燃气涡轮试验与研究
燃氣渦輪試驗與研究
연기와륜시험여연구
GAS TURBINE EXPERIMENT AND RESEARCH
2011年
4期
28-31
,共4页
复合角%多斜孔板%流量系数%几何结构参数%气动参数
複閤角%多斜孔闆%流量繫數%幾何結構參數%氣動參數
복합각%다사공판%류량계수%궤하결구삼수%기동삼수
compound angle%inclined multi-hole plates%discharge coefficient%configuration parameters%aerodynamic parameters
试验研究了多种结构多斜孔板的流量系数，分析了孔倾角、孔偏角、板厚等几何结构参数，和孔内流动雷诺数、主次流温比、主流马赫数等气动参数对具有复合角的多斜孔板流量系数的影响。研究结果表明：①孔内流动雷诺数小于4000时，流量系数与雷诺数呈线性关系，大于5000时流量系数变化不大；②孔偏角小于40。时，流量系数随孔偏角的增大而减小，大于40。时对流量系数的影响不大；③流量系数随板厚及主次流温比的增大而减小，孔内换热量对多斜孔板流量系数的影响较大；④流量系数随主流马赫数的增大而增大。本研究结果对航空发动机燃烧室空气流量分配及冷却设计具有一定的参考价值。
試驗研究瞭多種結構多斜孔闆的流量繫數，分析瞭孔傾角、孔偏角、闆厚等幾何結構參數，和孔內流動雷諾數、主次流溫比、主流馬赫數等氣動參數對具有複閤角的多斜孔闆流量繫數的影響。研究結果錶明：①孔內流動雷諾數小于4000時，流量繫數與雷諾數呈線性關繫，大于5000時流量繫數變化不大；②孔偏角小于40。時，流量繫數隨孔偏角的增大而減小，大于40。時對流量繫數的影響不大；③流量繫數隨闆厚及主次流溫比的增大而減小，孔內換熱量對多斜孔闆流量繫數的影響較大；④流量繫數隨主流馬赫數的增大而增大。本研究結果對航空髮動機燃燒室空氣流量分配及冷卻設計具有一定的參攷價值。
시험연구료다충결구다사공판적류량계수，분석료공경각、공편각、판후등궤하결구삼수，화공내류동뢰낙수、주차류온비、주류마혁수등기동삼수대구유복합각적다사공판류량계수적영향。연구결과표명：①공내류동뢰낙수소우4000시，류량계수여뢰낙수정선성관계，대우5000시류량계수변화불대；②공편각소우40。시，류량계수수공편각적증대이감소，대우40。시대류량계수적영향불대；③류량계수수판후급주차류온비적증대이감소，공내환열량대다사공판류량계수적영향교대；④류량계수수주류마혁수적증대이증대。본연구결과대항공발동궤연소실공기류량분배급냉각설계구유일정적삼고개치。
Measurements of discharge coefficients for different configurations of the inclined multi-hole plates with compound angle are presented. The factors affecting the discharge coefficient are discussed such as inclination angle, orientation angle, plate thickness, the Reynolds number, temperature ratio between the main flow and the secondary flow and Mach numbers of the main flow. Results show that linear relationship can be observed when Reynolds number is below 4 000, but more than 5 000 it doesn＇ t affect discharge co- efficient much; when orientation angle is below 40° the increased orientation angle results in decreased discharge coefficients; the discharge coefficient decreases as the plate thickness and the temperature ratio increases; and the increased Mach number leads to higher discharge coefficient. This study is referential to flow distribution and cooling design of aero-engine combustor.
