CBL - Campus del Baix Llobregat

Projecte llegit

Títol: Thermo-Structural Analysis of Rocket Engine Thrust Chamber


Estudiants que han llegit aquest projecte:


Director/a: ROJAS GREGORIO, JOSEP IGNASI

Departament: FIS

Títol: Thermo-Structural Analysis of Rocket Engine Thrust Chamber

Data inici oferta: 23-02-2018     Data finalització oferta: 23-02-2018



Estudis d'assignació del projecte:
    Tipus: Individual
     
    Lloc de realització: ERASMUS
     
            Supervisor/a extern: Luca d’Agostino
            Institució/Empresa: Università di Pisa, Pisa, Italy
            Titulació del Director/a: PhD, MEng, Bsc Mech Eng
     
    Paraules clau:
    Rocket Propulsion, Liquid Propellant Rocket Engines, Structural Analysis, Thermal Analysis, R-4D.
     
    Descripció del contingut i pla d'activitats:
    Thermal and mechanical loads represent the most stringent
    operational limitations of liquid propellant rocket engine
    combustion devices (chamber, injectors, expansion nozzle).
    The present thesis will therefore investigate the thermo-
    structural feasibility of these devices under the expected
    operational conditions.

    The procedure and methodology will be as follows:

    1. identification and selection of suitable materials and
    manufacturing processes;
    2. development of reduced-order models for preliminary
    steady/unsteady thermo-structural verification;
    3. development of simulation models for more accurate
    steady/unsteady thermo-structural verification using
    commercial softwares (e.g. Solid Works, Ansys Mechanical APDL
    or Workbench);
    4. the identification of the most critical operational
    conditions and their impact on the design of chemical rocket
    engine combustion devices;
    5. processing of test and simulation results;
    6. draw conclusions from the study; and
    7. write thesis and prepare final presentation
     
    Overview (resum en anglès):
    The rocket engine market today presents several new trends that will substantially change the current technological scenario. Apart from the imminent applications to the mega constellations and the advancement of electric propulsion, some aspects such as environmental protection require a conceptual redefinition of rocket propulsion systems with chemical propellants. One of the best technological options to contribute to the protection of the environment and personnel is to use "green" propellants to replace current toxic and / or ecologically harmful propellants.

    Thermal and mechanical loads represent the most stringent operating limits for liquid propellant rocket combustion devices (chamber, injectors, expansion nozzle). This report describes the two-dimensional model developed for the evaluation of the temperature distribution across the wall of the thrust chamber and the extension of a typical rocket motor.

    In the model the thrust chamber and the nozzle extension are divided into several stations using ANSYS APDL 16.0 and are subjected to a steady state and a transient analysis to study the characteristics of heat transfer and to understand the thermal response and structural of the model.

    The results obtained help to study the thermo-structural feasibility and to identify the most critical operating conditions and their impact on the design of the combustion devices of rocket engines with chemical propellants.

    The analysis developed in this paper includes the selection of the most suitable materials and the subsequent modeling of the rocket thrust chamber and the nozzle extension using the ANSYS APDL 16.0 software and the SolidWorks software. Loads and constraints on the structure are applied after the combination of the thermal and structural models.


    © CBLTIC Campus del Baix Llobregat - UPC