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公开(公告)号：US20100068048A1
公开(公告)日：2010-03-18
申请号：US12209355
申请日：2008-09-12
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D5/141 , F05D2240/30 , F05D2250/74 , Y10S416/02
摘要： An airfoil for a stator vane having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I is provided. The profile is carried only to three decimal places wherein Z is a distance from a platform on which the airfoil is mounted and X and Y are coordinates defining the profile at each distance Z from the platform.
摘要翻译： 提供了一种用于定子叶片的翼型，其具有基本上根据表I中所示的X，Y和Z的笛卡尔坐标值的未涂覆轮廓。 配置文件仅承载三个小数位，其中Z是与安装翼型的平台的距离，X和Y是从平台每个距离Z定义轮廓的坐标。
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公开(公告)号：US08113786B2
公开(公告)日：2012-02-14
申请号：US12209355
申请日：2008-09-12
IPC分类号： F01D9/00
CPC分类号： F01D9/041 , F01D5/141 , F05D2240/30 , F05D2250/74 , Y10S416/02
摘要： An airfoil for a stator vane having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I is provided. The profile is carried only to three decimal places wherein Z is a distance from a platform on which the airfoil is mounted and X and Y are coordinates defining the profile at each distance Z from the platform.
摘要翻译： 提供了一种用于定子叶片的翼型，其具有基本上根据表I中所示的X，Y和Z的笛卡尔坐标值的未涂覆轮廓。 配置文件仅承载三个小数位，其中Z是与安装翼型的平台的距离，X和Y是从平台每个距离Z定义轮廓的坐标。
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3.发明申请REPLACEABLE SEALS FOR TURBINE ENGINE COMPONENTS AND METHODS FOR INSTALLING THE SAME 有权涡轮发动机组件的可更换密封件及其安装方法公开(公告)号：US20140079538A1
公开(公告)日：2014-03-20
申请号：US13610269
申请日：2012-09-11
申请人： Sanji Ekanayake , Alston Ilford Scipio , Raymond Henry Goetze , Peter Samuel King , Douglas Corbin Warwick
发明人： Sanji Ekanayake , Alston Ilford Scipio , Raymond Henry Goetze , Peter Samuel King , Douglas Corbin Warwick
CPC分类号： F01D11/08 , B23P6/005 , F01D11/12 , Y10T29/49238
摘要： An assembly and method are provided for sealing a compressor in a gas turbine engine. The method comprises forming an annular groove in a compressor casing such that the groove extends circumferentially about a rotor that is housed within the casing. The compressor casing is then coupled to the rotor such that the compressor casing extends circumferentially about the rotor. A plurality of arcuate seal segments are then inserted into the annular groove without removing the rotor from the compressor casing such that the plurality of seal segments extend circumferentially about the rotor to facilitate sealing a gap that is defined between the rotor and the compressor casing.
摘要翻译： 提供了一种用于密封燃气涡轮发动机中的压缩机的组件和方法。 该方法包括在压缩机壳体中形成环形槽，使得凹槽围绕容纳在壳体内的转子周向延伸。 然后将压缩机壳体联接到转子，使得压缩机壳体围绕转子周向延伸。 然后将多个弓形密封段插入到环形槽中，而不从压缩机壳体移除转子，使得多个密封段围绕转子周向延伸，以便于密封限定在转子和压缩机壳体之间的间隙。
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4.发明授权Replaceable seals for turbine engine components and methods for installing the same 有权涡轮发动机部件的可更换密封件及其安装方法公开(公告)号：US09309776B2
公开(公告)日：2016-04-12
申请号：US13610269
申请日：2012-09-11
申请人： Sanji Ekanayake , Alston Ilford Scipio , Raymond Henry Goetze , Peter Samuel King , Douglas Corbin Warwick
发明人： Sanji Ekanayake , Alston Ilford Scipio , Raymond Henry Goetze , Peter Samuel King , Douglas Corbin Warwick
CPC分类号： F01D11/08 , B23P6/005 , F01D11/12 , Y10T29/49238
摘要： An assembly and method are provided for sealing a compressor in a gas turbine engine. The method comprises forming an annular groove in a compressor casing such that the groove extends circumferentially about a rotor that is housed within the casing. The compressor casing is then coupled to the rotor such that the compressor casing extends circumferentially about the rotor. A plurality of arcuate seal segments are then inserted into the annular groove without removing the rotor from the compressor casing such that the plurality of seal segments extend circumferentially about the rotor to facilitate sealing a gap that is defined between the rotor and the compressor casing.
摘要翻译： 提供了一种用于密封燃气涡轮发动机中的压缩机的组件和方法。 该方法包括在压缩机壳体中形成环形槽，使得凹槽围绕容纳在壳体内的转子周向延伸。 然后将压缩机壳体联接到转子，使得压缩机壳体围绕转子周向延伸。 然后将多个弓形密封段插入到环形槽中，而不从压缩机壳体移除转子，使得多个密封段围绕转子周向延伸，以便于密封限定在转子和压缩机壳体之间的间隙。
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