【作者】 屈展；

【导师】 朱惠人；

【作者基本信息】 西北工业大学 ， 工程热物理， 2004， 硕士

【摘要】 应航空发动机设计的要求，在大尺寸低速叶栅传热风洞中分别对发动机涡轮导向叶片和动叶表面的气膜冷却特性进行了研究，具体研究在不同气膜孔出流时，在不同主流雷诺数和吹风比情况下叶片表面局部换热系数的分布规律。实验中导叶叶片有15排气膜孔，动叶叶片有8排气膜孔，孔型都是圆柱孔。 对导叶和动叶，都是先研究了在150000，200000，250000，300000，350000，400000雷诺数下，没有气膜冷却时的表面换热系数分布，然后研究了气膜孔全打开和只打开单排孔时的表面换热系数分布曲线，重点研究来流雷诺数，吹风比和不同孔位出流对换热系数分布的影响规律。实验结果表明，不同孔位出流的换热由于孔排下游表面来流速度及叶片表面曲率的不同而有不同的规律，而主流雷诺数对叶片表面特别是压力面和前缘区域的换热系数比的影响较小，吹风比对换热系数影响较大(特别是导叶)，并且随气膜孔位置和来流雷诺数的变化而情况复杂。 研究了一种用用最小二乘法来拟和单排孔下游换热系数分布曲线的拟合公式，并得到了与实验数据符合良好的结果。更多还原

【Abstract】 Film cooling of the surface of a gas turbine blade was studied in a large-scale low-speed opening wind tunnel according to actual Requirement of the design of aero-engine. The surface of a gas turbine blade was cooled by cylindrical holes in the experiment,with the hole number of fifteen in stator and eight in rotor.Above all, the surface of the gas turbine blade including stator and rotor heat transfer coeficience with no film cooling hole was studied with the main stream Reynolds number of 150000,200000 50000,300000,350000,400000. Then, the heat transfer coefficience when all cooling holes opened and only one cooling hole opened was studied partly. And it’s studied how the mainstream Reynolds number, blowing ratio and the position of holes affect the heat transfer coefficience of the surface of blade. Results show that the influence of mainstream Reynolds numbers on heat transfer coefficience is little and the heat transfer coefficience raise with the increase of Reynolds numbers. The influence of the position of holes on heat transfer coefficience is complex and correlate with the mainstream speed and the balde surface curvature. And the influence of blowing ratio on heat transfer coefficience is more great (especially to stator) ,and show a complex relation to mainstream Reynolds number and the position of holes.A simulation fomular was studied to accord the heat transfer experimental data.更多还原