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公开(公告)号：US07056089B2
公开(公告)日：2006-06-06
申请号：US10803554
申请日：2004-03-18
申请人： Toyotaka Sonoda , Toshiyuki Arima , Koji Murata
发明人： Toyotaka Sonoda , Toshiyuki Arima , Koji Murata
IPC分类号： F01D21/00
CPC分类号： F01D5/141 , F04D21/00 , F04D29/324 , Y02T50/673 , Y10S416/02
摘要： A high-turning and high-transonic blade for use in a blade cascade of an axial-flow compressor, wherein a distribution of flow speed on an extrados at a leading edge of the blade has a supersonic region of a substantially constant flow speed in the rear of a first large value of the flow speed and inside a position corresponding to 15% of a chord length from the leading edge. The supersonic region is established so that a value obtained by the division of a difference between Mach numbers at front and rear ends of the supersonic region by a chord-wise length of the supersonic region is smaller than 1, and the maximum Mach number in the supersonic region is smaller than 1.4. A first large shock wave is positively generated at a position where the flow speed assumes a first maximum value, whereby a second shock wave generated in the supersonic region of the substantially constant flow speed in the rear of such a position can be weakened. Thus, boundary layer separation due to the second shock wave can be suppressed, to thereby remarkably reduce the pressure loss of a following flow on the blade.
摘要翻译： 一种用于轴流式压缩机的叶片级联的高转弯和高跨音速叶片，其中在叶片的前缘上的外凸上的流速分布具有基本上恒定的流速的超音速区域 在流动速度的第一大值之后并且位于对应于来自前缘的弦长的15％的位置的后方。 建立超音速区域，使得通过将超音速区域的前后端的马赫数之间的差除以超音速区域的弦长而得到的值小于1，并且最大马赫数 超音速区域小于1.4。 在流速呈现第一最大值的位置处积极地产生第一大的冲击波，由此在该位置的后方的基本上恒定的流速的超音速区域中产生的第二冲击波可以被削弱。 因此，可以抑制由于第二冲击波引起的边界层分离，从而显着降低叶片上的后续流动的压力损失。
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公开(公告)号：US20060275134A1
公开(公告)日：2006-12-07
申请号：US11294372
申请日：2005-12-06
IPC分类号： B64C11/16
CPC分类号： F01D5/141 , Y02T50/673 , Y10S416/02 , Y10S416/05
摘要： A first bent portion bent toward an intrados and a second bent portion located in the rear of the first bent portion and bent toward an extrados are provided on a camber line on a trailing edge in the rear of 90% of a chord length of a turbine blade having an extremely low aspect ratio for an axial-flow turbine. The inclination of the camber line immediately in the rear of the second bent portion on the side of a blade root is substantially equal to the inclination of the camber line immediately in front of the first bent portion, and the curvature of the second bent portion is decreased from the side of the blade root toward a blade tip. As a result, a higher-pressure portion on the intrados which is a pressure surface of the turbine blade is displaced toward the trailing edge, and thus a secondary flow from the side of the blade tip toward the blade root can be suppressed, whereby a pressure loss particularly in the vicinity of the blade root can be suppressed to the minimum.
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公开(公告)号：US06638021B2
公开(公告)日：2003-10-28
申请号：US09985177
申请日：2001-11-01
IPC分类号： F01D514
CPC分类号： F01D5/141 , F05D2250/713
摘要： A turbine blade for an axial-flow turbine includes an intrados generating a positive pressure, and an extrados generating a negative pressure, wherein the intrados and the extrados are provided between a leading edge and a trailing edge. An inflection point is provided between a concave portion on an upstream side and a convex portion on a downstream side in a region extending from a position of 80% on the intrados to a rear throat, and the length of a normal line drawn downwards from the intrados of one of the turbine blades to an extrados of the other turbine blade has at least one maximum value in a region extending from a front throat of the one turbine blade to a rear throat. Thus, it is possible to disperse a shock wave generated from the intrados at the trailing edge to prevent the generation of a strong shock wave, thereby reducing the pressure loss caused by the shock wave. In addition, a speed-reducing area can be formed on the extrados generating the negative pressure to promote the transition from a laminar flow boundary layer to a turbulent flow boundary layer, thereby preventing the separation of the boundary layer caused by the interference with a shock wave to reduce the pressure loss.
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公开(公告)号：US06527510B2
公开(公告)日：2003-03-04
申请号：US09866924
申请日：2001-05-30
申请人： Markus Olhofer , Bernhard Sendhoff , Edgar Körner , Yoshihiro Yamaguchi , Toyotaka Sonoda , Toshiyuki Arima
发明人： Markus Olhofer , Bernhard Sendhoff , Edgar Körner , Yoshihiro Yamaguchi , Toyotaka Sonoda , Toshiyuki Arima
IPC分类号： F04D2944
CPC分类号： F04D29/681 , F04D21/00 , F04D29/544
摘要： It is an object of the present invention to provide a stator blade for an axial-flow compressor, in which the wave drag due to the generation of a shock wave in a transonic speed range can be suppressed to the minimum. For this purpose, the stator blade in the axial-flow compressor has an intrados producing a positive pressure, and an extrados producing a negative pressure. Both of the intrados and the extrados are located on one side of a chord line. A first bulge and a second bulge are formed on the intrados of the stator blade at a location on the side of a leading edge and on the side of a trailing edge, respectively. Thus, the generation of a shock wave on the extrados can be moderated to reduce the wave drag by positively producing the separation of a boundary layer on the intrados by the first bulge. In addition, the boundary layer rendered unstable by the first bulge on the intrados can be stabilized again by the second bulge on the intrados and hence, the increase in frictional drag due to the separation of the boundary layer on the intrados can be suppressed to the minimum.
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公开(公告)号：US06802474B2
公开(公告)日：2004-10-12
申请号：US10410215
申请日：2003-04-10
IPC分类号： B64C300
CPC分类号： F01D5/141 , F04D29/544 , Y02T50/673
摘要： In a high turning airfoil capable of being suitably applied to each of blades constituting a blade row of an axial flow-type compressor, both of an intrados generating a positive pressure and an extrados generating a negative pressure exist on one side of a chord line, and the curvature of the extrados made non-dimensional by a chord length has a maximum value between a position corresponding to 10% of the chord length and a position corresponding to 35% of the chord length, and a minimum value in the rear of the position of the maximum value and between a position corresponding to 30% of the chord length and a position corresponding to 50% of the chord length. Preferably, a difference between the maximum value and the minimum value of the curvature is equal to or larger than 0.5, and a turning angle is equal to or larger than 40°. With this airfoil, the total pressure loss coefficient is decreased more than that in an airfoil according to a comparative example in the entire Reynolds number region including medium and high Reynolds number regions and particularly, is decreased remarkably more than that in the airfoil according to the comparative example in a region of low Reynolds number equal to or smaller than 130,000. This is considered because a laminar flow separation region on the extrados of the airfoil is small in the low Reynolds number region, and a phenomenon of reverse flow within bubbles in the laminar flow separation region is weakened.
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公开(公告)号：US20120315136A1
公开(公告)日：2012-12-13
申请号：US13483377
申请日：2012-05-30
IPC分类号： F01D9/04
CPC分类号： F04D29/526 , F01D5/143 , F01D5/145 , F01D25/162 , F04D29/544 , F05D2220/36
摘要： A generating line of a casing surrounding an outer periphery of vanes of a stator disposed downstream of a rotor of the axial-flow compressor includes: a recessed region recessed outward in a radial direction from a position forward of a front edge of each of the vanes to a position rearward of a rear edge of the vane; and a protruding region bulging inward in the radial direction at an intermediate position of the recessed region in a front-rear direction thereof. Thus, a distribution of static pressure in the radial direction on a surface of the vane is improved by a first recessed portion forward of the protruding region, and the static pressure on the tip side is raised by a second recessed portion rearward of the protruding region.
摘要翻译： 围绕设置在轴流式压缩机的转子下游的定子的叶片的外周围的壳体的发生线包括：从每个叶片的前边缘的前方的前方的位置沿径向向外凹陷的凹陷区域 到达叶片的后边缘的后方的位置; 以及在凹部区域的前后方向的中间位置沿径向向内凸出的突出区域。 因此，通过突出区域的前方的第一凹部来提高在叶片的表面上的径向上的静压力的分布，并且尖端侧的静压由突出区域的后方的第二凹部上升 。
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公开(公告)号：US07597544B2
公开(公告)日：2009-10-06
申请号：US11294372
申请日：2005-12-06
IPC分类号： F03B3/12
CPC分类号： F01D5/141 , Y02T50/673 , Y10S416/02 , Y10S416/05
摘要： A first bent portion bent toward an intrados and a second bent portion located in the rear of the first bent portion and bent toward an extrados are provided on a camber line on a trailing edge in the rear of 90% of a chord length of a turbine blade having an extremely low aspect ratio for an axial-flow turbine. The inclination of the camber line immediately in the rear of the second bent portion on the side of a blade root is substantially equal to the inclination of the camber line immediately in front of the first bent portion, and the curvature of the second bent portion is decreased from the side of the blade root toward a blade tip. As a result, a higher-pressure portion on the intrados which is a pressure surface of the turbine blade is displaced toward the trailing edge, and thus a secondary flow from the side of the blade tip toward the blade root can be suppressed, whereby a pressure loss particularly in the vicinity of the blade root can be suppressed to the minimum.
摘要翻译： 在位于第一弯曲部分的后部并朝向外侧弯曲的第一弯曲部分和第二弯曲部分设置在涡轮的90％的弦长的后部的后缘的外倾线上 叶片具有用于轴流涡轮机的非常低的纵横比。 立即在第二弯曲部分的叶片根部侧的后方的倾斜度基本上等于在第一弯曲部分的正前方的弯度线的倾斜度，并且第二弯曲部分的曲率是 从叶片根侧向叶片尖端减小。 结果，作为涡轮叶片的压力表面的突起内的高压部分向后缘移动，因此可以抑制从叶片侧的侧向叶片根部的二次流，由此， 特别是叶片根部附近的压力损失可以被抑制到最小。
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公开(公告)号：US06666654B2
公开(公告)日：2003-12-23
申请号：US10087986
申请日：2002-03-05
IPC分类号： F01D514
CPC分类号： F01D5/141
摘要： A blade for an axial-flow turbine includes an intrados producing a positive pressure between a leading edge and a trailing edge, and an extrados producing a negative pressure. The intrados is formed at its rear portion with a flat surface portion connected to the trailing edge, and the extrados has a curved surface portion formed at least at a portion corresponding to the flat surface portion. The trailing edge of the turbine blade is pointed at its end. The angle of intersection between the intrados and the extrados at the trailing edge is a right angle or an acute angle. Thus, it is possible to inhibit the flowing of a gas from the intrados at the trailing edge toward the extrados and to decrease the degree of curvature of the extrados at the trailing edge portion to reduce the flow speed, thereby minimizing a shock wave generated at the trailing edge portion to reduce the pressure loss and enhance the performance of the turbine.
摘要翻译： 用于轴流涡轮机的叶片包括产生前缘和后缘之间的正压的内部，以及产生负压的外径。 内部的后部形成有连接到后缘的平坦表面部分，并且外部具有至少形成在与平坦表面部分对应的部分处的弯曲表面部分。 涡轮机叶片的后缘指向其端部。 后缘和后端之间的交叉角度是直角或锐角。 因此，可以抑制气体从后缘处的内部流向外部并且降低后缘部分处的外凸的曲率以减小流速，从而最小化在 后缘部分，以减小压力损失并增强涡轮机的性能。
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公开(公告)号：US08192154B2
公开(公告)日：2012-06-05
申请号：US12103503
申请日：2008-04-15
IPC分类号： F01D9/04
CPC分类号： F01D9/06 , F01D5/145 , Y02T50/673 , Y10S416/02
摘要： An axial-flow gas turbine engine includes a plurality of inlet guide vanes (V) which are radially disposed in an annular gas passage defined between an inner peripheral wall (Ch) and an outer peripheral wall (Ct) of a turbine. The inner peripheral wall (Ch) of the gas passage includes inner peripheral concave portions (Cc1 and Cc3) on an upstream side, and inner peripheral convex portions (Cv1 and Cv3) on a downstream side. The outer peripheral wall (Ct) of the gas passage includes outer peripheral convex portions (Cv2 and Cv4) on an upstream side, and outer peripheral concave portions (Cc2 and Cc4) on a downstream side. Therefore, a pressure difference in a radial direction of the inlet guide vane V is reduced or partially reversed, and a secondary flow toward an inner side in the radial direction can be suppressed to reduce pressure loss.
摘要翻译： 轴流式燃气涡轮发动机包括多个入口引导叶片（V），其径向地设置在限定在涡轮机的内周壁（Ch）和外周壁（Ct）之间的环形气体通道中。 气体通道的内周壁（Ch）包括上游侧的内周凹部（Cc1，Cc3）和下游侧的内周凸部（Cv1，Cv3）。 气体通道的外周壁（Ct）包括上游侧的外周凸部（Cv2，Cv4）和下游侧的外周凹部（Cc2，Cc4）。 因此，入口引导叶片V的径向方向的压力差减少或部分反转，能够抑制向径向内侧的二次流动，减少压力损失。
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10.发明授权Airfoil for axial-flow compressor capable of lowering loss in low Reynolds number region 有权用于轴流式压缩机的翼型能够降低低雷诺数区域的损耗公开(公告)号：US08152459B2
公开(公告)日：2012-04-10
申请号：US11790865
申请日：2007-04-27
CPC分类号： F04D29/384 , F04D29/681 , Y10S415/914 , Y10S416/02 , Y10S416/05
摘要： In a transonic region with a Reynolds number not more than a critical Reynolds number, a flow velocity distribution on an extrados of an airfoil has a single supersonic maximum value within a range of up to 6% from a leading edge on a chord, or a shape factor has a maximum value in a region of 6 to 15% from the leading edge on the chord, the value being nearly constant in a region of 30 to 60% and gradually can increase up to 2.5 in a region downstream of 60% of chord. A pressure loss in a low Reynolds number region can be drastically reduced, while conventionally keeping low the pressure loss in a high Reynolds number region. Moreover, this pressure-loss reduction effect in the low Reynolds number region is exerted even if an inflow angle is changed in a wide range.
摘要翻译： 在雷诺数不超过临界雷诺数的跨音速区域中，翼型的外部流速分布在弦上的前缘具有高达6％的单个超音速最大值，或 形状因子在和弦前缘的6〜15％的区域中具有最大值，该值在30〜60％的区域中几乎是恒定的，并且在60％以下的区域中逐渐增加到2.5 弦。 低雷诺数区域的压力损失可以大大降低，而传统上保持较低的雷诺数区域的压力损失。 此外，即使流入角度在宽范围内变化，也能够实现低雷诺数区域的这种压力损失降低效果。
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