Study on the heat transfer characteristics of regenerative cooling for LOX/LCH4 variable thrust rocket engine

Song, Jie; Liang, Tao; Li, Qinglian; Cheng, Peng; Zhang, Dongdong; Cui, Peng; Sun, Jun

doi:10.1016/j.csite.2021.101664

Cited by 23 publications

(4 citation statements)

References 33 publications

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“…Here, the amount of heat vented from the reactant gas is recovered ("regenerated") using the employed liquid such that there occurs very reduced possibility of heat getting escaped 65) . This technique necessitates both flow and heat transfer estimation, since the high-speed exhaust flow inside the nozzle is coupled with low-speed coolant flow surrounding the nozzle.…”

Section: Fig3: An Illustration Of Regenerative Coolingmentioning

confidence: 99%

A Review on Advancements and Characteristics of Cryogenic Propulsion Rocket Engine

R¹,

Jeyan²

2023

Evergreen

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Future space exploration missions will require the synergistic integration of potentially lightweight, high thrust producing, and environmentally sustainable rocket engines. This article guides through one such capable rocket engine, the cryogenic propulsion rocket engine and some cutting-edge characteristics and novel engineering advancements affiliated with it. A typical cryogenic-propulsion rocket engine works similarly to all other LPRE's (Liquid Propellant Rocket Engines), in which the primary fluid (Cryogenic fuel 1) reacts chemically to get vaporized and get ignited by an oxidizer to provide extremely hot rocket thrust that escapes the engine nozzle and generates thrust from the combustion process. Considerable efforts have been made to optimize the engine's performance and reliability in order to utilize the most desirable output from it. Therefore, a brief overview of the different models and research approaches associated with it to provide predictions and results about the stability, dynamics, and cooling characteristics of the given engine configuration is presented.

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Section: Fig3: An Illustration Of Regenerative Coolingmentioning

confidence: 99%

A Review on Advancements and Characteristics of Cryogenic Propulsion Rocket Engine

R¹,

Jeyan²

2023

Evergreen

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“…Significant experimental research has been reported on cryogenic flow boiling in symmetrically heated circular channels [1]. However, rocket engine cooling channels experience asymmetric heat flux from the combustion chamber hot wall [17][18][19][20]. Moreover, the effect of high aspect ratio cooling channels on increasing regenerative cooling performance and improving pressure drop is well-documented [18].…”

Section: Introductionmentioning

confidence: 99%

Liquid Nitrogen Flow Boiling Critical Heat Flux in Additively Manufactured Cooling Channels

et al. 2023

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This paper presents an experimental characterization of liquid nitrogen (LN2) flow boiling in additively manufactured minichannels. There is a pressing need of concerted efforts from the space exploration and thermal transport communities to design high-performance rocket engine cooling channels. A close observation of the literature gaps warrants a systematic cryogenic flow boiling characterization of asymmetrically heated small (<3 mm) non-circular channels fabricated with advanced manufacturing technologies at mass flux > 3000 kg/m2s and pressure > 1 MPa. As such, this work presents the LN2 flow boiling results for three asymmetrically heated additively manufactured GR-Cop42 channels of 1.8 mm, 2.3 mm, and 2.5 mm hydraulic diameters. Twenty different tests have been performed at mass flux~3805–14,295 kg/m2s, pressures~1.38 and 1.59 MPa, and subcooling~0 and 5 K. A maximum departure from nucleate boiling (DNB)-type critical heat flux (CHF) of 768 kW/m2 has been achieved for the 1.8 mm channel. The experimental results show that CHF increases with increasing LN2 flow rate (337–459 kW/m2 at 25–57 cm3/s for 2.3 mm channel) and decreasing channel size (307–768 kW/m2 for 2.5–1.8 mm channel). Finally, an experimental DNB correlation has been developed with 10.68% mean absolute error.

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“…Unfortunately, a comprehensive thermal model cannot be readily used when multiple calculation loops are required, as during the optimization process typical of the design phase of a regeneratively cooled thrust chamber, or the analysis of different operative conditions. In such cases, simplified one-dimensional models, typically relying on semi-empirical correlations for the convective heat transfer, are widely adopted (e.g., [5][6][7]). The main drawbacks of the simplified approaches rely on the generally non-negligible uncertainty of the adopted semi-empirical correlations, which therefore should be properly calibrated for the specific class of problems under investigation, and the intimate multidimensional heat conduction within the wall, which cannot be easily reduced to a one-dimensional approach.…”

Section: Introductionmentioning

confidence: 99%

A Simplified Thermal Analysis Model for Regeneratively Cooled Rocket Engine Thrust Chambers and Its Calibration with Experimental Data

Fagherazzi¹,

Santi²,

Barato

et al. 2023

Aerospace

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An essential part of the design of a liquid rocket engine is the thermal analysis of the thrust chamber, which is a component whose operative life is limited by the maximum allowable wall temperature and heat flux. A simplified steady-state thermal analysis model for regeneratively cooled rocket engine thrust chambers is presented. The model is based on semi-empirical correlations for the hot-gas and coolant convective heat transfer and on an original multi-zone approach for the wall conduction. The hot-gas heat transfer is calibrated with experimental data taken from an additively manufactured water-cooled nozzle that is connected to a combustion chamber either fed with decomposed hydrogen peroxide or decomposed hydrogen peroxide and automotive diesel. The thrust chamber (i.e., combustion chamber and nozzle) is designed to produce about 450 N of thrust when operating with a chamber pressure of 11 bar. For this application, the calibrated model predicts the total wall heat transfer rate very accurately and the temperature distribution within the wall structure with an uncertainty of a few tens of kelvins. This level of accuracy can be considered more than adequate for the design, and generally for engineering-type thermal analysis, of similar thrust chambers.

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Study on the heat transfer characteristics of regenerative cooling for LOX/LCH4 variable thrust rocket engine

Cited by 23 publications

References 33 publications

A Review on Advancements and Characteristics of Cryogenic Propulsion Rocket Engine

A Review on Advancements and Characteristics of Cryogenic Propulsion Rocket Engine

Liquid Nitrogen Flow Boiling Critical Heat Flux in Additively Manufactured Cooling Channels

A Simplified Thermal Analysis Model for Regeneratively Cooled Rocket Engine Thrust Chambers and Its Calibration with Experimental Data

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