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公开(公告)号：US20150345305A1
公开(公告)日：2015-12-03
申请号：US14712287
申请日：2015-05-14
CPC分类号： F01D5/188 , F01D5/187 , F05D2250/14 , F05D2250/16 , F05D2250/23 , F05D2250/231 , F05D2250/292 , F05D2260/2212 , F23R2900/03045 , F28F1/40 , F28F3/022 , F28F13/02 , F28F13/12 , Y02T50/676
摘要： A structure for disrupting the flow of a fluid, the structure comprising: (a) a first lateral wall and a second lateral wall spaced apart from one another, yet joined, by a floor and a ceiling; and, (b) a vorticor pin extending incompletely between the first lateral wall and the second lateral wall in a direction parallel to an X-axis, the vorticor pin concurrently rising above and extending away from the floor to a height, in a direction parallel to a Y-axis, to provide a gap between the vorticor pin and the ceiling, the vorticor pin comprising: (i) a front surface extending incompletely between the first lateral wall and the second lateral wall, the front surface extending above the floor and having an arcuate portion that is transverse with respect to a Z-axis, which is perpendicular to the X-axis and the Y-axis, and (ii) a rear surface extending between the first lateral wall and the second lateral wall, the rear surface extending between the front surface and the floor, the rear surface having an inclining section that tapers in height, taken parallel to the Y-axis, in a direction parallel to the Z-axis.
摘要翻译： 一种用于破坏流体流动的结构，所述结构包括：（a）第一侧壁和第二侧壁，所述第一侧壁和第二侧壁彼此间隔开，但由地板和天花板连接; 以及（b）在平行于X轴的方向上在第一侧壁和第二侧壁之间不完全延伸的激素针，所述vorticor针同时上升并且从地板延伸到高度，平行于 以提供在所述vorticor针和天花板之间的间隙，所述vorticor针包括：（i）在所述第一侧壁和所述第二侧壁之间不完全延伸的前表面，所述前表面延伸到所述底板之上， 具有相对于垂直于X轴和Y轴的Z轴横向的弓形部分，以及（ii）在第一侧壁和第二侧壁之间延伸的后表面，后部 所述表面在所述前表面和所述地板之间延伸，所述后表面具有与所述Z轴平行的方向平行于所述Y轴的高度渐缩的倾斜部。
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公开(公告)号：US08109715B2
公开(公告)日：2012-02-07
申请号：US11667799
申请日：2004-11-16
申请人： Philippe Renaud , Denis Tisserant
发明人： Philippe Renaud , Denis Tisserant
IPC分类号： F01D9/02
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 后翼缘（Pte）由外翼型表面（2）和内翼型表面（4）连接，所述外翼型表面（2）基本上是凸的，并且所述内翼型表面（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）转变成凹部。 枢轴点（Pp）和局部极限（Pex）的位置被设定为使得即使当叶片被置于关闭位置时，排气流对趋向于打开喷嘴的叶片施加正扭矩。
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公开(公告)号：US20110188993A1
公开(公告)日：2011-08-04
申请号：US13018789
申请日：2011-02-01
申请人： Jean-Luc Bacha , Emmanuel Berche , Didier Jeannel
发明人： Jean-Luc Bacha , Emmanuel Berche , Didier Jeannel
IPC分类号： F01D9/04
CPC分类号： F01D11/24 , F05D2240/11 , F05D2250/14 , F05D2250/16 , F05D2250/24 , F05D2250/26 , F05D2260/201 , Y02T50/676
摘要： A turbine ring sector comprising: a wall presenting an inside face and an outside face, the inside face defining an axially oriented airflow passage through which gas flows; and a multiply-perforated metal sheet situated on the side of the wall that is opposite from the airflow passage, said multiply-perforated metal sheet having a bottom; wherein the space between the outside face of the wall and the bottom of the multiply-perforated metal sheet defines a gap; and wherein the variation in the value of the gap over the entire axial extent thereof decreases from a first maximum value towards a minimum value, said minimum value defining the minimum of the gap, and then increases from the minimum value to a second maximum value.
摘要翻译： 一种涡轮环形部分，包括：呈现内表面和外表面的壁，所述内表面限定气体流过的轴向定向气流通道; 以及位于与所述气流通道相对的所述壁侧的多孔金属片，所述多孔金属片具有底部; 其中所述壁的外表面和所述多孔金属片的底部之间的间隔限定了间隙; 并且其中在其整个轴向范围上的所述间隙的值的变化从第一最大值朝向最小值减小，所述最小值定义所述间隙的最小值，然后从所述最小值增加到第二最大值。
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公开(公告)号：US07955047B2
公开(公告)日：2011-06-07
申请号：US11895429
申请日：2007-08-24
申请人： Juerg Spuler
发明人： Juerg Spuler
IPC分类号： F01D17/14
CPC分类号： F01D17/143 , F02C6/12 , F05D2220/40 , F05D2250/14 , F05D2250/16 , F05D2250/19 , F05D2250/192 , F05D2250/193 , F05D2250/62 , F05D2250/70 , F05D2250/71 , F05D2260/96
摘要： Variable geometry turbine, in particular a gas turbine, comprising a housing (2, 22), a turbine rotor (4), a fluid inlet scroll (1) that surrounds the turbine rotor, a vaned nozzle interposed between the inlet scroll and the turbine rotor conceived to accelerate the flow of fluid, the nozzle comprising an axially adjustable ring (5, 25) conceived to vary the nozzle gap (3, 23) and having a wall (19) delimiting the nozzle gap, the wall having balance holes (6, 26, 26′) connecting the nozzle gap with a chamber (12) delimited by the housing and the ring, characterised in that the edges (16), formed by the holes with the surface (18) of the wall facing the nozzle gap, are rounded in the portion (17, 17′) located downstream the holes with respect to the fluid flow. Turbocharger and supercharged engine comprising the engine.
摘要翻译： 可变几何涡轮机，特别是燃气涡轮机，包括壳体（2,22），涡轮机转子（4），围绕涡轮机转子的流体入口涡旋件（1），插入在入口涡旋件和涡轮机 被设想为加速流体流动的喷嘴，喷嘴包括轴向可调节的环（5,52），其被设想为改变喷嘴间隙（3,23）并且具有限定喷嘴间隙的壁（19），壁具有平衡孔 将所述喷嘴间隙与由所述壳体和所述环限定的腔室（12）连接，其特征在于，由所述孔形成的所述边缘（16）与所述壁的面向所述喷嘴的所述表面（18） 间隙在相对于流体流动位于孔下游的部分（17,17'）中圆化。 包括发动机的涡轮增压器和增压发动机。
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公开(公告)号：US07484937B2
公开(公告)日：2009-02-03
申请号：US10870437
申请日：2004-06-18
申请人： Erik Johann
发明人： Erik Johann
IPC分类号： F01D5/14
CPC分类号： F01D5/16 , F01D5/141 , F01D5/145 , F01D25/06 , F04D29/324 , F04D29/681 , F05D2240/121 , F05D2240/122 , F05D2240/30 , F05D2240/303 , F05D2240/304 , F05D2250/14 , F05D2250/16 , F05D2250/611 , Y02T50/673
摘要： The compressor blades of an aircraft engine are, in at least one natural-vibration critical area, designed such that at the blade leading edge (6), the leading edge shock wave (14) attaches to the leading edge (6), as a result of which a laminar boundary layer flow (7) on the suction side (13) quickly transitions into a turbulent boundary layer flow (9) which is kept constant and prevented from re-lamination by the further, continuous curvature of the suction side. Therefore, the transition, whose periodic movement is also suppressed, cannot communicate with a suction-side compression shock (10), preventing the compression shock from augmenting the natural vibrations of the blade occurring under certain flight conditions. The blade leading edge can, for example, be designed as an ellipse with a semi-axis ratio equal to or smaller than 1:4.
摘要翻译： 飞机发动机的压缩机叶片在至少一个自然振动临界区域中被设计成使得在叶片前缘（6）处，前缘冲击波（14）附接到前缘（6），作为 其结果是吸力侧（13）上的层流边界层流（7）快速转变成湍流边界层流（9），其通过吸入侧的进一步的连续曲率保持恒定并防止其再次层压。 因此，其周期性运动也被抑制的过渡不能与吸力侧压缩冲击（10）连通，防止压缩冲击增加在某些飞行条件下发生的叶片的自然振动。 刀片前缘可以例如被设计为具有等于或小于1:4的半轴比的椭圆形。
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6.发明授权公开(公告)号：US06574964B1
公开(公告)日：2003-06-10
申请号：US09856610
申请日：2001-05-23
申请人： Jan Häggander , Jan Östlund , Mats Olofsson , John Änggård
发明人： Jan Häggander , Jan Östlund , Mats Olofsson , John Änggård
IPC分类号： F02K100
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° and 25°, (ii) a slight outward curvature, i.e. implying a contour shape with positive 2nd derivative of the radius r, or (iii) a slight inward curvature, i.e. with a negative 2nd derivative of r but lying externally of the parabola contour, in the last case the 3rd 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，即具有负二阶导数 的r，但位于抛物线轮廓的外部，在最后一种情况下，r的三阶导数始终等于零（0）。
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公开(公告)号：US5779443A
公开(公告)日：1998-07-14
申请号：US918709
申请日：1997-08-22
CPC分类号： F01D9/02 , F01D5/141 , F01D5/145 , F05D2230/12 , F05D2250/16 , Y02T50/673 , Y10S415/914
摘要： The invention relates to the design of (particularly) a fixed blade in an axial flow steam turbine. A conventional blade is of prismatic form with an aerofoil cross-section and extends radially between annular end blocks. The inventive blade is curved in the radial (height) direction, being convex from root to tip on its pressure face. The setting angle relative to the corresponding prismatic blade is therefore fine at the root and tip and coarse at the blade mid-height. The throat opening is thus reduced at root and tip and increased at mid-height so displacing some mass flow away from both lossy end wall regions. A considerable gain in the stage efficiency results. A further improvement results from providing an optimum corner fillet between the blades and end walls at the root and tip.
摘要翻译： 本发明涉及（特别地）轴流式汽轮机中的固定叶片的设计。 传统的叶片是具有翼型横截面的棱柱形式并且在环形端块之间径向延伸。 本发明的刀片在径向（高度）方向上弯曲，在其压力面上从根部到尖端凸起。 因此，相对于相应的棱柱形刀片的设定角度在根部和尖端处是细小的，并且在刀片中间高度处是粗糙的。 因此，喉部开口在根部和尖端处减小，并且在中间高度处增加，从而使一些质量流从两个有损的端壁区域移开。 舞台效率有相当大的提升。 进一步的改进是通过在叶片和根部和尖端的端壁之间提供最佳的角圆角。
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公开(公告)号：US20180058219A1
公开(公告)日：2018-03-01
申请号：US15251421
申请日：2016-08-30
发明人： Kevin Kampka , Karsten Kolk , Roger Matthews
CPC分类号： F01D5/02 , F01D5/066 , F01D5/3007 , F01D5/3053 , F01D5/32 , F05D2220/32 , F05D2240/24 , F05D2250/16 , F05D2250/71 , F05D2260/30 , F05D2260/36 , F16D1/076
摘要： A rotor disk of a rotor, in particular of a gas turbine, which has serrations, at least on one side, for torque transmission, having a plurality of teeth distributed over the circumference, the tooth flanks of which are aligned opposite with respect to a respective central plane, wherein the tooth flanks have a course that deviates from a radial direction in a cross section perpendicular to the rotor axis.
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公开(公告)号：US09863320B2
公开(公告)日：2018-01-09
申请号：US14577097
申请日：2014-12-19
申请人： SNECMA
CPC分类号： F02C7/185 , F01D25/12 , F02C7/14 , F05D2200/20 , F05D2210/12 , F05D2250/16 , F05D2250/38 , F05D2260/205 , F05D2260/213 , F05D2260/221 , F05D2260/2214 , F05D2260/22141 , F05D2260/98 , F28D1/0233 , F28D2021/0021 , F28D2021/0049 , F28F3/048 , F28F3/12 , F28F2215/00 , Y02T50/671 , Y02T50/675
摘要： The invention relates to a heat exchanger of an air circulation channel of a turbomachine, the heat exchanger being configured so as to have fluid to be cooled passing through it and including a plurality of fins protruding from a support surface, the heat exchanger being characterized in that each fin includes a base and a preferably continuous leading face which extends axially from the base in the air circulation direction while tapering from upstream to downstream along an axis parallel with the support surface.
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公开(公告)号：US20090097969A1
公开(公告)日：2009-04-16
申请号：US11895429
申请日：2007-08-24
申请人： Juerg Spuler
发明人： Juerg Spuler
IPC分类号： F01D17/16
CPC分类号： F01D17/143 , F02C6/12 , F05D2220/40 , F05D2250/14 , F05D2250/16 , F05D2250/19 , F05D2250/192 , F05D2250/193 , F05D2250/62 , F05D2250/70 , F05D2250/71 , F05D2260/96
摘要： Variable geometry turbine, in particular a gas turbine, comprising a housing (2, 22), a turbine rotor (4), a fluid inlet scroll (1) that surrounds said turbine rotor, a vaned nozzle interposed between said inlet scroll and said turbine rotor conceived to accelerate the flow of fluid, said nozzle comprising an axially adjustable ring (5, 25) conceived to vary the nozzle gap (3, 23) and having a wall (19) delimiting said nozzle gap, said wall having balance holes (6, 26, 26′) connecting the nozzle gap with a chamber (12) delimited by said housing and said ring, characterised in that the edges (16), formed by said holes with the surface (18) of said wall facing the nozzle gap, are rounded in the portion (17, 17′) located downstream the holes with respect to the fluid flow.Turbocharger and supercharged engine comprising said turbine.
摘要翻译： 可变几何涡轮机，特别是燃气涡轮机，包括壳体（2,22），涡轮转子（4），围绕所述涡轮转子的流体入口涡旋件（1），插入在所述入口涡旋件和所述涡轮机 设计成加速流体流动的转子，所述喷嘴包括轴向可调节的环（5,52），其被设想为改变喷嘴间隙（3,23）并且具有限定所述喷嘴间隙的壁（19），所述壁具有平衡孔 6,26,26'），其将所述喷嘴间隙与由所述壳体和所述环限定的腔室（12）连接，其特征在于，由所述孔形成的边缘（16），所述壁的面（18）面向喷嘴 间隙在相对于流体流动位于孔下游的部分（17,17'）中圆化。 包括所述涡轮机的涡轮增压器和增压发动机。
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