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Master'sDefense, Military Engineering & Land Systems Applications open

Master’s in Military Turbojet/Turbofan Propulsion Engineering

Online master's programme of 1,900 hours in military turbojet and turbofan propulsion engineering, structured in 12 modules covering cycle analysis, compressors, combustors, turbines, intakes and nozzles, engine structural integrity, FADEC control, testing, certification and sustainment, with an assigned technical tutor.

Duration1900 h
ModeOnline
LanguageEnglish
Start datesSet by the faculty
AwardSEIUM Institute diploma
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Learning outcomes

What you will be able to do

01

Analyse the thermodynamic cycle of turbojets and turbofans.

02

Simulate design-point and off-design performance.

03

Carry out the preliminary design of compressors, combustors and turbines.

04

Evaluate engine structural integrity.

05

Develop FADEC control strategies.

06

Plan engine testing and certification.

07

Assess future technologies and the sustainability of propulsion.

Profile

Who it's for

  • Propulsion engineers working on military or civil gas turbines.
  • Turbomachinery engineers focused on compressor and turbine design.
  • Engine performance engineers running cycle and off-design simulations.
  • Engine structural integrity engineers managing disc and blade life.
  • Engine control engineers working with FADEC systems.
  • Engine test engineers on test beds and certification campaigns.
  • Engineering or science graduates aiming to join aero-engine manufacturers.
Standards & tools

What you'll work with

  • CS-E (EASA certification specifications for engines)
  • JSSG-2007 (Joint Service Specification Guide for aircraft turbine engines)
  • MIL-HDBK-1783B (Engine Structural Integrity Program (ENSIP))
  • EMAR 21 (European military airworthiness requirements)
  • RTCA DO-178C (software considerations in airborne systems certification)
  • ASTM D7566 (aviation turbine fuel containing synthesised hydrocarbons)
  • SAE AS755 (gas turbine engine station nomenclature)
  • GasTurb
  • NPSS
  • Ansys CFX
  • MATLAB/Simulink
  • Ansys Mechanical
Syllabus

12 modules · 1900 h

  1. 1.1Brayton cycle
  2. 1.2Engine components
  3. 1.3Turbojets and turbofans
  4. 1.4Bypass ratio
  5. 1.5Thrust and specific fuel consumption
  6. 1.6Low- and high-bypass engines
  7. 1.7Afterburning: thermodynamic principles
  8. 1.8History of jet propulsion
  9. 1.9Legal and ethical framework of military propulsion
  10. 1.10Case study: cycle analysis of a low-bypass turbofan
  1. 2.1Design-point cycle analysis
  2. 2.2Off-design performance
  3. 2.3Component maps
  4. 2.4Operating lines
  5. 2.5Effects of altitude and speed
  6. 2.6Effects of bleed air and power extraction
  7. 2.7Installation and losses
  8. 2.8Cycle simulation tools
  9. 2.9Validation with test data
  10. 2.10Lab: performance simulation with GasTurb
  1. 3.1Axial compressor aerodynamics
  2. 3.2Velocity triangles
  3. 3.3Blade design
  4. 3.4Losses and efficiency
  5. 3.5Surge and rotating stall
  6. 3.6Stability margins
  7. 3.7Variable stator vanes
  8. 3.8Low pressure-ratio fans
  9. 3.9Turbomachinery CFD
  10. 3.10Practical exercise: preliminary design of a compressor stage
  1. 4.1Combustion chemistry
  2. 4.2Annular combustor design
  3. 4.3Injection and atomisation
  4. 4.4Flame stability
  5. 4.5Pollutant emissions
  6. 4.6Wall cooling
  7. 4.7Alternative fuels
  8. 4.8Combustion testing
  9. 4.9Combustion simulation
  10. 4.10Case study: balance of a combustion chamber
  1. 5.1Turbine aerodynamics
  2. 5.2Blade cooling
  3. 5.3Thermal barrier coatings
  4. 5.4Nickel superalloys
  5. 5.5Single-crystal blades
  6. 5.6Creep and thermal fatigue
  7. 5.7Tip clearance
  8. 5.8High- and low-pressure turbines
  9. 5.9Turbine testing
  10. 5.10Lab: thermal analysis of a cooled blade
  1. 6.1Subsonic intakes
  2. 6.2Supersonic intakes: principles
  3. 6.3Intake-engine compatibility
  4. 6.4Flow distortion
  5. 6.5Convergent and convergent-divergent nozzles
  6. 6.6Variable-geometry nozzles
  7. 6.7Airframe integration
  8. 6.8Jet noise
  9. 6.9Internal flow simulation
  10. 6.10Practical exercise: distortion analysis of an intake
  1. 7.1ENSIP programme
  2. 7.2Discs and their life
  3. 7.3Low- and high-cycle fatigue
  4. 7.4Blade containment
  5. 7.5Rotordynamics
  6. 7.6Bearings and squeeze-film dampers
  7. 7.7Damage tolerance analysis
  8. 7.8Component life management
  9. 7.9Integrity testing
  10. 7.10Case study: fatigue life of a turbine disc
  1. 8.1FADEC systems
  2. 8.2Control laws
  3. 8.3Sensors and actuators
  4. 8.4Limit protection
  5. 8.5Control redundancy
  6. 8.6Control software: DO-178C
  7. 8.7On-board models
  8. 8.8Diagnostics and monitoring
  9. 8.9Control cybersecurity
  10. 8.10Lab: turbofan control model in Simulink
  1. 9.1Engine test beds
  2. 9.2Simulated altitude testing
  3. 9.3Bird and ice ingestion tests
  4. 9.4Endurance testing
  5. 9.5CS-E certification
  6. 9.6Military engine specifications: JSSG-2007
  7. 9.7Military engine airworthiness
  8. 9.8Test instrumentation
  9. 9.9Test bed safety
  10. 9.10Practical exercise: endurance test plan
  1. 10.1Modular maintenance
  2. 10.2Condition monitoring
  3. 10.3Gas path trend analysis
  4. 10.4Borescope inspection
  5. 10.5Parts life management
  6. 10.6Overhaul
  7. 10.7Life-cycle cost
  8. 10.8Obsolescence
  9. 10.9Power-by-the-hour support contracts
  10. 10.10Case study: trend analysis of an engine fleet
  1. 11.1Adaptive cycles: principles
  2. 11.2Variable-cycle engines
  3. 11.3Integrated thermal management
  4. 11.4Sustainable aviation fuels
  5. 11.5Hybrid-electric propulsion
  6. 11.6Additive manufacturing in engines
  7. 11.7Ceramic matrix composites
  8. 11.8Emissions reduction
  9. 11.9Ethical framework and export controls
  10. 11.10Workshop: evaluation of sustainable fuels in a cycle
  1. 12.1Propulsion requirements
  2. 12.2Cycle analysis
  3. 12.3Preliminary component design
  4. 12.4Performance analysis
  5. 12.5Structural integrity
  6. 12.6Control strategy
  7. 12.7Test plan
  8. 12.8Conclusions
  9. 12.9Master's Thesis report
  10. 12.10Master's Thesis: defence before a panel
Methodology, software & labs

How you'll learn

Training is 100% online on the SEIUM campus, with downloadable material, recorded classes and an assigned technical tutor. There are no fixed timetables: you progress at your own pace within each intake, so the programme can be combined with work.

Each module combines theory, guided reading of the original standard and applied exercises. The working software is GasTurb, NPSS, Ansys CFX, MATLAB/Simulink and Ansys Mechanical, in free, academic or evaluation versions. Testing is studied through real procedures for turbofan cycle and performance simulation, preliminary design of turbomachinery components and fatigue life analysis of discs. Assessment is continuous per module plus the final Master's Thesis.

Standards covered: CS-E, JSSG-2007, MIL-HDBK-1783B, EMAR 21, RTCA DO-178C, ASTM D7566, SAE AS755.

Assigned technical tutor:every module ends with a deliverable that your tutor marks individually.
Standards-based learning:guided reading of CS-E, JSSG-2007 and MIL-HDBK-1783B applied to real cases, not as a theoretical annex.
Industry software:GasTurb, NPSS, Ansys CFX, MATLAB/Simulink and Ansys Mechanical, in free, academic or evaluation versions.
Master's Thesis with defence:A military turbofan propulsion project covering cycle analysis, component design, structural integrity, control strategy and test plan, defended before a panel.
Flexible format:100% online, no fixed timetables, compatible with full-time work.
Capstone project

Build it end to end

Your final project follows the real engineering workflow, step by step, reviewed by your tutor.

Cycle performance simulation
Simulate the performance of a turbofan with GasTurb.
Compressor stage design
Carry out the preliminary design of a compressor stage.
Disc fatigue life
Estimate the fatigue life of a turbine disc under ENSIP criteria.
FADEC control model
Build a turbofan control model in Simulink.
Master's Thesis
A complete propulsion project from requirements to control strategy and test plan, defended before a panel.
Career opportunities

Where this takes you

Propulsion engineerTurbomachinery engineerEngine performance engineerEngine structural integrity engineerEngine control engineerEngine test engineer
Admissions & scholarships

Requirements

  • A university degree in engineering, science or architecture, or equivalent demonstrable professional experience.
  • An internet connection and a computer capable of running the programme software.
  • English sufficient to read technical standards.

Ready to start?

Send your application today. Our admissions team replies within 72 hours with your study plan and funding options.

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FAQ

Frequently asked questions

The programme totals 1,900 hours over 12–14 months. You set your own pace within each intake, and your tutor helps you plan the workload around your job.

You work with GasTurb, NPSS, Ansys CFX, MATLAB/Simulink and Ansys Mechanical, using free, academic or evaluation versions. Your tutor indicates the free alternative wherever one exists.

A SEIUM Institute diploma, awarded on passing the continuous assessment and the Master's Thesis. It is SEIUM's own qualification, not an official state degree; its recognition depends on the programme completed and the regulations of each country.

Yes. Modules passed in a course or postgraduate diploma in the same area are recognised in the higher programme. Ask about the recognition policy when you enrol.

A degree in engineering, science or architecture (or equivalent professional experience), a computer able to run the programme software and English sufficient to read technical standards.

Start dates are set by SEIUM's faculty for each intake. Our admissions team will confirm the next available date when you apply.

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