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TURBINE BLADE OR VANE FOR A GAS TURBINE AND CASTING CORE FOR PRODUCTION THEREIN
TURBINE BLADE OR VANE FOR A GAS TURBINE AND CASTING CORE FOR PRODUCTION THEREIN
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机译：燃气轮机的涡轮叶片或叶片及其生产用铸件芯
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摘要
The invention relates to a turbine vane having a novel interior structure. The invention further relates to novel turbulence elements (42) connected directly upstream of openings (28) disposed at the rear edge (20) of the vane blade (16) of the turbine vane. The same are disposed in a sequence, each having a flow side (44) against which a coolant (40) flows and which is at least partially arched in a concave manner according to the invention. Preferably, the turbulence elements (42) are configured in a crescent-shaped manner. This aerodynamically particularly unfavorable shape of the turbulence elements (42) causes increased pressure loss, thus complicating the through-flow of coolants. This makes it possible to enlarge the openings (28) without resulting in an increased consumption of coolant. The invention also provides a substantially more stable casting core (110), since the openings (130) required in the casting core (110) for the production of the webs (30) of a turbine vane may now be placed at further distances than before. This results in higher stability of the casting core (110) in the region of the casting core rear edge (120), thus the same is less prone to breakage in said region, and thus may be handled in a more robust manner.
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