公开(公告)号：US20060275134A1

公开(公告)日：2006-12-07

申请号：US11294372

申请日：2005-12-06

申请人： Martina Hasenjager ,  Bernhard Sendhoff ,  Toyotaka Sonoda ,  Toshiyuki Arima

发明人： Martina Hasenjager ,  Bernhard Sendhoff ,  Toyotaka Sonoda ,  Toshiyuki Arima

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.

公开(公告)号：US06638021B2

公开(公告)日：2003-10-28

申请号：US09985177

申请日：2001-11-01

申请人： Markus Olhofer ,  Bernhard Sendhoff ,  Satoshi Kawarada ,  Toyotaka Sonoda ,  Toshiyuki Arima

发明人： Markus Olhofer ,  Bernhard Sendhoff ,  Satoshi Kawarada ,  Toyotaka Sonoda ,  Toshiyuki Arima

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.

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.

公开(公告)号：US06285968B1

公开(公告)日：2001-09-04

申请号：US09112928

申请日：1998-07-09

申请人： Keiichi Motoyama ,  Toshiyuki Arima ,  Masatoshi Shirotori

发明人： Keiichi Motoyama ,  Toshiyuki Arima ,  Masatoshi Shirotori

IPC分类号： G06F9455

CPC分类号： G06F17/5018 ,  G06F2217/16

摘要： An initial object shape is set in a first process, a numeric fluid dynamic grid is generated on the surface of the object shape in a second process, and Navier-Stokes equations are numerically solved by numerical fluid dynamics based on the object and the grid generated with the object shape and an object surface pressure is determined in a third process. The noise generated by the object is a determined in a fourth process, by solving Curle's formula based on the object surface pressure, and noises are again determined in a fifth process by updating the object shape and repeating the first through fourth processes. By determining an object shape based on a shape which generates the smallest noise from among the noises determined by the fifth process, it becomes possible to determine a shape of the object as a shape capable of minimizing aerodynamic noise generated upon movement of the object through a fluid medium.

摘要翻译： 在第一过程中设置初始对象形状，在第二过程中在对象形状的表面上生成数字流体动态网格，并且基于对象和网格生成的数值流体动力学数值解算Navier-Stokes方程 在第三过程中确定物体形状和物体表面压力。 由对象产生的噪声是在第四个处理中确定的，通过根据物体表面压力求解Curle公式，并且通过更新对象形状并重复第一至第四处理，在第五处理中再次确定噪声。 通过基于从由第五处理确定的噪声中产生最小噪声的形状来确定对象形状，可以将对象的形状确定为能够最小化通过物体的移动而产生的空气动力学噪声的形状 流体介质。

公开(公告)号：US20120315136A1

公开(公告)日：2012-12-13

申请号：US13483377

申请日：2012-05-30

申请人： Toyotaka Sonoda ,  Toshiyuki Arima ,  Giles Endicott ,  Markus Olhofer ,  Bernhard Sendhoff

发明人： Toyotaka Sonoda ,  Toshiyuki Arima ,  Giles Endicott ,  Markus Olhofer ,  Bernhard Sendhoff

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 。

公开(公告)号：US07597544B2

公开(公告)日：2009-10-06

申请号：US11294372

申请日：2005-12-06

申请人： Martina Hasenjäger ,  Bernhard Sendhoff ,  Toyotaka Sonoda ,  Toshiyuki Arima

发明人： Martina Hasenjäger ,  Bernhard Sendhoff ,  Toyotaka Sonoda ,  Toshiyuki Arima

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。

公开(公告)号：US07103483B2

公开(公告)日：2006-09-05

申请号：US11016470

申请日：2004-12-17

申请人： Yoshihiro Yamaguchi ,  Toshiyuki Arima

发明人： Yoshihiro Yamaguchi ,  Toshiyuki Arima

IPC分类号： G06F19/00 ,  G01N11/00

CPC分类号： G06F17/5018 ,  G06F2217/16

摘要： Fluid analyzing apparatus includes: an advection step density analyzing unit; an advection step internal energy analyzing unit; and an advection step pressure analyzing unit. The apparatus further includes: an advection step velocity analyzing unit; a nonadvection step small perturbation analyzing unit; and a nonadvection step velocity analyzing unit. The apparatus further includes: a nonadvection step density analyzing unit; a nonadvection step internal energy analyzing unit; and an iterative calculation control unit which iterates calculation in a predetermined order.

摘要翻译： 流体分析装置包括：平流阶梯密度分析单元; 对流步骤内部能量分析单元; 和对流级压力分析单元。 该装置还包括：对流步速分析单元; 非对流步骤小扰动分析单元; 和非对流步速分析单元。 该装置还包括：非流动步长密度分析单元; 非对流步骤内部能量分析单元; 以及以预定顺序迭代计算的迭代计算控制单元。

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。

公开(公告)号：US07047167B2

公开(公告)日：2006-05-16

申请号：US09930914

申请日：2001-08-15

申请人： Yoshihiro Yamaguchi ,  Toshiyuki Arima

发明人： Yoshihiro Yamaguchi ,  Toshiyuki Arima

IPC分类号： G06F17/10

CPC分类号： G06F17/5009 ,  F01D5/141 ,  G06F17/50 ,  G06F2217/16 ,  Y02T50/673

摘要： An initial set of individuals having design parameters of a blade as a gene, is determined at random (S12). Next, an analysis using Navier-Stokes equations is performed. On the basis of the analysis result, ranking (evaluation) of respective individuals are performed using a pressure loss coefficient, a trailing edge deviation angle and the like as objective functions (S14). When a shape of a blade having a desirable performance is obtained, or when a predetermined number of generations is achieved, the analysis is terminated assuming that a termination condition has been met (S22). When the termination condition has not been met, processes about individual selection, crossing between individuals and mutation are performed so that generation is incremented by 1. The above processes are repeated, so that Pareto solutions can be obtained according to MOGA in consideration of a trade-off relationship between the objective functions.

摘要翻译： 随机地确定具有作为基因的叶片的设计参数的初始组个体（S 12）。 接下来，执行使用Navier-Stokes方程的分析。 在分析结果的基础上，使用作为目标函数的压力损失系数，后缘偏离角等进行各个人的评价（评价）（S14）。 当获得具有期望性能的叶片的形状时，或者当达到预定数量的代数时，假定已满足终止条件，终止分析（S22）。 当终止条件尚未得到满足时，进行关于个体选择，个体间交叉和突变的处理，使得生成增加1.上述过程被重复，从而考虑到交易可以根据MOGA获得帕累托解 客观功能之间的关系。

公开(公告)号：US20050165562A1

公开(公告)日：2005-07-28

申请号：US11016470

申请日：2004-12-17

申请人： Yoshihiro Yamaguchi ,  Toshiyuki Arima

发明人： Yoshihiro Yamaguchi ,  Toshiyuki Arima

IPC分类号： G06F15/00 ,  G06F17/50 ,  G06F19/00

CPC分类号： G06F17/5018 ,  G06F2217/16

摘要： The invention provides a fluid analyzing apparatus, a fluid analyzing method, and a fluid analyzing program which can analyze an unsteady fluid with time developing, which do not depend on nonphysical parameters, and which can perform calculation with good convergence. The apparatus includes: an advection step density analyzing unit which calculates a density in an advection step; an advection step internal energy analyzing unit which calculates an internal energy in the advection step; and an advection step pressure analyzing unit which calculates a pressure developing after advection. The apparatus further includes: an advection step velocity analyzing unit which uses an equation obtained by adding a term of pressure gradient developing before advection to an advection equation of a momentum conservation equation to calculate a velocity in an advection step; a nonadvection step small perturbation analyzing unit which calculates a small perturbation from a pressure developing after advection in a nonadvection step; and a nonadvection step velocity analyzing unit which calculates a velocity developing after a unit time has elapsed. The apparatus further includes: a nonadvection step density analyzing unit which calculates a density developing after a unit time has elapsed; a nonadvection step internal energy analyzing unit which calculates an internal energy developing after the unit time has elapsed; and an iterative calculation control unit which iterates calculations in a predetermined order.

摘要翻译： 本发明提供一种流体分析装置，流体分析方法和流体分析程序，其可以随时间发展分析不稳定流体，其不依赖于非物理参数，并且可以以良好的收敛进行计算。 该装置包括：对流步长密度分析单元，计算对流步骤中的密度; 平流步骤内部能量分析单元，其计算对流步骤中的内部能量; 以及对流阶梯压力分析单元，其计算平流后的压力发展。 该装置还包括：平流阶跃速度分析单元，其使用通过将平流下展开的压力梯度项加到动量守恒方程的平流方程而获得的方程来计算平流步骤中的速度; 非对流步骤小扰动分析单元，其计算来自在非对流步骤中平流后发展的压力的小扰动; 以及计算在单位时间过去后的速度的非对流阶梯速度分析单元。 该装置进一步包括：非渐近阶梯密度分析单元，其计算经过单位时间后的密度; 计算在单位时间过去后内部能量发展的非对流步骤内部能量分析单元; 以及以预定顺序迭代计算的迭代计算控制单元。