Study and Numerical Simulation of Unconventional Engine Technology
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Considerations and Simulations About Pulse Detonation Engine
MATEC Web of Conferences 290, 04009 (2019) https://doi.org/10.1051/matecconf /2019290 04009 MSE 2019 Considerations and simulations about Pulse Detonation Engine Vasile Prisacariu1,*, Constantin Rotaru1, and Mihai Leonida Niculescu2 1Henri Coandă Air Force Academy, Aviation Department, Brașov, Romania 2INCAS, Aerodynamic Department, București, Romania Abstract. 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. Acronyms and symbols PDE pulse detonation engine AB PDE after burner pulse detonation engine DDT deflagration-to-detonation transition PDRE pulse detonation rocket engine ZDN Zel'dovich-von Neumann-Doering Mx, My Mach numbers p pressure v volume T temperature ρ density u1, u2 velocity h1, h2 enthalpy s1, s2 (S) entropy Vo,V∞ speed 1 INTRODUCTION Detonation is an effective means of burning a fuel mixture and transforming chemical energy into mechanical energy. However, this concept of running the propulsion systems involves difficulties both in rapidly achieving the fuel mixture at high speeds and in initiating and sustaining detonation in a controlled manner. PDE differs from conventional propulsion systems in two main aspects: it generates an intermittent pulse and produces high pressure increase in the combustion chamber, which also represents a major advantage of a PDE, see Figure 1. -
Aeronautical Engineering
NASA/S P--1999-7037/S U P PL407 September 1999 AERONAUTICAL ENGINEERING A CONTINUING BIBLIOGRAPHY WITH INDEXES National Aeronautics and Space Administration Langley Research Center Scientific and Technical Information Program Office The NASA STI Program Office... in Profile Since its founding, NASA has been dedicated CONFERENCE PUBLICATION. Collected to the advancement of aeronautics and space papers from scientific and technical science. The NASA Scientific and Technical conferences, symposia, seminars, or other Information (STI) Program Office plays a key meetings sponsored or cosponsored by NASA. part in helping NASA maintain this important role. SPECIAL PUBLICATION. Scientific, technical, or historical information from The NASA STI Program Office is operated by NASA programs, projects, and missions, Langley Research Center, the lead center for often concerned with subjects having NASA's scientific and technical information. substantial public interest. The NASA STI Program Office provides access to the NASA STI Database, the largest collection TECHNICAL TRANSLATION. of aeronautical and space science STI in the English-language translations of foreign world. The Program Office is also NASA's scientific and technical material pertinent to institutional mechanism for disseminating the NASA's mission. results of its research and development activities. These results are published by NASA in the Specialized services that complement the STI NASA STI Report Series, which includes the Program Office's diverse offerings include following report types: creating custom thesauri, building customized databases, organizing and publishing research TECHNICAL PUBLICATION. Reports of results.., even providing videos. completed research or a major significant phase of research that present the results of For more information about the NASA STI NASA programs and include extensive data or Program Office, see the following: theoretical analysis. -
Sunday Monday
Sunday Sunday, 29 July 2012 1-RECPT-1 Sunday Opening Reception Exhibit Hall 1830 - 2000 hrs Monday Monday, 30 July 2012 2-JPC-1/IECEC-1 JPC/IECEC Opening Monday Keynote Centennial Ballroom I 0800 - 0900 hrs Overview of NASA major program thrusts and Technology Development Opportunities Robert Lightfoot Associate Administrator NASA Monday, 30 July 2012 3-ABPSI-1/GTE-1 Turboelectric Distributed Propulsion I Hanover C Chaired by: H. KIM, NASA Glenn Research Center and A. GIBSON, Empirical Systems Aerospace LLC 1000 hrs 1030 hrs 1100 hrs 1130 hrs AIAA-2012-3700 AIAA-2012-3701 AIAA-2012-3702 Oral Presentation (Invited) Turboelectric Distributed Sensitivity of Mission Fuel Burn Hybrid Axial and Cross-Flow Evaluation of the Propulsion Propulsion System Modelling to Turboelectric Distributed Fan Propulsion for Transonic Integration Aerodynamics on a for Hybrid-Wing-Body Aircraft Propulsion Design Assumptions Blended Wing Body Aircraft Hybrid Wing Body Concept C. Liu, Self, Cranfield, United on the N3-X Hybrid Wing Body J. Kummer, J. Allred, Propulsive J. Chu, NASA Langley Research Kingdom Aircraft Wing, LLC, Elbridge, NY; J. Felder, Center, Hampton, VA J. Felder, G. Brown, NASA Glenn NASA Glenn Research Center, Research Center, Cleveland, OH; J. Cleveland, OH Chu, NASA Langley Research Center, Hampton, VA; M. Tong, NASA Glenn Research Center, Cleveland, OH Monday, 30 July 2012 4-HSABP/HYP-1/PC-1 Constant Volume Combustion Engines Regency VII Chaired by: V. TANGIRALA, General Electric Company and D. DAUSEN, Naval Postgraduate School 1000 hrs 1030 hrs 1100 hrs 1130 hrs AIAA-2012-3703 AIAA-2012-3704 AIAA-2012-3705 AIAA-2012-3706 Development of a Wave Disk Thermodynamics of the Wave Experimental Optimization of Experimental Study of Shock Engine Experimental Facility Disk Engine Static Valveless Self-Aspiration Transfer in a Multiple Pulse N. -
Program Schedule
Program Schedule AIAA Propulsion and Energy Forum and Exposition July 25 - 27, 2016 The Program Report was last updated July 20, 2016 at 01:01 AM EDT. To view the most recent meeting schedule online, visit https://aiaa-mpe16.abstractcentral.com/planner.jsp Monday, July 25, 2016 Time Session or Event Info 8:00 AM-9:00 AM, Ballroom A-D, PLNRY-01. INNOVATE OR DIE! (Note: Dying is easier) , Plenary, Forum Event 8:45 AM-9:30 AM, Exhibit Hall C, NW-01. Networking Coffee Break, Networking 9:30 AM-12:00 PM, 255 F, ABPSI-01. Nozzles and Exhaust, Technical Paper, 52nd AIAA/SAE/ASEE Joint Propulsion Conference, Chair: Chen Chuck, [email protected], Boeing Commercial Airplanes; Co-Chair: Darius Sanders, [email protected], Air Force Reseach Laboratory AIAA-2016-4500. Reducing residue in aluminized fuel-rich propellant 9:30-10:00 AM for Ramjets. N. Rathi; P. Ramakrishna AIAA-2016-4501. Prediction of NO Emissions Using a Stirred x 10:00-10:30 AM Reactor Modelling Approach for an Aero-Engine with RQL Combustor A. Prakash AIAA-2016-4502. Hot Streak Characterization in Serpentine Exhaust 10:30-11:00 AM Nozzles D.S. Crowe; C.L. Martin AIAA-2016-4503. Propulsion AerodynamicWorkshop II, Summary of 11:00-11:30 AM Participant Results for a Dual Separate Flow Reference Nozzle, Including Some Experimental Results R.L. Thornock AIAA-2016-4504. Open and Closed-Loop Responses of a Dual- 11:30-12:00 PM Throat Nozzle during Fluidic Thrust Vectoring M. Ferlauto; R. Marsilio 9:30 AM-12:00 PM, 255 E, ADP-01. -
Imece2007-44068-Pde
Proceedings of IMECE 2007 2007 ASME International Mechanical Engineering Congress and Exposition November 11–17, 2007, Seattle, Washington, USA IMECE2007–44068 PRACTICAL ISSUES IN GROUND TESTING OF PULSED DETONATION ENGINES Philip K. Panicker, Frank K. Lu, Donald R. Wilson Aerodynamics Research Center, Mechanical and Aerospace Engineering Department University of Texas at Arlington Arlington, Texas 76019 U.S.A. [email protected], [email protected], [email protected] ABSTRACT with or replaced by a low-pressure fan. Compact designs may be feasible, thereby achieving high thrust-to-weight ratios. In Pulsed detonation engines can potentially revolutionize aero- addition, various combinations and hybrids have been space propulsion and they are the subject of intense study. proposed, including ejector-augmented and combined cycle However, most of the studies involve single shot and very short engines [6–8], thereby extending the PDEs versatility. There duration test runs. Some of the practical issues in developing are also other potential non-aerospace applications of pulse PDEs are discussed from the viewpoint of developing ground- detonations, including electric power generation [9,10], slag based demonstrators. This represents only the beginning of a removal [11] and others [12]. roadmap toward the successful development of flightweight While a roadmap has been proposed for developing PDEs engines. Viable solutions are offered that may help overcome [13], there are no known operational PDEs presently. Instead, the difficulties posed by the high temperature and pressures on it appears that the lion’s share of experimental studies have the test rig and instrumentation. Commercial solenoid valves been performed using single-shot test beds or with short run and electronic fuel injectors are presented as means to achiev- times at frequencies below 50 Hz in the range of 10 to 20 s. -
WPP Presentation
AE705 /153M/ 152 Introduction to Flight Fatima Salehbhai Third Year U G Student Mechanical Engg. Deptt. IIT Bombay Types of Propulsion Systems AE-705 Introduction to Flight Lecture No 11 Capsule-06 What is propulsion? • Moving or Pushing an object forward Propulsion = pro (forward) + pellere (drive) Why is propulsion needed in aircraft? • Getting aloft - thrust + lift • produces thrust to push an object • used to accelerate, gain altitude, and to maneuver AE-705 Introduction to Flight Lecture No 11 Capsule-06 Revising Thrust • Drives an airplane forward • To sustain lift and counteract drag http://howthingsfly.si.edu/media/thrust • Energy required • Heat by the combustion • Propulsion system • A machine that accelerates air backwards https://www.nasa.gov/audience/forstudents/k-4/stories /nasa-knows/what-is-aerodynamics-k4.html AE-705 Introduction to Flight Lecture No 11 Capsule-06 Propulsion Systems Mechanisms to produce thrust for flight AE-705 Introduction to Flight Lecture No 11 Capsule-06 Types of Propulsion Systems We'll discuss the following : • Pistonpropeller • Pulsejet • Turbojet • Ramjet • Afterburning Turbojet • Scramjet • Turbofan • Electric Propulsion • Turboprop • Ionic Propulsion • Turboshaft AE-705 Introduction to Flight Lecture No 11 Capsule-06 Powerplant Selection based on mission Source: D. P. Raymer, Aircraft Design, A Conceptual Approach, AIAA Education Series, 4th edition, 2006 AE-705 Introduction to Flight Lecture No 11 Capsule-06 Reciprocating Engines Primary powerplant for general aviation image source: https://www.comsol.com/blogs/improving-the-operational-lifetime-of-a-reciprocating-engine/ -
Study and Optimization of a Cad/Cfd Model for Valveless Pulsejets
VOL. 13, NO. 21, NOVEMBER 2018 ISSN 1819-6608 ARPN Journal of Engineering and Applied Sciences ©2006-2018 Asian Research Publishing Network (ARPN). All rights reserved. www.arpnjournals.com STUDY AND OPTIMIZATION OF A CAD/CFD MODEL FOR VALVELESS PULSEJETS Luca Piancastelli1, Stefano Cassani2, Eugenio Pezzuti3 and Luca Lipparini1 1Department of Industrial Engineering, Alma Mater Studiorum University of Bologna, Viale Risorgimento, Bologna (BO), Italy 2MultiProjecta, Via Casola Canina, Imola (BO), Italy 3Università di Roma "Tor Vergata", Dip. di Ingegneria dell’Impresa "Mario Lucertini”, Via del Politecnico, Roma, Italy E-Mail: [email protected] ABSTRACT The method introduced in this paper aims to find a feasible method to evaluate the static thrust of a “valveless” pulsejet, starting from a CAD model. CFD (Computational Fluid Dynamic) simulation and golden section were used for this purpose. Even for new pulsejet designs, it is possible to evaluate the pulsating frequency from equations available in literature or with a mono-dimensional pressure wave model. Then the combustion energy should be introduced in the engine. In this CFD model, the heat flow due to the combustion is simulated through the application of a pulsating flow of hot gases through the walls of the combustion chamber. To minimize the error of this added flow, a stoichiometric combustion of pure oxygen is introduced. The temperature value of the hot gases was optimized with the Golden Section Method in order to obtain the same experimental results of the Department of Aerospace Engineering of California Polytechnic State University, San Luis Obispo [2]. In this way, it is possible to evaluate the performance of a new design of different geometry and size. -
2020 NASA Technology Taxonomy the Page Intentionally Left Blank
National Aeronautics and Space Administration 2020 NASA Technology Taxonomy The page intentionally left blank. i CONTENTS Letter from the Chief Technologist . iii Introduction . v TX01: Propulsion Systems . 1 TX02: Flight Computing and Avionics . 15 TX03: Aerospace Power and Energy Storage . 27 TX04: Robotic Systems . 35 TX05: Communications, Navigation, and Orbital Debris Tracking and Characterization Systems . 51 TX06: Human Health, Life Support, and Habitation Systems . 65 TX07: Exploration Destination Systems . 83 TX08: Sensors and Instruments . 95 TX09: Entry, Descent, and Landing . 105 TX10: Autonomous Systems . 115 TX11: Software, Modeling, Simulation, and Information Processing . 127 TX12: Materials, Structures, Mechanical Systems, and Manufacturing . 145 TX13: Ground, Test, and Surface Systems . 157 TX14: Thermal Management Systems . 173 TX15: Flight Vehicle Systems . 185 TX16: Air Traffic Management and Range Tracking Systems . 195 TX17: Guidance, Navigation, and Control . 201 Acronyms . 222 Acknowledgements . 225 ii Letter from the Chief Technologist “And as we renew our commitment to lead in space, let’s go with confidence and let’s go with faith. Faith in the vision and the goal that’s articulated today: that we can achieve it; that Americans can achieve anything that we put our minds to. Faith in the extraordinary ingenuity and capability of the men and women of NASA and America’s space enterprise, and their ability to meet those challenges if given the resources and the support to do it. And especially faith in the courage of the men and women who are now, and those who will join, the storied ranks of American astronauts—that next generation of restless pioneers that will carry American leadership into space. -
Ejector Enhanced Pulsejet Based Pressure Gain Combustors: an Old Idea with a New Twist
NASA/TM—2005-213854 AIAA–2005–4216 Ejector Enhanced Pulsejet Based Pressure Gain Combustors: An Old Idea With a New Twist Daniel E. Paxson Glenn Research Center, Cleveland, Ohio Kevin T. Dougherty QSS Group, Inc., Cleveland, Ohio August 2005 The NASA STI Program Office . in Profile Since its founding, NASA has been dedicated to • CONFERENCE PUBLICATION. Collected the advancement of aeronautics and space papers from scientific and technical science. The NASA Scientific and Technical conferences, symposia, seminars, or other Information (STI) Program Office plays a key part meetings sponsored or cosponsored by in helping NASA maintain this important role. NASA. The NASA STI Program Office is operated by • SPECIAL PUBLICATION. Scientific, Langley Research Center, the Lead Center for technical, or historical information from NASA’s scientific and technical information. The NASA programs, projects, and missions, NASA STI Program Office provides access to the often concerned with subjects having NASA STI Database, the largest collection of substantial public interest. aeronautical and space science STI in the world. The Program Office is also NASA’s institutional • TECHNICAL TRANSLATION. English- mechanism for disseminating the results of its language translations of foreign scientific research and development activities. These results and technical material pertinent to NASA’s are published by NASA in the NASA STI Report mission. Series, which includes the following report types: Specialized services that complement the STI • TECHNICAL PUBLICATION. Reports of Program Office’s diverse offerings include completed research or a major significant creating custom thesauri, building customized phase of research that present the results of databases, organizing and publishing research NASA programs and include extensive data results . -
FINAL PROGRAM Innovations in Propulsion and Energy Driving System Solutions
2O16 25–27 JULY 2016 SALT LAKE CITY, UT Innovations in Propulsion and Energy Driving System Solutions FINAL PROGRAM www.aiaa-propulsionenergy.org #aiaaPropEnergy 16-1225 Real-Time Q&A and Polling during AIAA Propulsion NEW! and Energy 2016 withwith ConferenceConference IO!IO! During Plenary and Forum 360 Sessions, go to aiaa.cnf.io Getting Your Question Answered is as EASY as 1-2-3! 1. Click the “Ask” button to submit a question. 2. Check out the questions that other attendees are asking. 3. If you see a question that you want answered, click on the arrow on the left. The most popular questions automatically rise to the top. Participate in Session Polls 1. If Polls are available they will appear at the top of the page. Simply click/tap on a Poll to respond. 2. Choose your response(s) and hit “submit”. 3. After responding you will be able to see the results on your own device!* * Some Poll results may be hidden NO DOWNLOADING REQUIRED! Executive Steering Committee 2O16 AIAA Propulsion and Energy 2016 Welcome Welcome to Salt Lake City, Utah, and AIAA Propulsion and Energy 2016. We are excited to share the next few days with you as we explore the most pressing issues facing the future of propulsion and energy systems – the true heart of aerospace. With so many insightful and dynamic speakers and panelists, we are confident you will find the information presented here thought-provoking, impactful, and immediately useful to you in your work. Daniel “Dan” Michael Heil During the forum you will hear from thought leaders, learn about the latest technical Dumbacher Ohio Aerospace breakthroughs, and most importantly collaborate with other attendees from Purdue University Institute (Ret.) government, industry, and academia. -
Centimeter Valveless Pulsejets at Low Subsonic Flight Speeds
ABSTRACT BOYETTE, WESLEY RYAN. Thrust and Specific Impulse Optimization of Eight- Centimeter Valveless Pulsejets at Low Subsonic Flight Speeds. (Under the direction of Dr. William L. Roberts). The purpose of this research was to develop a method of accurately measuring the thrust and specific impulse of valveless pulsejets that are approximately eight centimeters in length. Previous methods of doing such were largely unsuccessful. A vertically arranged thrust stand and electronic balance were ultimately able to produce reliable results. Seven inlets were then tested on a forward facing arrangement. The maximum thrust achieved was 24.4 mN and specific impulse peaked at 295 seconds. Comparison revealed that increasing inlet length has a positive effect on pulsejet performance. Each inlet was tested at simulated forward flight speeds as well, showing that shorter inlets perform optimally at lower speeds than longer inlets. Additionally, a relationship between pulsejet performance, frequency and exhaust temperature was identified. Similar tests were performed on hybrid configurations as well, which combine forward- facing and rearward-facing inlets. Of the five hybrid configurations tested, maximum thrust was 31.2 mN and maximum specific impulse was 232 seconds. This series of tests revealed that these configurations also showed improvement in performance at higher forward flight speeds and at smaller inlet areas. In all cases, hydrogen was used as the fuel, due to its very short chemical time. Pulsejets at this scale are also shown to be capable of operating on acetylene, although with reduced performance. Thrust and Specific Impulse Optimization of Eight-Centimeter Valveless Pulsejets at Low Subsonic Flight Speeds by Wesley Ryan Boyette A thesis submitted to the Graduate Faculty of North Carolina State University in partial fulfillment of the requirements for the Degree of Master of Science Aerospace Engineering Raleigh, North Carolina 2008 APPROVED BY: Dr. -
Combustion of Acetylene and Its Performance in Valveless Pulse Jet
Published by : International Journal of Engineering Research & Technology (IJERT) http://www.ijert.org ISSN: 2278-0181 Vol. 5 Issue 06, June-2016 Combustion of Acetylene and its Performance in Valveless Pulse Jet Engine M. Dhananiya Lakshmi Sri L. Oblisamy PG Scholar Assistant Professor Department of Aeronautical Engineering Department of Aeronautical Engineering Nehru Institute of Engineering and Technology Nehru Institute of Engineering and Technology Coimbatore, Tamil Nadu Coimbatore, Tamil Nadu G. Mari Prabu Assistant Professor Department of Aeronautical Engineering Sri Shakthi Institute of Engineering and Technology Coimbatore, Tamil Nadu Abstract—This paper summarizes the significance of barriers engine). Decreases non-linearly with decreasing characteristic involved in using acetylene as alternate fuel for valve less pulse engine length scale. Also, small scale engines with moving jet engine. Acetylene gas produces 2210 to 3300 degree Celsius parts are more prone to breakdown due to fatigue of the temperatures when allowed to combust with atmospheric air. moving components. Pulsejets, especially valveless The idea of high temperature engines is innovatory due to water pulsejets, are attractive as candidates for miniaturization due thermolysis which could accompany the combustion of to their extremely simple design.[7] acetylene. The use of acetylene will reduce emission and increase combustion efficiency. The project investigates the process of combustion of acetylene stoichiometrically with atmospheric air and also with oxygen computationally with the ANSYS Fluent commercial software in a valve less Bailey Machine Services hobby scale pulse jet of 15 centimeter class. The measurement of Pressure, thrust, temperature and concentrations of Carbon monoxide, Nitrous oxide and Hydrocarbons at the exit of pulse jet with acetylene and water thermolysis, Acetylene without water thermolysis and aviation gas without water thermolysis is analyzed and calculated.