Unified Length Scale of Spray Structure by Unlike Impinging Jets

In bi-propellant thrusters, impinging type injectors are widely used to deliver propellants to a combustion chamber. By impinging the jet streams of fuel and oxidizer, the spray spreads while the two liquids mix. To design the injectors, several correlations related to injection conditions have been...

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Published inTRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Vol. 62; no. 4; pp. 213 - 218
Main Authors WATANABE, Toshinori, HIMENO, Takehiro, FUJII, Go, INOUE, Chihiro, TAKEUCHI, Yuta, NOZAKI, Koji, DAIMON, Yu
Format Journal Article
LanguageEnglish
Published Tokyo THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 01.01.2019
Japan Science and Technology Agency
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ISSN0549-3811
2189-4205
2189-4205
DOI10.2322/tjsass.62.213

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Abstract In bi-propellant thrusters, impinging type injectors are widely used to deliver propellants to a combustion chamber. By impinging the jet streams of fuel and oxidizer, the spray spreads while the two liquids mix. To design the injectors, several correlations related to injection conditions have been proposed (e.g., Rupe factor), and practically utilized over the last half-century. However, the physical meanings of the past correlations are not well understood, because the essential scale of the spray structure is elusive. In this paper, we derive the global length scale of the spray produced by impinging injectors of unlike doublet, fuel-oxidizer-fuel triplet, and oxidizer-fuel-oxidizer triplet in a consistent manner. The unified length scale is found representing the spray width ratio of oxidizer to fuel evidenced by comprehensive cold-flow tests including several past studies, covering various parameters such as injector types, nozzle diameters, physical properties of working liquids, and injection velocities. Finally, we clearly provide the physical meaning based on practical correlations in a phenomenological sense.
AbstractList In bi-propellant thrusters, impinging type injectors are widely used to deliver propellants to a combustion chamber. By impinging the jet streams of fuel and oxidizer, the spray spreads while the two liquids mix. To design the injectors, several correlations related to injection conditions have been proposed (e.g., Rupe factor), and practically utilized over the last half-century. However, the physical meanings of the past correlations are not well understood, because the essential scale of the spray structure is elusive. In this paper, we derive the global length scale of the spray produced by impinging injectors of unlike doublet, fuel-oxidizer-fuel triplet, and oxidizer-fuel-oxidizer triplet in a consistent manner. The unified length scale is found representing the spray width ratio of oxidizer to fuel evidenced by comprehensive cold-flow tests including several past studies, covering various parameters such as injector types, nozzle diameters, physical properties of working liquids, and injection velocities. Finally, we clearly provide the physical meaning based on practical correlations in a phenomenological sense.
Author TAKEUCHI, Yuta
FUJII, Go
INOUE, Chihiro
DAIMON, Yu
HIMENO, Takehiro
NOZAKI, Koji
WATANABE, Toshinori
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  fullname: TAKEUCHI, Yuta
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References 11) Smith, S. H. and Mungal, M. G.: Mixing, Structure and Scaling of the Jet in Crossflow, J. Fluid Mech., 357 (1998), pp. 83–122.
2) Rupe, J. H.: A Correlation between the Dynamic Properties of a Pair of Impinging Streams and the Uniformity of Mixture-Ratio Distribution in the Resulting Spray, JPL Progress Report, 20 (1956), pp. 1–15.
12) Sato, K., Sudo, T., Tadano, M., Moro, A., and Kosaka, K.: A Study of N2O4/Amine Injector Elements, Part 1 Cold Flow Test, Technical Report of National Aerospace Laboratory, NAL TR-899, 1986.
1) Rupe, J. H.: The Liquid-Phase Mixing of a Pair of Impinging Streams, JPL Progress Report, 20 (1953), pp. 1–68.
13) Tamura, H., Wakamatsu, Y., Suzuki, A., Toyokawa, M., and Ono, F.: Injection and Combustion Characteristics of Unlike-Impinging Triplet Injector for LOX-Kerosene Rocket Combustor, Technical Report of National Aerospace Laboratory, NAL TR-648, 1981.
9) Inoue, C., Kouwa, J., Watanabe, T., Himeno, T., Uzawa, S., and Matsuno, S.: Normalized Spray Flux Distribution in Impinging Atomization, Trans. Jpn. Soc. Aeronaut. Space Sci., 60 (2017), pp. 255–258.
4) Falk, A. Y., Clapp, S. D., and Nagai, C. K.: Space Storable Propellant Performance Study Final Report, NASA CR-72487, 1968.
6) Won, Y. D., Cho, Y. H., Lee, S. W., and Yoon, W. S.: Effect of Momentum Ratio on the Mixing Performance of Unlike Split Triplet Injectors, J. Propul. Power, 18 (2002), pp. 847–854.
5) Stechman, R. C., Oberstone, J., and Howell, J. C.: Design Criteria for Film Cooling for Small Liquid-Propellant Rocket Engines, J. Spacecraft, 6 (1969), pp. 97–102.
8) Inoue, C., Nozaki, K., Fujii, G., and Daimon, Y.: Water Flow Diagnostics for Predicting Bi-Propellant Thruster Performance, AIAA Propulsion and Energy Forum, AIAA 2017-4934, 2017, pp. 1–9.
10) Broadwell, J. E. and Breidenthal, R. E.: Structure and Mixing of a Transverse Jet in Incompressible Flow, J. Fluid Mech., 148 (1984), pp. 405–412.
3) Elverum, G. W. and Morey, T. F.: Criteria for Optimum Mixture-Ratio Distribution Using Several Types of Impinging-Stream Injector Elements, JPL Memorandum, 30 (1959), pp. 1–11.
7) Yuan, T., Chen, C., and Huang, B.: Optical Observation of the Impingements of Nitrogen Tetroxide/Monomethylhydrazine Simulants, AIAA J., 44 (2006), pp. 2259–2266.
11
12
13
1
2
3
4
5
6
7
8
9
10
References_xml – reference: 2) Rupe, J. H.: A Correlation between the Dynamic Properties of a Pair of Impinging Streams and the Uniformity of Mixture-Ratio Distribution in the Resulting Spray, JPL Progress Report, 20 (1956), pp. 1–15.
– reference: 10) Broadwell, J. E. and Breidenthal, R. E.: Structure and Mixing of a Transverse Jet in Incompressible Flow, J. Fluid Mech., 148 (1984), pp. 405–412.
– reference: 9) Inoue, C., Kouwa, J., Watanabe, T., Himeno, T., Uzawa, S., and Matsuno, S.: Normalized Spray Flux Distribution in Impinging Atomization, Trans. Jpn. Soc. Aeronaut. Space Sci., 60 (2017), pp. 255–258.
– reference: 6) Won, Y. D., Cho, Y. H., Lee, S. W., and Yoon, W. S.: Effect of Momentum Ratio on the Mixing Performance of Unlike Split Triplet Injectors, J. Propul. Power, 18 (2002), pp. 847–854.
– reference: 8) Inoue, C., Nozaki, K., Fujii, G., and Daimon, Y.: Water Flow Diagnostics for Predicting Bi-Propellant Thruster Performance, AIAA Propulsion and Energy Forum, AIAA 2017-4934, 2017, pp. 1–9.
– reference: 4) Falk, A. Y., Clapp, S. D., and Nagai, C. K.: Space Storable Propellant Performance Study Final Report, NASA CR-72487, 1968.
– reference: 1) Rupe, J. H.: The Liquid-Phase Mixing of a Pair of Impinging Streams, JPL Progress Report, 20 (1953), pp. 1–68.
– reference: 12) Sato, K., Sudo, T., Tadano, M., Moro, A., and Kosaka, K.: A Study of N2O4/Amine Injector Elements, Part 1 Cold Flow Test, Technical Report of National Aerospace Laboratory, NAL TR-899, 1986.
– reference: 3) Elverum, G. W. and Morey, T. F.: Criteria for Optimum Mixture-Ratio Distribution Using Several Types of Impinging-Stream Injector Elements, JPL Memorandum, 30 (1959), pp. 1–11.
– reference: 5) Stechman, R. C., Oberstone, J., and Howell, J. C.: Design Criteria for Film Cooling for Small Liquid-Propellant Rocket Engines, J. Spacecraft, 6 (1969), pp. 97–102.
– reference: 7) Yuan, T., Chen, C., and Huang, B.: Optical Observation of the Impingements of Nitrogen Tetroxide/Monomethylhydrazine Simulants, AIAA J., 44 (2006), pp. 2259–2266.
– reference: 11) Smith, S. H. and Mungal, M. G.: Mixing, Structure and Scaling of the Jet in Crossflow, J. Fluid Mech., 357 (1998), pp. 83–122.
– reference: 13) Tamura, H., Wakamatsu, Y., Suzuki, A., Toyokawa, M., and Ono, F.: Injection and Combustion Characteristics of Unlike-Impinging Triplet Injector for LOX-Kerosene Rocket Combustor, Technical Report of National Aerospace Laboratory, NAL TR-648, 1981.
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SubjectTerms Bi-Propellant Thruster
Cold flow
Cold flow tests
Combustion chambers
Correlation
Fuels
Impinging Atomization
Injectors
Jet streams (meteorology)
Length Scale
Liquids
Mixing
Nozzles
Patternator
Physical properties
Propellant injection
Spray
Thrusters
Title Unified Length Scale of Spray Structure by Unlike Impinging Jets
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