Experimental study on flow distribution in micro backflow combustor

Experimental study on flow distribution in micro backflow combustor

Junli Yu Chungang Qu Xuan Wang 

Civil Aviation University of China, College of Aeronautical Engineering, Tianjin 300300, China

Corresponding Author Email: 
18 December 2017
15 May 2018
30 September 2018
| Citation



Based on the measurement principle of plugging method and the changes in the relationship between temperature and resistance of thermistor, this study explores the flow distribution of backflow combustor of a micro jet engine. The experimental results show that with the increase of the inlet flow of the combustion, the flow distribution of different airflow channels on the wall of the flame tube will change in the micro backflow combustor. When the combustor’s inlet flow is relatively large, the flow distribution approaches to the value calculated by the area method. At the same time, the experimental results show that this method is suitable for the study of flow distribution.


flow distribution, backflow combustor, plugging method, thermistor, micro jet engine

1. Introduction
2. Test Model
3. Measurement Principle of Test
4. Test Results and Analysis
5. Conclusions

Basic scientific research fee project of central colleges and universities (3122015C009); Experimental technological innovation fund (02-14-01); Scientific research startup fund project (2011QD07S).


[1] Xia C, Fu X, Wan Z, Huang GP, Chen J. (2013). Research on windmill startingcharacteristics of MTE-D micro turbine engine. Chinese Journal of Aeronautics 26(4): 858-867. http://dx.doi.org/10.1016/j.cja. 2013.06.003

[2] Rideau JF, Guyader G, Cloarec A. (2008). Microturbo families of turojet engine for missiles and UAV’s from the tr60 to the new bypass turpass turbojet engine generation. AIAA 2008-4590

[3] Aly ME, Mohamed KK, Hesham EK. (2016). Theoretical and experimental analysis of a micro turbojet engine’s performance. International Journal of Scientific & Engineering Research 7(1): 404-410.

[4] Ralph TD, Charles CG. (1956). Discharge coefficients for combustor liner air entry holes I-circular holes with parallel flow. NACA TN 3663.

[5] Ralph TD. (1958). Discharge coefficients for combustor liner air entry holes II-flush rectangular holes, Step Louvers, and Scoops. NACA TN 3924.

[6] Camaraza-Medina Y, Khandy NH, Carlson KM, Cruz-Fonticiella OM, García-Morales OF, Reyes-Cabrera D. (2018). Evaluation of condensation heat transfer in air-cooled condenser by dominant flow criteria. Mathematical Modelling of Engineering Problems 5(2): 76-82. https://doi.org/10.18280/mmep.050204

[7] Francis UH, Herman M. (1947). Effect of airflow distribution and total pressure loss on performance of one sixth segment of turbojet combustor. NACA-RM-SE7K16.

[8] Robert RT, Jack G. (1969). Analysis of total pressure loss and airflow distribution for annular gas turbine combustors. NASA-TN-D-5385.

[10]  in RS. (1988). Aviation gas turbine combustor. Aerospace publishing house, CHN.

[11] Liu X. (2018). Study on the temperature characteristics of phase-change energy storage building materials based on ansys. Chemical Engineering Transactions 66: 385-390. https://doi.org/10.3303/CET1866065

[12] Wang BJ, Chen T, Zhao Y, Peng W, Wang J, Xia JY, Jiang MZ. (2018). Effects of high voltage pulsed electric field on antioxidant activity and extraction of tea polysaccharides for third grade ripe pu’er tea. Chemical Engineering Transactions 64: 319-324. https://doi.org/10.3303/CET1864054