CAJ | 학술논문

为设计一套合理的带气膜燃气透平动叶冷却结构，采用一套设计流程对该结构进行设计，采用管网设计及三维温度场计算对比了2种不同的拓扑形式冷却结构，分析不同结构的冷却效果，并采用较优的结构进行详细设计。结果表明：对于前缘开设气膜孔的透平动叶，第二进口采用中腔进气，尾缘出气的结构比后腔进气尾缘及中腔出气效果好；采用这套设计流程能快速设计并评估冷却结构方案，并能够在设计方案的基础上进行详细的设计，达到冷却结构快速多方案设计的要求；该设计得出冷却结构最大温度1188.15 K，平均温度1067.10 K，冷却效率0.647。
위설계일투합리적대기막연기투평동협냉각결구，채용일투설계류정대해결구진행설계，채용관망설계급삼유온도장계산대비료2충불동적탁복형식냉각결구，분석불동결구적냉각효과，병채용교우적결구진행상세설계。결과표명：대우전연개설기막공적투평동협，제이진구채용중강진기，미연출기적결구비후강진기미연급중강출기효과호；채용저투설계류정능쾌속설계병평고냉각결구방안，병능구재설계방안적기출상진행상세적설계，체도냉각결구쾌속다방안설계적요구；해설계득출냉각결구최대온도1188.15 K，평균온도1067.10 K，냉각효솔0.647。
To design a reasonable cooling structure for gas turbine rotor blades with film cooling, a set of design procedure was used to complete the design of structure. Two different topologies of the cooling structures were compared by pipe-net calculation and three-dimensional temperature field calculation. The effect of different cooling structures was analysed. Then the optimum structure was used for the detailed design. The results show that for the turbine rotor blades with film cooling in the leading edge, it is better to using the middle chamber as the second inlet and the trailing edge as outlet than the rear one with the trailing edge as outlet. By using this design process, the cooling structure can be quickly designed and evaluated. Meanwhile the detail design can be conducted on this schematic design which will meet the requirements of multiple programs and rapid cooling structure design. After the process, the maximum temperature of the cooling structure is 1188.15 K, the average temperature is 1067.10K, and the cooling efficiency is 0.647.