A platform for research: civil engineering, architecture and urbanism
A platform for research: civil engineering, architecture and urbanism
METHOD AND SYSTEM FOR INTERFACING CERAMIC MATRIX COMPOSITE COMPONENT WITH METALLIC COMPONENT
PROBLEM TO BE SOLVED: To provide a method for interfacing a ceramic matrix composite component with a metallic component in a gas turbine engine.SOLUTION: An airfoil assembly for a gas turbine engine comprises: a forward end and an aft end with respect to an axial direction; and a radially outer end component 216 comprising a radially outwardly facing end surface 302 having a non-compression load-bearing feature extending radially outwardly from the outwardly facing end surface and formed integrally with the outer end component. The feature is configured to mate with a complementary feature formed in a radially inner surface 308 of a first airfoil assembly support structure 214, the feature selectively positioned orthogonally to a force imparted to the airfoil assembly. The airfoil assembly also comprises a radially inner end component 204, and a hollow airfoil body 210 extending therebetween, the airfoil body configured to receive a strut 208 couplable at a first end 206 to the first airfoil assembly support structure.SELECTED DRAWING: Figure 3
【課題】ガスタービンエンジンにおいてセラミックマトリクス複合材部品を金属部品に連結する方法を提供する。【解決手段】ガスタービンエンジン用の翼形部組立体は、軸方向に対し前方端と後方端と、外側を向いた端面３０２から径方向外向きに延出し外端部品２１６と一体の非圧縮負荷支持機構を有する径方向外側を向いた端面を含む径方向外端部品とを備え、機構は、第１の翼形部組立体支持構造体２１４の径方向内側面３０８に形成された相補的な機構と嵌合するように構成され、前記機構は、翼形部組立体にかかる力に直交して選択的に位置決めされる。翼形部組立体はまた、径方向内端部品２０４、およびその間で延出する中空の翼形部本体２１０を有し、前記翼形部本体は、第１の端部２０６で第１の翼形部組立体支持構造体に結合可能な支柱２０８を受けるように構成される。【選択図】図３
METHOD AND SYSTEM FOR INTERFACING CERAMIC MATRIX COMPOSITE COMPONENT WITH METALLIC COMPONENT
PROBLEM TO BE SOLVED: To provide a method for interfacing a ceramic matrix composite component with a metallic component in a gas turbine engine.SOLUTION: An airfoil assembly for a gas turbine engine comprises: a forward end and an aft end with respect to an axial direction; and a radially outer end component 216 comprising a radially outwardly facing end surface 302 having a non-compression load-bearing feature extending radially outwardly from the outwardly facing end surface and formed integrally with the outer end component. The feature is configured to mate with a complementary feature formed in a radially inner surface 308 of a first airfoil assembly support structure 214, the feature selectively positioned orthogonally to a force imparted to the airfoil assembly. The airfoil assembly also comprises a radially inner end component 204, and a hollow airfoil body 210 extending therebetween, the airfoil body configured to receive a strut 208 couplable at a first end 206 to the first airfoil assembly support structure.SELECTED DRAWING: Figure 3
【課題】ガスタービンエンジンにおいてセラミックマトリクス複合材部品を金属部品に連結する方法を提供する。【解決手段】ガスタービンエンジン用の翼形部組立体は、軸方向に対し前方端と後方端と、外側を向いた端面３０２から径方向外向きに延出し外端部品２１６と一体の非圧縮負荷支持機構を有する径方向外側を向いた端面を含む径方向外端部品とを備え、機構は、第１の翼形部組立体支持構造体２１４の径方向内側面３０８に形成された相補的な機構と嵌合するように構成され、前記機構は、翼形部組立体にかかる力に直交して選択的に位置決めされる。翼形部組立体はまた、径方向内端部品２０４、およびその間で延出する中空の翼形部本体２１０を有し、前記翼形部本体は、第１の端部２０６で第１の翼形部組立体支持構造体に結合可能な支柱２０８を受けるように構成される。【選択図】図３
METHOD AND SYSTEM FOR INTERFACING CERAMIC MATRIX COMPOSITE COMPONENT WITH METALLIC COMPONENT
セラミックマトリクス複合材部品を金属部品に連結する方法およびシステム
BRYCE LORING HEITMAN (author) / SENILE DARRELL G (author) / MICHAEL RAY TUERTSCHER (author) / GREGG SCOTT PHELPS (author) / GREGG FEIE BRIAN (author) / STEVEN JAMES MURPHY (author)
2017-02-02
Patent
Electronic Resource
Japanese
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