首页> 外文OA文献 >Structural tailoring of aircraft engine blade subject to ice impact constraints
【2h】

Structural tailoring of aircraft engine blade subject to ice impact constraints

机译:受冰冲击约束的飞机发动机叶片的结构调整

代理获取
本网站仅为用户提供外文OA文献查询和代理获取服务,本网站没有原文。下单后我们将采用程序或人工为您竭诚获取高质量的原文,但由于OA文献来源多样且变更频繁,仍可能出现获取不到、文献不完整或与标题不符等情况,如果获取不到我们将提供退款服务。请知悉。

摘要

Results are presented for the minimum weight design of SR2 unswept blade made of (titanium/graphite-epoxy/titanium) sub s fiber composite. The blade which is rotating at high RPM is subject to ice impact. The root chord length, blade thicknesses at five stations, and graphite-epoxy ply orientation are chosen as design variables. Design constraints are placed on the behavior variables: local leading edge strain and root damage parameter (combined stress failure criteria) as a function due to ice impact, maximum spanwise centrifugal stress at the root of the deformed blade due to local damage, first three natural frequencies, and resonance margin after impact. The method of feasible directions is employed to solve the inequality constrained minimization problem. The effect of ice speed and the ice impact location on the final design are discussed.
机译:给出了由(钛/石墨-环氧/钛)亚微米级纤维复合材料制成的SR2未清扫刀片的最小重量设计结果。以高RPM旋转的叶片易受冰冲击。选择根部弦长,五个工位处的叶片厚度以及石墨-环氧树脂层定向作为设计变量。设计约束放在行为变量上:局部前缘应变和根部损坏参数(组合应力破坏准则)由于冰的影响而变化,因局部损坏而导致变形叶片根部的最大翼展方向离心应力,前三个自然频率和撞击后的共振余量。采用可行方向法求解不等式约束最小化问题。讨论了冰速和冰撞击位置对最终设计的影响。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
代理获取

客服邮箱:kefu@zhangqiaokeyan.com

京公网安备:11010802029741号 ICP备案号:京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有
  • 客服微信

  • 服务号