Vaporization-controlled simplified model for liquid propellant rocket engine combustion chamber design

Belal, Hatem M.; Makled, Ah. El-S.; Al-Sanabawy, M. A.

doi:10.1088/1757-899x/610/1/012088

Cited by 7 publications

(8 citation statements)

References 3 publications

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“…The chamber size must be optimized in order to achieve the highest performance, since the L * affects directly the characteristic velocity C * [1,7,[10][11][12]17,19]. This is due to the fact that if the chamber is too short, incomplete combustion is achieved inside the combustion chamber and may lead to combustion instabilities [20].…”

Section:  Maurício Sá Gontijo 2022mentioning

confidence: 99%

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A review of vaporization models as design criterion for bipropellant thrust chambers

Gontijo

2022

aktt

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In the beginning of liquid propellant rocket engine development, the thrust chamber sizes were obtained, mainly, empirically. With the technological advancements over the years, several approaches have been developed in order to optimize its sizes and predict more accurately the performance. Besides the clear contribution in predicting efficiencies, the use of accurate vaporization models to optimize combustion chambers decreases losses and the number of required tests. To increase efficiencies, the chamber must be optimized. In case the chamber is too small, incomplete combustion is achieved and combustion instability may occur. In case the chamber is too large, losses due to weight and heat transfer increase and the vehicle becomes larger (leading to more drag losses). Additionally, the number of tests is reduced since models were experimentally validated and less experimental iterations are required in order to obtain the optimized design. Although there are many models, all of them reach similar conclusions, such as an increase in chamber pressure, a decrease in injected droplet size and velocity, and others, lead to a decrease in the required chamber size. Nowadays, with the advancements in computing budget, more complex and accurate models have be developed. Some of these models account for chemical reactions, turbulence effects, droplet collisions and interactions, two- and three-dimensional modeling, and others. Also, the use of CFD codes provides relevant contributions to the analytical and numerical models, especially in validating them, and, additionally, decreases the amount of required experimental tests. The main propulsive parameter that rules this phenomenon is the characteristic length, which accounts the required chamber size for the propellants to be injected, atomized, vaporized, mixed and combusted. Most of the available models neglect the atomization, mixing and combustion of the propellant, since those phenomena occur much faster compared with the vaporization. This work provides a review of those vaporization models, focusing on the main used models worldwide. Such review is of great importance in order to supply enough information and comparison between models, making possible for the researcher/engineer to choose the model that better fit its necessities, requirements and limitations.

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Section:  Maurício Sá Gontijo 2022mentioning

confidence: 99%

“…Mixing is also achieved very fast, since droplets are oftenly colliding. And, combustion and chemical reactions are commonly neglected in vaporization models assuming it occurs in an infinitesimal time step [7][8][9][10][11][12]. With these statements, it is quite accurate to calculate the chamber size with vaporization models.…”

Section: Introductionmentioning

confidence: 99%

A review of vaporization models as design criterion for bipropellant thrust chambers

Gontijo

2022

aktt

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Section: Combustion Modelingmentioning

confidence: 99%

Injector and Combustion Chamber Design for a Nitrous Oxide and Ethanol Rocket Engine

Ceotto¹,

Tavares²

2021

Preprint

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The basic design of a rocket engine injector and combustion chamber for saturated nitrous oxide and liquid ethanol is presented. At first, an oxidant-fuel mixture is selected based on a thermochemical analysis that explores several existing options and other combinations that have not yet been studied. As a result, nitrous oxide is chosen as an oxidant and ethanol as fuel. Then a simplified methodology is proposed for the design of a pressure-swirl injector responsible for ethanol. Computational fluid dynamics is used to verify the validity of the above-mentioned analysis, using Volume of Fluid (VOF). For the nitrous oxide injector, the flash-boiling phenomenon is investigated, verifying its importance for the ongoing project. The effect is treated analytically using the Dyer model to account for non-equilibrium thermodynamics. Simplified zero-dimensional and one-dimensional combustion models are explored as tools to design the rocket combustion chamber. Furthermore, combustion instability due to acoustic phenomena is studied, with the first spinning tangential mode being computed for the herein developed motor and an ensemble of acoustic cavities being developed to suppress the aforementioned mode. Finally, a diagram of the static test bench which will be used to validate the injectors and the designed engine is also presented.

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“…While CFD and even DNS are increasingly more relevant for combustion chamber design, the computational infrastructure available to the authors made their use impractical considering the scope and duration of this work. However, simplified zero-dimensional and one-dimensional models are sufficient to compute a suitable chamber diameter-length combination (Belal, Makled, and Al-Sanabawy, 2019). These models involve algebraic and ordinary differential equations, making them computationally inexpensive, which allows for faster design iterations, parametric studies and design optimization.…”

Section: Combustion Modelingmentioning

confidence: 99%

“…In turn, ethanol droplets are expected to have a lifetime orders of magnitudes greater than the characteristic combustion time scale, which should have a similar order of magnitude as the ignition delay presented previously. In this section, a one-dimensional reactor will be modeled inspired by (Turns, 1996), (Spalding, 1959) and (Belal, Makled, and Al-Sanabawy, 2019) to verify these hypothesis and calculate the lifetime of ethanol droplets. These reactor will also be used in a reactor network in subsequent sections.…”

Section: Vaporization-controlled Plug Flow Reactormentioning

confidence: 99%

Injector and Combustion Chamber Design for a Nitrous Oxide and Ethanol Rocket Engine

Tavares¹,

Ceotto²

2021

Preprint

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This report presents the basic design of a rocket engine injector and combustion chamber for saturated nitrous oxide and liquid ethanol, as well as details of the construction and operation of the engine in which the injectors will be used. At first, an oxidant-fuel mixture is selected based on a thermochemical analysis that explores several existing options and other combinations that have not yet been studied. As a result, nitrous oxide is chosen as an oxidant and ethanol as fuel. Then a simplified methodology is proposed for the design of a pressure-swirl injector responsible for ethanol. Computational fluid dynamics is used to verify the validity of the above-mentioned analysis, using Volume of Fluid (VOF). For the nitrous oxide injector, the flash-boiling phenomenon is investigated, verifying its importance for the ongoing project. The effect is treated analytically using the Dyer model to account for non-equilibrium thermodynamics. Simplified zero-dimensional and one-dimensional combustion models are explored as tools to design the rocket combustion chamber. Furthermore, combustion instability due to acoustic phenomena is studied, with the first spinning tangential mode being computed for the herein developed motor and an ensemble of acoustic cavities being developed to suppress the aforementioned mode. Finally, a preliminary diagram of the static test bench which will be used to validate the injectors and the designed engine is also presented.

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Vaporization-controlled simplified model for liquid propellant rocket engine combustion chamber design

Cited by 7 publications

References 3 publications

A review of vaporization models as design criterion for bipropellant thrust chambers

A review of vaporization models as design criterion for bipropellant thrust chambers

Injector and Combustion Chamber Design for a Nitrous Oxide and Ethanol Rocket Engine

Injector and Combustion Chamber Design for a Nitrous Oxide and Ethanol Rocket Engine

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