| 摘要 |
<p>PROBLEM TO BE SOLVED: To provide gas turbine engine rotor blades that have enhanced vibration behavior such that resonance excitation does not occur at rotating blades of first and following stages.SOLUTION: A gas turbine blade comprises an airfoil 1 extending in the radial direction from a blade root 2 to a blade tip 3, defining a span (s) ranging from 0% at the blade root 2 to 100% at the blade tip 3, and extending in the axial direction from a leading edge 9 to a trailing edge 10. The leading edge 9 and the trailing edge 10 limit a chord with an axial chord length 6 defined by an axial length of a straight line connecting the leading edge 9 and trailing edge 10 of the airfoil 1 depending on the span. The axial chord length 6 increases at least from 80% span to 100% span.</p> |
