines
    5.
    发明授权
    Starting fuel control system for gas turbine engines 失效
    启动燃气轮机发动机燃料控制系统

    公开(公告)号：US3902315A

    公开(公告)日：1975-09-02

    申请号：US47880674

    申请日：1974-06-12

    Applicant: UNITED AIRCRAFT CORP

    Inventor： MARTIN ANTHONY N

    IPC: F02C7/26 ,  F02C9/04

    CPC classification number: F02C7/26

    Abstract: The fuel flow in a gas turbine engine which is started by an auxiliary compressed air supply or cartridge is initially scheduled as a function of engine speed at all ambient conditions, resulting in an initially grossly over-rich fuel-air mixture and burning downstream beyond the combustor. The temperature in the tailpipe is sensed, and control of the engine fuel flow is automatically switched from the starting control schedule to an acceleration and speed control schedule when either the tailpipe temperature is decreasing at a rate greater than a reference value, or when the tailpipe temperature increases to a preselected value selected as a function of compressor inlet pressure and engine speed. Engine tailpipe temperature is sensed by a thermocouple having its cold junction located at the engine compressor inlet so that the tailpipe measurement reflects only the heat added to the exhaust gas by combustion.

    Abstract translation: 燃气涡轮发动机中由辅助压缩空气供应或料筒启动的燃料流量最初作为所有环境条件下的发动机转速的函数进行调节，导致最初过度富含燃料 - 空气的混合物并在下游燃烧 燃烧器。 当尾管温度以大于参考值的速率下降时，或者当尾管（10）的速度下降时，感测到排气管中的温度，并且发动机燃料流量的控制被自动地从启动控制调度切换到加速和速度控制调度 温度升高到根据压缩机入口压力和发动机转速而选择的预选值。 发动机尾管温度由其冷端位于发动机压缩机入口处的热电偶感测，使得尾管测量仅反映通过燃烧而添加到排气中的热量。

    Process for fixturing a workpiece by quenching a liquid resin
    7.
    发明授权
    Process for fixturing a workpiece by quenching a liquid resin 失效
    通过淬灭液体树脂固定工件的方法

    公开(公告)号：US3897535A

    公开(公告)日：1975-07-29

    申请号：US39282473

    申请日：1973-08-29

    Applicant: UNITED AIRCRAFT CORP

    Inventor： LAPAC EDWARD F ,  MIAZGA JOSEPH F ,  MITTLEMAN IRVING M

    IPC: B23Q3/08 ,  G01N1/06 ,  G01N1/42 ,  B29C13/00 ,  B25B11/00 ,  B29C6/04

    CPC classification number: B23Q3/086 ,  G01N1/06 ,  G01N1/42

    Abstract: A process for fixturing a workpiece includes disposing a liquid organic resin workholding material within a workholder around the workpiece and quenching the assembly at between 40*F and 73*F to solidify the workholding material. The cold quench within this particular temperature range gives improved holding strength and reduces shrinkage of the organic workholding material. In one embodiment ceramic stones are heated and disposed within the workholder to heat the workholder and the workpiece prior to pouring the workholding material into the workholder. The stones further increase the holding strength of the workholding material and reduce shrinkage even more.

    Abstract translation: 用于固定工件的方法包括在工件内围绕工件设置液体有机树脂夹持材料，并在40°F至73°F之间淬火组件以固化夹持材料。 在该特定温度范围内的冷淬火提高了保持强度并降低了有机夹持材料的收缩。 在一个实施例中，陶瓷石头被加热并设置在工件夹持件内，以在将工件夹持材料注入到夹持器之前加热夹持器和工件。 石头进一步提高了夹持材料的保持力，减少了收缩。

    Centrifugal compressor boundary layer control
    8.
    发明授权
    Centrifugal compressor boundary layer control 失效
    离心压缩机边界层控制

    公开(公告)号：US3893787A

    公开(公告)日：1975-07-08

    申请号：US45125774

    申请日：1974-03-14

    Applicant: UNITED AIRCRAFT CORP

    Inventor： JONES BURTON A

    IPC: F04D27/02 ,  F04D29/68 ,  F04D7/02

    CPC classification number: F04D29/685 ,  F04D29/162 ,  F04D29/4206 ,  Y10S415/914

    Abstract: A centrifugal compressor is shown with an inlet directing a fluid thereto and a diffuser into which the compressor directs its output. A group or array of circumferential grooves are located in the surface of a stationary shroud which covers the blades of the compressor.

    Abstract translation: 示出了一个离心式压缩机，其中有一个流体引导流体和一个扩散器，压缩机引导其输出。 一组或多个周向槽位于固定护罩的覆盖压缩机叶片的表面中。

    Process of coating a gas turbine engine alloy substrate
    9.
    发明授权
    Process of coating a gas turbine engine alloy substrate 失效
    喷涂燃气轮机发动机合金基板的工艺

    公开(公告)号：US3890456A

    公开(公告)日：1975-06-17

    申请号：US38626673

    申请日：1973-08-06

    Applicant: UNITED AIRCRAFT CORP

    Inventor： DILS RAY R

    IPC: C23C28/00 ,  F01D5/28 ,  F01D21/00 ,  B44D1/14

    CPC classification number: F01D21/003 ,  C23C28/321 ,  C23C28/34 ,  C23C28/341 ,  C23C28/345 ,  C23C28/3455 ,  F01D5/288 ,  Y10S428/926 ,  Y10T428/12451 ,  Y10T428/12611 ,  Y10T428/12875 ,  Y10T428/24975

    Abstract: A method of coating a gas turbine engine alloy substrate comprising depositing a rare earth and aluminum-containing alloy initial layer to a thickness sufficient to produce and maintain an adherent irregular aluminum oxide, mechanically working the surface of the initial layer to induce irregularity and angular topography in the aluminum oxide to be produced, oxidizing the initial layer to produce a sufficiently thick and irregular aluminum oxide layer to establish mechanical adherence of a noble metal layer and prevent alloying between the initial layer and the noble metal layer, depositing a noble metal layer on the oxidized layer to a thickness of approximately 0.1-0.2 mils and oxidatively treating the coated substrate to cause additional growth of the oxide layer to metallurgically insulate the noble metal layer from the substrate and the initial metal layer.

    Abstract translation: 一种涂覆燃气涡轮发动机合金基材的方法，包括将稀土和含铝合金初始层沉积到足以产生和保持粘附的不规则氧化铝的厚度，机械地加工初始层的表面以诱导不规则性和角形地形 在要生产的氧化铝中，氧化初始层以产生足够厚且不规则的氧化铝层，以建立贵金属层的机械粘附并防止初始层和贵金属层之间的合金化，将贵金属层沉积在 氧化层至约0.1-0.2密耳的厚度，并且氧化处理涂覆的基底以引起氧化物层的额外生长，从而使贵金属层与基底和初始金属层冶金绝缘。

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