| 摘要 |
A method of decreasing the operational stresses acting on a target airfoil (130) row in a turbine engine (100); wherein the target airfoil (130) row is bordered on each side by a first upstream airfoil (130) row and a first downstream airfoil (130) row; the first upstream airfoil (130) row and the first downstream airfoil (130) row having substantially the same number of similar airfoils (130) and both comprising one of a row of rotor blades (120), (126) and a row of stator blades (122), (128), and the target airfoil (130) row comprising the other; the method comprising the step of: configuring the circumferential position of the airfoils (130) of the first upstream airfoil (130) row and the airfoils (130) of first downstream airfoil (130) row such that at least 90% of the airfoils (130) of the first upstream airfoil (130) row and at least 90% of the airfoils (130) of the first downstream airfoil (130) row comprise a clocking relationship of between 25% and 75% pitch.
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