| 摘要 |
A method for varying the aerodynamic shape of a blade (22, 24) of a gas turbine provides for this blade (22, 24) to be provided with a coating (42) composed of a shape-memory alloy. Hot air (36) is transported via channels (32) to the coated blade (22, 24), in order to cause a phase change in the coating (42), and an aerodynamic shape change to the blade (22, 24).
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