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1. 发明申请

WO2018002618A1 CENTRIFUGAL COMPRESSOR WITH DIFFUSER WITH THROAT 审中-公开
标题翻译：离心式压缩机与扩散器与喉
公开(公告)号：WO2018002618A1
公开(公告)日：2018-01-04
申请号：PCT/GB2017/051893
申请日：2017-06-29
申请人： CUMMINS LTD
发明人： SIVAGNANASUNDARAM, Subenuka
IPC分类号： F04D17/10 , F04D29/44
CPC分类号： F04D17/10 , F04D29/441 , F05D2250/16 , F05D2250/323 , F05D2250/324 , F05D2250/52 , F05D2250/71 , F05D2250/711
摘要： A diffuser is proposed which is formed as the gap between rotationally-symmetric surfaces which face each other. Moving in the radial direction, the axial extent of the gap generally decreases to a minimum value in a throat portion of the diffuser, and then generally increases again. The distance from the rotational axis of the compressor to the throat may be approximately at least 125% of the radius of the compressor wheel. The inventors have found that a throat at this distance from the rotational axis may lead to higher efficiency at high flow rates, especially for relatively low turbo speeds. This is because the spacing between the compressor wheel and the throat permits diffusion of the gas streams leaving the compressor wheel.
摘要翻译：提出了一种扩散器，其形成为彼此面对的旋转对称表面之间的间隙。在径向方向上移动时，间隙的轴向范围通常在扩散器的喉部中减小到最小值，然后通常再次增加。从压缩机的旋转轴线到喉部的距离可以约为压缩机叶轮的半径的至少125％。发明人已经发现，在距离旋转轴线这个距离处的喉部可能导致在高流速下更高的效率，尤其是对于相对低的涡轮速度。这是因为压缩机叶轮和喉管之间的间距允许离开压缩机叶轮的气流扩散。

2. 发明申请

WO2011042696A2 TURBOMACHINE 审中-公开
标题翻译：叶轮机
公开(公告)号：WO2011042696A2
公开(公告)日：2011-04-14
申请号：PCT/GB2010/001870
申请日：2010-10-06
申请人： CUMMINS LTD , McEWEN, James Alexander , DENHOLM, Tim
发明人： McEWEN, James Alexander , DENHOLM, Tim
IPC分类号： F02C6/12
CPC分类号： F01D17/143 , F05D2220/40 , F05D2250/132 , F05D2250/16 , F05D2250/17 , F05D2250/61
摘要： A variable geometry turbine comprises a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls; and a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the inlet; wherein the annular inlet is divided into at least two axially offset inlet passages which axially overlap.
摘要翻译：可变几何涡轮机包括安装用于围绕壳体内的涡轮机轴线旋转的涡轮机叶轮，壳体限定围绕涡轮机叶轮并限定在第一和第二入口侧壁之间的环形入口; 以及圆柱形套筒，其轴向可移动穿过所述环形入口以改变通过所述入口的气体流动路径的尺寸; 其中所述环形入口被分成轴向重叠的至少两个轴向偏置的入口通道。

3. 发明申请

WO2017095438A1 TURBINE AIRFOIL WITH BIASED TRAILING EDGE COOLING ARRANGEMENT 审中-公开
标题翻译：涡轮机翼带偏航后缘冷却装置
公开(公告)号：WO2017095438A1
公开(公告)日：2017-06-08
申请号：PCT/US2015/064006
申请日：2015-12-04
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： MARSH, Jan H. , GOLSEN, Matthew J. , JOO, Daniel
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/304 , F05D2250/14 , F05D2250/16 , F05D2250/22 , F05D2250/23
摘要： An airfoil (10) for a turbine engine includes an array of features (22) positioned in an interior portion (11) of the airfoil (10). Each feature (22) extends from a pressure (14) side to a suction side (16). The array includes multiple radial rows (A-N) of features (22) with the features (22) in each row (A-N) being interspaced radially to define coolant passages (24) therebetween. The radial rows (A-N) are spaced along a forward-to-aft direction toward an airfoil trailing edge (20). The coolant passages (24) of the array are fluidically interconnected to lead a pressurized coolant toward the trailing edge (20) via a serial impingement on to the rows of features (22). The coolant passages (24) are geometrically configured to bias a coolant flow therethrough toward a first side (14) in relation to a second side (16) of the outer wall (12) to effect a greater cooling of the first side (14) than the second side (16).
摘要翻译：用于涡轮发动机的翼型件（10）包括位于翼型件（10）的内部部分（11）中的特征阵列（22）。每个特征（22）从压力（14）侧延伸到吸力侧（16）。该阵列包括多个特征（22）的径向行（A-N），每行（A-N）中的特征（22）径向间隔开以在其间限定冷却剂通道（24）。径向排（A-N）沿前后方向朝向翼型后缘（20）间隔开。阵列的冷却剂通道（24）流体互连以通过一系列冲击到特征（22）排上而将加压的冷却剂引向后缘（20）。冷却剂通道（24）在几何结构上被配置为将通过其的冷却剂流相对于外壁（12）的第二侧（16）朝向第一侧（14）偏置以实现第一侧（14）的更大的冷却，比第二面（16）。

4. 发明申请

WO00034641A1 ROCKET NOZZLE CONTOUR FOR FLOW SEPARATION CONTROL AND SIDE LOAD REDUCTION 审中-公开
标题翻译：用于流动分离控制和侧负载减少的ROCKET喷嘴轮廓
公开(公告)号：WO00034641A1
公开(公告)日：2000-06-15
申请号：PCT/SE1998/002222
申请日：1998-12-04
IPC分类号： F02K9/97
CPC分类号： F02K9/97 , F05D2250/16
摘要： The invention refers to a full-flow rocket nozzle having a longitudinal contour essentially corresponding to a parabola. For obtaining a flow separation control and also a side load reduction the invention suggests that the parabola contour shape from the point of 50% expansion ratio onwards or more distant from the throat of the nozzle is changing over into (i) strictly conical shape having an angle to the center line of between 15 DEG and 25 DEG , (ii) a slight outward curvature, i.e. implying a contour shape with positive 2 derivative of the radius r, or (iii) a slight inward curvature, i.e. with a negative 2 derivative of r but lying externally of the parabola contour, in the last case the 3 derivative of r being constantly equal to zero (0).
摘要翻译：本发明涉及一种具有基本对应于抛物线的纵向轮廓的全流量火箭喷嘴。为了获得流动分离控制以及侧向负载的减小，本发明提出从远离喷嘴喉部的50％膨胀比起的抛物线轮廓形状转变成（i）具有与中心线的角度在15°和25°之间，（ii）略微向外的曲率，即意味着具有半径r的正二阶导数的轮廓形状，或（iii）略微向内的曲率，即具有 r的负二阶导数，但位于抛物线轮廓外部，在最后一种情况下，r的3π导数始终等于零（0）。

5. 发明申请

WO2011042696A3 VARIABLE GEOMETRY TURBINE 审中-公开
标题翻译：可变几何涡轮
公开(公告)号：WO2011042696A3
公开(公告)日：2011-11-10
申请号：PCT/GB2010001870
申请日：2010-10-06
申请人： CUMMINS LTD , MCEWEN JAMES ALEXANDER , DENHOLM TIM
发明人： MCEWEN JAMES ALEXANDER , DENHOLM TIM
IPC分类号： F01D17/14 , F02C6/12
CPC分类号： F01D17/143 , F05D2220/40 , F05D2250/132 , F05D2250/16 , F05D2250/17 , F05D2250/61
摘要： A variable geometry turbine comprises a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls; and a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the inlet; wherein the annular inlet is divided into at least two axially offset inlet passages which axially overlap.
摘要翻译：可变几何涡轮机包括安装用于围绕壳体内的涡轮机轴线旋转的涡轮机叶轮，壳体限定围绕涡轮机叶轮并限定在第一和第二入口侧壁之间的环形入口; 以及圆柱形套筒，其轴向可移动穿过所述环形入口以改变通过所述入口的气体流动路径的尺寸; 其中所述环形入口被分成轴向重叠的至少两个轴向偏置的入口通道。

6. 发明申请

WO2009103528A2 PARAMETRIC BLADES WITH EITHER SINUSOIDAL LEAN OR AIRFOILS WITH ARCS OF ELLIPSES 审中-公开
标题翻译：参数叶片具有正弦曲线或椭圆曲线
公开(公告)号：WO2009103528A2
公开(公告)日：2009-08-27
申请号：PCT/EP2009/001184
申请日：2009-02-19
申请人： PIETRICOLA, Paolo
发明人： PIETRICOLA, Paolo
IPC分类号： F04D29/32
CPC分类号： F04D29/322 , F01D5/141 , F04D29/325 , F05D2240/301 , F05D2250/14 , F05D2250/16 , F05D2250/17 , F05D2250/184 , F05D2250/74
摘要： This invention concerns rotor and stator parametric blades for employment in axial and mix flow rotary machines. The blades are characterized either from a sinusoidal lean or from airfoils '11' and/or '22' designed with a number of arches of ellipses. The blades object of this invention are suitable to be used either in classic designs or within optimization procedures, may be realized with 3D parametric CAD system and can be used in embodiments realized with at least one row of blades. The blades may be designed interpolating parametric airfoils (realized with circumferences, ellipses, and/or curves with continues curvature) along sinusoidal staking based on various combinations of lean & sweep. The proposed solutions allow to design & simulate improved & reliable 3D blades for rotary machine and aid reducing aerodynamic losses, acoustic emissions and mechanical stresses in a wide range of practical application.
摘要翻译：本发明涉及用于轴流和混流旋转机器中的转子和定子参数叶片。叶片的特征或者来自正弦曲线倾斜，或者来自设计有多个椭圆拱的翼型件11'和/或'22'。本发明的叶片对象适用于经典设计或优化程序中，可以用3D参数化CAD系统来实现，并且可以在由至少一排叶片实现的实施例中使用。叶片可以被设计成基于各种稀薄和不平滑组合的插值参数翼型（沿周向放样的圆周，椭圆和/或具有连续曲率的曲线）扫。所提出的解决方案允许设计＆amp; 模拟改进的＆amp; 可靠的3D刀片用于旋转机械，并有助于在广泛的实际应用中减少空气动力学损失，声发射和机械应力。

7. 发明申请

WO2006053579A1 VARIABLE NOZZLE TURBOCHARGER 审中-公开
标题翻译：可变的喷嘴涡轮增压器
公开(公告)号：WO2006053579A1
公开(公告)日：2006-05-26
申请号：PCT/EP2004/012992
申请日：2004-11-16
申请人： HONEYWELL INTERNATIONAL INC. , RENAUD, Philippe , TISSERANT, Denis
发明人： RENAUD, Philippe , TISSERANT, Denis
IPC分类号： F01D17/16 , F01D5/14
CPC分类号： F01D17/165 , F01D5/141 , F05D2220/40 , F05D2250/16 , F05D2250/711 , F05D2250/712 , F05D2250/713
摘要： There is provided a turbocharger with a variable nozzle assembly having a plurality of cambered vanes positioned annularly around a turbine wheel, each vane (20) being pivotable around a pivot point (Pp) and being configured to have a leading edge (Ple) and a trailing edge (Pte) connected by an outer airfoil surface (2) and an inner airfoil surface (4), said outer airfoil surface (2) being substantially convex and said inner airfoil surface (4) having a convex section at the leading edge (Ple) which has a local extreme (Pex) of curvature and transitions into a concave section towards the trailing edge (Pte). The positions of the pivot point (Pp) and the local extreme (Pex) are set such that, even when the vanes are placed in a closed position, the exhaust gas stream exercises a positive torque on the vanes which tends to open the nozzle.
摘要翻译：提供了一种具有可变喷嘴组件的涡轮增压器，其具有围绕涡轮机轮环定位的多个弧形叶片，每个叶片（20）围绕枢转点（Pp）可枢转并且构造成具有前缘（Ple）和后缘（Pte）由外翼面（2）和内翼面（4）连接，所述外翼面（2）基本上是凸的，所述内翼面（4）在前缘具有凸形部分 Ple），其具有曲率的局部极值（Pex）并且朝向后缘（Pte）转变成凹形部分。枢轴点（Pp）和局部极限（Pex）的位置被设定为使得即使当叶片处于关闭位置时，排气流对趋向于打开喷嘴的叶片施加正扭矩。

8. 发明申请

WO2009103528A3 PARAMETRIC BLADES WITH EITHER SINUSOIDAL LEAN OR AIRFOILS WITH ARCS OF ELLIPSES 审中-公开
标题翻译：具有独立倾斜或风力发动机的参数刀片与ELLIPSES ARCS
公开(公告)号：WO2009103528A3
公开(公告)日：2009-10-29
申请号：PCT/EP2009001184
申请日：2009-02-19
申请人： PIETRICOLA PAOLO
发明人： PIETRICOLA PAOLO
IPC分类号： F04D29/32
CPC分类号： F04D29/322 , F01D5/141 , F04D29/325 , F05D2240/301 , F05D2250/14 , F05D2250/16 , F05D2250/17 , F05D2250/184 , F05D2250/74
摘要： This invention concerns rotor and stator parametric blades for employment in axial and mix flow rotary machines. The blades are characterized either from a sinusoidal lean or from airfoils '11' and/or '22' designed with a number of arches of ellipses. The blades object of this invention are suitable to be used either in classic designs or within optimization procedures, may be realized with 3D parametric CAD system and can be used in embodiments realized with at least one row of blades. The blades may be designed interpolating parametric airfoils (realized with circumferences, ellipses, and/or curves with continues curvature) along sinusoidal staking based on various combinations of lean & sweep. The proposed solutions allow to design & simulate improved & reliable 3D blades for rotary machine and aid reducing aerodynamic losses, acoustic emissions and mechanical stresses in a wide range of practical application.
摘要翻译：本发明涉及用于轴向和混合流动旋转机器的转子和定子参数叶片。叶片的特征可以是正弦倾斜或来自设计有多个椭圆形拱形的翼型'11'和/或'22'。本发明的刀片对象适用于经典设计或优化程序中，可以用3D参数CAD系统来实现，并且可以用至少一行刀片实现的实施例中使用。叶片可以基于各种稀薄和扫掠的组合，沿着正弦波纹来设计内插参数翼型（具有圆周，椭圆和/或具有连续曲率的曲线）。所提出的解决方案允许设计和模拟旋转机器的改进和可靠的3D叶片，并有助于在广泛的实际应用中减少空气动力学损失，声发射和机械应力。

9. 发明申请

WO2005054633A1 VARIABLE NOZZLE FOR A GAS TURBINE 审中-公开
标题翻译：用于气体涡轮的可变喷嘴
公开(公告)号：WO2005054633A1
公开(公告)日：2005-06-16
申请号：PCT/EP2004/013657
申请日：2004-11-30
申请人： NUOVO PIGNONE HOLDING S.p.A. , SASSANELLI, Giuseppe
发明人： SASSANELLI, Giuseppe
IPC分类号： F01D17/16
CPC分类号： F01D17/162 , F01D5/14 , F01D5/141 , F05D2200/22 , F05D2200/221 , F05D2200/222 , F05D2200/24 , F05D2200/25 , F05D2240/128 , F05D2240/301 , F05D2250/16 , F05D2250/17 , F05D2250/70 , F05D2250/71 , F05D2250/711 , F05D2250/712 , F05D2260/74
摘要： Variable nozzle (10) for a gas turbine fixed to a shaft (11) equipped with a pressurized upper surface (12) and a depressurized lower surface opposite to the upper surface (12), the variable nozzle comprises a series of substantially "C"-shaped sections, each having a first rounded end and a second rounded end each section of the series of sections also having the concavity facing upwards with respect to a base (90) and arranged one after another continuously, in the direction of an axis of the shaft (11) along a curved line (60), the at least second degree curved line (60) lies on a surface (70) having an axis orthogonal to the axis of the shaft (11) and also tilted with respect to the base (90) by an angle (80).
摘要翻译：固定在具有加压上表面（12）的轴（11）和与上表面（12）相对的减压下表面的燃气轮机的可变喷嘴（10），所述可变喷嘴包括一系列基本上“C” 每个部分具有第一圆形端部和第二圆形端部，所述一系列部分的每个部分还具有相对于基部（90）面向上的凹部，并且沿着轴线方向连续布置所述轴（11）沿着曲线（60），所述至少第二度曲线（60）位于具有与所述轴（11）的轴线正交的轴线的表面（70）上，并且还相对于所述轴线基座（90）角度（80）。

10. 发明申请

WO2004081348A1 TURBINE NOZZLE AIRFOIL 审中-公开
标题翻译：涡轮喷嘴气翼
公开(公告)号：WO2004081348A1
公开(公告)日：2004-09-23
申请号：PCT/JP2004/003134
申请日：2004-03-10
申请人： ISHIKAWAJIMA-HARIMA HEAVY INDUSTRIES CO. LTD.
发明人： TSURU, Atsushi , NISHIMURA, Keiji
IPC分类号： F01D5/14
CPC分类号： F01D5/16 , F01D5/141 , F05D2250/16 , Y02T50/673 , Y10S416/02
摘要： An easily producible turbine nozzle for a gas turbine engine is provided, which is capable of preventing flutter of the turbine nozzle during operation of the gas turbine engine. The turbine nozzle comprises airfoils stacked along the stacking axis. The high curvature portions on suction surface in airfoil section successively formed along the stacking axis of the airfoil describe a parabola line that curves toward the pressure side of the airfoil when seen from the front or rear of the turbine nozzle. The high curvature portions on suction surface in airfoil section curve most at the center along the stacking axis of the airfoil from a straight line that connects with a first intersection between the parabola line and an inner band in the turbine nozzle and with a second intersection between the parabola line and an outer band in the turbine nozzle. The maximum curvature falls within a range from 0.02 to 0.03-fold of the stacking axis of the airfoil.
摘要翻译：提供了一种易于生产的用于燃气涡轮发动机的涡轮喷嘴，其能够在燃气涡轮发动机的运行期间防止涡轮喷嘴的颤动。涡轮喷嘴包括沿着堆叠轴线堆叠的翼型件。沿着翼型的堆叠轴线依次形成的翼型部分的吸力表面上的高弯曲部分描述了从涡轮喷嘴的前部或后部观察时朝向翼型的压力侧弯曲的抛物线。在翼型部分的吸力表面上的高曲率部分在沿着翼型的堆叠轴线的中心处最大程度地从与抛物线和涡轮喷嘴中的内带之间的第一交点连接的直线弯曲，并且在第二交点处抛物线和涡轮喷嘴中的外带。最大曲率落在翼型的堆积轴的0.02〜0.03倍的范围内。

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