推进技术
推進技術
추진기술
JOURNAL OF PROPULSION TECHNOLOGY
2015年
4期
587-594
,共8页
杨晓东%侯安平%李漫露%周盛
楊曉東%侯安平%李漫露%週盛
양효동%후안평%리만로%주성
频率失谐%气弹稳定性%颤振%能量法%气动阻尼%叶片间相角
頻率失諧%氣彈穩定性%顫振%能量法%氣動阻尼%葉片間相角
빈솔실해%기탄은정성%전진%능량법%기동조니%협편간상각
Frequency mistuning%Aeroelastic stability%Flutter%Energy method%Aerodynamic damping%In-ter-blade phase angle
为了深入理解频率失谐对跨声速压气机气弹稳定性的影响,基于能量法建立了跨声速颤振实验转子的全周气动阻尼计算模型,数值分析了转子叶片频率交替失谐、随机失谐以及线性失谐对其气弹稳定性的影响。数值计算了该转子的气动性能,颤振边界和叶片模态,其结果和实验数据吻合较好;研究不同模态、不同叶片间相位角条件下谐调转子的气动阻尼,结果表明叶片间相位角对叶片气动阻尼均有较大的影响,尤其在一弯模态下,叶片气动阻尼对叶片间相位角最敏感;对该转子所有叶片的平均气动阻尼而言,失谐的存在弱化了叶片间相角对叶片气动阻尼的影响,显著提高了该转子最不稳定状态的平均阻尼达到7~11倍,反之使其最稳定状态的平均阻尼降低约50%;失谐转子中不同叶片的气动阻尼表现出显著差异,其受叶片局部失谐模式及失谐量的影响较大。
為瞭深入理解頻率失諧對跨聲速壓氣機氣彈穩定性的影響,基于能量法建立瞭跨聲速顫振實驗轉子的全週氣動阻尼計算模型,數值分析瞭轉子葉片頻率交替失諧、隨機失諧以及線性失諧對其氣彈穩定性的影響。數值計算瞭該轉子的氣動性能,顫振邊界和葉片模態,其結果和實驗數據吻閤較好;研究不同模態、不同葉片間相位角條件下諧調轉子的氣動阻尼,結果錶明葉片間相位角對葉片氣動阻尼均有較大的影響,尤其在一彎模態下,葉片氣動阻尼對葉片間相位角最敏感;對該轉子所有葉片的平均氣動阻尼而言,失諧的存在弱化瞭葉片間相角對葉片氣動阻尼的影響,顯著提高瞭該轉子最不穩定狀態的平均阻尼達到7~11倍,反之使其最穩定狀態的平均阻尼降低約50%;失諧轉子中不同葉片的氣動阻尼錶現齣顯著差異,其受葉片跼部失諧模式及失諧量的影響較大。
위료심입리해빈솔실해대과성속압기궤기탄은정성적영향,기우능량법건립료과성속전진실험전자적전주기동조니계산모형,수치분석료전자협편빈솔교체실해、수궤실해이급선성실해대기기탄은정성적영향。수치계산료해전자적기동성능,전진변계화협편모태,기결과화실험수거문합교호;연구불동모태、불동협편간상위각조건하해조전자적기동조니,결과표명협편간상위각대협편기동조니균유교대적영향,우기재일만모태하,협편기동조니대협편간상위각최민감;대해전자소유협편적평균기동조니이언,실해적존재약화료협편간상각대협편기동조니적영향,현저제고료해전자최불은정상태적평균조니체도7~11배,반지사기최은정상태적평균조니강저약50%;실해전자중불동협편적기동조니표현출현저차이,기수협편국부실해모식급실해량적영향교대。
A full-annulus computational model for aerodynamic damping prediction based on energy method is demonstrated by the consideration of a transonic flutter test rotor to improve the understanding of the influence of frequency mistuning on aeroelastic stability of transonic compressor. The numerical analysis of alternate ,ran?dom and linear frequency mistuning was performed in detail. The numerical results of rotor aerodynamic perfor?mance,flutter boundary and blade mode shape are respectively consistent with experimental results closely. Ac?cording to the aerodynamic damping of tuned rotor under the different inter-blade phase angle (IBPA) and modes,it indicates that blade aerodynamic damping is affected greatly by IBPA,especially for the first bending mode. The blade aerodynamic damping is most sensitive to IBPA. The further investigation on various frequency mistuning modes show that,the existence of mistuning weaken the effect of IBPA on blade average aerodynamic damping. Especially,the average aerodynamic damping of all blades at the most unstable condition increases about 7 to 11 times. On the contrary,it decreases about 50%at the most stable condition. There are significant dif?ferences among the aerodynamic damping of each mistuned blade which is affected obviously by the blade local mistuned mode and mistuning amount.