Analysis of influence design parameters ejector pipe at the detonation specifications engine
Journal Title: Механіка гіроскопічних систем - Year 2015, Vol 0, Issue 30
Abstract
The engines that use a detonation cycle have greater thermal efficiency than engines with constant-pressure combustion cycle. The mechanisms of ejector augmentation are evident in secondary air entrainment. The impulse characteristics of a pulse detonation engine (PDE) with ejector were investigated under different parameters. The propagation of a detonation wave in an ejector-augmented pulse detonation rocket engine fueled with a hydrogen-oxygen methane-oxygen and hydrocarbon-oxygen mixture is studied. The straight cylindrical ejector was coaxially installed at different axial locations relative to the exit of the detonation chamber. The use of a non-steady ejector is modeled for pulse detonation engine performance improvement. In this paper, a two-dimensional numerical model is developed to help design the basic geometry and operating parameters of the device. The unsteady flow processes are simulated and compared with a baseline PDE without ejector enhancement. Various features including detonation-shock interaction, detonation diffraction and vortex formation are observed. It is observed that the design of detonation wave flow path in detonation tube, ejector and operating parameters such as Mach numbers are mainly responsible for improving the propulsion performance of PDE. Object оf numerical simulation is the cylindrical detonation chamber with a diameter of Dc = 25 mm and a length of Lc = 100 mm. The cylindrical ejectors with a length of Le = 100 mm and diameters De = 35, 40, 45, 50 that 55 mm were attached to the chamber. Also ejectors with a diameter of De = 35 mm and lengths of Le = 50, 100, 150, 200 that a 250 mm respectively were attached to the chamber. The calculation was performed with a computer program that implements a numerical TVD-scheme. The results of calculations were presented as the dependence of specific thrust impulse Isp/Ispo ratio (Isp - specific thrust impulse with ejector nozzle; Ispo - specific thrust impulse of a chamber only) to the ejector-to-PDE diameter ratio (De/Dc), to the ejector-to-PDE length ratio (Le/Lc) and to the displacement of an ejector-to-PDE length ratio ((Ld +Lc)/Lc), where Ld – distance from the input section of the nozzle to the thrust wall of a detonation chamber. The method of a numerical simulation proved the possibility of a significant increase of pulse detonation engine performance through the use of ejector nozzle.
Authors and Affiliations
Олександра Валерівна Сосновська,, Олександр Євгенович Золотько,, Юрій Іванович Мороз, Олена Василівна Золотько
Keywords
Related Articles
- EP ID EP540030
- DOI -
- Views 84
- Downloads 0
Экспериментальное подтверждения работоспособности капиллярного заборного устройства при отделении космического аппарата
Описаны методы определения модельных условий (выбор масштаба опытной конструкции, вида модельной жидкости, величины ускорений и т.д.), дано описание стенда разработанного специально под данные испытания и приведены резул...
Method of determining the geographic meridian plane by ground-based pendulum gyrocompass in exponential acceleration mode of its rotor
A method of determining the position of the geographic meridian by threefold pendulum gyrocompass during the process of exponential acceleration of its rotor. Obtained an algorithm identifying the initial position of the...
3D-models design concept of complex technical objects using knowledge-based technology
<p>3D-models design of complex technical objects (CTO) is performed using information technology (IT). Such technology includes continuous acquisition and life cycle support (CALS) being tools set for its creation. 3D-mo...
Compact portable indicator-meterof ozone concentration
Compact portable indicator-meter of ozone concentration is the most suitable device to measure the ozone concentration in the work zone and control its maximum allowable concentration. The analysis of existing ozone meas...
Improving the accuracy of the inertial navigation system by means of technical vision
The development of the inertial navigation system (INS) errors correction method by means and methods of technical vision(MTV) is an actual and effective application problem. Having the values of the UAV distance and di...