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公开(公告)号：US08882443B2
公开(公告)日：2014-11-11
申请号：US12995376
申请日：2009-05-28
CPC分类号： F04D27/0207 , F04D27/0215 , F04D27/0238 , F04D29/526 , F04D29/681 , F04D29/684
摘要： A turbomachine or high pressure compressor including a stator casing housing a plurality of compression stages that are spaced apart in an axial direction along the central axis of the turbomachine, each compression stage including a row of rotor blades followed by a row of stator vanes. The compressor further includes an air injection system including at least one air injection passage through the casing and including an outlet segment that opens out in an inclined manner upstream from and directed towards a row of rotor blades into a set-back zone of the inside face of the casing.
摘要翻译： 一种涡轮机或高压压缩机，包括容纳沿着涡轮机的中心轴线沿轴向隔开的多个压缩级的定子壳体，每个压缩级包括一排转子叶片，随后是一排定子叶片。 压缩机还包括一个空气注入系统，该系统包括至少一个通过该壳体的空气注入通道，并且包括一个出口段，该出口段以倾斜的方式向上转向一排转子叶片进入内表面的后退区域 的套管。
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公开(公告)号：US20060193721A1
公开(公告)日：2006-08-31
申请号：US11359408
申请日：2006-02-23
申请人： Gerard Adam , Xavier Agneray , Kevin Dos Santos , Son Le Hong
发明人： Gerard Adam , Xavier Agneray , Kevin Dos Santos , Son Le Hong
IPC分类号： F04D29/58
CPC分类号： F01D25/246 , F01D25/145 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2260/231 , F05D2300/614 , Y02T50/675
摘要： The present invention relates to an improvement in the clearances 12 between a casing and the moving blades 11 of a rotor 1 of a turbomachine, in particular a casing provided for this purpose, and also to a turbomachine fitted with such a casing. The invention applies in particular to aircraft turbojet engines. It relates more particularly to a turbomachine inner casing 21 comprising a plurality of annular shrouds 23 that are provided with flanges 24 for joining two adjacent shrouds 23 together. According to the invention, this inner casing 21 further includes: at least one circumferential heat shield 5 covering the flanges 24 in contact with two adjacent shrouds 23; and a cavity 6 filled with a first thermal insulation 8, said cavity being located between a concave internal surface 51a, 52a of the heat shield 5 and the flanges 24. The heat shield 5 is formed by a plurality of sectors 50 joined end to end.
摘要翻译： 本发明涉及壳体与涡轮机的转子1的动叶片11之间的间隙12的改进，特别是为此目的而设置的壳体，以及装配有这种壳体的涡轮机。 本发明特别适用于飞机涡轮喷气发动机。 更具体地涉及一种涡轮机内壳21，其包括多个环形护罩23，其具有用于将两个相邻的罩23连接在一起的凸缘24。 根据本发明，该内壳21还包括：至少一个圆周热屏蔽5，其覆盖与两个相邻的罩23接触的凸缘24; 以及填充有第一绝热层8的空腔6，所述空腔位于隔热罩5的凹形内表面51a，52a和凸缘24之间。隔热罩5由多个扇形区50形成， 结束
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公开(公告)号：US20110076133A1
公开(公告)日：2011-03-31
申请号：US12995376
申请日：2009-05-28
IPC分类号： F03B11/00
CPC分类号： F04D27/0207 , F04D27/0215 , F04D27/0238 , F04D29/526 , F04D29/681 , F04D29/684
摘要： A turbomachine or high pressure compressor including a stator casing housing a plurality of compression stages that are spaced apart in an axial direction along the central axis of the turbomachine, each compression stage including a row of rotor blades followed by a row of stator vanes. The compressor further includes an air injection system including at least one air injection passage through the casing and including an outlet segment that opens out in an inclined manner upstream from and directed towards a row of rotor blades into a set-back zone of the inside face of the casing.
摘要翻译： 一种涡轮机或高压压缩机，包括容纳沿着涡轮机的中心轴线沿轴向隔开的多个压缩级的定子壳体，每个压缩级包括一排转子叶片，随后是一排定子叶片。 压缩机还包括一个空气注入系统，该系统包括至少一个通过该壳体的空气注入通道，并且包括一个出口段，该出口段以倾斜的方式向上转向一排转子叶片进入内表面的后退区域 的套管。
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公开(公告)号：US07614845B2
公开(公告)日：2009-11-10
申请号：US11359408
申请日：2006-02-23
IPC分类号： F01D25/26
CPC分类号： F01D25/246 , F01D25/145 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2260/231 , F05D2300/614 , Y02T50/675
摘要： The present invention relates to an improvement in the clearances 12 between a casing and the moving blades 11 of a rotor 1 of a turbomachine, in particular a casing provided for this purpose, and also to a turbomachine fitted with such a casing. The invention applies in particular to aircraft turbojet engines.It relates more particularly to a turbomachine inner casing 21 comprising a plurality of annular shrouds 23 that are provided with flanges 24 for joining two adjacent shrouds 23 together. According to the invention, this inner casing 21 further includes: at least one circumferential heat shield 5 covering the flanges 24 in contact with two adjacent shrouds 23; and a cavity 6 filled with a first thermal insulation 8, said cavity being located between a concave internal surface 51a, 52a of the heat shield 5 and the flanges 24. The heat shield 5 is formed by a plurality of sectors 50 joined end to end.
摘要翻译： 本发明涉及壳体与涡轮机的转子1的动叶片11之间的间隙12的改进，特别是为此目的而设置的壳体，以及装配有这种壳体的涡轮机。 本发明特别适用于飞机涡轮喷气发动机。 更具体地涉及一种涡轮机内壳21，其包括多个环形护罩23，其具有用于将两个相邻的罩23连接在一起的凸缘24。 根据本发明，该内壳21还包括：至少一个圆周热屏蔽5，其覆盖与两个相邻的罩23接触的凸缘24; 以及填充有第一绝热层8的空腔6，所述空腔位于隔热罩5的凹形内表面51a，52a和凸缘24之间。隔热罩5由多个扇形区50形成，这些扇形区50端对端 。
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