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EGR 4347 - Analysis and Design of Propulsion Systems

Dr. Ken Van Treuren Department of Engineering Baylor University. EGR 4347 - Analysis and Design of Propulsion Systems. Date: 17 December 1903 Location: Kitty Hawk, North Carolina. BEGINNINGS. Faster -- Higher -- Farther.

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EGR 4347 - Analysis and Design of Propulsion Systems

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  1. Dr. Ken Van Treuren Department of Engineering Baylor University EGR 4347 - Analysis and Design of Propulsion Systems

  2. Date: 17 December 1903 Location: Kitty Hawk, North Carolina BEGINNINGS

  3. Faster -- Higher -- Farther

  4. “In its present state, and even considering the improvements possible in adopting the higher temperatures proposed for the immediate future, the gas turbine could hardly be considered a feasible application of airplanes, mainly because of the difficulty in complying with the stringent weight requirements imposed by aeronautics.” National Academy of Sciences - Late 1930’s Prevailing Thoughts

  5. Sir Frank Whittle (1941) W.1 Gloster E28/29 Experimental Aircraft

  6. Hans von Ohain (1937) HeS 3B He 178

  7. 1940’s Jumo 004 World’s 1st mass produced turbojet http://www.soton.ac.uk/~aeroastr/4projects/Genesis/Level2/Engines/Jumo4.htm ME 262 http://www.iag.net/~emccann/models/me262rec.htm

  8. 1950’s J-79 http://www.seattleu.edu/~jmatt/pictures/J79.gif F-4E http://www.wpafb.af.mil/museum/research/fighter/f4e-18.jpg

  9. 1960’s TF-39 http://www.seattleu.edu/~jmatt/pictures/TF39.gif C5A http://www.primenet.com/~gbe/Midway/C5A_Galaxy.htm

  10. 1970’s F100 F-15 http://www.wpafb.af.mil/museum/modern_flight/mf21b.htm

  11. 1980’s-1990’s F-119 F-22

  12. 1990’s - 2000’s YF-120, with axisymmetric vectoring nozzle http://www.aeroworldnet.com/fth15.htm JSF

  13. 2002+ Uninhabited Combat Air Vehicle (UCAV) X-43, Hypersonic Research Vehicle http://popularmechanics.com/popmech/sci/tech/9709TUMIAM.html Predator, Medium Altitude Endurance UAV Dark Star, LO High Endurance UAV Global Hawk, High-Alt Long Endurance Aerial Recon UAV http://www.fas.org/irp/agency/daro/uav95/gifs/predcomp.gif http://www.fas.org/irp/program/collect/darkstar.htm http://defenselink.dtic.mil/photos/Feb1997/970220-D-0000G-001.html

  14. 2002+ Space Launch Initiative (SLI) Airbus A-380 Aviation Week & Space Technology, April 1, 2002, p28 Aerospace Engineering, March 2001, p7 Boeing Sonic Cruiser Aviation Week & Space Technology, April 15, 2002, p69 B-X Supersonic “Quiet” Bomber M400 Skycar Mechanical Engineering, May 2001, p96 Aviation Week & Space Technology, May 6, 2002, p28

  15. Basic Turbine Engine Components Compressor Turbine Nozzle Combustor

  16. Turbojet • Advantages • Few Moving Parts • Large Operating Envelope • Static Thrust • Small Frontal Area • Disadvantages • Large Number of Parts • Expensive • Low Thrust at Low Mach • High noise • High TSFC • Application - broad range • Small Mass to High Velocity J-79

  17. Turbojet - Applications SR-71 Harpoon (TJ+solid fuel booster) F-4 Concorde

  18. Low Bypass Ratio Turbofan • Advantages • Few Moving Parts • Large Operating Envelope • More Static Thrust • Better Subsonic TSFC • FOD protection of HPC • Large Afterburner Possible • Low Noise • Disadvantages • Large Number of Parts • Expensive • Medium Frontal Area • Engine Response • Air Start • Application - medium mass to medium velocity F100

  19. Low Bypass Ratio Turbofan - Applications YF-22 Tomahawk Cruise Missile UCAV JSF

  20. High Bypass Ratio Turbofan GE-90

  21. High Bypass Ratio Turbofan - Applications A-10 KC-10 C-5A 777

  22. Turboprop/Turboshaft T-800 • Advantages • Few Moving Parts • Large Operating Envelope • Best Static Thrust • Best Low Subsonic TSFC • Constant RPM Possible • Low Noise • Propeller Reverse • Disadvantages • Large Number of Parts • Expensive • Complex Gearbox • Large Frontal Area • Propeller Governor • Application - Low Mach (Large mass to low velocity) T-56

  23. Turboprop/Turboshaft - Applications Saab 2000 C-130 V-22 RAH-66 Comanche

  24. Ramjet/SCRAMjet • Advantages • No moving parts • Simple • Inexpensive • Small frontal area • Disadvantages • No accessory drive • Optimized for design condition • No static thrust • Application High Mach • Bomarc missle • Future missles Liquid Propellant Ramjet Solid Fuel Ramrocket at Launch - Rocket Mode SCRAMjet (StrutJet)

  25. Ramjet/SCRAMjet - Applications Fasthawk Hyper -X Bomarc D-21 Drone Hypersoar

  26. Principles of Jet Propulsion - Engine Performance • Installed Performance • Thrust, T • Thrust Specific Fuel Consumption, • Uninstalled Performance • Thrust, F • Thrust Specific Fuel Consumption, • Installation losses • Inlet Drag, Dinlet • Nozzle Drag, Dnozzle • Relationships • T = F - Dinlet - Dnozzle = F(1-finlet - fnozzle) • TSFC = S/ (1-finlet - fnozzle)

  27. Opposite force causes the balloon to move Forces removed by opening the stem Principles of Jet Propulsion - THRUST Direction of Movement Escaping Air

  28. ma 1 dM 1 d(mV) F = gc gc dt gc dt m Fn = (Vj - Va) + Aj (Pj - Patm) gc Principles of Jet Propulsion - THRUST S F = = Note: Momentum = M = mV Force = mass x acceleration Net thrust = change in momentum + pressure force at exit Thrust is therefore produced when air exits the engine faster than when it entered.

  29. Principles of Jet Propulsion - THRUST • From a thermodynamic perspective, the engine’s job is to convert chemical • energy of the fuel into kinetic energy of the air passing through the engine. • The following engine components enable this energy conversion and determine • the efficiency at which this conversion takes place: • INLET - Converts kinetic energy of entering air into a pressure rise by decelerating the flow • COMPRESSOR - Increases air pressure to increase combustion cycle efficiency • COMBUSTOR - Add chemical energy to the air to provide power to the turbine and to produce desired thrust • TURBINE - Extracts energy from the hot gases to drive the compressor and aircraft accessories • EXHAUST DUCT AND NOZZLE - Collects, straightens, and accelerates the air

  30. High- pressure compr H P T L P T Low-pressure compressor Inlet Combustor Nozzle 0 1 2.5 3 4 4.5 5 8 Basic Turbine Engine Components - Schematic & Numbering Gas generator HPT = High-pressure turbine LPT = Low-pressure turbine

  31. 350 300 250 200 150 100 50 0 Static Temperature and PressureVariations Through Engine Static Pressure (psia) Static Temperature (R)

  32. F  (Ve - Vi) gc m Engine Types Turbojet - large velocity change Low Bypass Ratio Turbofan - large velocity change & increased mass flow High Bypass Ratio Turbofan - very large mass flow & small velocity increases Turboprop - energy extracted by a low pressure turbine drives a gear box which runs a prop. Large mass flow, very small velocity change through prop Turboshaft (similar to turboprop) - runs a rotor or power producing shaft Ramjet - M>1 applications, large mass flow & small velocity increase SCRAMjet - M>5 applications, very large mass flow & small velocity increase

  33. Engine Performance Characteristics

  34. Engine Performance Characteristics

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