| 摘要 |
<p>#CMT# #/CMT# The method involves draping a set of folds (7) over a core comprising perforations, and optionally cutting the folds along incisions (8) formed opposite to the perforations. Blades (12) of vanes or vane preforms are inserted via the incisions and perforations, where the vanes are made of composite or metal material. Another set of folds (10) is draped over vane platforms (9) forming a rectifier preform. Resin is injected into a closed mold with the preform, and the resin-impregnated preform is polymerized. Molded piece having shape and dimensions of a rectifier is retrieved from the mold. #CMT#USE : #/CMT# Method for manufacturing a rectifier of a turbomachine (claimed) for separating rotating vanes of low or high pressure compressors. #CMT#ADVANTAGE : #/CMT# The method enables avoiding flaws in aerodynamic flow when large portion of blade/platform connecting radius is found in thickness of an outer ring, thus minimizing disruption in aerodynamic level. The vane platforms are connected to each other to ensure angular wedging and better mechanical resistance. The method enables avoiding the need for fastening elements such as rivets and bolts, to simplify assembly among the vanes and rings. The method enables eliminating the need of welding the flanges that are distanced from a platform/ring assembly area and reducing the length of a low-pressure compressor. The method ensures realization of composite outer rings and vanes to create mass gain of about 13 percentage relative to a welded assembly among outer rings and vanes made of titanium. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows a three-dimensional view explaining insertion of stator vanes during draping of an outer ring. 7, 10 : Folds 8 : Incisions 9 : Vane platforms 12 : Vane blades.</p> |
