Thermodynamic cycle performance of detonation gas turbine with variable specific heat capacity
-
摘要: 为分析变比热容下爆震燃气轮机的热力循环性能,建立了考虑比热容随工质成分及温度变化的爆震燃气轮机热力循环模型,分析中同时考虑了压气机、燃烧室、透平等部件的效率.在不同比较条件下,利用变比热容法对比分析研究了燃气轮机爆震循环(DCGT)、Brayton循环和Humphrey循环燃气轮机的热力循环性能.计算结果表明:与Brayton循环相比,DCGT具有较大性能优势;在透平前温度为1620K且压比为16.5时,DCGT热效率较Brayton循环高28.8%;在无量纲吸热量为4.25且压比为16.5时,DCGT热效率则较Brayton循环高30.7%.Abstract: In order to analyze the thermodynamic cycle performance of detonation gas turbine with variable specific heat capacity, the thermodynamic cycle model of detonation gas turbine was established by considering the specific heat capacity varying with the composition and temperature of the working fluid, as well as the efficiency of the compressor, combustor, turbine and other components. Under different comparison conditions, the thermodynamic cycle performances of detonation cycle of gas turbine (DCGT), Brayton cycle and Humphrey cycle gas turbine were analyzed by using variable specific heat capacity method. The results show that the performance of DCGT is better than that of Brayton cycle. When the turbine inlet temperature is 1620K and the pressure ratio is 16.5, the thermal efficiency of DCGT is increased by 28.8% compared with Brayton cycle. When the dimensionless absorbed heat is 4.25 and the pressure ratio is 16.5, the thermal efficiency of DCGT is 30.7% higher than Brayton cycle.
-
Key words:
- variable specific heat capacity /
- gas turbine /
- detonation /
- thermodynamic cycle /
- performance analysis
-
[1] 严传俊,范玮,黄希桥.脉冲爆震发动机原理及关键技术[M].西安:西北工业大学出版社,2005. [2] William H H,David T P.Thermodynamic cycle analysis of pulse detonation engines[J].Journal of Propulsion and Power,2002,18(1):68-76. [3] WU Yuhui,MA Fuhua,Yang V.System performance and thermodynamic cycle analysis of air breathing pulse detonation engines[J].Journal of Propulsion and Power,2003,19(4):556-567. [4] Vutthivithayarak R,Braun E M,Lu F K.On thermodynamic cycles for detonation engines[R].Manchester,UK:28th International Symposium on Shock Waves,2012. [5] Nordeen C A.Thermodynamics of a rotating detonation engine[D].Connecticut,US:University of Connecticut,2013. [6] 邱华,严传俊,范玮.部分充填下脉冲爆震发动机的热力循环性能分析[J].航空动力学报,2008,23(4):718-723. QIU Hua,YAN Chuanjun,FAN Wei.Analysis on thermodynamic performance of partially-fueled pulse detonation engine[J].Journal of Aerospace Power,2008,23(4):718-723.(in Chinese) [7] 邱华,严传俊,熊姹.带喷管脉冲爆震发动机单循环性能分析模型[J].航空动力学报,2005,20(5):818-821. QIU Hua,YAN Chuanjun,XIONG Cha.A single-cycle performance model of the pulse detonation engine with nozzle[J].Journal of Aerospace Power,2005,20(5):818-821.(in Chinese) [8] 张强,何立明,陈鑫,等.两级脉冲爆震发动机的理想热力循环及性能分析[J].推进技术,2012,33(4):499-504. ZHANG Qiang,HE Liming,CHEN Xin,et al.Ideal thermodynamic cycle and performance analysis of 2-stage pulse detonation engine[J].Journal of Propulsion Technology,2012,33(4):499-504.(in Chinese) [9] 陈鑫,于锦禄,何立明,等.脉冲爆震发动机热力循环性能分析[J].空军工程大学学报,2011,12(2):1-5. CHEN Xin,YU Jinlu,HE Liming,et al.The analysis of pulse detonation engine thermodynamic cycle performance[J].Journal of Air Force Engineering University,2011,12(2):1-5.(in Chinese) [10] 范孝华,林志勇,周进.脉冲爆震和斜爆震发动机热力循环过程分析[C]//第十四届全国激波与激波管学术会议论文集.北京:中国力学学会,2010:260-266. [11] 李晓丰,郑龙席,邱华,等.两相脉冲爆震涡轮发动机原理性试验[J].航空动力学报,2013,28(12):2731-2736. LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.Principle experiments on two phase pulse detonation turbine engine[J].Journal of Aerospace Power,2013,28(12):2731-2736.(in Chinese) [12] LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.Experimental investigations on the power extraction of a turbine driven by a pulse detonation combustor[J].Chinese Journal of Aeronautics,2013,26(6):1353-1359. [13] 李晓丰.脉冲爆震涡轮发动机技术研究[D].西安:西北工业大学,2013. LI Xiaofeng.The technology research on the pulse detonation turbine engine[D].Xi'an:Northwestern Polytechnical University,2013.(in Chinese) [14] The Engineering ToolBox.Specific heat of oxygen gas-O2-at temperatures ranging 175-6000K[EB/OL].[2014-12-10].http://www.engineeringtoolbox.com/oxygen-d_978.html. [15] The Engineering ToolBox.Specific heat of carbon dioxide gas-CO2-temperatures ranging 175-6000K[EB/OL].[2014-12-10].http://www.engineeringtoolbox.com/carbon-dioxide-d_974.html. [16] The Engineering ToolBox.Specific heat of nitrogen gas-N2-at temperatures ranging 175-6000K[EB/OL].[2014-12-10].http://www.engineeringtoolbox.com/nitrogen-d_977.html. [17] The Engineering ToolBox.Specific heat of water vapor-H2O-at temperatures ranging 175-6000K[EB/OL].[2014-12-10].http://www.engineeringtoolbox.com/water-vapor-d_979.html. [18] The Engineering Toolbox.Specific heat of methane gas-CH4-at temperatures ranging 200-1100K[EB/OL].[2014-12-10].http://www.engineeringtoolbox.com/methane-d_980.html.
点击查看大图
计量
- 文章访问数: 939
- HTML浏览量: 2
- PDF量: 493
- 被引次数: 0