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公开(公告)号：EP0590032B1
公开(公告)日：1999-04-28
申请号：EP92913702.4
申请日：1992-03-09
发明人： FORMAN, Thomas, P. , FOX, Rance, B. , SABAK, George, E. , SANDS, Timothy, A. , VALLIER, Paul, A.
CPC分类号： B29D99/0025 , B29C33/301 , B29C33/72 , B29C47/003 , B29C47/004 , B29C47/0057 , B29C69/001 , B29C69/002 , B29C70/347 , B29C70/48 , B29K2105/0809 , F01D5/282 , F01D9/02 , F05D2230/00 , Y02T50/43 , Y02T50/672 , Y10T428/13 , Y10T428/1314 , Y10T428/1321 , Y10T428/1362 , Y10T428/1369 , Y10T428/24058 , Y10T428/24124 , Y10T428/249922
摘要： A multi-vane structure for incorporation in an aircraft gas turbine engine has vanes of complex geometry made of braided fibers which are continuous about the cavities defined by the vanes. These complex geometry parts are prepared by providing a plurality of removable mandrels, stacking the mandrels along a horizontal axis in a cavity end to cavity end configuration, braiding about the mandrels, cutting the mandrels adjacent the cavity end faces, side stacking the mandrels so the faces are placed in a parallel orientation and molding. Utilizing braided fibers instead of hand lay-up woven fibers eliminates seams and produces cavities having continuous fibers about the periphery thereof which substantially increases the strength and dimensional reproducibly of the part.
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公开(公告)号：EP0590032A1
公开(公告)日：1994-04-06
申请号：EP92913702.0
申请日：1992-03-09
发明人： FORMAN, Thomas, P. , FOX, Rance, B. , SABAK, George, E. , SANDS, Timothy, A. , VALLIER, Paul, A.
CPC分类号： B29D99/0025 , B29C33/301 , B29C33/72 , B29C47/003 , B29C47/004 , B29C47/0057 , B29C69/001 , B29C69/002 , B29C70/347 , B29C70/48 , B29K2105/0809 , F01D5/282 , F01D9/02 , F05D2230/00 , Y02T50/43 , Y02T50/672 , Y10T428/13 , Y10T428/1314 , Y10T428/1321 , Y10T428/1362 , Y10T428/1369 , Y10T428/24058 , Y10T428/24124 , Y10T428/249922
摘要： A multi-vane structure for incorporation in an aircraft gas turbine engine has vanes of complex geometry made of braided fibers which are continuous about the cavities defined by the vanes. These complex geometry parts are prepared by providing a plurality of removable mandrels, stacking the mandrels along a horizontal axis in a cavity end to cavity end configuration, braiding about the mandrels, cutting the mandrels adjacent the cavity end faces, side stacking the mandrels so the faces are placed in a parallel orientation and molding. Utilizing braided fibers instead of hand lay-up woven fibers eliminates seams and produces cavities having continuous fibers about the periphery thereof which substantially increases the strength and dimensional reproducibly of the part.
摘要翻译： 复杂几何形状，由连续纤维构成，并围绕由限定的腔体的编织结构的多个叶片（18），设计成配合在具有叶片飞机的燃气涡轮发动机和（9）所述刀片。 具有复杂几何形状，这些部件通过多个可拆卸模具（14A，14B），其通过接触所述腔的端部（15B沿着以图案的水平轴线（18）堆栈，16a的方式制成 ）; 然后执行围绕矩阵编织（23），基质被切割以邻近所述腔体（17）的端面上的位置，横向堆叠矩阵，以便将他们的脸平行的方向和 执行模制。 使用编织纤维代替机械编织增强纤维消除了接头并为其周边提供了带有连续纤维的空腔，这大大增加了工件的强度和尺寸再现性。
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