摘要
内燃机功率提高以及高原、高空功率恢复的要求,推动着内燃机增压比不断提高,高增压技术成为先进内燃机发展的核心关键技术之一.提高压比将导致离心压气机稳定工作范围和效率急剧降低,高压比离心压气机的气动稳定性与扩稳成为高增压技术研究的核心和难点.为拓宽跨声速离心压气机的稳定工作范围,对一种离心压气机叶片式机匣处理结构开展了研究,利用数值模拟研究了叶片式机匣内部流动特性与拓稳机理,并对导叶形式进行了优化,最后通过试验进行验证,结果表明:采用优化的导叶机匣处理结构,能够有效拓宽离心压气机高压比流动范围,喘振流量可拓宽6%~8%.
The turbocharging boost ratio of internal combustion engines is increasing with the requirements of power intensification and power recovery at high altitudes.High turbocharging technology has become one of the key technologies in advanced internal combustion engines area.The increase of the pressure ratio will lead to a sharp decrease in the stable working range and the efficiency of centrifugal compressor.The aerodynamic stability and working range expansion of the high-pressure-ratio centrifugal compressor become a core research area.In order to broaden the stable working range,a centrifugal compressor with blade casing was studied using numerical simulation to investigate the internal flow characteristics and stability mechanism.The blade form was optimized,and finally verified by experiments.The test results show that the optimized guide vane casing structure can effec-tively broaden the flow range of the high-pressure-ratio centrifugal compressor,and the surge flow range is ex-panded by 6%—8%.
作者
田红艳
侯康
佟鼎
刘欣源
王宪磊
赵洋
Tian Hongyan;Hou Kang;Tong Ding;Liu Xinyuan;Wang Xianlei;Zhao Yang(School of Mechanical Engineering,Hebei University of Technology,Tianjin 300401,China;China North Engine Research Institute,Tianjin 300400,China)
出处
《内燃机学报》
EI
CAS
CSCD
北大核心
2023年第4期361-368,共8页
Transactions of Csice
基金
国防科技重点实验室基金资助项目(6142212180101)
河北省自然科学基金资助项目(A2021202014).
关键词
离心压气机
叶片式机匣
高压比
数值模拟
centrifugal compressor
vane casing treatment
high-pressure-ratio
numerical simulation
