装有脉冲爆震主燃烧室的燃气涡轮发动机热力性能计算  

Calculating Performance of Gas Turbine Engine with Embedded PDC(Pulse Detonation Combustor)

作　　者：邓君香[1] 严传俊[1] 郑龙席[1] 邱华[1] 蒋联友[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《西北工业大学学报》2008年第3期362-367,共6页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金重点项目(50336030)资助

摘　　要：建立了用脉冲爆震燃烧室代替传统燃气涡轮发动机主燃烧室的热力性能分析模型,进行了装有脉冲爆震主燃烧室的混合式燃气涡轮发动机与传统燃气涡轮发动机在设计点的工作参数和性能参数的对比与分析,还比较了飞行状态改变时2种发动机性能变化趋势。计算结果表明:与传统燃气涡轮发动机相比,装有脉冲爆震主燃烧室的燃气涡轮发动机的单位推力提高27.1%,单位燃油消耗率降低21.3%;在飞行高度一定的情况下,随着飞行马赫数的增大,混合式发动机的单位推力减小,单位燃油消耗率增大;在飞行马赫数一定的情况下,随着飞行高度的增大,混合式发动机的单位推力增大,单位燃油消耗率降低;若使涡轮前燃气压力相等,则可以减少混合式发动机的压气机和涡轮的级数,减轻发动机的重量,提高发动机的推重比。Keeping in mind what has been done in Refs. 3 through 6 on the performance mentioned in the title, we develop our method of calculation and the necessary software. In the full paper, we explain in some detail our method of calculation and the analysis of calculated results. In this abstract, we just add some pertinent remarks to listing the three topics of explanation. The first topic is.. gas turbine engine with embedded PDC. In the first topic, Fig. 2 in the full paper shows the ideal thermodynamic cycle of gas turbine engine with embedded PDC. The second topic is. the method of performance calculation. In the second topic, although eqs. （1） through （6） are all well known, we explain how to utilize them in our performance calculation. The third topic is ： calculated performance results and their analysis. In the third topic, we compare gas turbine engine with embedded PDC with a conventional gas turbine engine. The three subtopics of the third topic are： static performance at sea level （subtopic 3.1）, the effect of flight speed on engine performance （subtopic 3.2）, and the effect of flight altitude on engine performance （subtopic 3.3）. In subtopic 3.1, Table 1 shows that the gas turbine engine with embedded PDC produces 27.1% higher specific thrust and has 21.3% lower specific fuel consumption than a conventional gas turbine engine. In subtopic 3.2, we give Figs. 3 through 8 to show that the specific thrust decreases with increasing flight speed at a given flight altitude. In subtopic 3.3, Figs. 9 through 14 show that the specific thrust increases with increasing flight altitude at a given flight speed.

关 键 词：燃气涡轮 燃烧室 热力循环 脉冲爆震主燃烧室(PDC) 性能 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]