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3 edition of Multiple-cycle simulation of a pulse detonation engine ejector found in the catalog.

Multiple-cycle simulation of a pulse detonation engine ejector

Multiple-cycle simulation of a pulse detonation engine ejector

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Published by National Aeronautics and Space Administration, Glenn Research Center, Available from NASA Center for Aerospace Information in [Cleveland, Ohio], Hanover, MD .
Written in English

    Subjects:
  • Pulsed detonation engine.,
  • Unsteady reacting flows.,
  • Computational fluid dynamics.

  • Edition Notes

    Other titlesMultiple cycle simulation of a pulse detonation engine ejector
    StatementS. Yungster [and] H.D. Perkins.
    SeriesNASA/TM -- 2002-211888, NASA technical memorandum -- 211888.
    ContributionsPerkins, Hugh Douglas., NASA Glenn Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL18838739M

    1. Introduction. A pulse detonation rocket engine (PDRE),,, is a new-concept propulsion system utilizing repetitive detonations to produce thrust or power. It differs from conventional systems in two major ways: unsteady operation and detonation by: Conference Papers: Joshi DD, Lu FK “A new method to predict flow rates of gaseous fuels injected intermittently for pulse detonation engines,” AIAA Propulsion and Energy Forum and Exposition, AIAA –, July 27–29, , Orlando, Florida.


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Multiple-cycle simulation of a pulse detonation engine ejector Download PDF EPUB FB2

Multiple-Cycle Simulation of a Pulse Detonation Engine Ejector S. Yungster Institute for Computational Mechanics in Propulsion, Cleveland, Ohio H.D.

Perkins Glenn Research Center, Cleveland, Ohio Prepared for the 38th Joint Propulsion Conference and Exhibit cosponsored by the AIAA, ASME, SAE, and ASEE Indianapolis, Indiana, JulyMultiple-Cycle Simulation of a Pulse Detonation Engine Ejector.

This paper presents the results of a study involving single and multiple-cycle numerical simulations of various PDE-ejector configurations utilizing hydrogen-oxygen mixtures. The objective was to investigate the thrust, impulse and mass flow rate characteristics of these devices. Multiple-cycle Simulation of a Pulse Detonation Engine Ejector.

The results indicate that ejector systems can utilize the energy stored in the strong shock wave exiting the detonation tube to augment the impulse obtained from the Multiple-cycle simulation of a pulse detonation engine ejector book tube alone. Impulse augmentation ratios of Author: H.

Perkins and S. Yungster. Books. AIAA Education Series; Library of Flight; Multiple-Cycle Simulation of a Pulse Detonation Engine Ejector. Shaye Yungster and Hugh Perkins; 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit June Multiphase Detonations in Pulse Detonation Engines-A Status Report.

Experimental Investigation of a Pulse Detonation Engine with a Two-Dimensional Ejector. Rotary wave-ejector enhanced pulse detonation engine. 3 December | Shock Waves, Multiple-cycle simulation of a pulse detonation engine ejector book.

22, No. Multiple-Cycle Simulation of a Pulse Detonation Engine by: Performance Studies of Pulse Detonation Engine Ejectors.

Experimental study of an air-breathing pulse detonation engine ejector. Experimental Thermal and Fluid Science, Vol. 35, No. Unsteady Ejectors: The Effect of Driver Jet Mark-Space Ratio Multiple-Cycle Simulation of a Pulse Detonation Engine by:   Parametric Cycle Analysis of Multiple-cycle simulation of a pulse detonation engine ejector book Rotating Detonation Ejector-Augmented Rocket Engine.

Huan V. Cao. the deflagration to detonation transition length. As the transition length decreases the length and weight of engine reduces. The minimum length for the deflagration to detonation transition is 10 times the tube diameter.

A pulse detonation engine is a multi-cycle engine. A single. A typical pulse detonation combustor of 3 inches diameter with propane at stiochiometric fuel/air mixture is assumed and simulated in Ansys fluent study work cycle of pulse detonation engine, has been formulated in V.V.

Mitrofanov & S.A. Zhdan’s, work (). The formula of specific impulse is derived, and calculations of engine thrust characteristics were carried out. At flight Mach numbers below and compressions rate lower than 80 the engine File Size: KB. The operating cycles of PDE consist of fuel-air mixture, combustion, blowdown, and purging.

The combustion process in pulse detonation engine is the most important phenomenon as it produces reliable and repeatable detonation by: Engine Gasdynamics And Performance C. Morris* NASNGeorge C. Marshall Space Flight Center TD4O/Propulsion Research Center Marshall Space Flight Center, AL USA Submitted to Journal of Propulsion and Power, Jan.

Abstract Pulse detonation rocket engines (PDREs) offer potential performance improvements over con-File Size: 1MB. Experimental Studies of the Unsteady Ejector Mode of a Pulse Detonation Rocket-Based Combined Cycle Engine. Nicholas Mercurio, Sibtosh Pal, Roger Woodward and Robert Santoro.

Multiple-cycle simulation of a pulse detonation engine ejector (OCoLC) Microfiche version: Yungster, Shaye. Multiple-cycle simulation of a pulse detonation engine ejector (OCoLC) Material Type: Government publication, National government publication, Internet resource: Document Type: Book, Internet Resource: All Authors.

A pulse detonation engine, or "PDE", is a type of propulsion system that uses detonation waves to combust the fuel and oxidizer engine is pulsed because the mixture must Multiple-cycle simulation of a pulse detonation engine ejector book renewed in. Multiple-cycle simulation of a pulse detonation engine ejector (OCoLC) Microfiche version: Yungster, Shaye.

Multiple-cycle simulation of a pulse detonation engine ejector (OCoLC) Material Type: Document, Government publication, National government publication, Internet resource: Document Type: Internet Resource, Computer File. Numerical simulation of the nozzle and ejector effect on the performance of a pulse detonation engine Article (PDF Available) in Thermal Science 22(00) January with 42 Reads.

Pulse Detonation Engine - A Next Gen Propulsion 1. International Journal of Modern Engineering Research (IJMER) Vol.2, Issue.6, Nov-Dec. pp ISSN: Pulse Detonation Engine - A Next Gen Propulsion T K Jindal Assistant Professor PEC University of Technology ct: Pulse detonation technology has the potential to explained by.

Detonation Control for Propulsion: Pulse Detonation and Rotating Detonation Engines Jiun-Ming Li, Chiang Juay Teo, Boo Cheong Khoo, Jian-Ping Wang, Cheng Wang (eds.) This book focuses on the latest developments in detonation engines for aerospace propulsion, with a focus on the rotating detonation engine (RDE).

applicable to a hybrid Pulse Detonation/Turbofan Engine. The ejector would be intended for applications that would replace the high-pressure compressor and high-pressure turbine sections of the core of a high bypass turbofan engine.

The objective of the present study is to characterize the thrust augmentation achievable with a PDE-ejector and. All about pulse detonation engine. x - Lect 24 - Rolling Motion, Gyroscopes, VERY NON-INTUITIVE - Duration: Lectures by Walter Lewin.

After all, an engine is an engine, capable of immense power (and who knows when such innovations will trickle down to the civilian sector). So with that in mind, let's look at the rotating detonation engine -- a type of gas-turbine that's designed for efficiency, with its carefully constructed, consistent cycle of injections and : Cherise Threewitt.

A pulse detonation engine is a type of propulsion system that uses detonation waves to combust the fuel and oxidizer mixture. The engine is pulsed because the mixture must be renewed in the combustion chamber between each detonation wave and the next.

Theoretically, a PDE can operate from subsonic up to a hypersonic flight speed of roughly Mach 5. An ideal PDE design can have a. Nozzle effects on thrust and inlet pressure of a multi-cycle air-breathing pulse detonation engine (APDE) are investigated experimentally.

An APDE with 68 mm in diameter and 2 mm in length is. engines. Pulse detonation engine is the new concept in propulsion technology for future propulsion system.

In this contrast, an ejector was used to modify the detonation wave propagation structure in pulse detonation engine combustor. In this paper k-ε turbulence model was used for detonation wave shock pattern simulationCited by: 1. Yungster, S. and Perkins, H. Multiple cycle simulation of a pulse detonation engine ejector.

38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Joint Propulsion Conferences & Exhibit, Indianapolis, – () Google ScholarAuthor: Guangyu Li, Xiaowei Li, Jue Ding, Peifen Weng, Zhanbin Lu.

The use of a non-steady ejector based on wave rotor technology is modeled for pulse detonation engine performance improvement and for compatibility with turbomachinery components in hybrid propulsion systems. The rotary wave ejector device integrates a pulse detonation process with an efficient momentum transfer process in specially shaped channels of a single wave-rotor by: 5.

An analysis of a pulse detonation engine (PDE) driven ejector was performed. Thrust augmentation and specific impulse gains provided by a constant area cross section ejector were computed.

To improve the performance of pulse detonation engines, a 48 cm long cylindrical combustion chamber of 5cm internal diameter (i.d.) is fitted with an ejector of constant section. The role of the ejector is (i) to provide partial confinement of the detonation products escaping from the chamber and (ii) to suck in fresh air and then to increase Cited by: 2-D Simulation with OH* Kinetics of a Single-Cycle Pulse Detonation Engine Article in Journal of Applied Fluid Mechanics 12(4) July with Reads How we measure 'reads'.

Numerical simulation to investigate the effect of obstacle on detonation wave propagation in a pulse detonation engine combustor. Inter. Emerging Tech. and Adv. Eng.

() – Google Scholar; M. Amin, H. Roufand J.-L. Cambier. Numerical investigation on the effects of nozzle geometry on the performance of a pulse Author: Saurabh Tripathi, Krishna Murari Pandey. A rotating detonation engine (RDE) is a proposed engine using a form of pressure gain combustion, where one or more detonations continuously travel around an annular channel.

Computational simulations and experimental results have shown that the RDE has potential in transport and other applications. In detonative combustion, the results expand at supersonic speed. I am attempting to simulate a Ejector-Augmented Pulse detonation rocket.

A set up in which the PDR is housed within an ejector duct, thus exhausting into a secondary flow stream. The ejector is preceded by a 15 degree wedge, consequently the secondary flow stream has the flow characteristics of flow passing over the wedge.

Numerical simulation of a hydrocarbon fuelled valveless pulsejet. J.L. Hoke, Assessment of the performance of a pulsejet and comparison with a pulse-detonation engine, in: Proceedings of the 43rd AIAA Aerospace Sciences Meeting and Exhibit, JanuaryAIAApp. 2,7, Cited by: 1.

US Air Force Research Laboratory-produced video showcasing the work done on pulsed detonation engines (PDEs), which are being looked at replace combustion chambers or afterburners in turbine engines. Review on Recent Advances in Pulse Detonation Engines 1.

Review Article Review on Recent Advances in Pulse Detonation Engines K. Pandey and Pinku Debnath Department of Mechanical Engineering, National Institute of Technology, Silchar, AssamIndia Correspondence should be addressed to K.

Pandey; [email protected] Received 27 July ; Revised. A key concept envisioned for Pulse Detonation Engine (PDE) technology is a hybrid engine, where a Pulse Detonation Combustor (PDC) replaces the combustor in a conventional gas turbine. A systems level performance estimation model for a PDC-based hybrid engine cycle was by: The primary goal of this research project has been to use high resolution numerical methods to explore reactive and magnetohydrodynamic (MHD) flow phenomena as a means of potentially improving the performance of hypersonic propulsion through a range of alternative and innovative combined-cycle concepts, such as the Pulse Detonation Rocket-Induced MHD Ejector (PDRIME) Concept.

Investigation of Pulse Detonation Engines; Theory, Design and Analysis Jeff Vizcaino Pressure Distribution for 1-D simulation 42 Figure Peak Pressure Region for 1-D simulation 43 Mass vs. Pulse Width curves for Propane Figure Mass vs. Pulse Width curves for Air : Jeff Vizcaino. The 'Pulse detonation wave engine' section.

Google search for "pulse detonation wave engine" OR "pulsed detonation wave engine" -wikipedia (the minus sign means "exclude") found "about 5," results.

So this is a significant topic that people may want information about, whether pulse detonation wave engines exist in the real world or not.

High thermal pdf of pulse detonation engine attracts researchers to apply it as a new technology for aerospace propulsion. One way to improve thrust are ejectors. The increase in thrust is Author: A. Korobov, S. V. Golovastov, V. V. Golub.Unsteady Engines Engines such as the pulse detonation engine or pulse jet engines are solely based download pdf unsteady combustion operation.

Combustion in these engines is very similar and occurs in a cyclical manner producing unsteady thrust.

To obtain useful parameters, cycles are repeated with a constant frequency yielding average thrust measurements.The pulsed detonation engine may optionally include a volume of ejector/bypass air surrounding ebook detonation ebook, which captures the detonation engine exhaust and mixes the exhaust with the ejector air, and a back pressure device for feeding dynamic pressure ejector air to the interior of the detonation chamber near its outlet by: