| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide a rotor blade platform in a gas turbine engine. <P>SOLUTION: The rotor blade platform (130) includes a first platform leg (142), a second platform leg (144) and a platform portion (140) coupled to the first and second platform legs, wherein the first platform leg is secured to the platform portion by a first retainer (150) coupled to a first rotor blade (102), and the second platform leg is secured to the platform portion by a second retainer (152) coupled to a second rotor blade (104). <P>COPYRIGHT: (C)2009,JPO&INPIT</p> |
