航空科学技术
航空科學技術
항공과학기술
AERONAUTICAL SCIENCE AND TECHNOLOGY
2015年
2期
1-9
,共9页
高压涡轮%气膜冷却%数值仿真%源项法%耦合计算
高壓渦輪%氣膜冷卻%數值倣真%源項法%耦閤計算
고압와륜%기막냉각%수치방진%원항법%우합계산
high-pressure turbine%iflm-cooling%numerical simulation%source term method%coupling calculation
随着航空发动机性能的不断提高，高压涡轮进口燃气温度不断提升，远远超过了金属许用温度。为了安全运行，需要对涡轮进行冷却。由于气膜冷却具有冷却效率高、易于实现等优点，在航空发动机中得到了广泛的应用。但由于用于气膜冷却的空气流量大、且与主流掺混过程复杂，如何准确模拟冷气与主流的掺混是气冷涡轮的设计关键。本文对气膜冷却涡轮仿真采用的冷气喷射源项法和真实气膜孔仿真方法的国内外发展及现状进行了阐述，总结了两种方法的优缺点和工程应用情况，并从工程应用角度对下一步的研究方向提出了建议。
隨著航空髮動機性能的不斷提高，高壓渦輪進口燃氣溫度不斷提升，遠遠超過瞭金屬許用溫度。為瞭安全運行，需要對渦輪進行冷卻。由于氣膜冷卻具有冷卻效率高、易于實現等優點，在航空髮動機中得到瞭廣汎的應用。但由于用于氣膜冷卻的空氣流量大、且與主流摻混過程複雜，如何準確模擬冷氣與主流的摻混是氣冷渦輪的設計關鍵。本文對氣膜冷卻渦輪倣真採用的冷氣噴射源項法和真實氣膜孔倣真方法的國內外髮展及現狀進行瞭闡述，總結瞭兩種方法的優缺點和工程應用情況，併從工程應用角度對下一步的研究方嚮提齣瞭建議。
수착항공발동궤성능적불단제고，고압와륜진구연기온도불단제승，원원초과료금속허용온도。위료안전운행，수요대와륜진행냉각。유우기막냉각구유냉각효솔고、역우실현등우점，재항공발동궤중득도료엄범적응용。단유우용우기막냉각적공기류량대、차여주류참혼과정복잡，여하준학모의랭기여주류적참혼시기랭와륜적설계관건。본문대기막냉각와륜방진채용적랭기분사원항법화진실기막공방진방법적국내외발전급현상진행료천술，총결료량충방법적우결점화공정응용정황，병종공정응용각도대하일보적연구방향제출료건의。
Inlet gas temperature of the high pressure turbine is increasing as aircraft engine performance improving, which is much higher than metal endurable temperature. So cooling technology is used in turbine for working safety. Film-cooling, with high cooling efifciency and easy realization, is widely applied in aircraft engines. However, for the usage of large mass flow cooling air and the complexity of mixing with main gas flow, how to simulate the mixing process become a key step of design in cooling turbine. In this paper, the developments of source term method and real film hole method were expatiated, the two methods were widely used in film-cooling turbine aerodynamic simulation. The advantages, disadvantages and engineering application status of the two methods were summarized, and the next research directions in engineering application were suggested.
