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Effect of Chemical Reactions on the Fluidic Thrust Vectoring of a Plane Nozzle

  • Research Article-Chemical Engineering
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Abstract

During the last years, several thrust control systems of aerospace rocket engines have been developed. The fluidic thrust vectoring is one of them; it is simple in design and offers a substantial gain in weight and in performance. Most of the studies related to this device were carried out with cold gas. It is quite legitimate to expect that the thermophysical properties of the gases may affect considerably the flow behavior. Besides, the effects of reacting gases at high temperatures, under their effects all flow parameters like to vary. This study aims to develop a new methodology that allows studying and analyzing the fluidic thrust vectoring for a perfect gas, by taking into account the effects chemical reactions on the flow parameters, such as separation point, reattachment point downstream and pressure distribution upstream the injection port. In this study, the thrust vectorization implying frozen reacting hot gases was carried out by considering a chemical reaction mechanism. The thermodynamic parameters of the flow are calculated within the combustion chamber and different sections of the supersonic part of the nozzle. The results show a good agreement for cold gas, and as expected a slight difference for hot reacting gases. In parallel, in order to give more credibility to our work a study was carried out by numerical simulation for supersonic reactive and perfect flows in order to analyze the results of the method developed. In this work, the CFD performance of the fluidic thrust vectoring has been qualitatively and quantitatively analyzed. The Schlieren visualization and the wall pressure results are compared to analytical and experimental findings. Performance analysis is conducted, and basic conclusions are drawn in terms of thermodynamic gas properties effect on the fluidic thrust vector system. The primary effect was related to the gas molecular weight and its specific heat ratio. It is observed that for fixed injection conditions, the vectoring angle is different when the injected gas molecular weight and specific heat ratio are different. For a given mission of the launcher, it can be concluded that the mass of the embedded gas, used for the fluidic vectorization system, can be significantly reduced, depending on its molecular weight and specific heat ratio.

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Abbreviations

A :

Section (m2)

F x :

Axial effort (Kg m/s2)

F y :

Normal effort (Kg m/s2)

h :

Fluidic obstacle height (m)

M :

Mach number

ṁ :

Mass flow (Kg/s)

P, p :

Total pressure and static pressure (Pa)

V :

Velocity vector

u :

Axial velocity (m/s)

a :

Velocity of sound (m/s)

T :

Temperature (K)

x :

Axial direction

y :

Normal direction

γ :

Ration of specific heats (γ = cp/cv)

δ :

Thrust vector angle (°)

ρ :

Density (Kg/m3)

C P :

Specific heat at constant pressure of mixture (J/Kg-K)

H :

Specific enthalpy of mixture (J/Kg)

S :

Specific entropy of mixture (J/Kg-K)

R :

Universal gas constant (J/mole-K)

C :

Molar concentration (mole/m3)

M s :

Molar mass of the species s (Kg/mole)

av:

Conditions of flow downstream of the control volume

j :

Injection conditions

s :

Separation

t :

Throat of the nozzle

b :

Width of the injection slot (m)

0:

Stagnation conditions

1:

Flow condition downstream of the shock

NPR:

Nozzle pressure ratio pressure = Poi/pa

SPR:

Secondary pressure ratio = Poj/Poi

SVC:

Shock vector control principle of injection in the divergent

CN:

Conical nozzle

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Authors and Affiliations

  1. Laboratoire des Sciences Aéronautique, Institut d`Aéronautique et des Etudes Spatiales, Université Saad Dahlab-Blida 1, BP 270, Route de Soumâa, Blida, Algeria

    R. Chouicha & S. Bergheul

  2. LMEE, Univ Evry, Université Paris-Saclay, 91020, Evry Cedex, France

    M. Sellam

Authors
  1. R. Chouicha
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  2. M. Sellam
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  3. S. Bergheul
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Correspondence to R. Chouicha.

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Chouicha, R., Sellam, M. & Bergheul, S. Effect of Chemical Reactions on the Fluidic Thrust Vectoring of a Plane Nozzle. Arab J Sci Eng 45, 7191–7204 (2020). https://doi.org/10.1007/s13369-020-04350-8

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  • DOI: https://doi.org/10.1007/s13369-020-04350-8

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