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Design of Shear-Coaxial Rocket Engine Injectors for Combustion of Liquid Oxygen with Methane and Propane

Institut
Lehrstuhl für Raumfahrtantriebe
Typ
Bachelorarbeit / Semesterarbeit / Masterarbeit /
Inhalt
theoretisch / konstruktiv /  
Beschreibung

Master/Bachelor/Semester’s Thesis

Topic: Design of Shear-Coaxial Rocket Engine Injectors for Combustion of Liquid Oxygen with Methane and Propane

Mechanical Engineering, Aerospace Engineering or MSE Student (Bachelor – Master Level)

Description

At the Chair of Space Propulsion and Mobility injection systems are investigated which shall address the needs of future flexible and robust rocket engines. Due to its combustion-defining character and the coupling thereof to the feed system, the injection system is central for these rocket engines: It must ensure fast mixing, sustained and stable combustion, while also limiting thermal loads. In addition, complexity reductions and ease of manufacturing are sought to reduce costs. Future rocket engine injectors must comply with all these requirements.

In the scope of this thesis, a shear-coaxial injector is designed for the injection of liquid oxygen (LOX) and gaseous and liquid methane or propane (GCH4/LCH4, GC3H8/LC3H8). This requires a design procedure that considers the physical processes of injection and combustion for different operating regimes. In order to apply the procedure to different engine thrust classes, the design must be scalable. Hence, the design procedure shall be implemented into a Python design toolbox. Based on this, a detailed CAD-design of the single-element injector is created which is then manufactured for experimental investigation. This single-element design is extended to a complete injector head design for a 500N-thrust-class research engine.[1][2]

 

[1] Lux, Johannes & Haidn, Oskar. (2009). Flame Stabilization in High-Pressure Liquid Oxygen/Methane Rocket Engine Combustion. Journal of Propulsion and Power. Vol. 25. 10.2514/1.36852.

[2] Singla, Ghislain & Scouflaire, Philippe & Rolon, C. & Candel, Sebastien. (2005). Transcritical oxygen/transcritical or supercritical methane combustion. Proceedings of the Combustion Institute. 30. 2921-2928. 10.1016/j.proci.2004.08.063.

 

Your Tasks
  • Review and assess the existing test chamber
  • Develop a test chamber concept that meets the required operating conditions
  • Generate a CAD-design of the test chamber including
    • Mechanical design and interfaces
    • Electrical interfaces
    • Test chamber conditioning system
    • Selection of suitable hardware components
    • Setup the test chamber

 

Your Profile
  • Mechanical Engineering, Aerospace Engineering or MSE Student
  • Independent working attitude
  • Team player
  • Ability to trade-off different technical solutions with respect to requirements
  • Interest in mechanical design work

 

We offer
  • An amazing team to work with
  • A large network of people
  • Challenging exchanges with peers
  • The possibility of getting involved into something big

 

Möglicher Beginn
01.03.2023
Kontakt
Alexander Polidar, M.Sc.
Raum: Lise-Meitner-Str. 8, 85521 Ottobrun, Raum 133
Tel.: +49 89 289 55593
alexander.polidartum.de
Ausschreibung