| 主权项 |
1. A compressor blade for a gas turbine engine, comprising:
an airfoil extending between a leading edge and a trailing edge and operable to affect a change in total pressure between an upstream side of the airfoil and a downstream side of the airfoil; a stalk having a lower attachment portion and an upper portion defining a platform, the platform having a first side and a second side, a portion of the first side of the platform being coupled to the airfoil, the platform extending between first and second opposite ends, the platform including a leading edge having two corners at the upstream side of the airfoil at the respective first and second opposite ends of the platform, and a trailing edge having two corners at the downstream side of the airfoil at the respective first and second opposite ends of the platform; and only first and second single corner undercuts,
the first single corner undercut located only beneath a first single corner of the leading edge of the platform and only beneath a portion of the leading edge of the airfoil, the first single corner undercut located at the second end of the platform;the second corner undercut located only beneath a second single corner of the trailing edge of the platform and only beneath a portion of the trailing edge of the airfoil, the second single corner undercut located at the first end of the platform. |
