| 摘要 |
For the rotor and stator blades of turbomachines, more particularly of gas-turbine engines, an airfoil design is provided with a defined area of a skeleton line angle distribution for skeleton lines of airfoil sections near the gap. With the distribution of the dimensionless skeleton line angles (α) over the chord length (l) in a certain area between two limiting curves (7, 8) according to the present invention, and the corresponding course of the skeleton lines in a blade portion extending up to 30 percent of the blade height, a uniformed pressure distribution is ensured, minimizing disturbances and losses due to the influence of the gap.
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