ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Tests of pulse detonation turbine engine performance with thrust augmentation devices
Received date: 2015-01-13
Revised date: 2015-03-25
Online published: 2015-04-21
Supported by
National Natural Science Foundation of China(50906072,51306154);the Fundamental Research Funds for the Central Universities(3102014JCY01003);Natural Science Basic Research Plan in Shaanxi Province of China(2015JM5221)
To acquire experimental propulsive performance of pulse detonation turbine engine(PDTE), thrust augmentation devices, such as converge/diverge nozzles and ejector, are installed on the turbine exit of two-tube PDTE experimental system. Experimental investigations are carried out to research the influences of thrust augmentation devices on the working condition and propulsive performance of PDTE. The PDTE experimental system is in the self-airbreathing working mode with working frequency from 10 Hz to 20 Hz. Liquid gasoline is used as fuel. Results show that the turbine speed, compression ratio and flow of compressor are all decreased with different degrees when converge/diverge nozzles are installed to the PDTE experimental system. However, the engine thrust is increased with the use of nozzles. Compared with the system without nozzle(thrust of which is 114.95 N at working frequency 20 Hz), the maximum thrust of the system with nozzle is 143.3 N and the thrust augmentation is 24.7%. And the maximum specific thrust is 749.87 N·s/kg. The thrust of the PDTE experimental system can be further increased with the installation of ejector to the system with nozzle. The maximum thrust at this condition is 200.67 N and the thrust augmentation is 39.8%. And the thrust augmentation can still be increased with the increase of working frequency.
QIU Hua , XU Zeyang , ZHENG Longxi , DUAN Xiaoyao . Tests of pulse detonation turbine engine performance with thrust augmentation devices[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016 , 37(2) : 522 -532 . DOI: 10.7527/S1000-6893.2015.0083
[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, 2005:1-12. YAN C J, FAN W, HUANG X Q. Principle and key technologies of pulse detonation[M]. Xi'an:Northwestern Polytechnical University Press, 2005:1-12(in Chinese).
[2] KAILASANATH K. Review of propulsion applications of detonation waves[J]. AIAA Journal, 2000, 38(9):1698-1708.
[3] ROY G D, FROLOV S M, BORISOV A A, et al. Pulse detonation propulsion:Challenges, current status, and future perspective[J]. Progress in Energy and Combustion Science, 2004, 30(6):545-672.
[4] WILLIAM H H, DAVID T P. Thermodynamic cycle analysis of pulse detonation engines[J]. Journal of Propulsion and Power, 2002, 18(1):68-76.
[5] SCRAGG R L. Detonation cycle gas turbine engine system having intermittent fuel and air delivery:US006000214A[P]. 1997-12-14.
[6] JOHNSON J E, DUNBAR L W, BUTLER L. Combined cycle pulse detonation turbine engine:US6442930B[P]. 2002-09-03.
[7] VENKATARAMANI K S, BUTLER L, BAILEY W A. Pulse detonation system for a gas turbine engine:US6928804B2[P]. 2005-08-15.
[8] ORLANDO R J, VENKATARAMANI K S, LEE C P. Gas turbine engine having improved core system:US7093446B2[P]. 2006-08-22.
[9] PETTERS D P, FELDER J L. Engine system performance of pulse detonation concepts using the NPSS program:AIAA-2002-3910[R]. Reston:AIAA, 2002.
[10] GOLDMEER J, TANGIRALA V, DEAN A. Systems-level performance estimation of a pulse detonation based hybrid engine[J]. Journal of Engineering for Gas Turbines & Power, 2008, 130(1):82-93.
[11] ANDRUS I Q, KING P I. Evaluation of a high bypass turbofan hybrid utilizing a pulsed detonation combustor:AIAA-2007-5074[R]. Reston:AIAA, 2007.
[12] 何龙, 郑龙席, 邱华, 等. 脉冲爆震涡轮发动机性能计算[J]. 推进技术, 2012, 33(5):665-670. HE L, ZHENG L X, QIU H, et al. Calculating performance of pulse detonation turbo engine[J]. Journal of Propulsion Technology, 2012, 33(5):665-670(in Chinese).
[13] RASHEED A, FURMAN A H, DEAN A J. Pressure measurements and attenuation in a hybrid multitube pulse detonation turbine system[J]. Journal of Propulsion and Power, 2009, 25(1):148-161.
[14] RASHEED A, FURMAN A H, DEA A J. Experimental investigations of the performance of a multitube pulse detonation turbine system[J]. Journal of Propulsion and Power, 2011, 27(3):586-596.
[15] ANDREW S G, ROBERT D, DAVID M, et al. Experimental comparison of axial turbine performance under pulsed-air and pulsed-detonation flows:AIAA-2013-3624[R]. Reston:AIAA, 2013.
[16] ROUSER K P, KING P I, SCHAUER F R, et al. Time-resolved flow properties in a turbine driven by pulsed detonations[J]. Journal of Propulsion and Power, 2014, 30(6):1528-1536.
[17] MAEDA S, KASAHARA J, MATSUO A, et al. Analysis on thermal efficiency of non-compressor type pulse detonation turbine engines[J]. Transactions of the Japan Society for Aeronautical and Space Sciences, 2010, 53(181):192-206.
[18] DENG J X, ZHENG L X, YAN C J, et al. Experimental investigations of a pulse detonation combustor integrated with a turbine[J]. International Journal of Turbo & Jet-Engines, 2008, 25(4):247-257.
[19] LI X F, ZHENG L X, QIU H, 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.
[20] 李晓丰, 郑龙席, 邱华, 等. 脉冲爆震涡轮发动机原理性试验研究[J]. 实验流体力学, 2013, 27(6):1-5. LI X F, ZHENG L X, QIU H, et al. Experimental study on principle of pulse detonation turbine engine[J]. Journal of Experiments in Fluid Mechanics, 2013, 27(6):1-5(in Chinese).
[21] 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 X F, ZHENG L X, QIU H, et al. Principle experiments on two phase pulse detonation turbine engine[J]. Journal of Aerospace Power, 2013, 28(12):2731-2736(in Chinese).
[22] SCHAUER F, BRADLEY R, HOKE J. Interaction of a pulsed detonation engine with a turbine:AIAA-2003-0891[R]. Reston:AIAA, 2003.
[23] TOSHIYUKI T, SHINICHI S, TERUO Y, et al. Interaction between two cylinders in a pulse detonation engine[J]. International Journal of Energetic Materials and Chemical Propulsion, 2009, 8(6):489-500.
[24] MCBRIDE B J, GORDON S. Computer program for calculation of complex chemical equilibrium compositions and applications:NASA RP-1311[R]. Washington, D.C.:NASA, 1996.
[25] MA F H, CHOI J Y, YANG V. Propulsive performance of airbreathing pulse detonation engines[J]. Journal of Propulsion and Power, 2006, 22(6):1188-1203.
[26] QIU H, XIONG C, FAN W. One-dimensional unsteady design method for pulsed detonation engine nozzles[J]. Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering, 2014, 228(13):2496-2507.
/
| 〈 |
|
〉 |
CJA