BLADE/DISK DOVETAIL BACKCUT FOR BLADE/DISK STRESS REDUCTION (6FA AND 6FA+e, STAGE 1)
摘要
<p>Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.</p>
申请公布号
WO2006124618(A1)
申请公布日期
2006.11.23
申请号
WO2006US18471
申请日期
2006.05.12
申请人
GENERAL ELECTRIC COMPANY;CHAN, SZE BUN, BRIAN;GOPALAKRISHNAN, BABU, SANTHANA;ZEMITIS, WILLIAM, SCOTT
发明人
CHAN, SZE BUN, BRIAN;GOPALAKRISHNAN, BABU, SANTHANA;ZEMITIS, WILLIAM, SCOTT