-
公开(公告)号：US08684669B2
公开(公告)日：2014-04-01
申请号：US13027354
申请日：2011-02-15
IPC分类号： F01D11/14
CPC分类号： F01D11/122 , F01D17/02 , F05D2240/11 , G01B5/14
摘要： A measuring assembly for use in a gas turbine engine includes an indicia portion that extends radially inwardly from an inner surface of a ring seal structure to a location radially inwardly from tips of blades mounted on a rotor. The indicia portion of the measuring assembly comprises a section that is abraded by the blades during rotational movement of the rotor to provide a visual indication of a distance between the tips of the blades and the inner surface.
摘要翻译： 用于燃气涡轮发动机的测量组件包括从环形密封结构的内表面径向向内延伸到从安装在转子上的叶片的尖端径向向内的位置的标记部分。 测量组件的标记部分包括在转子的旋转运动期间被叶片磨损的部分，以提供叶片的尖端和内表面之间的距离的视觉指示。
-
公开(公告)号：US20120207586A1
公开(公告)日：2012-08-16
申请号：US13027354
申请日：2011-02-15
CPC分类号： F01D11/122 , F01D17/02 , F05D2240/11 , G01B5/14
摘要： A measuring assembly for use in a gas turbine engine includes an indicia portion that extends radially inwardly from an inner surface of a ring seal structure to a location radially inwardly from tips of blades mounted on a rotor. The indicia portion of the measuring assembly comprises a section that is abraded by the blades during rotational movement of the rotor to provide a visual indication of a distance between the tips of the blades and the inner surface.
摘要翻译： 用于燃气涡轮发动机的测量组件包括从环形密封结构的内表面径向向内延伸到从安装在转子上的叶片的尖端径向向内的位置的标记部分。 测量组件的标记部分包括在转子的旋转运动期间被叶片磨损的部分，以提供叶片的尖端和内表面之间的距离的视觉指示。
-
公开(公告)号：US20090022594A1
公开(公告)日：2009-01-22
申请号：US11879923
申请日：2007-07-19
IPC分类号： F01D5/30
CPC分类号： F01D5/22 , F01D5/3092
摘要： A turbine airfoil support system for supporting a turbine blade to prevent wear during turning gear operation when a rotor assembly supporting the turbine blade rotates at about two revolutions per minute (RPM) to keep the turbine ready for quick startup requirements. The turbine airfoil support system may be formed from a radial biasing spring positioned between a radially outermost point of a disk steeple extending from a rotor assembly and a radially inner surface of the platform. The radial biasing spring may be formed from a first flat member with a disk steeple engaging surface, a second flat member with a blade platform engaging surface, a bent biasing section extending from the first flat member to the second flat member and biasing the first and second flat members away from each other, and a stress reducing member extending from the second flat member toward the first flat member.
摘要翻译： 一种涡轮机翼型支撑系统，用于支撑涡轮叶片以防止在转动齿轮操作期间的磨损，当支撑涡轮机叶片的转子组件以每分钟约两转（RPM）旋转以保持涡轮机准备快速起动要求时。 涡轮机翼型支撑系统可以由位于从转子组件延伸的盘尖端的径向最外点与平台的径向内表面之间的径向偏置弹簧形成。 径向偏置弹簧可以由具有盘尖接合表面的第一平坦构件，具有叶片平台接合表面的第二平坦构件形成，从第一平坦构件延伸到第二平坦构件的弯曲偏压部分，并且偏压第一和 第二平面构件彼此远离，以及从所述第二平坦构件朝向所述第一平坦构件延伸的应力减小构件。
-
公开(公告)号：US08485785B2
公开(公告)日：2013-07-16
申请号：US11879923
申请日：2007-07-19
CPC分类号： F01D5/22 , F01D5/3092
摘要： A turbine airfoil support system for supporting a turbine blade to prevent wear during turning gear operation when a rotor assembly supporting the turbine blade rotates at about two revolutions per minute (RPM) to keep the turbine ready for quick startup requirements. The turbine airfoil support system may be formed from a radial biasing spring positioned between a radially outermost point of a disk steeple extending from a rotor assembly and a radially inner surface of the platform. The radial biasing spring may be formed from a first flat member with a disk steeple engaging surface, a second flat member with a blade platform engaging surface, a bent biasing section extending from the first flat member to the second flat member and biasing the first and second flat members away from each other, and a stress reducing member extending from the second flat member toward the first flat member.
-
公开(公告)号：US20140301834A1
公开(公告)日：2014-10-09
申请号：US13855886
申请日：2013-04-03
IPC分类号： F01D25/10
CPC分类号： F01D25/10 , F01D11/24 , F02C7/26 , F05D2260/20
摘要： A turbine engine heating system configured to heat compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine heating system may include a heating air extraction system configured to withdraw air from the turbine engine and to pass that air thru a heating element configured to increase a temperature of the air supplied by the heating air extraction system. The air may then be passed to a heating air supply system via an air movement device. The heating air supply system may be in communication with a turbine cylinder cavity of the turbine engine positioned radially outward from at least one turbine assembly. The heated air may be passed into the turbine cylinder cavity to reduce the cooling rate of the turbine vane carriers after shutdown and before a warm restart to limit tip rubbing.
摘要翻译： 公开了一种涡轮发动机加热系统，其构造成加热压缩机和涡轮叶片组件以消除燃气涡轮发动机的热重启期间的涡轮机和压缩机叶片尖端摩擦。 涡轮发动机加热系统可以包括加热空气抽取系统，该系统构造成从涡轮发动机抽出空气，并使该空气通过构造成增加由加热空气抽取系统供应的空气的温度的加热元件。 然后可以经由空气移动装置将空气传送到加热空气供应系统。 加热空气供应系统可以与从至少一个涡轮机组件径向向外定位的涡轮发动机的涡轮机气缸腔连通。 加热的空气可以进入涡轮机气缸腔，以降低关闭后和热再启动之前的涡轮叶片载体的冷却速率，以限制末端摩擦。
-
公开(公告)号：US5639216A
公开(公告)日：1997-06-17
申请号：US606909
申请日：1996-02-26
CPC分类号： F01D5/187 , F05D2240/81
摘要： A turbine blade has a cooling air flow path specifically directed toward cooling the platform portion of the blade root. Two cooling air passages are formed in the blade root platform just below its upper surface. Each passage extends radially outward from an inlet that receives a flow of cooling air and then extend axially along almost the entire length of the platform. Each passage also has an outlet formed in the downstream face of the platform that allows the cooling air to exit the platform and enter the hot gas flow path. The passages are formed in portions of the platform that overhang the shank portion of root.
摘要翻译： 涡轮机叶片具有专门用于冷却叶片根部的平台部分的冷却空气流动路径。 两个冷却空气通道形成在其上表面正下方的叶片根平台中。 每个通道从容纳冷却空气流的入口径向向外延伸，然后沿着平台的整个长度轴向延伸。 每个通道还具有形成在平台的下游面中的出口，其允许冷却空气离开平台并进入热气流动路径。 通道形成在平台的突出在根部的柄部上的部分中。
-
公开(公告)号：US5358379A
公开(公告)日：1994-10-25
申请号：US141756
申请日：1993-10-27
摘要： A vane for the turbine section of a gas turbine has an airfoil portion with leading edge, center and trailing edge portions. The leading edge portion is attached to the center portion by a dove tail joint that allows the leading edge portion to slide in the radial direction with respect to the center portion while preventing movement in the axial and circumferential directions, thereby eliminating thermal stresses created by differential thermal expansion between the leading edge portion and the remainder of the vane. An opening in the vane inner shroud that is normally sealed by a closure plate allows the leading edge portion to be readily replaced in the event of damage. The leading edge portion may be formed from a ceramic material and need not be supplied with cooling air.
摘要翻译： 燃气轮机的涡轮部分的叶片具有具有前缘，中心和后缘部分的翼型部分。 前缘部分通过鸠尾接头连接到中心部分，其允许前缘部分相对于中心部分在径向方向上滑动，同时防止在轴向和圆周方向上的移动，从而消除由差速器产生的热应力 前缘部分和叶片的其余部分之间的热膨胀。 通常由封闭板密封的叶片内护罩中的开口允许在损坏的情况下容易地更换前缘部分。 前缘部分可以由陶瓷材料形成，并且不需要提供冷却空气。
-
-
-
-
-
-
搜索结果
7 条记录 (耗时 0.019 秒)
