Practical Uses of Liquid Methane in Rocket Engine Applications

Neill, Todd; Judd, D. C.; Veith, Eric M.; Rousar, D. C.

doi:10.2514/6.iac-06-c4.1.01

Cited by 5 publications

(3 citation statements)

References 3 publications

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“…With the space market being more and more competitive, reusable launchers are envisioned as a key technology to reduce the costs of access to orbit. Encompassed in this logic, methane (𝐶𝐻 4 ) has been identified as the best candidate fuel for the development of low-cost reusable space launch systems (high energy density, low operating cost, and good overall performances in terms of specific impulse [1]). As a consequence, several methanebased projects are currently being studied and developed around the world [2] [3], making the understanding of pure methane/oxygen combustion (flame dynamics, kinetics, etc.)…”

Section: Introductionmentioning

confidence: 99%

Laminar flame speed evaluation for CH4/O2 mixtures at high pressure and temperature for rocket engine applications

Mouze-Mornettas

Benito

Dayma

et al. 2023

Proceedings of the Combustion Institute

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Section: Introductionmentioning

confidence: 99%

Laminar flame speed evaluation for CH4/O2 mixtures at high pressure and temperature for rocket engine applications

Mouze-Mornettas

Benito

Dayma

et al. 2023

Proceedings of the Combustion Institute

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“…The liquid-type propellant rocket techniques have recently gotten a lot of attention. The pressure inside the chamber has been augmented to meet the requirements of efficiency and compactness [9][10][11].…”

Section: Introductionmentioning

confidence: 99%

Thermodynamic Analysis of a Jet Engine Using a Liquid Propellant

Alliche

Rebhi

İnç

et al. 2022

Preprint

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Combustion-chamber is a critical component of the propulsion engine, which is widelyused in the space industry and aeronautics. The goal of this article is to perform a numericalanalysis on the combustion process using a liquid-type propellant. The steps that must be followeduntil total combustion is achieved are emphasized. It concerns the fuel feeding phase, its injectionand the combustion operation. The amount of combustion products and the energy generated areevaluated. It has been shown that the liquid propellant may present an efficient alternative fuelthan the kerosene. In addition, the temperature of combustion does not exceed a certain limit toavoid structural problems in the chamber. The parametric survey allowed determining the range ofthe most influence factors, including the pressure, mixture richness, velocity and flow rates ofinjection for the fuel and oxidizer. The number and type of injectors revealed a considerableinfluence on the velocity and flow rates of injection. To maximize thrust force and systempropulsion, a careful selection of chamber material and ignition methods is required. A thorough inspection on the issues of walls cooling showed the necessary survey of maximum temperaturesthat may be reached during the combustion. Finally, an investigation of the thermal exchangethrough the walls will be very interesting.

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“…Some of the advantages of methane include higher density, higher storage temperature (110°K), and low flammability limits. In addition, methane is relatively safe when compared to LH2, MMH, and NTO [Neill, 2009]. This allows for a system that consumes less energy and subsequent expense while being easier to maintain, making it a preferred choice for exploration missions [Crawly, 2008].…”

Section: Chapter 1: Introductionmentioning

confidence: 99%

Cryogenic System Development for LOX/Hydrocarbon Propulsion Research

Pineda

2011

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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I would like to extend my most sincere gratitude to my advisor Dr. Ahsan Choudhuri. His patience, guidance and teachings were invaluable to my development as an engineer. Thank you for giving me the opportunity to follow my dreams. I also want to thank Mr. Nate Robinson for his sound advice and supervision of this project. In addition, I want to recognize the entire staff of the cSETR because without their hard work, this project would not have been possible. I want to thank my committee for their given time and contribution to this thesis. Thank you NASA for providing the means to make all this possible. Special thanks to Mr. Jesus Betancourt-Roque, his collaboration made this project a success. Jesus R. Flores, Chance P. Garcia, Chris Navarro and the rest of my colleagues at the cSETR, thank you. Finally, I would like to give a special recognition to my family and girlfriend, their support and motivation got me through challenging times, and for that I am grateful.

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Practical Uses of Liquid Methane in Rocket Engine Applications

Cited by 5 publications

References 3 publications

Laminar flame speed evaluation for CH4/O2 mixtures at high pressure and temperature for rocket engine applications

Laminar flame speed evaluation for CH4/O2 mixtures at high pressure and temperature for rocket engine applications

Thermodynamic Analysis of a Jet Engine Using a Liquid Propellant

Cryogenic System Development for LOX/Hydrocarbon Propulsion Research

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