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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2006, Vol. 27 ›› Issue (6): 998-1004.

• 论文 • Previous Articles     Next Articles

Numerical Simulation of the Aerodynamic Performance of Turbine with Coolant Injection

ZHANG Man1, QIAO Wei-yang1, ZENG Jun2, HUANG Kang-cai2   

  1. 1. School of Engine and Energy, Northwestern Polytechnical University, Xi'an 710072, China;2. Gas Turbine Establishment, Chengdu 610500, China
  • Received:2005-07-11 Revised:2005-12-08 Online:2006-12-25 Published:2006-12-25

Abstract: Detailed numerical simulations are performed to research the mechanics of the total pressure loss at the three-dimensional turbine flow field with coolant injection from single row of holes at the different directions and from all the rows of holes.The results show that the flow loss is reduced with the increasing of the coolant mass when the injection angle is 30° at the instant of injection from single row of holes.The interaction among the different rows of coolant injection is the major reason of the flow loss for the multi-rows film cooling.The further numerical investigations indicate that the optimizing election of coolant injection mass flow rate can reduce the total pressure loss apparently.It is shown that the interval rows of holes on the blade surface may be the best way to reduce the flow loss.

Key words: coolant injection, flow loss, numerical simulation, optimizing election, interval row of holes

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