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Liquid Film Formation and Heat Transfer Characteristics of a Liquid Jet Obliquely Impinging onto a Wall

Sako, Noritaka 京都大学 DOI:10.14989/doctor.k24715

2023.03.23

概要

Bipropellant thrusters are used for orbit maneuvering and attitude control of satellites
and small size spacecraft. In bipropellant thrusters, a liquid film cooling technique is
employed to protect the chamber wall from high-temperature combustion gases. In the
present thesis, the formation processes of the liquid film by a liquid jet impingement are
discussed. Chapter 1 provides an introduction of the present study.
1.1 Background
In recent years, the space industry has made remarkable progress, and many countries
around the world are making great efforts for space development. Additionally, private
companies have been actively entering the market of the space industry, as seen in the
example that Space X succeeded for the first time in human spaceflight as a private
company. Therefore, the market size of the space industry is expected to exceed 100
trillion yen by 2040 [1] due to the increase in the number of countries engaged in space
development and the expansion of commercial use of space.
One of space developments in Japan is represented in “Hayabusa” which succeeded
in returning to Earth with planetary materials (sample return) from the asteroid “Itokawa”
in 2010 [2]. The subsequent project of “Hayabusa2” succeeded in sample return from the
asteroid “Ryugu” in 2020 very recently [3]. The next Japanese flagship launch vehicle HⅢ rocket [4] has planned to be launched, and new lander missions such as SLIM (Smart
Lander for Investigating Moon) [5] and MMX (Martian Moons eXploration) [6] are also
going to be conducted.
In the various missions mentioned above, rocket propulsion systems play an important
role. Rocket propulsion systems are mainly classified into chemical rocket propulsion,
nuclear rocket propulsion, and electric rocket propulsion, according to the types of energy
sources [7, 8]. The following is an overview of the mechanism for each propulsion system.
1) Chemical rocket propulsion
In a chemical rocket propulsion system, the combustion reaction of the chemical
propellant, which is generally a combination of a fuel and an oxidizer, occurs, and
then, the high-temperature combustion gases are accelerated through a nozzle to
produce thrust. Chemical rocket engines are used most commonly for any kind of
mission because they cover a varied range of thrust by types of chemical propellants. ...

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参考文献

Chapter 2

[1] Noritaka Sako, Jun Hayashi, Yu Daimon, Hiroumi Tani, and Hiroshi Kawanabe,

“Experimental analysis of the spreading of a liquid film on a bipropellant thruster

chamber wall,” Journal of Thermal Science and Technology, vol. 16, issue 1, pages

JTST0008, 2021, https://doi.org/10.1299/jtst.2021jtst0008.

Chapter 3

[2] Noritaka Sako, Kouhei Noda, Jun Hayashi, Yu Daimon, and Hiroshi Kawanabe,

“Quenching of a heated wall with spatial temperature gradient using a liquid film

through oblique jet impingement,” International Journal of Heat and Mass Transfer,

vol.

192,

Article

122925,

2022,

https://doi.org/10.1016/j.ijheatmasstransfer.2022.122925.

Chapter 4

[3] Noritaka Sako, Kouhei Noda, Jun Hayashi, Yu Daimon, and Hiroshi Kawanabe,

“Liquid film and heat transfer characteristics during superheated wall cooling via

pulsed injection of a liquid jet,” International Journal of Heat and Mass Transfer,

vol.

205,

Article

123934,

2023,

https://doi.org/10.1016/j.ijheatmasstransfer.2023.123934.

Chapter 5

[4] Noritaka Sako, Jun Hayashi, Chihiro Inoue, Hiroshi Kawanabe, and Yu Daimon,

“Boiling induced atomization appeared in the liquid film by wall impinging jet on

the superheated wall,” Proceedings of International Conference on Liquid

Atomization and Spray Systems ICLASS 2021, Paper 287, 2021,

https://doi.org/10.2218/iclass.2021.6007.

119

Others

[5] Noritaka Sako, Kouhei Noda, Jun Hayashi, Yu Daimon, and Hiroshi Kawanabe,

“Heat Transfer Characteristics of Liquid Film Formed on a Superheated Wall during

Pulsed Injection of Liquid Jet,” AIAA SCITECH 2023 Forum, AIAA-2023-0512,

2023, https://doi.org/10.2514/6.2023-0512.

[6] Yu Daimon, Masaharu Nakajima, Noritaka Sako, Jun Hayashi, Hiroshi Kawanabe,

and Himeko Yamamoto, “Laminar Diffusion Flame-holding Characteristics in Crossflow Formed at the Wake of the Injector Post,” AIAA SCITECH 2023 Forum, AIAA2023-0901, 2023, https://doi.org/10.2514/6.2023-0901.

Conference papers

[1] Noritaka Sako, Jun Hayashi, Yu Daimon, Hiroumi Tani, and Hiroshi Kawanabe,

“Visualization of Liquid Film for Film Cooling Formed on Combustion Chamber

Wall of Bipropellant Thruster”, The Proceedings of the Second Pacific Rim Thermal

Engineering Conference, Maui, Hawaii, USA, 2019.

[2] Noritaka Sako, Kouhei Noda, Jun Hayashi, Yu Daimon, Hiroumi Tani, and Hiroshi

Kawanabe, “Heat transfer characteristics of thin liquid film formed on a heated wall

with spatial temperature gradient,” The Proceedings of the Thermal Engineering

Conference, Online, 2020 (in Japanese).

[3] Noritaka Sako, Kouhei Noda, Jun Hayashi, and Hiroshi Kawanabe, “STUDY ON

LIQUID FILM COOLING BY WALL-IMPINGING JET IN A BIPROPELLANT

THRUSTER,” The Proceedings of the 20th Seoul National – Kyoto – Tsinghua

University Thermal Engineering Conference, Online, 2020.

[4] Noritaka Sako, Jun Hayashi, Chihiro Inoue, Hiroshi Kawanabe, and Yu Daimon,

“Nucleate boiling induced atomization appeared in the thin liquid film on the heated

solid wall,” The Proceedings of the 29th ILASS-Japan Symposium, Online, 2020 (in

Japanese).

[5] Kouhei Noda, Noritaka Sako, Jun Hayashi, Yu Daimon, and Hiroshi Kawanabe,

“Cooling of the Heated Wall Surface by Liquid Film during a Repetitive Pulsed

120

Injection of Liquid Jet,” The Proceedings of the Thermal Engineering Conference,

Online, 2021 (in Japanese).

[6] Noritaka Sako, Jun Hayashi, Hiroshi Kawanabe, Takahiro Sako, and Masashi

Katsuki, “Numerical analysis on nitrogen origin of NOx formed in an ammonia/air

flame,” The Proceedings of the 59th Symposium (Japanese) on Combustion, Online,

2021 (in Japanese).

[7] Masaharu Nakajima, Noritaka Sako, Jun Hayashi, Yu Daimon, and Hiroshi

Kawanabe, “Flammable characteristics of diffusion flame in the cross flow at the

wake of step,” The Proceedings of the 59th Symposium (Japanese) on Combustion,

Online, 2021 (in Japanese).

[8] Noritaka Sako, Kouhei Noda, Jun Hayashi, and Hiroshi Kawanabe, “STUDY ON

LIQUID FILM DEVELOPMENT AND ITS HEAT TRANSFER PROCESS

THROUGH AN IMPINGING JET ON A SUPERHEATED WALL,” The

Proceedings of the 21st Kyoto - Tsinghua - Seoul National University Thermal

Engineering Conference, Online, 2021.

[9] Noritaka Sako, Jun Hayashi, Chihiro Inoue, Hiroshi Kawanabe, and Yu Daimon,

“Bubble bursting and subsequent fragmentation induced by nucleate boiling in a

liquid film,” The Proceedings of the 30th ILASS-Japan Symposium, Online, 2021 (in

Japanese).

[10] Noritaka Sako, Jun Hayashi, Hiroshi Kawanabe, Takahiro Sako, and Masashi

Katsuki, “Numerical analysis on formation characteristics of Fuel-NOx in

NH3/CH4/Air flame,” The Proceedings of the Thermal Engineering Conference,

Tokyo, Japan, 2022 (in Japanese).

[11] Masaharu Nakajima, Noritaka Sako, Jun Hayashi, Yu Daimon, and Hiroshi

Kawanabe, “Effects of velocities of fuel and oxidizer on the flame stability of

diffusion flame formed in crossflow,” The Proceedings of the Fluids Engineering

Conference, Kumamoto, Japan, 2022 (in Japanese).

121

Acknowledgement

I would like to deeply thank my supervisor, Prof. Hiroshi Kawanabe, for the endless

support and constant guidance of my study from the 4th year undergraduate to the Doctoral

course. Owing to his supervision, I was able to learn how to develop my research in a

constructive manner and finally complete this thesis.

Besides my supervisor, I would like to express my sincerest gratitude to Prof. Jun Hayashi.

His insightful comment and continuous encouragement helped me all through my

research. In addition, valuable discussions with him broadened my horizons and

improved the quality of my study.

In addition, I must thank Prof. Hitoshi Fujimoto and Associate Prof. Naoto Horibe for his

insightful comments and hard questions which enabled my thesis to be improved.

Especially, Associate Prof. Naoto Horibe also gave technical support and comments

through my doctoral course.

I would like to express my special gratitude to Dr. Yu Daimon at JAXA for his continuous

support and thoughtful advice for my research. I learned a lot as a researcher.

I also would like to thank Associate Prof. Chihiro Inoue at Kyushu Univ., Dr. Hiroumi

Tani at JAXA (currently at Space X), and Emeritus Prof. Masashi Katsuki at Osaka Univ.

for valuable discussions.

I am indebted to Mr. Kouhei Noda, Mr. Masaharu Nakajima, Mr. Kakeru Mizukoshi, Mr.

Taishi Kataoka, and other students at Combustion and Power Engineering Laboratory

who worked with me and gave powerful support through my doctoral course.

I also thank the officers, Mrs. Wakako Takamura and Mrs. Miki Okuyama. Their great

support helped me to conduct my research so smoothly.

Last but not least, I would like to express my utmost gratitude to my family, Takahiro,

Satoko, and Kaori for their warm love, understanding, encouragement, and support.

Noritaka Sako

122

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