Thermodynamic analysis of cryogenic rocket engines with Matlab tools
Tutor / director / evaluatorSoria Guerrero, Manel
Document typeMaster thesis
Rights accessRestricted access - author's decision
The present Master Thesis discusses the efforts of the author to perform thethermodynamic analysis of two modern cryogenic rocket engines. The first one, withthe name SE21D, will be used as validation case to test the accuracy of the methodologydeveloped. Once it has been approved this simulation, the next step will consist in applythis scheme to the study case, called LE9.The special characteristic that distinguish these two models is the employment offeeding system type: Expander Bleed Cycle. They will be studied all the mechanicalcomponents that are involved in this feeding system, which includes pumps, turbines,mixer and valves. Secondary, the combustion process as well as the engine performanceare assessed. Finally, the heat exchange and regenerative cooling that occurs in theCombustion Chamber walls is modeled. The final results are accurate enough once thevalidity of this thermodynamic analysis model has been approved and this Master Thesisalso leaves room to future researchers to continue with this project.This simulation have been performed by means of an intensive bibliographic researchand the employment of MATLAB software and two additional packages, created in-housePolytechnic University of Catalonia and already validated, called HGS and INIST. Thislast one collects the fluid properties for the most common substances used as rocketpropellants and it was used to define the state of the fuel and oxidizer at each stage of thefeeding system. The latter, however, it is a chemical solver based on NASA’s polynomialsand it was utilized mainly in the combustion process that takes places in the CombustionChamber of both rocket engines.Nevertheless, the features of these two additional software packages were not enoughto accomplish the goal of this Master Thesis. For that reason, the author performedmaintenance and updating tasks of INIST package. The capacity of adding new data wasrestored as well as the inclusion of new fluid properties that complements the existing one,such as the transport properties (viscosity and thermal conductivity). Indeed, for thoseconditions that are out of the range of this tool, it was developed an approach based onsemi-empirical models to the obtaining of these magnitudes.
Understand the different methods in use to feed both fuel and oxidiser into a rocket engine combustion chamber, as well as too refrigerate the nozzle. Understand the properties of the cryogenic fluids involved. Implement a model of an engine
|TFM JUAN MANUEL GARCIA.pdf||2,653Mb||Restricted access|
All rights reserved. This work is protected by the corresponding intellectual and industrial property rights. Without prejudice to any existing legal exemptions, reproduction, distribution, public communication or transformation of this work are prohibited without permission of the copyright holder