液体火箭发动机涡轮泵低温空化实验研究进展

doi:10.7527/S1000-6893.2022.27131

Abstract

Abstract:

Turbopump， which can be called the heart of engines， is a critical component of the cryogenic Liquid Rocket Engine （LRE）. The improvement of its performance is limited by cavitation conditions. Due to cavitation thermodynamic effect of cryogenic fluids， the cryogenic cavitation is far more complicated than room-temperature water cavitation. The theoretical basis and key design points of cryogenic turbopump cavitation experimental systems are introduced， and the state-of-the-art similarity criterion for the cavitation thermal effect is revealed. Then several typical cryogenic LTR turbopump cavitating flow experimental systems and investigation results are introduced in detail， it is found that the application of thermal sensitive fluids as the substitution cryogen is technology development tendency， but it is important to keep the thermal effect similarity； Developed test technologies such as optics technique and wireless data transform have been introduced into cavitating flow analysis， they are worth to develop further. At last， the theoretical modeling of the cavitation thermal effect is concluded， it is found that most published works focus on the steady cavitation performance， the theoretical modeling of unsteady cavitation characteristics have been rarely reported. This paper may provide reference for further promoting the performance and reliability of the pump-pressurizing cryogenic liquid rocket engine.

Key words: liquid rocket engine, cryogenic cavitation, turbopump, thermodynamic effect, modeling

CLC Number:

V431

Le XIANG, Kaifu XU, Hui CHEN, Suibo LI, Kai ZHANG, Shixin LIU. Experimental studies on cavitating flow for liquid rocket engine cryogenic turbopump: Review[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(7): 27131.

Figures/Tables 21

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参数	工况Ⅰ	工况Ⅱ
p_in/MPa	1.2	0.1
Q_in/（L·s^-1）	300	9.16
Ω/（r·min^-1）	18 000	3 000
T/K	100	374
D/mm	170	100
工质	液氧	水

介质	T_∞/K	B^*	H_T/m
O₂	85	2.16	2.1
H₂	20	0.03	26.25
H₂O	293	4 972	0.001
	353	29.9	0.06
	373	7.79	0.2
	393	1.39	1

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Experimental studies on cavitating flow for liquid rocket engine cryogenic turbopump: Review

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