燃气涡轮试验与研究
燃氣渦輪試驗與研究
연기와륜시험여연구
GAS TURBINE EXPERIMENT AND RESEARCH
2014年
2期
14-20
,共7页
航空发动机%气动矢量喷管%轴对称%双喉道%几何参数%内特性%第四代战斗机
航空髮動機%氣動矢量噴管%軸對稱%雙喉道%幾何參數%內特性%第四代戰鬥機
항공발동궤%기동시량분관%축대칭%쌍후도%궤하삼수%내특성%제사대전두궤
aero-engine%fluidic thrust-vectoring nozzle%axisymmetric%dual-throat%geometrical parameter%internal performance%the fourth generation fighter
采用数值模拟方法，就轴对称双喉道气动矢量喷管主要几何参数对喷管内特性(气动矢量角、气动矢量效率、推力系数、流量系数)的影响进行了分析，并得到了一组内特性较优的喷管几何参数。结果表明，次流注入角、空腔收敛角、空腔长度等几何因素对喷管矢量特性影响较大，次流注入角、空腔扩张角等对喷管推力特性有较大影响。优选后的喷管矢量角可达15.5°，矢量效率达5.70°/1%，喷管推力系数为0.92。
採用數值模擬方法，就軸對稱雙喉道氣動矢量噴管主要幾何參數對噴管內特性(氣動矢量角、氣動矢量效率、推力繫數、流量繫數)的影響進行瞭分析，併得到瞭一組內特性較優的噴管幾何參數。結果錶明，次流註入角、空腔收斂角、空腔長度等幾何因素對噴管矢量特性影響較大，次流註入角、空腔擴張角等對噴管推力特性有較大影響。優選後的噴管矢量角可達15.5°，矢量效率達5.70°/1%，噴管推力繫數為0.92。
채용수치모의방법，취축대칭쌍후도기동시량분관주요궤하삼수대분관내특성(기동시량각、기동시량효솔、추력계수、류량계수)적영향진행료분석，병득도료일조내특성교우적분관궤하삼수。결과표명，차류주입각、공강수렴각、공강장도등궤하인소대분관시량특성영향교대，차류주입각、공강확장각등대분관추력특성유교대영향。우선후적분관시량각가체15.5°，시량효솔체5.70°/1%，분관추력계수위0.92。
Numerical studies on the effect of geometrical parameters on internal performance of axisymmet-ric dual-throat fluidic thrust-vectoring nozzles were performed, and the optimized geometrical parameters of nozzle were obtained. The results indicated that vector performance was influenced by secondary inject angle, cavity divergence angle and cavity length, and thrust performance was greatly influenced by second-ary inject angle and cavity divergence angle. The optimized results indicated that vector angle could reach 15.5°, vector efficiency 5.70°/1%, and thrust ratio 0.92.
