Analysis of Pulse Detonation Turbojet Engines PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Analysis of Pulse Detonation Turbojet Engines PDF full book. Access full book title Analysis of Pulse Detonation Turbojet Engines by Ronnachai Vutthivithayarak. Download full books in PDF and EPUB format.
Author: Ronnachai Vutthivithayarak
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Research over the last two decades has shown the potential advantages of pulse detonation engines (PDEs) over existing aero-engines in terms of improved thermodynamics efficiency, improved thrust performance, simplicity of design, and exibility to operate over a wide speed range. The inherently unsteady characteristic of PDEs makes it di culty to analyze and evaluate their performance. The conventional method that relies on steady-state assumptions cannot be directly applied. PDE studies have to employ unsteady gasdynamics behavior. In this study, the thermodynamic cycle of a PDE, which can be called the ZND cycle, is theoretically analyzed. A parametric analysis of turbojet PDEs is considered for both ideal and non-ideal cases. The conventional turbojet with a Brayton cycle is brought in the comparison to verify that PDEs can provide better performance.
Author: Ronnachai Vutthivithayarak
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Research over the last two decades has shown the potential advantages of pulse detonation engines (PDEs) over existing aero-engines in terms of improved thermodynamics efficiency, improved thrust performance, simplicity of design, and exibility to operate over a wide speed range. The inherently unsteady characteristic of PDEs makes it di culty to analyze and evaluate their performance. The conventional method that relies on steady-state assumptions cannot be directly applied. PDE studies have to employ unsteady gasdynamics behavior. In this study, the thermodynamic cycle of a PDE, which can be called the ZND cycle, is theoretically analyzed. A parametric analysis of turbojet PDEs is considered for both ideal and non-ideal cases. The conventional turbojet with a Brayton cycle is brought in the comparison to verify that PDEs can provide better performance.
Author: Gabriel Roy
Publisher: Butterworth-Heinemann
ISBN: 0123693942
Category : Business & Economics
Languages : en
Pages : 505
Get Book Here
Book Description
Chemical propulsion comprises the science and technology of using chemical reactions of any kind to create thrust and thereby propel a vehicle or object to a desired acceleration and speed. Cumbustion Processes in Propulsion focuses on recent advances in the design of very highly efficient, low-pollution-emitting propulsion systems, as well as advances in testing, diagnostics and analysis. It offers unique coverage of Pulse Detonation Engines, which add tremendous power to jet thrust by combining high pressure with ignition of the air/fuel mixture. Readers will learn about the advances in the reduction of jet noise and toxic fuel emissions-something that is being heavily regulated by relevant government agencies. Lead editor is one of the world's foremost combustion researchers, with contributions from some of the world's leading researchers in combustion engineering Covers all major areas of chemical propulsion-from combustion measurement, analysis and simulation, to advanced control of combustion processes, to noise and emission control Includes important information on advanced technologies for reducing jet engine noise and hazardous fuel combustion emissions
Author: Jiun-Ming Li
Publisher: Springer
ISBN: 3319689061
Category : Technology & Engineering
Languages : en
Pages : 246
Get Book Here
Book Description
This book focuses on the latest developments in detonation engines for aerospace propulsion, with a focus on the rotating detonation engine (RDE). State-of-the-art research contributions are collected from international leading researchers devoted to the pursuit of controllable detonations for practical detonation propulsion. A system-level design of novel detonation engines, performance analysis, and advanced experimental and numerical methods are covered. In addition, the world’s first successful sled demonstration of a rocket rotating detonation engine system and innovations in the development of a kilohertz pulse detonation engine (PDE) system are reported. Readers will obtain, in a straightforward manner, an understanding of the RDE & PDE design, operation and testing approaches, and further specific integration schemes for diverse applications such as rockets for space propulsion and turbojet/ramjet engines for air-breathing propulsion. Detonation Control for Propulsion: Pulse Detonation and Rotating Detonation Engines provides, with its comprehensive coverage from fundamental detonation science to practical research engineering techniques, a wealth of information for scientists in the field of combustion and propulsion. The volume can also serve as a reference text for faculty and graduate students and interested in shock waves, combustion and propulsion.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 42
Get Book Here
Book Description
The performance analysis of the supersonic pulse-detonation-jet engine system represents some revision of earlier results, including new ideas of scavenging flow. Curves of the drag coefficient of a typical supersonic long- range missile showed that four 36-in.-diam engines have enough reserve power to propel the missile through sonic flight velocities and up to a flight Mach number of 2.80. A unit small enough to be mounted on the blade tip of a helicopter was analyzed. The unit has a maximum diameter of 8.25 in., with combustion tubes 6 in. long and ranging in diameter from 0.60 to 0.25 in. The total weight of 1 unit would be about 35 lb. Combustion would be achieved in the unit by surface contact with the hot walls of the ceramic tubes, and it would proceed radially inward. A unit of this type would produce a thrust of 110 lb at a maximum temperature of 2000 deg F, and would have a specific fuel consumption of 1.65 lb/hr/lb of thrust.
Author: Gabriel Roy
Publisher: Butterworth-Heinemann
ISBN: 9781493300709
Category : Business & Economics
Languages : en
Pages : 480
Get Book Here
Book Description
Chemical propulsion comprises the science and technology of using chemical reactions of any kind to create thrust and thereby propel a vehicle or object to a desired acceleration and speed. This book focuses on recent advances in the design of very highly efficient, low-pollution-emitting propulsion systems, as well as advances in testing, diagnostics and analysis. It offers unique coverage of Pulse Detonation Engines, which add tremendous power to jet thrust by combining high pressure with ignition of the air/fuel mixture. Readers will learn about the advances in the reduction of jet noise and toxic fuel emissions-something that is being heavily regulated by relevant government agencies. * Lead editor is one of the world's foremost combustion researchers, with contributions from some of the world's leading researchers in combustion engineering * Covers all major areas of chemical propulsion-from combustion measurement, analysis and simulation, to advanced control of combustion processes, to noise and emission control * Includes important information on advanced technologies for reducing jet engine noise and hazardous fuel combustion emissions
Author: Haider Hekiri
Publisher:
ISBN: 9780542448836
Category : Aerospace engineering
Languages : en
Pages :
Get Book Here
Book Description
The performance of an ejector-driven pulse detonation engine (PDE) with an afterburner is analytically estimated. In the analysis, the PDE was modeled as a straight tube, closed at the front end and open at the other. A detonation wave starts to travel after it is ignited at the closed end, causing a Chapman-Jouguet detonation wave followed by a Taylor rarefaction to travel to the open end. At that point, rarefaction waves are reflected back to the closed end. The result is a high thrust due to both the primary and secondary flows of the ejector-driven PDE. A theoretical analysis is made to determine the average thrust density and the impulse density per cycle of the primary flow. The mixed flow of the PDE tube and the ejector is then subjected to afterburning. The overall engine performance was eventually derived.
Author: S. N. B. Murthy
Publisher: AIAA
ISBN: 9781600863912
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 558
Get Book Here
Book Description
Annotation Leading researchers provide a cohesive treatment of the complex issues in high-speed propulsion, as well as introductions to the current capabilities for addressing several fundamental aspects of high-speed vehicle propulsion development. Includes more than 380 references, 290 figures and tables, and 185 equations.
Author: J. Kasahara
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Sivarai Amith Kumar
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
The performance of a hybrid pulse detonation engine (PDE), with the PDE tubes installed in the bypass duct of a turbofan engine is investigated in this study. Performance parameters for the duct burning PDE engine are compared with a baseline turbofan engine. The PDE analysis is based on an updated numerical analysis by Endo-Fujiwara, whereas the turbofan calculations are based on Mattingly's gas turbine model. The calculations were done with MATLAB 2010 as a platform. A mixer analysis was performed for the hybrid engine concept. In the duct burning PDE, the PDE exhaust was mixed with the turbine exhaust prior to entering the nozzle. For this configuration, core air was mixed with the PDE exhaust to cool the flow prior to entering the turbine. The performance of both configurations was compared for parametric variations of compressor and fan pressure ratio, bypass ratio, PDE tube length and frequency. A performance analysis was carried out for the resulting hybrid baseline engine at different altitudes and Mach numbers.
Author: Jeff Vizcaino
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 510
Get Book Here
Book Description
"Detonation and constant volume combustion has been known to the scientific community for some time but only recently has active research been done into its applications. Detonation based engines have received much attention in the last two decades because of its simple design and potential benefits to the aerospace industry. It is the goal of this study to provide a background into detonation theory and application and establish the basis for future detonation based research at Embry-Riddle Aeronautical University. In this paper we will discuss the experimental aspects of building, testing, and analysis of a pulsed detonation tube including the development of a pulsed detonation testbed and analysis via computational fluid dynamics."--Leaf iv.
