CAJ | 학술논문

压气机叶型的椭圆形前缘相比传统圆弧形前缘能减小流动损失，扩大攻角范围，但加工难度提高。为了尽可能减少加工成本、充分利用椭圆形前缘的气动优势，研究了在不同来流条件下椭圆形前缘与圆弧形前缘的气动性能差异。利用椭圆方程重新设计CDA叶型的前缘；引入SST湍流模型加γ-θ转捩模型对计算模型进行数值模拟，分析叶片前缘的切向速度与熵分布；研究了叶片前缘曲率与局部流动损失的相关性，并详细比较了在不同来流条件下椭圆形前缘与圆弧形前缘的气动性能。分析结果表明，在攻角小于2°的正攻角、较高来流马赫数、较低来流湍流度与雷诺数条件下椭圆形前缘优势更明显。
압기궤협형적타원형전연상비전통원호형전연능감소류동손실，확대공각범위，단가공난도제고。위료진가능감소가공성본、충분이용타원형전연적기동우세，연구료재불동래류조건하타원형전연여원호형전연적기동성능차이。이용타원방정중신설계CDA협형적전연；인입SST단류모형가γ-θ전렬모형대계산모형진행수치모의，분석협편전연적절향속도여적분포；연구료협편전연곡솔여국부류동손실적상관성，병상세비교료재불동래류조건하타원형전연여원호형전연적기동성능。분석결과표명，재공각소우2°적정공각、교고래류마혁수、교저래류단류도여뢰낙수조건하타원형전연우세경명현。
Compared to the traditional arc-shaped leading edge, the elliptical leading edge of a compressor blade can reduce flow loss and expand the range of attack angle.However, it also increases manufacture difficulties.To minimize processing costs and make full use of the aerodynamic advantages of the elliptical leading edge, the aero-dynamic performance differences under different conditions of arc-shaped leading edge and elliptical leading edge were studied.The leading edge of CDA airfoils was redesigned by elliptic equations.By numerical simulation using SST turbulence model andγ-θtransition model, the tangential velocity and static entropy distribution were analyzed. The correlation between the curvature of leading edge and local flow loss was studied.Furthermore, the aerodynamic performances of different shapes of leading edge compressor blades were compared.The results showed that in the condition of higher Mach number, lower stream turbulence intensity and Reynolds, the advantage of elliptical lead-ing edge is more obvious when the attack angle is positive and less than 2°.