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Time:2016/1/6 Read:1125Time 【Font:Big Middle Small】 【Color -              
    For the shortcomings of existing gas turbine blade cooling nozzle hole to overcome from tip to hub alignment caused by each hole of the pressure and swirl uneven, and therefore, the cooling effect is not, cooling holes is designed to adapt to the arrangement of the form of the rotation direction of the swirl burner device. In a clockwise direction, from the upstream flow, the leading edge of the blade tip cooling pore at the hub of the cooling holes is further to the left; and in the left, from the upstream flow, the leading edge of the blade tip cooling pore at the hub of the cooling holes more to the right. In this way, the pressure, the flow field and the cooling effect can be achieved at each cooling hole.
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