Effects of Large-Scale Transient Loading and Waste Heat Rejection on a Three Stream Variable Cycle Engine

Total Page:16

File Type:pdf, Size:1020Kb

Effects of Large-Scale Transient Loading and Waste Heat Rejection on a Three Stream Variable Cycle Engine Wright State University CORE Scholar Browse all Theses and Dissertations Theses and Dissertations 2011 Effects of Large-Scale Transient Loading and Waste Heat Rejection on a Three Stream Variable Cycle Engine Michael William Corbett Wright State University Follow this and additional works at: https://corescholar.libraries.wright.edu/etd_all Part of the Mechanical Engineering Commons Repository Citation Corbett, Michael William, "Effects of Large-Scale Transient Loading and Waste Heat Rejection on a Three Stream Variable Cycle Engine" (2011). Browse all Theses and Dissertations. 524. https://corescholar.libraries.wright.edu/etd_all/524 This Thesis is brought to you for free and open access by the Theses and Dissertations at CORE Scholar. It has been accepted for inclusion in Browse all Theses and Dissertations by an authorized administrator of CORE Scholar. For more information, please contact [email protected]. EFFECTS OF LARGE-SCALE TRANSIENT LOADING AND WASTE HEAT REJECTION ON A THREE STREAM VARIABLE CYCLE ENGINE A thesis submitted in partial fulfillment of the requirements for the degree of Master of Science in Engineering By MICHAEL WILLIAM CORBETT B.S., Wright State University, 2006 2011 Wright State University Distribution Statement A: Unlimited Distribution Cleared for Public Release by AFRL/WS Public Affairs on 14 DEC 2011 Case Number 88ABW-2011-6439 The views expressed in this article are those of the author and do not reflect the official policy or position of the United States Air Force, Department of Defense, or the U.S. Government. WRIGHT STATE UNIVERSITY GRADUATE SCHOOL December 6, 2011 I HEREBY RECOMMEND THAT THE THESIS PREPARED UNDER MY SUPERVISION BY Michael William Corbett ENTITLED Effects of Large-Scale Transient Loading and Waste Heat Rejection on a Three Stream Variable Cycle Engine BE ACCEPTED IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF Master of Science in Engineering. _________________________________________ J. Mitch Wolff, Ph.D. Thesis Director _________________________________________ George P. G. Huang, Ph.D., P.E. Chair Department of Mechanical and Materials Engineering College of Engineering and Committee on Final Examination Computer Science _________________________________________ J. Mitch Wolff, Ph.D. _________________________________________ Joseph C. Slater, Ph.D., P.E. _________________________________________ Rory A. Roberts, Ph.D. _________________________________________ Nicholas J. Kuprowicz, Ph.D. _________________________________________ Andrew T. Hsu, Ph.D. Dean, Graduate School ABSTRACT Corbett, Michael William. M.S.Egr., Department of Mechanical Engineering, Wright State University, 2011. Effects of Large-Scale Transient Loading and Waste Heat Rejection on a Three Stream Variable Cycle Engine. The objective of the research presented in this document was to gain an understanding of the feasibility of extracting large amounts of transient shaft power from a variable cycle engine and to reject waste heat into the third stream bypass duct. This first required the development of a transient engine and controller simulation. After performing basic verification of the model, such as ensuring conservation of mass, tests were run for three missions using a low-efficiency periodic load which both required shaft power and created low quality waste heat. The waste heat generated by that load was lifted by a cooling system and rejected into the third stream duct. The impact of the external load and the mission conditions on cooled cooling air behavior and engine performance was assessed. Overall, the engine was capable of performing the missions, providing the required shaft power, and rejecting the waste heat to the third stream. v TABLE OF CONTENTS I. INTRODUCTION ........................................................................................................................................ 1 Overview of Variable Cycle Turbine Engines ................................................................................ 2 Overview of Engine Power Extraction ............................................................................................. 9 II. MODEL DEVELOPMENT ..................................................................................................................... 17 Engine Simulation Computational Framework ......................................................................... 17 Study Engine Model .............................................................................................................................. 19 Physics Modeled ..................................................................................................................................... 25 Ambient and Inlet Start ....................................................................................................... 25 Inlet .............................................................................................................................................. 25 Closed Loop Bridge ............................................................................................................... 26 Bleed ............................................................................................................................................ 27 Duct .............................................................................................................................................. 27 Fan/Compressor .................................................................................................................... 28 Splitter ........................................................................................................................................ 30 Duct with Air Gap and Heat Exchanger (Specified ) ............................................. 31 Fan Duct Heat Exchanger with Air Gap (Calculated ) .......................................... 34 Burner ......................................................................................................................................... 36 Turbine ....................................................................................................................................... 37 Mixer ........................................................................................................................................... 41 Afterburner ............................................................................................................................... 41 Nozzle ......................................................................................................................................... 42 Shaft ............................................................................................................................................. 42 Heat Soak ................................................................................................................................... 45 Spillage Drag ............................................................................................................................ 46 Aft Body Drag ........................................................................................................................... 47 Flow Holding ............................................................................................................................ 48 Cooled Cooling Air ................................................................................................................. 49 vi TABLE OF CONTENTS (CONTINUED) Customer Power Extraction ............................................................................................... 51 Physics Not Modeled ............................................................................................................................ 56 Controls ...................................................................................................................................................... 60 Overall Controller Structure .............................................................................................. 62 Fuel Control .............................................................................................................................. 65 Variable Geometry Control ................................................................................................ 68 III. RESULTS .................................................................................................................................................... 70 Basic Model Verification ..................................................................................................................... 70 Ground Attack Mission ........................................................................................................................ 80 Overall Mission Performance ............................................................................................ 81 Mission Leg Performance When the Periodic Load Is Inactive ........................... 94 Mission Leg Performance When the Periodic Load Is Active .............................. 95 Periodic Load Parameter Variations ........................................................................... 107 Intercept Mission ................................................................................................................................ 114 Dogfight Mission .................................................................................................................................. 120 IV. CONCLUSIONS
Recommended publications
  • Aerospace Engine Data
    AEROSPACE ENGINE DATA Data for some concrete aerospace engines and their craft ................................................................................. 1 Data on rocket-engine types and comparison with large turbofans ................................................................... 1 Data on some large airliner engines ................................................................................................................... 2 Data on other aircraft engines and manufacturers .......................................................................................... 3 In this Appendix common to Aircraft propulsion and Space propulsion, data for thrust, weight, and specific fuel consumption, are presented for some different types of engines (Table 1), with some values of specific impulse and exit speed (Table 2), a plot of Mach number and specific impulse characteristic of different engine types (Fig. 1), and detailed characteristics of some modern turbofan engines, used in large airplanes (Table 3). DATA FOR SOME CONCRETE AEROSPACE ENGINES AND THEIR CRAFT Table 1. Thrust to weight ratio (F/W), for engines and their crafts, at take-off*, specific fuel consumption (TSFC), and initial and final mass of craft (intermediate values appear in [kN] when forces, and in tonnes [t] when masses). Engine Engine TSFC Whole craft Whole craft Whole craft mass, type thrust/weight (g/s)/kN type thrust/weight mini/mfin Trent 900 350/63=5.5 15.5 A380 4×350/5600=0.25 560/330=1.8 cruise 90/63=1.4 cruise 4×90/5000=0.1 CFM56-5A 110/23=4.8 16
    [Show full text]
  • 2. Afterburners
    2. AFTERBURNERS 2.1 Introduction The simple gas turbine cycle can be designed to have good performance characteristics at a particular operating or design point. However, a particu­ lar engine does not have the capability of producing a good performance for large ranges of thrust, an inflexibility that can lead to problems when the flight program for a particular vehicle is considered. For example, many airplanes require a larger thrust during takeoff and acceleration than they do at a cruise condition. Thus, if the engine is sized for takeoff and has its design point at this condition, the engine will be too large at cruise. The vehicle performance will be penalized at cruise for the poor off-design point operation of the engine components and for the larger weight of the engine. Similar problems arise when supersonic cruise vehicles are considered. The afterburning gas turbine cycle was an early attempt to avoid some of these problems. Afterburners or augmentation devices were first added to aircraft gas turbine engines to increase their thrust during takeoff or brief periods of acceleration and supersonic flight. The devices make use of the fact that, in a gas turbine engine, the maximum gas temperature at the turbine inlet is limited by structural considerations to values less than half the adiabatic flame temperature at the stoichiometric fuel-air ratio. As a result, the gas leaving the turbine contains most of its original concentration of oxygen. This oxygen can be burned with additional fuel in a secondary combustion chamber located downstream of the turbine where temperature constraints are relaxed.
    [Show full text]
  • A Supersonic Fan Equipped Variable Cycle Engine for a Mach 2.7 Supersonic Transport
    University of New Hampshire University of New Hampshire Scholars' Repository Applied Engineering and Sciences Scholarship Applied Engineering and Sciences 8-22-1985 A Supersonic Fan Equipped Variable Cycle Engine for a Mach 2.7 Supersonic Transport Theodore S. Tavares University of New Hampshire, Manchester, [email protected] Follow this and additional works at: https://scholars.unh.edu/unhmcis_facpub Recommended Citation Tavares, T.S., “A Supersonic Fan Equipped Variable Cycle Engine for a Mach 2.7 Supersonic Transport,” NASA-CR-177141, 1986. This Report is brought to you for free and open access by the Applied Engineering and Sciences at University of New Hampshire Scholars' Repository. It has been accepted for inclusion in Applied Engineering and Sciences Scholarship by an authorized administrator of University of New Hampshire Scholars' Repository. For more information, please contact [email protected]. https://ntrs.nasa.gov/search.jsp?R=19860019474 2018-07-25T19:53:49+00:00Z ^4/>*>?/ GAS TURBINE LABORATORY DEPARTMENT OF AERONAUTICS AND ASTRONAUTICS MASSACHUSETTS INSTITUTE OF TECHNOLOGY CAMBRIDGE, MA 02139 A FINAL REPORT ON NASA GRANT NAG-3-697 entitled A SUPERSONIC FAN EQUIPPED VARIABLE CYCLE ENGINE FOR A MACH 2.7 SUPERSONIC TRANSPORT by T. S. Tavares prepared for NASA Lewis Research Center Cleveland, OH 44135 (NASA-CB-177141) A SDPEBSCNIC FAN EQUIPPED N86-28946 VARIABLE CYCLE ENGINE.JOB A MACH 2.? SDPEESONIC TBANSPOBT Final Report (Massachusetts Inst. of Tech.) 107 p Unclas CSCL 21E G3/07 43461 August 22, 1985 A SUPERSONIC FAN EQUIPPED VARIABLE CYCLE ENGINE FOR A HACK 2.7 SUPERSONIC TRANSPORT by Theodore Sean Tavares A SUPERSONIC FAN EQUIPPED VARIABLE CYCLE ENGINE FOR A MACH 2.7 SUPERSONIC TRANSPORT by THEODORE SEAN TAVARES ABSTRACT A design stud/ was carried out to evaluate the concept of a variable cycle turbofan engine with an axially supersonic fan stage as powerplant for a Mach 2.7 supersonic transport.
    [Show full text]
  • The Power for Flight: NASA's Contributions To
    The Power Power The forFlight NASA’s Contributions to Aircraft Propulsion for for Flight Jeremy R. Kinney ThePower for NASA’s Contributions to Aircraft Propulsion Flight Jeremy R. Kinney Library of Congress Cataloging-in-Publication Data Names: Kinney, Jeremy R., author. Title: The power for flight : NASA’s contributions to aircraft propulsion / Jeremy R. Kinney. Description: Washington, DC : National Aeronautics and Space Administration, [2017] | Includes bibliographical references and index. Identifiers: LCCN 2017027182 (print) | LCCN 2017028761 (ebook) | ISBN 9781626830387 (Epub) | ISBN 9781626830370 (hardcover) ) | ISBN 9781626830394 (softcover) Subjects: LCSH: United States. National Aeronautics and Space Administration– Research–History. | Airplanes–Jet propulsion–Research–United States– History. | Airplanes–Motors–Research–United States–History. Classification: LCC TL521.312 (ebook) | LCC TL521.312 .K47 2017 (print) | DDC 629.134/35072073–dc23 LC record available at https://lccn.loc.gov/2017027182 Copyright © 2017 by the National Aeronautics and Space Administration. The opinions expressed in this volume are those of the authors and do not necessarily reflect the official positions of the United States Government or of the National Aeronautics and Space Administration. This publication is available as a free download at http://www.nasa.gov/ebooks National Aeronautics and Space Administration Washington, DC Table of Contents Dedication v Acknowledgments vi Foreword vii Chapter 1: The NACA and Aircraft Propulsion, 1915–1958.................................1 Chapter 2: NASA Gets to Work, 1958–1975 ..................................................... 49 Chapter 3: The Shift Toward Commercial Aviation, 1966–1975 ...................... 73 Chapter 4: The Quest for Propulsive Efficiency, 1976–1989 ......................... 103 Chapter 5: Propulsion Control Enters the Computer Era, 1976–1998 ........... 139 Chapter 6: Transiting to a New Century, 1990–2008 ....................................
    [Show full text]
  • Turbomachinery Technology for High-Speed Civil Flight
    4 NASA Technical Memorandum 102092 . Turbomachinery Technology for High-speed Civil Flight , Neal T. Saunders and Arthur J. Gllassman Lewis Research Center Cleveland, Ohio Prepared for the 34th International Gas Turbine Aepengine Congress and Exposition sponsored by the American Society of Mechanical Engineers Toronto, Canada, June 4-8, 1989 ~ .. (NASA-TH-102092) TURBOHACHINERY TECHPCLOGY N89-24320 FOR HIGH-SPEED CIVIL FLIGHT (NBSEL, LEV& Research Center) 26 p CSCL 21E Unclas G3/07 0217641 TURBOMACHINERY TECHNOLOGY FOR HIGH-SPEED CIVIL FLIGHT Neal T. Saunders and Arthur J. Glassman ABSTRACT This presentation highlights some of the recent contributions and future directions of NASA Lewis Research Center's research and technology efforts applicable to turbomachinery for high-speed flight. For a high-speed civil transport application, the potential benefits and cycle requirements for advanced variable cycle engines and the supersonic throughflow fan engine are presented. The supersonic throughf low fan technology program is discussed. Technology efforts in the basic discipline areas addressing the severe operat- ing conditions associated with high-speed flight turbomachinery are reviewed. Included are examples of work in internal fluid mechanics, high-temperature materials, structural analysis, instrumentation and controls. c INTRODUCTION Future Emphasis Shifting to High-speed Flight Two years ago, the aeronautics community commemorated the 50th anniversary of the first successful operation of a turbojet engine. This remarkable feat by Sir Frank Whittle represents the birth of the turbine engine industry, which has greatly refined and improved Whittle's invention into the splendid engines that are flying today. NASA, as did its predecessor NACA, has assisted indus- try in the creation and development of advanced technologies for each new gen- eration of engines.
    [Show full text]
  • 04 Propulsion
    Aircraft Design Lecture 2: Aircraft Propulsion G. Dimitriadis and O. Léonard APRI0004-­1, Aerospace Design Project, Lecture 4 1 Introduction • A large variety of propulsion methods have been used from the very start of the aerospace era: – No propulsion (balloons, gliders) – Muscle (mostly failed) – Steam power (mostly failed) – Piston engines and propellers – Rocket engines – Jet engines – Pulse jet engines – Ramjet – Scramjet APRI0004-­1, Aerospace Design Project, Lecture 4 2 Gliding flight • People have been gliding from the-­ mid 18th century. The Albatross II by Jean Marie Le Bris-­ 1849 Otto Lillienthal , 1895 APRI0004-­1, Aerospace Design Project, Lecture 4 3 Human-­powered flight • Early attempts were less than successful but better results were obtained from the 1960s onwards. Gerhardt Cycleplane (1923) MIT Daedalus (1988) APRI0004-­1, Aerospace Design Project, Lecture 4 4 Steam powered aircraft • Mostly dirigibles, unpiloted flying models and early aircraft Clément Ader Avion III (two 30hp steam engines, 1897) Giffard dirigible (1852) APRI0004-­1, Aerospace Design Project, Lecture 4 5 Engine requirements • A good aircraft engine is characterized by: – Enough power to fulfill the mission • Take-­off, climb, cruise etc. – Low weight • High weight increases the necessary lift and therefore the drag. – High efficiency • Low efficiency increases the amount fuel required and therefore the weight and therefore the drag. – High reliability – Ease of maintenance APRI0004-­1, Aerospace Design Project, Lecture 4 6 Piston engines • Wright Flyer: One engine driving two counter-­ rotating propellers (one port one starboard) via chains. – Four in-­line cylinders – Power: 12hp – Weight: 77 kg APRI0004-­1, Aerospace Design Project, Lecture 4 7 Piston engine development • During the first half of the 20th century there was considerable development of piston engines.
    [Show full text]
  • An Online Performance Calculator for Ramjet, Turbojet, Turbofan, and Turboprop Engines
    An Online Performance Calculator for Ramjet, Turbojet, Turbofan, and Turboprop Engines Evan P. Warner∗ Virginia Tech, Blacksburg, VA, 24061, USA This paper documents the theory, equations, and assumptions behind an HTML-based online performance calculator for ramjet, turbojet, turbofan, and turboprop engines. Based on inputs of design parameters, flight con- ditions, and engine parameters, the specific thrust (()), thrust specific fuel consumption ()(), propulsive efficiency ([ ?), thermal efficiency ([Cℎ), and overall efficiency ([0) will be output for the engine of interest. Several sample cases are analyzed to verify the functionality of the calculator. These sample cases are derived from engines associated with Virginia Tech, which include: Pratt & Whitney’s PT6A-20 and JT15D-1, Honeywell’s TFE731-2B, and the Rolls Royce Trent 1000. With the help of this calculator, students will now be able to verify their air-breathing jet engine performance value calculations. This calculator is available here. I. Nomenclature "0 = Ambient Mach Number 2 ?1 = Specific Heat of the Burner W0 = Ambient Specific Heat Ratio 2 ?C = Specific Heat of the Turbine W3 = Diffuser Specific Heat Ratio 2 ? 5 = Specific Heat of the Fan W2 = Compressor Specific Heat Ratio )0 = Ambient Static Temperature W1 = Burner Specific Heat Ratio ?0 = Ambient Static Pressure WC = Turbine Specific Heat Ratio ?4 = Exit Static Pressure W= = Nozzle Specific Heat Ratio '08A = Gas Constant for Air W 5 = Fan Specific Heat Ratio '?A>3 = Gas Constant for the Products of Fuel/Air Mixture W= 5 = Fan Nozzle
    [Show full text]
  • Modelling and Simulation of the Revolutionary Turbine Accelerator
    Announcement “This final year project was an exam. Commentary made during the presentation is not taken into account.” "Deze eindverhandeling was een examen. De tijdens de verdediging geformuleerde opmerkingen werden niet opgenomen". Preface Here I would like to thank everyone who made a contribution to my thesis. Also to all the people I forgot or do not call by name below. First of all I would like to thank my both VKI promoters. Guillermo Paniagua and Victor Fernández Villacé for their guidance, theoretical support and the help finding the exact information I was searching for. Also thanks to my KHBO promoter, Wim Vanparys who also gave me support, in addition to his clear view on the project and future considerations. Second I would like to say thank you to JeanFrançois Herbiet for his EcosimPro help, in which Victor also made his contribution, and for the information about the conical inlet and its implementation. Without the IT help of Olivier Jadot there would be no EcosimPro at the VKI, on my computer and it definitely would not be accessible at home. Also the people of the VKI library deserve a great thank you for delivering the requested papers as soon as possible which were essential to understand the working principle of the RTA. Next, a thank you to my VKI-colleagues, Piet Van den Ecker, Marylène Andre and Maarten De Moor for the great time and discussions about the occurring problems. Most of the time they helped me, without them knowing it, determining and resolving the problems. Of course to all the others as well, to keep up the spirit in the little room were we spent our time.
    [Show full text]
  • Aerospace Propulsion from Insects to Spaceflight
    AEROSPACE PROPULSION FROM INSECTS TO SPACEFLIGHT Ulf Olsson Volvo Aero Corporation Vice president Technology (ret) - 2 - Olsson,Ulf Aerospace Propulsion from Insects to Spaceflight Copyright © 2006 by Volvo Aero Corporation. 1st Edition 2006 published Heat and Power Technology, KTH, Stockholm, Sweden. 2nd Edition April 2012 PREFACE This book is an introduction to the theory and history of aerospace propulsion. It describes how this specific technology has reached its present form and how it may develop in the future. To understand the technical parts, the reader is assumed to know about thermodynamics and aerodynamics at university level but no prior knowledge of aerospace propulsion technologies is required. For those wishing to go directly to the mathematics, a number of calculation schemes are given in the text as Appendices to various Chapters. They make it possible to write computer programs for performance estimates of the various types of engines. A number of exercises are included at the end of the different chapters. Solutions to the examples are provided in a separate Chapter at the end of the book together with the relevant equations being used. This can be used as a short handbook to the most important equations. For the reader specifically interested in the history of propulsion, a separate guide to the main topics and the most famous names is given under Contents below. Historical notes are also underlined in the text to be easily located. Ulf Olsson April 2012 ii iii CONTENTS Preface 0. Introduction Page 1 1. The balloons lighter than air 5 2. Newton and the reaction force 11 3.
    [Show full text]
  • The F119 Engine: a Success Story of Human Systems Integration in Acquisition
    2 8 4 | A Publication of the Defense Acquisition University www.dau.mil THE F119 ENGINE: A SUCCESS STORY OF HUMAN SYSTEMS INTEGRATION IN ACQUISITION 2ndLt Kevin K. Liu, USMC, Ricardo Valerdi, Donna H. Rhodes, Col Larry Kimm, USAF, and Lt Col Alvis Headen, USAF The Department of Defense recently mandated the incorpora- tion of Human Systems Integration (HSI) early in the acquisition cycle to improve system performance and reduce ownership cost. However, little documentation of successful examples of HSI within the context of systems engineering exists, making it difficult for the acquisition community to disseminate and apply best practices. This article presents a case study of a large Air Force project that represents a successful applica- tion of HSI. The authors explore the influence of both the Air Force and the project contractor. Additionally, they identify top-level leadership support for integrating HSI into systems engineering processes as key to HSI success, reinforcing the importance of treating HSI as an integral part of pre-Milestone A activities. Keywords: Human Systems Integration, Systems Engineering, Acquisition Process, Human Factors Engineering, Integrated Product Development image designed by Harambee Dennis » HSI Manpower Personnel Training Environment Safety Occupational Health Habitability Survivability Human Factors Engineering optimize total system performance 2 8 6 | A Publication of the Defense Acquisition University www.dau.mil Human Systems Integration (HSI) is defined as the “interdisciplinary technical and management processes for integrating human considerations within and across all system elements; an essential enabler to systems engineering practice” (Haskins, 2007). The primary objective of HSI is to integrate the human as a critical system element, regardless of whether humans in the system function as individuals, teams, or organizations.
    [Show full text]
  • ITU Beengine for a Next Generation Trainer
    ITU BeEngine for a Next Generation Trainer AIAA 2015 - 2016 Undergraduate Engine Design Competition Team ITU BeEngine Proposal Advisor : Assoc. Prof. Dr. Onur TUNÇER Team ITU BeEngine Olcay SARI Orçun BULAT ABSTRACT The aim of this ITU BeEngine Design Project is to design a conceptual new engine to replace GE J-85-5A engine of T-38 supersonic jet trainer with better fuel consumption, performance and weight properties. New designed BeEngine is capable of providing the required thrust values with an improved fuel consumption values. On the other hand, since the purpose of T-38 is to train pilots for 5th generation fighter aircrafts, better performance properties are included into new engine. With the involvement of latest materials properties, such as TiAl alloys and CMC (Ceramic Matrix Composites), engine weight is decreased significantly for a similar but a little smaller size. Under the mixed flow low bypass turbofan category, new engine pushes the limits of overall pressure ratio of 16 through 8 compressor stages with a slightly higher bypass ratio of 1.2. Counter rotating 2-spool new engine is aimed to provide optimum values for prepared mission profile for trainer aircrafts while providing extended range of ≈1800nmi. With all ultimate technology limits, each spool is supported by a single stage turbine. Additionally, BeEngine is quite flexible on the afterburner operations thanks to its higher bypass ratio. Apart from achieving the required afterburner thrust values, it is also possible to increase maximum thrust limit in order to compete with other ultimate supersonic jet trainers in market. Furthermore, with new designed convergent-divergent nozzle with vectoring for allowing extra maneuverability for training purposes.
    [Show full text]
  • HECTOR Candidate Engines for a Supersonic Business Jet
    Aerospace Engineering Department Middle East Technical University HECTOR Candidate Engines for a Supersonic Business Jet Team Members Berkay Keleş Furkan Göktürk Öztiryaki Melisa Başak Mert Durmaz Ülkü Ünver Advisor Asst.Prof. Sıtkı Uslu 15.05.2020 Signatures ii Abstract The HECTOR is a two-spool, mixed flow, low bypass ratio turbofan engine designed as a candidate for a supersonic business jet. The HECTOR is capable of achieving both subsonic cruise at Mach 0.98, transonic cruise at 1.15 and supersonic cruise at Mach 2.1 up to Mach 3. Since lighter weight, lower take-off noise, reduced emissions at high altitudes and affordable fares are demanded, the HECTOR is designed in such a way that it satisfies general improvements given by Request of Proposal. Besides, for the highest operating performance, reducing the rate of total fuel consumption is considered throughout the design point and off-design engine missions. Table 1 Engine Component Improvement and Technology Inlet System 2 Ramp External Compression Supersonic Inlet Transonic Fan Carbon Fiber Rain-Forced Polymer with Ti-6Al-4V Leading Edges High-Pressure Compressor Ti-45Al-8Nb Compressor Blades Combustion System Hybrid Diffuser Lean Direct Injection (LDI) Combustor Convective Film Cooling via SiC/CMC with Pedestal Liner High-Pressure Turbine T-238 5th Generation Single Crystal Super Alloy Low-Pressure Turbine Ti-45Al-8Nb PST Single Crystal Mixer Force Flow Lobed Mixer with Chevrons Exhaust System Fully Variable Convergent-Divergent Nozzle iii Contents 1 Introduction 1 2 State of Art 2 3 Cycle Analysis 3 3.1 Advanced Engine Cycle Concepts for HECTOR . .3 3.1.1 Variable Bypass Technology .
    [Show full text]