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1. 发明申请

WO1995026010A1 A METHOD AND APPARATUS FOR IDENTIFYING THE ORIENTATION OF A DOT MATRIX CODE MARKING OF AN ARTICLE 审中-公开
标题翻译：用于识别文章的基准矩阵标记的方向的方法和装置
公开(公告)号：WO1995026010A1
公开(公告)日：1995-09-28
申请号：PCT/GB1995000572
申请日：1995-03-16
申请人： ROLLS-ROYCE PLC , CLARKE, Michael, Andrew, Nadin , BOOTH, Christopher, Roy
发明人： ROLLS-ROYCE PLC
IPC分类号： G06K07/10
CPC分类号： G06K7/1093 , G06K7/14 , G06K7/1443 , G06K7/1456
摘要： An apparatus for identifying a component (10) carrying a dot matrix code comprises a lamp (14) illuminating the dot matrix code, a video camera (18) for reading the illuminated dot matrix code. A computer (20) has an image grabber card (22) to produce a digitised image of the dot matrix code. The personal computer (20) has algorithms (24, 26, 28, 30 and 32) to measure the distances between every dot located in the digitised image, to determine the fundamental inter dot spacing (D). The dots separated by the fundamental inter dot spacing (D) lie in rows and columns of the dot matrix code. There are means to determine the angles ( beta and alpha ) between the dots which are in the rows and columns and a camera datum. There are means to determine the orientation and location of the dot matrix code from the angles ( beta and alpha ).
摘要翻译：用于识别携带点阵码的部件（10）的装置包括照亮点阵码的灯（14），用于读取照明点阵码的摄像机（18）。计算机（20）具有图像获取卡（22）以产生点阵码的数字化图像。个人计算机（20）具有测量位于数字化图像中的每个点之间的距离的算法（24,26,28,30和32），以确定基本间距（D）。由基点间距（D）分隔的点位于点阵码的行和列中。有确定行和列之间的点之间的角度（β和α）以及相机基准的方法。有从角度（β和α）确定点阵代码的方向和位置的方法。

2. 发明申请

WO1992019915A1 COMBUSTION CHAMBER ASSEMBLY IN A GAS TURBINE ENGINE 审中-公开
标题翻译：燃气轮机组合在燃气涡轮发动机中
公开(公告)号：WO1992019915A1
公开(公告)日：1992-11-12
申请号：PCT/GB1992000745
申请日：1992-04-23
申请人： ROLLS-ROYCE PLC , BURNELL, Anthony, David , PRICE, Peter, David
发明人： ROLLS-ROYCE PLC
IPC分类号： F23R03/10
CPC分类号： F23R3/10 , Y02T50/675
摘要： Overrich regions of fuel mixture in the combustion chamber of a gas turbine engine are dispersed by a jet of air directed into the region. Plumes of fuel/air mixture from adjacent airspray burners overlap to create overrich regions which tend to produce soot. Aligned apertures (20) in the head of the combustion chamber direct jets of high pressure air at the regions with as little loss of momentum as possible, to disperse them. The apertures (20) may be in the form of slots to provide fan-shaped jets.

3. 发明申请

WO1992018760A1 A COMBUSTION CHAMBER ASSEMBLY 审中-公开
标题翻译：燃烧室组件
公开(公告)号：WO1992018760A1
公开(公告)日：1992-10-29
申请号：PCT/GB1992000017
申请日：1992-01-06
申请人： ROLLS-ROYCE PLC , TAYLOR, David, Howard , GRIFFIN, Arthur, Bernard
发明人： ROLLS-ROYCE PLC
IPC分类号： F02C07/20
CPC分类号： F02C7/20 , F23R3/60
摘要： The smaller diameter end of a first stiff frustoconical casing member (74) is secured to a compressor casing (34) and the smaller diameter end of a second stiff frustoconical casing member (80) is secured to the nozzle guide vanes (40). A plurality of hollow axially extending members (86) are secured to the first and second stiff frustoconical members (74, 80) to transfer tensile and compressive stresses between the compressor casing (34) and the nozzle guide vanes (40). The larger diameter end of the first stiff frustoconical member (74) is secured to an engine casing (52) by a first radially and axially flexible member (88) to define a second chamber (100), and the larger diameter end of the second stiff frustoconical member (80) is secured to the engine casing (52) by a second radially and axially flexible member (94) to define a third chamber (102). The hollow axially extending members (86) define passages (104) to allow cooling air to flow from the first chamber (100) through the second chamber (102) to a turbine. The axially extending members (86) pass circumferentially between adjacent tubular combustion chambers (42) which have their axes arranged radially.
摘要翻译：第一刚性截头圆锥形壳体构件（74）的较小直径端固定到压缩机壳体（34），并且第二刚性截头圆锥形壳体构件（80）的较小直径端固定到喷嘴导向叶片（40）。多个中空的轴向延伸构件（86）固定到第一和第二刚性截头圆锥构件（74,80），以在压缩机壳体34和喷嘴导向叶片40之间转移拉伸和压缩应力。第一刚性截头圆锥形构件（74）的较大直径的端部通过第一径向和轴向柔性构件（88）固定到发动机壳体（52），以限定第二室（100），并且第二刚性的截头圆锥形构件（80）通过第二径向和轴向柔性构件（94）固定到发动机壳体（52），以限定第三室（102）。空心轴向延伸构件（86）限定通道（104），以允许冷却空气从第一室（100）通过第二室（102）流动到涡轮机。轴向延伸构件（86）周向地在相邻的管状燃烧室（42）之间通过，这些管状燃烧室的轴线径向布置。

4. 发明申请

WO1992017686A1 TURBINE CASING 审中-公开
标题翻译：涡轮机
公开(公告)号：WO1992017686A1
公开(公告)日：1992-10-15
申请号：PCT/GB1992000024
申请日：1992-01-07
申请人： ROLLS-ROYCE PLC , HUTCHINSON, David
发明人： ROLLS-ROYCE PLC
IPC分类号： F01D11/08
CPC分类号： F01D11/18
摘要： A turbine casing (20) is surrounded by a cowling (29) so that a gap (31) is defined between them for the flow of cooling air. The gap (31) between the cowling (29) and the casing (20) is locally reduced adjacent thickened casing portions (27) in order to provide increased velocity cooling air flow over those casing portions (27).
摘要翻译：涡轮机壳体（20）由整流罩（29）围绕，使得它们之间限定用于冷却空气流动的间隙（31）。在整流罩（29）和壳体（20）之间的间隙（31）在加厚的套管部分（27）附近局部地减小，以便在这些套管部分（27）上提供增加的速度冷却空气流。

5. 发明申请

WO1992007221A1 GASTURBINE COMBUSTION CHAMBER AND METHOD OF OPERATION THEREOF 审中-公开
标题翻译： GASTURBINE燃烧室及其运行方法
公开(公告)号：WO1992007221A1
公开(公告)日：1992-04-30
申请号：PCT/GB1991001658
申请日：1991-09-26
申请人： CURRIN, John, Oakey +lm , ROLLS-ROYCE PLC , TOON, Ian, James , O'DELL, Stephen, James , WILLIS, Jeffrey, Douglas
发明人： CURRIN, John, Oakey +lm , ROLLS-ROYCE PLC , CURRIN, Paul, Royston +di
IPC分类号： F23R03/14
CPC分类号： F23R3/346 , F23C6/047 , F23R3/14
摘要： A gas turbine engine combustion chamber (36) which has staged combustion to reduce nitrous oxides comprises a first radial flow swirler (70) and a second radial flow swirler (74) which supply primary air into a first fuel and air mixing zone (64). A pilot injector (86) only supplies fuel to be burnt into the mixing zone (64) at low power levels. At high power levels primary fuel injectors (88) inject fuel into the passages (72, 80) formed between the vanes (70, 74) of the first and second swirlers so that fuel and air mixture flows into the first fuel and air mixing zone (64) to be burnt. Simultaneously secondary fuel injectors (104) inject fuel into an annular secondary fuel and air mixing zone (94) which surrounds the first mixing zone (64). Fuel and air from the second mixing zone (94) flow through apertures (106) into the combustion chamber (36) downstream of the first mixing zone (64) and the additional fuel is burnt in the zone (112).
摘要翻译：具有分段燃烧以减少一氧化二氮的燃气涡轮发动机燃烧室（36）包括将一次空气供应到第一燃料和空气混合区（64）中的第一径向流旋流器（70）和第二径向流旋流器（74）。先导喷射器（86）仅在低功率水平下将待燃烧的燃料供入混合区（64）。在高功率水平下，初级燃料喷射器（88）将燃料喷射到形成在第一和第二旋流器的叶片（70,74）之间的通道（72,80）中，使得燃料和空气混合物流入第一燃料和空气混合区（64）被烧。同时二次燃料喷射器（104）将燃料喷射到围绕第一混合区（64）的环形二次燃料和空气混合区（94）中。来自第二混合区（94）的燃料和空气在第一混合区（64）的下游流过孔（106）进入燃烧室（36），并且附加燃料在区域（112）中燃烧。

6. 发明申请

WO1989005445A1 AN ACOUSTIC EMISSION TRANSDUCER AND AN ELECTRICAL OSCILLATOR 审中-公开
标题翻译：声学发射传感器和电振荡器
公开(公告)号：WO1989005445A1
公开(公告)日：1989-06-15
申请号：PCT/GB1988001008
申请日：1988-11-17
申请人： ROLLS-ROYCE PLC , HOLROYD, Trevor, John , SADLER, Michael
发明人： ROLLS-ROYCE PLC
IPC分类号： G01H11/08
CPC分类号： H03H9/176 , B06B1/0603 , B06B1/0651 , G01H11/08 , H03H9/173 , H03H9/174 , H04R17/08
摘要： An acoustic emission transducer assembly (100) comprises a baseplate (102), and a piezoceramic member (104). The piezoceramic member (104) is mounted on the baseplate (102), and the baseplate (102) is adapted for acoustic coupling to surface of a component. The baseplate (102) forms a part of a circuit board. The circuit board may be a printed ceramic circuit board with electronic components mounted thereon or a hybrid electronic circuit. The acoustic emission transducer assembly (100) is integral with a part of an electrical circuit. The piezoceramic member (104) is arranged to lie over a circular depression formed on a surface of the baseplate (102). The piezoceramic member (104) has an annular peripheral region (122) by which it is secured to the baseplate (102). An electrical oscillator is also provided which comprises a piezoceramic member which is mounted on a baseplate. The baseplate again forms a part of a circuit board.
摘要翻译：声发射换能器组件（100）包括基板（102）和压电陶瓷构件（104）。压电陶瓷构件（104）安装在基板（102）上，并且基板（102）适于与部件表面的声耦合。基板（102）形成电路板的一部分。电路板可以是其上安装有电子部件的印刷陶瓷电路板或混合电子电路。声发射换能器组件（100）与电路的一部分是一体的。压电陶瓷构件（104）布置成位于形成在基板（102）的表面上的圆形凹部上。压电陶瓷构件（104）具有环形周边区域（122），固定到基板（102）。还提供了一种电振荡器，其包括安装在基板上的压电陶瓷构件。底板再次形成电路板的一部分。

7. 发明申请

WO1995023298A1 A MAGNETIC BEARING 审中-公开
标题翻译：磁性轴承
公开(公告)号：WO1995023298A1
公开(公告)日：1995-08-31
申请号：PCT/GB1995000378
申请日：1995-02-23
申请人： ROLLS-ROYCE PLC , COOMBS, Timothy, Arthur
发明人： ROLLS-ROYCE PLC
IPC分类号： F16C39/06
CPC分类号： F16C32/0438 , Y10S505/876 , Y10S505/903 , Y10S505/905
摘要： A magnetic thrust bearing (110) comprises a magnet (112) mounted on a shaft (114) and a plurality of equi-angularly spaced superconductors (116) mounted on a static structure (118). Each superconductor (116) is mounted onto the static structure (118) by a parallel hinge strip (120) which allows the superconductor (116) to move radially relative to the axis of rotation of the shaft (114). The radial movement of the superconductors (116) changes the cross-sectional area of the magnetic field between the magnet and the superconductors (116) and this changes the stiffness of the magnetic bearing (110). The superconductors (116) move radially due to the pivoting of the parallel hinge strips (120) due to changes in the loads acting on the magnetic bearing (110). It is possible to detect movement of the shaft and to actively move the superconductors to control the stiffness of the magnetic bearing and to control the clearance in the magnetic bearing, as in figure 5.
摘要翻译：磁性止推轴承（110）包括安装在轴（114）上的磁体（112）和安装在静态结构（118）上的多个等角间隔的超导体（116）。每个超导体（116）通过平行铰链条（120）安装到静态结构（118）上，该平行铰链条允许超导体（116）相对于轴（114）的旋转轴线径向移动。超导体（116）的径向移动改变磁体和超导体（116）之间的磁场的横截面面积，并且这改变了磁性轴承（110）的刚度。由于作用在磁性轴承（110）上的负载的变化，超导体（116）由于平行铰链条（120）的枢转而径向移动。可以检测轴的运动，并主动移动超导体以控制磁性轴承的刚度并控制磁性轴承的间隙，如图5所示。

8. 发明申请

WO1993021425A1 ROTORS FOR GAS TURBINE ENGINES 审中-公开
标题翻译：用于气体涡轮发动机的转子
公开(公告)号：WO1993021425A1
公开(公告)日：1993-10-28
申请号：PCT/GB1993000372
申请日：1993-02-23
申请人： ROLLS-ROYCE PLC , KNOTT, David, Sydney
发明人： ROLLS-ROYCE PLC
IPC分类号： F01D11/00
CPC分类号： F01D11/008 , F01D5/3007
摘要： Fan blades (14) of a rotor stage (12) do not have platforms and separate wall members (20) are provided to bridge the space between adjacent blades (14). The wall members (20) define an inner wall of a flow annulus through the rotor (12). Each of the wall members (20) has a plurality of hooks (27) and (28) which extend radially inwardly to engage correspondingly shaped hooks (30) and (31) provided on the radially outer face (18) of the disc (16). Further hooks (29, 38) engage rings (34, 36) mounted on the rotor (12) adjacent the disc (16) to lock the wall member (20) in position. This ensures that the hooks (27) and (28) on the wall member (20) engage the hooks (30) and (31) on the radially outer face (18) of the disc (16).
摘要翻译：转子平台（12）的风扇叶片（14）不具有平台，并且提供分离的壁构件（20）以桥接相邻叶片（14）之间的空间。壁构件（20）通过转子（12）限定流动环的内壁。每个壁构件（20）具有多个径向向内延伸的钩（27）和（28），以接合设置在盘（16）的径向外表面（18）上的相应形状的钩（30）和（31））。另外的钩（29,38）接合安装在邻近盘（16）的转子（12）上的环（34,36），以将壁构件（20）锁定就位。这确保壁构件（20）上的钩（27）和（28）接合在盘（16）的径向外表面（18）上的钩（30）和（31）。

9. 发明申请

WO1993006007A1 DUCTED FAN GAS TURBINE ENGINE ACCESSORY DRIVE SYSTEM 审中-公开
标题翻译：导向风机涡轮发动机附件驱动系统
公开(公告)号：WO1993006007A1
公开(公告)日：1993-04-01
申请号：PCT/GB1992001179
申请日：1992-06-30
申请人： ROLLS-ROYCE PLC , NEWTON, Arnold, Charles
发明人： ROLLS-ROYCE PLC
IPC分类号： B64D41/00
CPC分类号： B64D41/007 , F02C7/32 , Y02T50/44 , Y02T50/671
摘要： A ducted fan gas turbine engine (10) includes a fan (13) which is driven by a low pressure turbine (19) via a load transmitting shaft (24). The load transmitting shaft (24) additionally drives the accessories (28-31) of the engine (10) and the aircraft upon which it is mounted. In the event of an engine failure, the power produced by the windmilling of the engine fan (13) is sufficient to provide continuity of drive to the accessories (28-31).
摘要翻译：风管式燃气涡轮发动机（10）包括通过负载传递轴（24）由低压涡轮机（19）驱动的风扇（13）。负载传递轴（24）另外驱动发动机（10）的附件（28-31）和安装在其上的飞行器。在发动机故障的情况下，通过发动机风扇（13）的风车产生的动力足以提供对附件（28-31）的驱动连续性。

10. 发明申请

WO1993002920A1 GAS TURBINE ENGINE NACELLE ASSEMBLY 审中-公开
标题翻译：燃气轮机发动机组件
公开(公告)号：WO1993002920A1
公开(公告)日：1993-02-18
申请号：PCT/GB1992000994
申请日：1992-06-03
申请人： ROLLS-ROYCE PLC , NEWTON, Arnold, Charles
发明人： ROLLS-ROYCE PLC
IPC分类号： B64D29/00
CPC分类号： B64D29/00
摘要： A gas turbine engine nacelle assembly (10) comprises a pylon (13) for mounting the assembly on an aircraft, a nacelle (11) and a gas turbine engine (12) enclosed within the nacelle (11). Part (15) of the nacelle (11) is structurally integral with the pylon (13) and has the remainder of the nacelle (11) attached to it. The nacelle part (15) additionally provides at least partial support for the gas turbine engine (12). The arrangement provides weight savings.
摘要翻译：燃气涡轮发动机舱组件（10）包括用于将组件安装在飞机上的吊架（13），封闭在机舱（11）内的机舱（11）和燃气涡轮发动机（12）。机舱（11）的部分（15）在结构上与塔架（13）成一体，并且机舱（11）的其余部分连接到其上。机舱部分（15）另外为燃气涡轮发动机（12）提供至少部分支撑。该装置可以节省重量。

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