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Influence de l’épaisseur du bord de fuite sur les performances aérodynamiques d’une aube de turbine basse pression
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Tran_81161200_2018.pdf
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- One of the biggest challenges in turbomachinery is to reduce the production cost, the maintenance cost and the weight of the turbojet engine. The adopted ideology is to decrease the number of the blades while having the same, or better, capabilities. The industry has chosen the very high lift blades which can extract more work by paying the price of a strong adverse pressure gradient on the suction side. At cruise altitude, theses blades can be affected by the diminution the Reynolds number. This study focuses on the performance of the very high lift blade of low pressure turbine under those conditions, and it will also focus on the influence of the trailing edge thickness. Three types of very high lift blade of different trailing edge thickness will be submitted to multiple flows with a Reynolds number, based on the chord, ranging between 50 000 and 250 000. A wake generator is used to simulate the rotor part of the turbine. A big focus will be put on the analysis of the obtained measures from the point of view of an experimenter.