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Títol: Thermo-Structural Analysis of Rocket Engine Thrust Chamber

Estudiants que han llegit aquest projecte:
MADHU SURYAVANSHI, CHETHAN (data lectura: 20-12-2018)
Cerca aquest projecte a Bibliotècnica

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:

MU AEROSPACE S&T 15

Tipus: Individual

Lloc de realització: ERASMUS

Supervisor/a extern: Luca dAgostino
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.