成果報告書詳細
管理番号20160000000718
タイトル*平成27年度中間年報 次世代構造部材創製・加工技術開発 次世代構造部材創製・加工技術開発事業の周辺技術・関連課題における小規模研究開発の実施 航空機エンジン耐熱部品 革新的プリフォーム成形・複合化技術の研究開発
公開日2016/12/3
報告書年度2015 - 2015
委託先名三菱重工航空エンジン株式会社
プロジェクト番号P15006
部署名材料・ナノテクノロジー部
和文要約
英文要約Title:Development of Technologies for Next-Generation structure component creation and processing. (FY2015-FY2016)FY2015 Annual Report
The mechanical fasteners are used to assemble airframe composite parts in current aircraft structures. In the recent development of the commercial aero engines, geared turbo fan engine optimizes the work and efficiency between high and low pressure turbine, in the results, low pressure turbine could bare the more higher speed spool and inlet gas temperature. There is increasing interests of high temperature capability of Ceramic Matrix Composites (CMCs), therefore the needs of development of the SiC/SiC CMCs material and application for gas turbine engines. It is true that CMCs is expensive to manufacturing and a challenge to reduce the manufacturing cost to embody the CMCs parts in the commercial aero engines. This study would develop innovative preforming manufacturing technology and composite process technology, which are simplifying the three dimensional preform into quasi two dimensional preforms, and reducing extensive composite process time into cost effective manufacturing time. This study will conduct designing the CMCs prototype part as low pressure turbine blade and manufacture the subject. The CMCs prototype part has the two dimensional aerofoil feature with certain fiber orientation and volume percent of fiber as high mechanical and thermal loaded low pressure turbine blade. In this work, the commercial grade fiber, UBE Tyranno ZMI fiber has been chosen. The two different types of preforming methods were considered for producing near-net shape of aerofoil geometry with designated fiber orientation. Melt Infiltration (MI) technology is considered as shorter composite process cycle comparing to PIP process. UBE Tyranno ZMI fiber does not have temperature capability sustaining against the conventional MI in-process temperature. With this back ground, the high speed MI method is considered to reduce the silicon infiltration exposure time without the degradation of fiber characteristics. This year of our study focus on producing the various plate type preforms to confirm that the matrix infiltrates through representative aerofoil thickness. The two plate type preforms have been produced as the result. These plate test pieces will be used for developing high speed MI technology and the micro-structural and mechanical characterization will be evaluate in subsequent of this study. Also the various protective layers on the ZMI fiber surface have been tested to reduce degradation due to the MI processing heat as a basic experimental study.
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