<p>The present invention relates to a fan blade (34) in an axial gas turbine engine. The blade platform (46) is constructed to fracture adjacent the airfoil portion (48) of the blade so as to locate the fractured edge of the platform in the root portion (44). As a result of this benign platform, damage to successive fan blades during a blade loss condition is reduced. In addition, various construction details are developed in the airfoil and root portion of the fan blade to reduce damage to fan blades during impact with adjacent blades. <IMAGE></p>
申请公布号
EP0874136(B1)
申请公布日期
2003.08.13
申请号
EP19980303199
申请日期
1998.04.24
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
ZIPPS, ROBERT H.;SPAULDING, REGINALD H.;TODD, EDWARD S.;KASPROW, ROBERT F.;KLAPPROTH, HERMAN C.;WELCH, DOUGLAS A.;KURZ, PHYLLIS L.;CAFASSO, JOSEPH J.