Aerospace Propulsion

Universidad Carlos III de Madrid

Course Description

  • Course Name

    Aerospace Propulsion

  • Host University

    Universidad Carlos III de Madrid

  • Location

    Madrid, Spain

  • Area of Study

    Aerospace Engineering

  • Language Level

    Taught In English

  • Prerequisites

    Introduction to Fluid Mechanics
    Fluid Mechanics
    Thermal Engineering
    Introduction to structural analysis
    We strongly advise you not to take this course if you have not passed Fluid Mechanics and Thermal Engineering

  • Course Level Recommendations

    Upper

    ISA offers course level recommendations in an effort to facilitate the determination of course levels by credential evaluators.We advice each institution to have their own credentials evaluator make the final decision regrading course levels.

    Hours & Credits

  • ECTS Credits

    6
  • Recommended U.S. Semester Credits
    3
  • Recommended U.S. Quarter Units
    4
  • Overview

    Aerospace Propulsion
    Course Number: 251 - 15343
    ECTS credits: 6
    YEAR 3/ Upper Division

    PREREQUISITES/STUDENTS ARE EXPECTED TO HAVE COMPLETED:
    Introduction to Fluid Mechanics
    Fluid Mechanics
    Thermal Engineering
    Introduction to structural analysis
    We strongly advise you not to take this course if you have not passed Fluid Mechanics and Thermal Engineering


    COMPETENCES AND SKILLS THAT WILL BE ACQUIRED AND LEARNING RESULTS:

    Applied knowledge of: theory of propulsion; jet engine performance; propulsion system engineering.

    DESCRIPTION OF CONTENTS:

    1    Introduction to aerospace propulsion:
    Thrust generation and jet propulsion
    Effect of external expansion on thrust
    Global performance parameters
    Range of aircraft
    Efficiencies

    2    Aircraft Engine Modeling:  the Turbojet:
    Thrust equation
    Shaft balance for the turbojet
    Fuel consumption
    Design parameters
    Effect of mass flow on thrust
    Note on Ramjets
    Propulsive efficiency
    Thermal and overall efficiencies

    3   Introduction to Component Matching and Off-Design Operation
    Discussion on nozzle choking  
    Component matching
    Effects of Mach number  
    Examples  
    Compressor-turbine matching. Gas generators

    4   Turbofan Engines
    Ideal turbofan model
    Shaft balance
    Velocity matching condition
    Optimal compression ratio

    5   Inlets  and Nozzles
    Inlets or Diffusers
    Subsonic Inlets  
    Supersonic Inlets  
    Exhaust nozzles

    6   Principles of Compressors and Fans
    Euler equation    
    Velocity triangles
    Isentropic efficiency and compressor map . .

    7   Compressor Blading,  design and multi-staging
    Diffusion factor.  Stall and surge
    Compressor blading and radial variations
    Multi-staging and flow area variation
    Mach Number Effects  
    The Polytropic Efficiency  
    Starting and Low-Speed Operation

    8   Turbines. Stage characteristics.  Degree of reaction:
    Euler¿s Equation
    Degree of Reaction
    Radial variations
    Rotating blade temperature

    9   Turbine solidity.  Mass flow limits.  Internal cooling:
    Solidity and aerodynamic loading
    Mass flow per unit of annulus area and blade stress
    Turbine cooling. General trends and systems. Internal cooling.

    10 Film  cooling. Thermal stresses. Impingement:
    Film cooling
    Impingement cooling
    Thermal stresses
    How to design cooled blades

    11 Combustion:  Combustors and Pollutants
    Combustion process
    Combustor chambers
    Combustor sizing
    Afterburners
    Pollutants: regulations
    Mechanisms for pollutant formation
    Upper-Atmospheric Emissions

    12 Introduction to engine noise and aeroacoustics:
    Noise propagation
    Acoustic energy density and power flux
    Noise sources and noise modeling
    Jet Noise
    Turbomachinery noise

    13 Engine rotating  structures
    Blade loads
    Centrifugal stresses and disc design

    14 Fundamentals of rotordynamics:
    Bearings and engine arrangements
    Lumped mass model
    Critical speeds
    Forces on bearings
    Comments on blade vibrations

    LEARNING ACTIVITES AND METHODOLOGY:

    Theory sessions.
    Problem sessions working individually and in groups.
    Computer sessions.
    Lab-sessions.

    ASSESSMENT SYSTEM:

    In order to pass the subject, two requirements need to be met:

    1) To have a MINIMUM mark of 4.0/10 in the end-of-term exam;
    2) To have a MINIMUM  overall mark of 5.0/10 (weighing 60% the end-of-term exam mark and 40% the mark of the continuous evaluation).
        
    BIBLIOGRAPHY:

       J.L. Kerrebrock. Aircraft Engines and Gas Turbines. MIT Press. 1992
        D. R. Greatrix. Powered Flight. The Engineering of Aerospace Propulsion. Springer. 2012
        J. D. Mattingly. Elements of Propulsion: Gas Turbines and Rockets. AIAA. 2006
        N. Cumpsty. Jet Propulsion. Cambridge Univ. Press. 2003

Course Disclaimer

Courses and course hours of instruction are subject to change.

ECTS (European Credit Transfer and Accumulation System) credits are converted to semester credits/quarter units differently among U.S. universities. Students should confirm the conversion scale used at their home university when determining credit transfer.