System Analysis of Low Frequency Combustion Instabilities in Liquid Rocket Engines

Leonardi, Marco; Matteo, Francesco Di; Steelant, Johan; Nasuti, Francesco; Onofri, Marcello

doi:10.2514/6.2015-4208

Cited by 4 publications

(3 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Various approaches have been used to solve this problem: Jokhakar and Naraghi [3] proposed a 3-D modelling for the heat conduction through the wall and a 2-D approach based on semiempirical correlations for the coolant and the hot gas flows; a similar approach was proposed by Kawashima, Hideto et al [4] for liquid rocket engines fed by methane. To overcome the complexity and the computational cost introduced by 3-D approaches, simplified quasi-2-D models have been extensively used to solve the heat transfer problem [5][6][7][8][9][10][11]. The aim of the present paper is to model the "DEMO-0A" engine designed and realized by the Italian Aerospace Research Center (CIRA) by means of 1-D components offered by the EcosimPro software.…”

Section: Introductionmentioning

confidence: 99%

1D numerical simulations aimed to reproduce the operative conditions of a LOX/LCH4 engine demonstrator.

Romano,

Ricci,

Battista

2024

Preprint

View full text Add to dashboard Cite

The utilization of liquid oxygen/liquid methane couple (LOX/LCH4) as a potential candidate to substitute hypergolic propellants and hydrazine in the next future propulsion systems has arisen an increasing interest due to the advantages offered in terms of low environmental impact, re-usability, cooling capabilities and relatively high specific impulse. In this perspective, the Italian Aerospace Research Center manages the “HYPROB” research program, cofunded by the Italian Research and University Ministry, that has the objective to improve the national capabilities into developing engines, fed by hydrocarbons, that could be successfully applied as propulsion units for third stages of launchers for space exploration. The “HYPROB” program led to the realization of a LOX/LCH4 engine named “DEMO-0A”, a 30 kN thrust class demonstrator, technologically representative of a regenerative thrust chamber assembly of an expander engine. The present paper describes the results of the numerical simulations performed by means of the EcosimPro software, aimed at reproducing the operative conditions, both cold flow both firing, of the regenerative thrust chamber “DEMO-0A”. An assessment of the capabilities of the software in predicting the behaviour of the demonstrator by modelling it with a 1-D approach and by considering different wall heat exchange semiempirical correlations has been done by comparing numerical results and the available experimental data gathered during both cold flow both firing test campaigns.

show abstract

Section: Introductionmentioning

confidence: 99%

1D numerical simulations aimed to reproduce the operative conditions of a LOX/LCH4 engine demonstrator.

Romano,

Ricci,

Battista

2024

Preprint

View full text Add to dashboard Cite

show abstract

“…Accordingly, the throttling pressure drop may be as high as 3 MPa or more. A good chill-down process of the pipeline system after the valve determines the stability of the engine hot-fire starting [26,27]. In the previous study, a horizontal liquid oxygen pipeline contracted at the outlet of D i = 15 mm was tested, the test pressure was varied in the range of 0.5~0.9 MPa, and the suggested correlations of T LFP and q LFP , T CHF , and q CHF were given [28].…”

Section: Introductionmentioning

confidence: 99%

Characteristics of Flow Development and Boiling Transitions in the Liquid Oxygen Chill-Down Process in a Straight Horizontal Exit-Contracted Pipe

Chen

Zhang

2023

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

Liquid oxygen chill-down in a straight horizontal pipe was studied experimentally. The effect of the entrance corner was excluded, and much denser wall temperature sensors along the pipe have been set compared to the present studies. In this way, the chill-down process, as well as the development of the flow pattern, has been drawn for every test. As a result, the mechanism of LO2 chill-down would be obtained for various pressure sections. For cases with stable pressure below 1.25 MPa, liquid rewetting in the pipe is controlled by the propagation of quenching fronts. For cases with a higher pressure, liquid rewetting in the second half of the pipe is controlled by the sudden liquid fill-in. Based on the transition points obtained, heat transfer coefficients on the Leidenfrost point and critical heat flux have been correlated for various pressure sections using new approaches. Conclusions show that the correlation equations are dependent on the chill-down mechanisms.

show abstract

“…Various approaches have been used to solve this problem: the possibility to use a 3-D modelling for the heat conduction through the wall and a 2-D approach, based on semiempirical correlations for the coolant and the hot gas flows, has been evaluated in [2], [3]. To overcome the complexity and the computational cost introduced by 3-D approaches, simplified quasi-2-D models have been extensively used to solve the heat transfer problem ( [4], [5], [6]).…”

Section: Introductionmentioning

confidence: 99%

1D numerical simulations aimed to reproduce the operative conditions of a LOx/LCH4 engine demonstrator

Romano

2023

Materials Research Proceedings

View full text Add to dashboard Cite

Abstract. The present paper describes the results of the numerical simulations performed by means of the “EcosimPro” software, aimed at reproducing the operative conditions of the regenerative thrust chamber “DEMO-0A” designed by the Italian Aerospace Research Center. The operative conditions simulated are both cold flow and firing conditions. A validation of the numerical cold flow results has been performed by comparing them with the experimental data gathered during a cold flow campaign. Once validated the cold flow numerical model, various hot test conditions of the demonstrator have been simulated by considering different heat wall exchange coefficient correlations, in order to obtain information about the thermal power released during the combustion process and to assess the simulation capabilities of the “EcosimPro” software in predicting the behaviour of the demonstrator in firing conditions by modelling it with a 1-D approach.

show abstract

System Analysis of Low Frequency Combustion Instabilities in Liquid Rocket Engines

Cited by 4 publications

References 9 publications

1D numerical simulations aimed to reproduce the operative conditions of a LOX/LCH4 engine demonstrator.

1D numerical simulations aimed to reproduce the operative conditions of a LOX/LCH4 engine demonstrator.

Characteristics of Flow Development and Boiling Transitions in the Liquid Oxygen Chill-Down Process in a Straight Horizontal Exit-Contracted Pipe

1D numerical simulations aimed to reproduce the operative conditions of a LOx/LCH4 engine demonstrator

Contact Info

Product

Resources

About