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 86
- Downloads 0
Робастна система керування безпілотного літального апарату
<p><span>У даній статті був розроблений регулят</span><span>ор для безпілотного літального апарату (БПЛА). БПЛА рухається по аеробалістичній траекторії. Як наслідок, параметри БПЛА змінюються досить сильно, що у свою че...
Features of influence of the gyroscopic system on oscillation of the vibration protection system of passive type
The paper examines the impact of gyroscopic system on vibration protection system. Object of research is adjustable gyro compass. It is shown that the horizontal vibration of base can cause hull angular oscillations of t...
BENDING OF COMPOSITE SHELLS BASED ON NON-LINEAR DISTRIBUTION OF DISPLACEMENTS ACROSS THE THICKNESS OF FILLER
This paper presents a methodology of calculation the composite laminated shells, which is based on the variational-grid approach of forming the necessary functionals. Further minimizing of them was performed by the coord...
Стимулювання інновацій в ракетно-космічній промисловості на прикладі NASA і Роскосмос
<p>В статті зроблена спроба проаналізувати напрямки стимулювання інновацій в ракетно-космічній техніці на прикладі NASA і Роскосмос. Розглянути принципи та методи стимулювання інновацій. Автором зроблена спроба на основі...
УЗГОДЖЕНИЙ ПОЛІТ ГРУПИ БЕЗПІЛОТНИХ ПОВІТРЯНИХ СУДЕН
<p class="a"><span lang="EN-US">Пропонується підхід, для автономного керування польотом безпілотних авіаційних комплексів (БАК). Для розробки алгоритмів систем керування груповим польотом БАК, об’єднаємо динаміку декільк...