-
公开(公告)号：US20100322758A1
公开(公告)日：2010-12-23
申请号：US12528436
申请日：2008-02-14
IPC分类号： F01D11/00
CPC分类号： F04D29/542 , F01D5/143 , F01D9/042 , F01D25/246 , F04D29/644 , Y02T50/673
摘要： The invention relates to a compressor, particularly a high pressure compressor, of a gas turbine, particularly of a gas turbine aircraft engine, having at least one rotating blade ring on the rotor side, and having at least one guide blade ring on the stator side, wherein the, or each, guide blade ring is formed of a plurality of guide blade segments, and wherein each guide blade segment is formed of a plurality of individual blades. According to the invention, adjacent individual blades (11, 12; 12, 13; 13, 14) are permanently connected to each other within each guide blade segment (10) of at least one guide blade ring on opposing surfaces positioned radially outward, whereas the same are not connected to each other on opposing surfaces positioned radially inward.
摘要翻译： 本发明涉及一种特别是燃气轮机飞机发动机的燃气轮机的压缩机，特别是高压压缩机，其具有在转子侧上的至少一个旋转叶片环，并且在定子侧具有至少一个导向叶片环 其中所述导向叶片环或每个引导叶片环由多个引导叶片段形成，并且其中每个引导叶片段由多个单独叶片形成。 根据本发明，相邻的单个叶片（11,12; 12,13; 13,14）在位于径向向外定位的相对表面上的至少一个引导叶片环的每个引导叶片段（10）内彼此永久连接，而 它们在径向向内定位的相对表面上彼此不相连。
-
公开(公告)号：US08333553B2
公开(公告)日：2012-12-18
申请号：US12528436
申请日：2008-02-14
CPC分类号： F04D29/542 , F01D5/143 , F01D9/042 , F01D25/246 , F04D29/644 , Y02T50/673
摘要： The invention relates to a compressor, particularly a high pressure compressor, of a gas turbine, particularly of a gas turbine aircraft engine, having at least one rotating blade ring on the rotor side, and having at least one guide blade ring on the stator side, wherein the, or each, guide blade ring is formed of a plurality of guide blade segments, and wherein each guide blade segment is formed of a plurality of individual blades. According to the invention, adjacent individual blades (11, 12; 12, 13; 13, 14) are permanently connected to each other within each guide blade segment (10) of at least one guide blade ring on opposing surfaces positioned radially outward, whereas the same are not connected to each other on opposing surfaces positioned radially inward.
摘要翻译： 本发明涉及一种特别是燃气轮机飞机发动机的燃气轮机的压缩机，特别是高压压缩机，其具有在转子侧上的至少一个旋转叶片环，并且在定子侧具有至少一个导向叶片环 其中所述导向叶片环或每个引导叶片环由多个引导叶片段形成，并且其中每个引导叶片段由多个单独叶片形成。 根据本发明，相邻的单个叶片（11,12; 12,13; 13,14）在位于径向向外定位的相对表面上的至少一个引导叶片环的每个引导叶片段（10）内彼此永久连接，而 它们在径向向内定位的相对表面上彼此不相连。
-
搜索结果
2 条记录 (耗时 0.012 秒)
