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    • 2. 发明授权
    • Cantilevered structures
    • 悬臂结构
    • US4243360A
    • 1981-01-06
    • US43421
    • 1979-05-29
    • William B. Wright
    • William B. Wright
    • F01D5/22
    • F01D5/22F05D2200/11
    • A cantilevered structure comprises two cantilevers of unequal length adapted to span a gap (L) and overlap at their free ends so that load transfer may take place from the longer to the shorter cantilever. The cantilevers have the same Youngs Modulus, cross-sectional shape and same load per unit length applied to them, and the line of action of the load transfer between the cantilevers is up to 34% of the distance (L) between their encastres. The sum of the leading moments at the encastres of such cantilevers is lower than is the case with overlapping cantilevers where the line of action of load transfer between them is more than 34% of the distance between their encastres.
    • 悬臂结构包括两个不等长度的悬臂,其适于跨越间隙(L)并且在其自由端处重叠,使得负载传递可以从较长的悬臂向较短的悬臂发生。 悬臂具有相同的杨氏模量,横截面形状和施加到它们的每单位长度的相同载荷,并且悬臂之间的载荷传递的作用线达到其承载之间的距离(L)的34%。 这种悬臂的封盖的主要时刻的总和低于重叠悬臂的情况,其中它们之间的载荷转移的作用线超过其承受者之间的距离的34%。
    • 3. 发明授权
    • Flow control method and means
    • 流量控制方法和手段
    • US5340271A
    • 1994-08-23
    • US960367
    • 1993-01-14
    • Christopher FreemanIvor J. DayWilliam B. Wright
    • Christopher FreemanIvor J. DayWilliam B. Wright
    • F04D27/02F01D17/08
    • F04D27/0215F04D27/001F04D27/0238F05D2270/101
    • The method controls gas flow in an axial flow compressor in which the flow at one or more chosen station in the direction of flow through the compressor is sensed at a series of circumferentially spaced positions. Flow variations above a predetermined limit are evaluated to initiate a response if a disturbance above a predetermined acceptable level is detected. When such a disturbance is detected, higher pressure gas bled from downstream is injected at a station to supplement the main gas flow. An incipient rotating stall cell will appear as a variation occurring sequentially at the circumferentially spaced positions. By responding to such a condition with a pressure injection, it is found possible to suppress both rotating stall and surge conditions in the compressor before this disturbance develops fully. The same method can be arranged to counter steady state distortion.
    • PCT No.PCT / GB91 / 01407 Sec。 371日期1949年1月14日 102(e)日期1993年1月14日PCT 1991年8月19日PCT PCT。 出版物WO92 / 03661 日期为1992年3月5日。该方法控制轴流式压缩机中的气流,其中在一个或多个所选站处的流动通过压缩机的流动的流动以一系列周向间隔的位置被感测。 如果检测到高于预定可接受水平的扰动,则评估高于预定极限的流量变化以启动响应。 当检测到这种干扰时,从站下游排出较高压力的气体,以补充主气流。 初始旋转失速单元将作为在周向间隔开的位置处依次发生的变化出现。 通过利用压力注入对这样的状况进行响应,可以抑制压缩机内的旋转失速和喘振状态,同时完全干扰。 可以设置相同的方法来对抗稳态失真。
    • 4. 发明授权
    • Pitch change arrangement for a variable pitch fan
    • 可变间距风扇的间距变化布置
    • US4810164A
    • 1989-03-07
    • US119475
    • 1987-11-12
    • William B. Wright
    • William B. Wright
    • F04D29/36B64C11/06B64C11/38
    • F04D29/323F01D7/00
    • A pitch arrangement for a variable pitch fan assembly of a turbofan gas turbine engine comprises a plurality of fan blades, each of which has a root portion rotatably mounted, in a thrust bearing on a fan rotor. A control ring is arranged coaxially with and is rotatably mounted on the fan rotor, and each of the fan blades is connected to the control ring by a lever arm. The pitch of the fan blades is varied by rotation of the control ring in either direction. A plurality of hydraulic rams are arranged to drive the control ring through a plurality of bell cranks. The hydraulic rams are mounted on the fan rotor so that the pistons and shafts move in a radial direction such that the centrifugal force of the pistons and shafts is applied to the bell cranks so that a counter turning movement is applied to the control ring to oppose the centrifugal turning moment of the fan blades.
    • 涡轮风扇式涡轮发动机的变桨距风扇组件的俯仰装置包括多个风扇叶片,每个风扇叶片具有可旋转地安装在风扇转子上的止推轴承中的根部部分。 控制环与风扇转子同轴地并且可旋转地安装,并且每个风扇叶片通过杠杆臂连接到控制环。 风扇叶片的间距通过控制环在任一方向的旋转而变化。 多个液压柱塞被布置成通过多个钟形曲柄来驱动控制环。 液压柱塞安装在风扇转子上,使得活塞和轴沿径向方向移动,使得活塞和轴的离心力施加到钟形曲柄,使得反向转动运动被施加到控制环以对抗 风扇叶片的离心转矩。
    • 5. 发明授权
    • Propeller module for an aero gas turbine engine
    • 用于航空燃气涡轮发动机的螺旋桨模块
    • US4688995A
    • 1987-08-25
    • US832771
    • 1986-02-25
    • William B. WrightAddison C. Maguire
    • William B. WrightAddison C. Maguire
    • B64C11/32B64C11/30B64C11/48B64D35/06
    • B64C11/306
    • A propeller module for an aero gas turbine engine comprises two contra-rotating propellers driven by a reduction gearbox positioned axially between the propellers.Pitch change mechanisms operated by a pitch change power unit are provided to change the pitch of the propeller blades. The pitch change power unit is positioned in the hub of the second multi-bladed propeller and is remote from the first multi-bladed propeller. The first and second pitch change mechanisms are mounted on the reduction gearbox. The first pitch change mechanism comprises first pitch change gears which are rotatably mounted on a carrier of the reduction gearbox by spindles which extend axially through planet gears of the gearbox. The second pitch change mechanism comprises second pitch change gears rotatably mounted on the carrier.
    • 用于航空燃气涡轮发动机的螺旋桨模块包括由轴向位于螺旋桨之间的减速齿轮箱驱动的两个反向旋转螺旋桨。 提供由变桨动力单元操作的俯仰变化机构以改变螺旋桨叶片的桨距。 变桨动力单元位于第二多叶螺旋桨的轮毂中,并且远离第一多叶螺旋桨。 第一和第二变桨机构安装在减速齿轮箱上。 第一变桨机构包括通过轴向可旋转地安装在减速齿轮箱的行星架上的第一变桨齿轮,轴通过齿轮箱的行星齿轮延伸。 第二间距变换机构包括可旋转地安装在托架上的第二变桨齿轮。
    • 10. 发明授权
    • Propeller module for an aero gas turbine engine
    • 用于航空燃气涡轮发动机的螺旋桨模块
    • US4738589A
    • 1988-04-19
    • US939884
    • 1986-12-09
    • William B. Wright
    • William B. Wright
    • B64C11/48B64C11/30F01D7/00B64C11/44
    • F01D7/00B64C11/306B64D2027/005F05D2260/74F05D2260/76Y02T50/66Y02T50/671
    • A propeller module for an aero gas turbine engine comprising two contra-rotating propellers has a reduction gear train positioned axially between the propellers. Pitch change mechanism are provided to change the pitch of the blades of both propellers independently of the differential speed of the propellers. The pitch change mechanisms comprise two sets of hydraulic motors one set of which is mounted on a carrier member of the gear train within the planet gears, the other set is mounted on the hub of the second propeller. Pitch selector valves control the supply of hydraulic fluid to the hydraulic motors, and the pitch selector valves are operated by a pitch change power unit. The pitch selector valves are positioned coaxially of the propellers and a transfer tube extends coaxially between the pitch selector valves to transfer hydraulic fluid therebetween independently of differential speed of the propellers.
    • 包括两个反向旋转螺旋桨的用于航空燃气涡轮发动机的螺旋桨模块具有轴向位于推进器之间的减速齿轮系。 提供间距改变机构,以独立于螺旋桨的差速来改变两个螺旋桨叶片的桨距。 间距改变机构包括两组液压马达,其中一组液压马达安装在行星齿轮内的齿轮系的承载构件上,另一组安装在第二螺旋桨的轮毂上。 间距选择阀控制液压马达的液压油供给,变桨选择阀由变桨动力单元操作。 沥青选择阀与螺旋桨同轴设置,传动管同时延伸在换桨之间,以独立于螺旋桨的差速传递液压油。