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公开(公告)号:US08172518B2
公开(公告)日:2012-05-08
申请号:US11617911
申请日:2006-12-29
CPC分类号: F01D5/20 , F01D5/147 , F05D2250/314 , Y10T29/49318 , Y10T29/49321 , Y10T29/49325 , Y10T29/49336
摘要: A method for assembling a rotor assembly and a rotor assembly are provided. The method comprises providing a rotor blade including a first sidewall, a second sidewall, where the first and second sidewalls are connected at a leading edge and a trailing edge and extend in span from a root portion to a tip portion, removing blade material from the tip portion to form a tip portion rake angle that enables the tip portion to extend obliquely between the first and second sidewalls, and coupling the rotor blade to a shaft such that during tip rubs the tip portion rake angle facilitates reducing radial loading induced to the blade during tip rubs.
摘要翻译: 提供了组装转子组件和转子组件的方法。 该方法包括提供包括第一侧壁和第二侧壁的转子叶片,其中第一和第二侧壁在前缘和后缘处连接,并且从根部到顶端部分的跨度延伸, 尖端部分以形成尖端部前角,其能够使尖端部分在第一和第二侧壁之间倾斜地延伸,并且将转子叶片联接到轴上,使得在末端摩擦期间尖端部分前角有助于减小引起叶片的径向负载 在尖端磨擦。
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公开(公告)号:US20090053067A1
公开(公告)日:2009-02-26
申请号:US11837680
申请日:2007-08-13
IPC分类号: B64C27/473
CPC分类号: B64C11/205 , F01D5/147 , F01D5/282 , F01D5/286 , F01D5/288 , F04D29/023 , F04D29/324 , F05D2230/23 , F05D2230/90 , F05D2240/121 , F05D2240/303 , F05D2250/18 , F05D2250/182 , F05D2250/60 , F05D2250/61 , F05D2300/10 , Y02T50/673
摘要: An airfoil is disclosed having a concave pressure side and a convex suction side defining a chord length, and a leading edge and a trailing edge. A leading edge protective strip is adhered by a bond layer to and protectively covers the leading edge and respective predetermined portions of the pressure side and suction side of the airfoil body from the leading edge downstream towards the trailing edge. The leading edge protective strip includes a multiplicity of inwardly-facing grooves in which the bond layer is embedded. The grooves define adjacent segments of a predetermined size sufficiently small that, if detached from the vane during engine operation, impact with downstream engine components will not cause damage to the downstream engine components.
摘要翻译: 公开了一种具有限定弦长的凹压侧和凸吸力侧以及前缘和后缘的翼型。 前缘保护带通过接合层粘合并保护性地覆盖翼型体的压力侧和吸力侧的前缘和相应的预定部分从前缘向下缘向后缘。 前缘保护带包括多个向内凹槽,其中嵌入有粘合层。 凹槽限定了足够小的预定尺寸的相邻段,如果在发动机操作期间与叶片分离,则与下游发动机部件的冲击不会对下游发动机部件造成损坏。
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公开(公告)号:US20090025365A1
公开(公告)日:2009-01-29
申请号:US11781485
申请日:2007-07-23
CPC分类号: B64C11/205 , F01D5/147 , F01D5/282 , F01D5/286 , F01D5/288 , F04D29/023 , F04D29/324 , F05D2230/23 , F05D2230/90 , F05D2240/121 , F05D2240/303 , F05D2250/18 , F05D2250/182 , F05D2250/60 , F05D2250/61 , F05D2300/10 , Y02T50/673
摘要: An airfoil is disclosed having a concave pressure side and a convex suction side defining a chord length, and a leading edge and a trailing edge. A leading edge protective strip is adhered by a bond layer to and protectively covers the leading edge and respective predetermined portions of the pressure side and suction side of the airfoil body from the leading edge downstream towards the trailing edge. The predetermined portion of the suction side covered by the leading edge protective strip is less than the predetermined portion of the pressure side covered by the leading edge protective strip.
摘要翻译: 公开了一种具有限定弦长的凹压侧和凸吸力侧以及前缘和后缘的翼型。 前缘保护带通过接合层粘合并保护性地覆盖翼型体的压力侧和吸力侧的前缘和相应的预定部分从前缘向下缘向后缘。 由前缘保护带覆盖的吸入侧的预定部分小于由前缘保护带覆盖的压力侧的预定部分。
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公开(公告)号:US20080159869A1
公开(公告)日:2008-07-03
申请号:US11617911
申请日:2006-12-29
IPC分类号: F01D5/14
CPC分类号: F01D5/20 , F01D5/147 , F05D2250/314 , Y10T29/49318 , Y10T29/49321 , Y10T29/49325 , Y10T29/49336
摘要: In one aspect, a method for assembling a rotor assembly is provided. The method comprises providing a rotor blade including a first sidewall, a second sidewall, where the first and second sidewalls are connected at a leading edge and a trailing edge and extend in span from a root portion to a tip portion, removing blade material from the tip portion to form a tip portion rake angle that enables the tip portion to extend obliquely between the first and second sidewalls, and coupling the rotor blade to a shaft such that during tip rubs the tip portion rake angle facilitates reducing radial loading induced to the blade during tip rubs.
摘要翻译: 一方面,提供了组装转子组件的方法。 该方法包括提供包括第一侧壁和第二侧壁的转子叶片,其中第一和第二侧壁在前缘和后缘处连接,并且从根部到顶端部分的跨度延伸, 尖端部分以形成尖端部前角,其能够使尖端部分在第一和第二侧壁之间倾斜地延伸,并且将转子叶片联接到轴上,使得在末端摩擦期间尖端部分前角有助于减小引起叶片的径向负载 在尖端磨擦。
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公开(公告)号:US08180596B2
公开(公告)日:2012-05-15
申请号:US10889742
申请日:2004-07-13
申请人: Thomas Richard Henning , John Douglas Mickol , Daniel Edward Mollmann , Michael Harvey Schneider
发明人: Thomas Richard Henning , John Douglas Mickol , Daniel Edward Mollmann , Michael Harvey Schneider
IPC分类号: G06F17/50
CPC分类号: F04D27/001 , F04D15/0088 , F04D29/666 , Y10T29/49316
摘要: A processor-implemented method of assembling a rotatable machine is provided. The machine includes a plurality of blades that extend radially outwardly from a rotor. The method includes determining a geometric parameter for each blade in a row of blades that is relative to a ratio, R of an inlet area and an outlet area of a predetermined volume defined between each pair of blades, determining an initial sequence map for the row of blades that facilitates minimizing a difference of R between circumferentially adjacent pairs of blades, and iteratively remapping the sequence of the blades to facilitate reducing a moment weight vector sum of the rotor to a value that is less than a predetermined value.
摘要翻译: 提供了一种组装可旋转机器的处理器实现方法。 机器包括从转子径向向外延伸的多个叶片。 该方法包括确定一排叶片中每个叶片的几何参数,其相对于在每对叶片之间限定的预定体积的入口面积和出口面积的比率R,确定该行的初始序列图 的叶片,其有助于最小化周向相邻的叶片对之间的R的差异,并且迭代地重新映射叶片的序列,以便于将转子的力矩加权矢量和减小到小于预定值的值。
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公开(公告)号:US07736130B2
公开(公告)日:2010-06-15
申请号:US11781485
申请日:2007-07-23
IPC分类号: F01D5/28
CPC分类号: B64C11/205 , F01D5/147 , F01D5/282 , F01D5/286 , F01D5/288 , F04D29/023 , F04D29/324 , F05D2230/23 , F05D2230/90 , F05D2240/121 , F05D2240/303 , F05D2250/18 , F05D2250/182 , F05D2250/60 , F05D2250/61 , F05D2300/10 , Y02T50/673
摘要: An airfoil is disclosed having a concave pressure side and a convex suction side defining a chord length, and a leading edge and a trailing edge. A leading edge protective strip is adhered by a bond layer to and protectively covers the leading edge and respective predetermined portions of the pressure side and suction side of the airfoil body from the leading edge downstream towards the trailing edge. The predetermined portion of the suction side covered by the leading edge protective strip is less than the predetermined portion of the pressure side covered by the leading edge protective strip.
摘要翻译: 公开了一种具有限定弦长的凹压侧和凸吸力侧以及前缘和后缘的翼型。 前缘保护带通过接合层粘合并保护性地覆盖翼型体的压力侧和吸力侧的前缘和相应的预定部分从前缘向下缘向后缘。 由前缘保护带覆盖的吸入侧的预定部分小于由前缘保护带覆盖的压力侧的预定部分。
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公开(公告)号:US07090464B2
公开(公告)日:2006-08-15
申请号:US10889945
申请日:2004-07-13
申请人: Thomas Richard Henning , John Douglas Mickol , Daniel Edward Mollmann , Michael Harvey Schneider , Andrew Breeze-Stringfellow , Max Farson
发明人: Thomas Richard Henning , John Douglas Mickol , Daniel Edward Mollmann , Michael Harvey Schneider , Andrew Breeze-Stringfellow , Max Farson
CPC分类号: F01D5/3007 , F01D5/027 , F01D5/30 , F05D2230/60 , F05D2240/30 , F05D2240/40 , Y02T50/672 , Y02T50/673 , Y10T29/49323
摘要: A method and apparatus for ordering blades in a rotatable machine is provided. The machine includes a plurality of blades that extend radially outwardly from a rotor. The method includes determining a moment weight of each blade in a row of blades, determining a geometric parameter of each blade in the same row of blades, and determining a mapping order of each blade using the moment weight and the geometric parameter. The apparatus includes a computer system that includes a software product code segment for minimizing imbalance in a bladed rotor wherein the segment is configured to receive a moment weight value for each blade to be installed in said rotor, receive a geometric parameter value for each blade to be installed in said rotor, calculate a blade location on the rotor based on the received values, and generate a blade map based on the calculated location.
摘要翻译: 提供了一种用于在可旋转机器中订购刀片的方法和装置。 机器包括从转子径向向外延伸的多个叶片。 该方法包括确定一行叶片中的每个叶片的力矩重量,确定同一行叶片中每个叶片的几何参数,以及使用力矩和几何参数确定每个叶片的映射顺序。 该装置包括计算机系统,该计算机系统包括用于最小化叶片式转子中的不平衡的软件产品代码段,其中该段被配置为接收要安装在所述转子中的每个叶片的力矩权值,接收每个叶片的几何参数值 安装在所述转子中,基于所接收的值计算转子上的叶片位置,并且基于所计算的位置生成叶片图。
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公开(公告)号:US07789630B2
公开(公告)日:2010-09-07
申请号:US11837680
申请日:2007-08-13
IPC分类号: F01D5/28
CPC分类号: B64C11/205 , F01D5/147 , F01D5/282 , F01D5/286 , F01D5/288 , F04D29/023 , F04D29/324 , F05D2230/23 , F05D2230/90 , F05D2240/121 , F05D2240/303 , F05D2250/18 , F05D2250/182 , F05D2250/60 , F05D2250/61 , F05D2300/10 , Y02T50/673
摘要: An airfoil is disclosed having a concave pressure side and a convex suction side defining a chord length, and a leading edge and a trailing edge. A leading edge protective strip is adhered by a bond layer to and protectively covers the leading edge and respective predetermined portions of the pressure side and suction side of the airfoil body from the leading edge downstream towards the trailing edge. The leading edge protective strip includes a multiplicity of inwardly-facing grooves in which the bond layer is embedded. The grooves define adjacent segments of a predetermined size sufficiently small that, if detached from the vane during engine operation, impact with downstream engine components will not cause damage to the downstream engine components.
摘要翻译: 公开了一种具有限定弦长的凹压侧和凸吸力侧以及前缘和后缘的翼型。 前缘保护带通过接合层粘合并保护性地覆盖翼型体的压力侧和吸力侧的前缘和相应的预定部分从前缘向下缘向后缘。 前缘保护带包括多个向内凹槽,其中嵌入有粘合层。 凹槽限定了足够小的预定尺寸的相邻段,如果在发动机操作期间与叶片分离,则与下游发动机部件的冲击不会对下游发动机部件造成损坏。
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