Volume 20, Issue 7 (July 2020)
Modares Mechanical Engineering 2020, 20(7): 1761-1771 |
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1- Heat & Fluids Department, Mechanical Engineering Faculty, Babol Noshirvani University of Technology, Babol, Iran
2- Heat & Fluids Department, Mechanical Engineering Faculty, Babol Noshirvani University of Technology, Babol, Iran ,ranjbar@nit.ac.ir
2- Heat & Fluids Department, Mechanical Engineering Faculty, Babol Noshirvani University of Technology, Babol, Iran ,
Abstract: (3691 Views)
Variable-area injectors are suitable for developing throttleable rocket engines because it is difficult to efficiently control thrust when fixed-area injectors are used. A pintle injector is a variable-area injector that can be used to control the mass flow rate of propellants. In practice, an injector plate containing several fixed-area injectors is replaced with a single pintle injector. In this research, a two-stage pintle injector is designed, manufactured, and tested for the effects of dimensionless numbers (Momentum ratio, Weber number, and discharge coefficient) on the injector’s performance, including the spray angle change, which is an important characteristic of the spray. The tests were done at ambient temperature and pressure conditions. The Weber number ranged from 19 to 1830, and the ratio of the fuel to the oxidizer momentum was varied from 0.2 to 13. Water is used instead of the oxidizer as a central propellant, and the air is used instead of the fuel as an external propellant. Shadowgraph and photography were used to measure the spray angle and study the desired parameters. Empirical relationships between functional parameters and dimensionless numbers were obtained that can be used in the design process.
Article Type: Original Research |
Subject:
Two & Multi Phase Flow
Received: 2019/09/17 | Accepted: 2020/05/3 | Published: 2020/05/3
Received: 2019/09/17 | Accepted: 2020/05/3 | Published: 2020/05/3
References
1. Lefebvre A. Atomization and sprays. Boca Raton: CRC Press; 1989. [Link] [DOI:10.1201/9781482227857]
2. Gill GS, Nurick WH. Liquid Rocket Engine Injectors. Washington: NASA; 1976. Report no: NASA-SP-8089. Contract no: NAS3-12014. [Link]
3. Casiano MJ, Hulka JR, Yang V. Liquid-propellant rocket engine throttling: A comprehensive review. Journal of Propulsion and Power. 2010;26(5):897-923. [Link] [DOI:10.2514/1.49791]
4. Gilroy R, Sackheim R. The Lunar module descent engine-a historical summary. 25th Joint Propulsion Conference, 12-16 July 1989, Monterey, CA, USA. Reston: AIAA; 1989. [Link] [DOI:10.2514/6.1989-2385]
5. Betts EM, Jr Frederick RA. A historical systems study of liquid rocket engine throttling capabilities. 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 25-28 July 2010, Nashville, TN. Reston: AIAA; 2010. [Link] [DOI:10.2514/6.2010-6541]
6. Dressler GA, Bauer JM. TRW pintle engine heritage and performance characteristics. 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 24-28 July 2000, Las Vegas, NV, USA. Reston: AIAA; 2000. [Link] [DOI:10.2514/6.2000-3871]
7. Gavitt KR, Mueller TJ. Testing of the 650 klbf LOX/LH2 low cost pintle engine. 37th Joint Propulsion Conference and Exhibit, 08-11 July 2001, Salt Lake City, UT, USA. Reston: AIAA; 2001. [Link] [DOI:10.2514/6.2001-3987]
8. Calvignac J, Dang L, Tramel TL, Paseur L. Design and testing of non-toxic RCS thrusters for second generation reusable launch vehicle. 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 20-23 July 2003, Huntsville, Alabama. Reston: AIAA; 2003. [Link] [DOI:10.2514/6.2003-4922]
9. Gromski JM, Majamaki AN, Chianese SG, Weinstock VD, Kim TS. Northrop grumman TR202 LOX/LH2 deep throttling engine technology project status. 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 25-28 July 2010, Nashville, TN. Reston: AIAA; 2010. [Link] [DOI:10.2514/6.2010-6725]
10. Seedhouse E. Space X: Making commercial spaceflight a reality. New York: Springer; 2013. pp. 156-165. [Link]
11. Austin BL, Heister SD, Anderson WE. Characterization of pintle engine performance for nontoxic hypergolic bipropellants. Journal of Propulsion and Power. 2005;21(4):627-635. [Link] [DOI:10.2514/1.7988]
12. Bedard M, Feldman T, Rettenmaier A, Anderson W. Student design/build/test of a throttleable LOX-LCH4 thrust chamber. 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 30 July 2012-01 August 2012, Atlanta, Georgia. Reston: AIAA; 2012. [Link] [DOI:10.2514/6.2012-3883]
13. Yue CG, Chang XL, Yang SJ, Zhang YH. Numerical simulation of a pintle variable thrust rocket Engine. In: Yu Y, Yu Z, Zhao J, editors. Computer Science for Environmental Engineering and EcoInformatics, CSEEE 2011, Communications in Computer and Information Science. 159th vol. Berlin: Springer; 2011. [Link] [DOI:10.1007/978-3-642-22691-5_84]
14. Sakaki K, Kakudo H, Nakaya S, Tsue M, Isochi H, Suzuki K, et al. Optical measurements of ethanol/liquid oxygen rocket engine combustor with planar pintle Injector. 51st AIAA/SAE/ASEE Joint Propulsion Conference, July 27-29, 2015, Orlando, FL. Reston: AIAA; 2015. [Link] [DOI:10.2514/6.2015-3845]
15. Sakaki K, Kakudo H, Nakaya S, Tsue M, Kanai R, Suzuki K, et al. Performance evaluation of rocket engine combustors using ethanol/liquid oxygen pintle injector. 52nd AIAA/SAE/ASEE Joint Propulsion Conference, July 25-27, 2016, Salt Lake City, UT. Reston: AIAA; 2016. [Link] [DOI:10.2514/6.2016-5080]
16. Son M, Yu K, Koo J, Kwon OC, Kim JS. Injection condition effects of a pintle injector for liquid rocket engines on atomization performances. Journal of ILASS-Korea. 2015;20(2):114-120. [Link] [DOI:10.15435/JILASSKR.2015.20.2.114]
17. Son M, Yu K, Koo J, Kwon OC, Kim JS. Effects of momentum ratio and weber number on spray half angles of liquid controlled pintle injector. Journal of Thermal Science. 2015;24:37-43. [Link] [DOI:10.1007/s11630-015-0753-7]
18. Yu K, Son M, Koo J. Effects of opening distance on liquid-gas spray of pintle injector under atmospheric condition. Journal of the Korean Society for Aeronautical and Space Sciences. 2015;43(7):585-592. [Korean] [Link] [DOI:10.5139/JKSAS.2015.43.7.585]
19. Son M, Radhakrishnan K, Koo J, Kwon OC, Kim HD. Design Procedure of a movable pintle injector for liquid rocket engines. Journal of Propulsion and Power. 2017;33(4). [Link] [DOI:10.2514/1.B36301]
20. Olyaei Gh, Kebriaee A. Experimental study of liquid sheet breakup in cross flow. Modares Mechanical Engineering. 2019;19(4):845-853. [Persian] [Link]
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