Mathematical Model and CFD Analysis of Partially Premixed Combustion in a Turbojet

Rotaru, Constantin; Constantinescu, George-Cristian; Ciuică, Oliver; Cîrciu, Ionică; Mihai, Eduard

doi:10.19062/1842-9238.2016.14.2.10

Cited by 2 publications

(2 citation statements)

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“…According to conventional boundary layer approaches [25][26] and PDE papers [14,17,[23][24] detonation is modelled as a Zel'dovich-von Neumann-Doering (ZND) normal wavelength, in the fuel-air mixture of a uniform tube, which is almost at rest for combustion inlet conditions, see Figure 6. Due to the difficulty of initiating air-fuel mixtures in short tubes and obtaining a constant detonation firing, methods involving deflagrative combustion processes leading to detonation reactions by the placement of optimized obstacles to create turbulent mixtures and to accelerate the gas flow (DDT), as an example, we describe the Shchelkin spiral coil, perforated plates or convergent-divergent jaws, see Figure 7, [18,19,20,21,22].…”

Section: Principle and Stages Of Operationmentioning

confidence: 99%

Considerations and simulations about Pulse Detonation Engine

2019

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PDE propulsion can work from a subsonic regime to hypersonic regimes; this type of engine can have higher thermodynamic efficiency compared to other turbojet or turbofan engines due to the removal of rotating construction elements (compressors and turbines) that can reduce the mass and total cost of propulsion system. The PDE experimental researches focused on both the geometric configuration and the thermo-gas-dynamic flow aspects to prevent uncontrolled self-ignition. This article presents a series of numerical simulations on the functioning of PDE with hydrogen at supersonic regimens.

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Section: Principle and Stages Of Operationmentioning

confidence: 99%

Considerations and simulations about Pulse Detonation Engine

2019

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“…As an object moving in the air, the rocket is subject to aerodynamic forces [5]. Those are consequences of the rocket moving in the air.…”

Section: The Mathematical Model For the Unguided Rocket Trajectorymentioning

confidence: 99%

Aspects Regarding the Unguided Rocket Effectiveness

Moldoveanu¹,

PARC²,

Șomoiag³

2017

Review of the Air Force Academy

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Abstract:The inaccuracy on the unguided rockets impact can be caused by many factors, like initial conditions perturbations as a small displacement of the firing pods between two launches due to its oscillations. As a consequence, all those parameters have to be taken into account in order to obtain an efficacy firing. This paper will focus on the unguided rocket effectiveness. Using the physical model for the trajectory, we will study the accuracy of the unguided rocket through a statistical analysis and several target models.

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Mathematical Model and CFD Analysis of Partially Premixed Combustion in a Turbojet

Cited by 2 publications

References 4 publications

Considerations and simulations about Pulse Detonation Engine

Considerations and simulations about Pulse Detonation Engine

Aspects Regarding the Unguided Rocket Effectiveness

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