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1. 发明授权

US08721257B2 Rotor blade tip clearance control 有权
标题翻译：转子叶片顶端间隙控制
公开(公告)号：US08721257B2
公开(公告)日：2014-05-13
申请号：US13050367
申请日：2011-03-17
申请人： Leo V. Lewis , Marko Bacic
发明人： Leo V. Lewis , Marko Bacic
IPC分类号： F04D29/58
CPC分类号： F01D11/24 , F05D2240/11 , F05D2260/201 , Y02T50/676
摘要： A gas turbine engine has a row of circumferentially spaced rotor blades and a plurality of seal segments circumscribing the rotor blade tips and attached to a radially inward side of a casing of the engine. The seal segments are spaced from the casing by a spacing cavity. A flow of relatively hot cooling air is routed to the spacing cavity to cool the seal segments. The engine has an external cooling arrangement for impinging relatively cold cooling air on a radially outward side of the casing. The engine has a wall containing a plurality of through-holes which is attached to a radially inward side of the casing adjacent the seal segments. The wall is spaced from the casing to define a heating control chamber between the wall and the casing. The engine has one or more closable ducts which allow air to be exhausted from the heating control chamber.
摘要翻译：燃气涡轮发动机具有一排周向间隔开的转子叶片和围绕转子叶片尖端并附接到发动机壳体的径向内侧的多个密封段。密封段通过间隔腔与壳体间隔开。相对热的冷却空气的流动被引导到间隔空腔以冷却密封段。发动机具有外部冷却装置，用于在壳体的径向向外侧上冲击相对冷的冷却空气。发动机具有包含多个通孔的壁，其邻近密封段附接到壳体的径向向内侧。壁与壳体间隔开以在壁和壳体之间限定加热控制室。发动机具有允许空气从加热控制室排出的一个或多个可关闭的管道。

2. 发明申请

US20110229306A1 ROTOR BLADE TIP CLEARANCE CONTROL 有权
标题翻译：转子叶尖间隙控制
公开(公告)号：US20110229306A1
公开(公告)日：2011-09-22
申请号：US13050367
申请日：2011-03-17
申请人： Leo V. LEWIS , Marko BACIC
发明人： Leo V. LEWIS , Marko BACIC
IPC分类号： F01D11/08
CPC分类号： F01D11/24 , F05D2240/11 , F05D2260/201 , Y02T50/676
摘要： A gas turbine engine has a row of circumferentially spaced rotor blades and a plurality of seal segments circumscribing the rotor blade tips and attached to a radially inward side of a casing of the engine. The seal segments are spaced from the casing by a spacing cavity. A flow of relatively hot cooling air is routed to the spacing cavity to cool the seal segments. The engine has an external cooling arrangement for impinging relatively cold cooling air on a radially outward side of the casing. The engine has a wall containing a plurality of through-holes which is attached to a radially inward side of the casing adjacent the seal segments. The wall is spaced from the casing to define a heating control chamber between the wall and the casing. The engine has one or more closable ducts which allow air to be exhausted from the heating control chamber.
摘要翻译：燃气涡轮发动机具有一排周向间隔开的转子叶片和围绕转子叶片尖端并附接到发动机壳体的径向内侧的多个密封段。密封段通过间隔腔与壳体间隔开。相对热的冷却空气的流动被引导到间隔空腔以冷却密封段。发动机具有外部冷却装置，用于在壳体的径向向外侧上冲击相对冷的冷却空气。发动机具有包含多个通孔的壁，其邻近密封段附接到壳体的径向向内侧。壁与壳体间隔开以在壁和壳体之间限定加热控制室。发动机具有允许空气从加热控制室排出的一个或多个可关闭的管道。

3. 发明申请

US20110002771A1 ROTOR BLADE OVER-TIP LEAKAGE CONTROL 有权
标题翻译：转子叶片过压泄漏控制
公开(公告)号：US20110002771A1
公开(公告)日：2011-01-06
申请号：US12825493
申请日：2010-06-29
申请人： Leo V. LEWIS , Bengt E G BLIDMARK
发明人： Leo V. LEWIS , Bengt E G BLIDMARK
IPC分类号： F01D11/14 , F01D5/20
CPC分类号： F01D11/122 , F01D11/125
摘要： A system is provided for controlling rotor blade over-tip leakage of a working fluid in rotating machine. The system has a circumferential row of rotor blades, and a circumferential row of seal segments for sealing with the radially outer tips of the rotor blades to reduce over-tip leakage of the working fluid. The seal segments have an inboard abradable layer which is adapted to be abraded by the blade tips to form a wear track for the blade tips. The system further has one or more tip wearing bodies which are adapted to wear down the blade tips. The thickness of the abradable layer and the cold build radial positions of the blade tips, seal segments and tip wearing bodies are arranged such that, during running-in of the machine, a wear track having a uniform radius is formed in the abradable layer by the blade tips, and the tip wearing bodies also wear down the blade tips to provide a uniform blade tip radius.
摘要翻译：提供一种用于控制旋转机器中工作流体的转子叶片过尖端泄漏的系统。该系统具有周向排的转子叶片和周向排的密封段，用于与转子叶片的径向外部末端密封以减少工作流体的过度尖端泄漏。密封段具有内侧可磨损层，其适于被刀片尖端磨损以形成刀片尖端的磨损轨迹。该系统还具有一个或多个尖端磨损体，其适于磨损刀片尖端。可磨损层的厚度和叶片尖端，密封段和尖端磨损体的冷构造径向位置被布置成使得在机器进入期间，在可磨损层中形成具有均匀半径的磨损轨迹刀片尖端和尖端磨损体也磨损刀片尖端以提供均匀的刀尖半径。

4. 发明授权

US5230540A Fluid-tight joint with inclined flange face 失效
标题翻译：带有法兰面的流体接头
公开(公告)号：US5230540A
公开(公告)日：1993-07-27
申请号：US768427
申请日：1991-09-13
申请人： Leo V. Lewis , Thomas H. Hyde , Heinrich Fessler , Barry J. Marsden
发明人： Leo V. Lewis , Thomas H. Hyde , Heinrich Fessler , Barry J. Marsden
IPC分类号： F16L23/036 , F02K1/80 , F16L23/02 , F16L23/16
CPC分类号： F16L23/032 , F02K1/80 , F16L23/162
摘要： A special type of flange ring (201) for making bolted flanged joints between axially consecutive component parts of hollow fabrications, such as gas turbine aero engine casings (210). Each flange joint face (206) has, at its radially inner circumference, a radially extending sealing land or flat (216), the remainder of the flange joint face comprising, when in the unstressed condition, a frustoconical surface (209) inclined at a small angle (c.degree.) to the radial plane (207) of the sealing flat (216). The frustoconical surface (209) is drawn into contact with a complementary joint surface (208) when the bolts (204) are tightened. The flange rear face (212) is parallel to the frustoconical surface (209). This configuration creates a joint having a large line reaction force along the sealing land (216), thereby providing efficient sealing against internal pressure even when tension forces in the casing (210) are present. Alternative embodiments are described.
摘要翻译： PCT No.PCT / GB90 / 00377 Sec。 371日期1991年9月13日 102（e）1991年9月13日PCT PCT 1990年3月13日PCT公布。第WO90 / 10812号公报 1990年9月20日。一种特殊类型的法兰环（201），用于在中空制品的轴向连续部件之间制造螺栓连接的法兰接头，例如燃气轮机航空发动机外壳（210）。每个凸缘接合面（206）在其径向内圆周处具有径向延伸的密封平台或平面（216），所述凸缘接合面的其余部分在处于无应力状态时包括倾斜在与密封平台（216）的径向平面（207）的小角度（c DEG）。当螺栓（204）被紧固时，截头圆锥形表面（209）被拉伸与互补接合表面（208）接触。凸缘后表面212平行于截头圆锥表面209。这种构造产生沿着密封平台（216）具有大的线反作用力的接头，从而即使存在壳体（210）中的拉力，也能够有效地抵抗内部压力。描述了替代实施例。

5. 发明授权

US08734090B2 Combination of mechanical actuator and case cooling apparatus 有权
标题翻译：机械执行器与箱体冷却装置的组合
公开(公告)号：US08734090B2
公开(公告)日：2014-05-27
申请号：US12689661
申请日：2010-01-19
申请人： Leo V. Lewis
发明人： Leo V. Lewis
IPC分类号： F01D25/26
CPC分类号： F01D11/22 , F01D11/24 , F04D29/526 , F04D29/563 , F04D29/584
摘要： A rotor blade tip clearance control apparatus for a gas turbine engine includes a plurality of circumferentially distributed segments which form an annular shroud surrounding the outer tips of a row of rotor blades. A mechanical arrangement is operatively connected to the segments. Actuation of the arrangement causes the segments to move in a radial direction thereby controlling a clearance between the segments and the outer tips. A case cooling system supplies cooling air to an engine case to which the segments are mounted. The cooling air regulates thermal expansion of the case and thereby also controls the clearance between the segments and the outer tips.
摘要翻译：用于燃气涡轮发动机的转子叶片顶端间隙控制装置包括多个周向分布的段，其形成围绕一排转子叶片的外部尖端的环形护罩。机械装置可操作地连接到段。该布置的致动使得片段沿径向方向移动，从而控制片段和外部尖端之间的间隙。壳体冷却系统将冷却空气提供给安装有段的发动机壳体。冷却空气调节壳体的热膨胀，从而也控制区段和外端之间的间隙。

6. 发明授权

US08688245B2 System control 有权
标题翻译：系统控制
公开(公告)号：US08688245B2
公开(公告)日：2014-04-01
申请号：US13176423
申请日：2011-07-05
申请人： Marko Bacic , Leo V Lewis
发明人： Marko Bacic , Leo V Lewis
IPC分类号： G05B13/02 , G05B13/04
CPC分类号： G05B13/041 , G05B13/048
摘要： A method of controlling a system that has a finite execution time in the optimization of a cost function: J = ∑ i = 1 N ⁢ F ⁡ ( u ⁡ ( k + i | k ) , y ⁡ ( k + i | k ) ) , where N is selected such that J is convergent; k+i is the time in the future after the passage of i time increments; u(k+i|k) and y(k+i|k) are restricted to values of the respective control variables u and performance variables y that are compatible with predetermined system operational constraints; and for each time increment i=1 . . . N, values for F(u(k+i|k), y(k+i|k)) are calculated using a system model M to determine y(k+i|k) for a plurality of respective discrete values of u(k+i|k) that are limited to and representatively sampling the range of possible values of u that are compatible with the predetermined system operational constraints, J being optimised by identifying the combination {u(k+1|k),u(k+2|k), . . . u(k+N|k)} of respective discrete values u(k+i|k) over N time increments that combination yields an optimised value for J.
摘要翻译：一种控制在成本函数优化中具有有限执行时间的系统的方法：J =Σi = 1 N F⁡（u⁡（k + i | k），y⁡（k + i | k）），其中N被选择使得J是收敛的; k + i是i时间增量通过后的时间; u（k + i | k）和y（k + i | k）被限制为与预定系统操作约束兼容的各个控制变量u和性能变量y的值; 并且对于每次增量i = 1。。。使用系统模型M来计算F（u（k + i | k），y（k + i | k），y（k + i | k））的值，以对于u的多个相应的离散值来确定y（k + i | （k + i | k），其被限制并且代表性地对与预定系统操作约束兼容的u的可能值的范围进行采样，J通过识别组合{u（k + 1 | k），u（ k + 2 | k），。。。 u（k + N | k）}的N个时间增量相应的离散值u（k + i | k），该组合产生了J.

7. 发明申请

US20120022838A1 SYSTEM CONTROL 有权
标题翻译：系统控制
公开(公告)号：US20120022838A1
公开(公告)日：2012-01-26
申请号：US13176423
申请日：2011-07-05
申请人： Marko BACIC , Leo V. LEWIS
发明人： Marko BACIC , Leo V. LEWIS
IPC分类号： G06F17/10
CPC分类号： G05B13/041 , G05B13/048
摘要： A method of controlling a system that has a finite execution time in the optimisation of a cost function: J = ∑ i = 1 N  F  ( u  ( k + i | k ) , y  ( k + i | k ) ) , where N is selected such that J is convergent; k+i is the time in the future after the passage of i time increments; u(k+i|k) and y(k+i|k) are restricted to values of the respective control variables u and performance variables y that are compatible with predetermined system operational constraints; and for each time increment i=1 . . . N, values for F(u(k+i|k), y(k+i|k)) are calculated using a system model M to determine y(k+i|k) for a plurality of respective discrete values of u(k+i|k) that are limited to and representatively sampling the range of possible values of u that are compatible with the predetermined system operational constraints, J being optimised by identifying the combination {u(k+1|k),u(k+2|k), . . . u(k+N|k)} of respective discrete values u(k+i|k) over N time increments that combination yields an optimised value for J.
摘要翻译：一种控制在成本函数优化中具有有限执行时间的系统的方法：J =Σi = 1 N（F（k + i | k），y（k + i | k）），其中N被选择使得J是收敛的; k + i是i时间增量通过后的时间; u（k + i | k）和y（k + i | k）被限制为与预定系统操作约束兼容的各个控制变量u和性能变量y的值; 并且对于每次增量i = 1。。。使用系统模型M来计算F（u（k + i | k），y（k + i | k），y（k + i | k））的值，以对于u的多个相应的离散值来确定y（k + i | （k + i | k），其被限制并且代表性地对与预定系统操作约束兼容的u的可能值的范围进行采样，J通过识别组合{u（k + 1 | k），u（ k + 2 | k），。。。 u（k + N | k）}的N个时间增量相应的离散值u（k + i | k），该组合产生了J.

8. 发明申请

US20120227414A1 GAS TURBINE ENGINE SWIRLED COOLING AIR 有权
标题翻译：气体涡轮发动机旋转冷却空气
公开(公告)号：US20120227414A1
公开(公告)日：2012-09-13
申请号：US13399424
申请日：2012-02-17
申请人： Leo V. LEWIS , Timothy J. SCANLON
发明人： Leo V. LEWIS , Timothy J. SCANLON
IPC分类号： F02C6/08 , F02C7/12
CPC分类号： F01D5/082 , F05D2210/40 , F05D2260/14
摘要： A gas turbine engine has in flow series a compressor section, a combustor, and a turbine section. The engine includes a turbine section rotor disc, and a stationary wall forward of a front face or rearward of a rear face of the rotor disc. The wall defines a cavity between the stationary wall and the rotor disc, and has a plurality of air entry nozzles through which cooling air can be delivered into the cavity at an inlet swirl angle. The engine further includes a cooling air supply arrangement which accepts a flow of compressed air and supplies the compressed air to the nozzles for delivery into the cavity. The cooling air supply arrangement and the nozzles are configured such that the inlet swirl angle of the air delivered into the cavity can be varied between a first inlet swirl angle and a second inlet swirl angle.
摘要翻译：燃气涡轮发动机具有流动系列，压缩机部分，燃烧器和涡轮部分。发动机包括涡轮部分转子盘和转子盘的后表面的前面或后方的固定壁。该壁在固定壁和转子盘之间限定一个空腔，并且具有多个空气入口喷嘴，冷却空气可以通过该空气入口喷嘴以入口旋转角度输送到空腔中。发动机还包括冷却空气供应装置，其接收压缩空气流并将压缩空气供应到喷嘴以输送到空腔中。冷却空气供给装置和喷嘴构造成使得输送到空腔中的空气的入口旋转角度可以在第一入口旋转角度和第二入口旋转角度之间变化。

9. 发明申请

US20080247863A1 Sensor 有权
标题翻译：传感器
公开(公告)号：US20080247863A1
公开(公告)日：2008-10-09
申请号：US11905589
申请日：2007-10-02
申请人： Anthony G. Razzell , Lee Mansfield , Leo V. Lewis
发明人： Anthony G. Razzell , Lee Mansfield , Leo V. Lewis
IPC分类号： F04D29/08
CPC分类号： G01D5/241 , F01D11/20 , F05D2270/821 , G01B7/14
摘要： Sensors (32, 52, 72) for determining a gap between a conductive member (34, 54, 74) such as a blade in a gas turbine engine and a seal segment (31, 51) are known to use capacitive variants in order to create an electrical signal indicative of the gap width. Thermal disparities can create problems with regard to sensor ageing and accuracy. By creating a sensor incorporating a metal rod (33, 53, 74) typically integrally formed or associated with the seal segment (31, 51) and coupled through inductive coupling loops (35, 36; 55, 56; 75) it is possible to create a tuned circuit with a Q value which is more stable and therefore acceptable with regard to producing more accurate results at elevated temperatures with less problems with regard to thermal disparities.
摘要翻译：已知用于确定诸如燃气涡轮发动机中的叶片的导电构件（34,54,74）和密封段（31,51）之间的间隙的传感器（32,52,72）使用电容变型，以便产生指示间隙宽度的电信号。热差异可能会对传感器老化和精度造成问题。通过产生一个传感器，该传感器包括通常与密封段（31,51）整体形成或相连的金属杆（33,53,74），并通过电感耦合回路（35,36; 55,56; 75）耦合，创建具有更稳定的Q值的调谐电路，因此在高温下产生更准确的结果是可接受的，而在热差异方面较少的问题。

10. 发明申请

US20070189890A1 Gas turbine engine rotor ventilation arrangement 有权
标题翻译：燃气轮机发动机转子通风装置
公开(公告)号：US20070189890A1
公开(公告)日：2007-08-16
申请号：US11702589
申请日：2007-02-06
申请人： Guy D. Snowsill , Timothy J. Scanlon , Colin Young , Leo V. Lewis
发明人： Guy D. Snowsill , Timothy J. Scanlon , Colin Young , Leo V. Lewis
IPC分类号： F03B11/00
CPC分类号： F01D5/082 , F01D5/085 , F05D2260/20 , F05D2270/112
摘要： A rotor assembly for a gas turbine engine, the rotor assembly comprises at least two rotors defining a cavity therebetween. A first rotor defines a cooling air inlet in its radially inward portion. A second rotor defines a cooling air outlet in its radially outward portion, such that the cooling air passes radially outwardly through the cavity.
摘要翻译：一种用于燃气涡轮发动机的转子组件，转子组件包括至少两个在其间限定空腔的转子。第一转子在其径向向内部分限定冷却空气入口。第二转子在其径向向外的部分中限定冷却空气出口，使得冷却空气径向向外通过空腔。

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