Thermal Analysis on Regenerative Cooled Liquid Propellant Rocket Thrust Chamber Using ANSYS
Open Access
- 1 February 2021
- journal article
- research article
- Published by IOP Publishing in IOP Conference Series: Materials Science and Engineering
- Vol. 1059 (1), 012068
- https://doi.org/10.1088/1757-899x/1059/1/012068
Abstract
In this research work, thermal analysis has done on a rocket engine's thrust chamber with four different shapes like, circular, rectangular with greater breath (b>d), rectangular with greater depth (d>b) and rectangular with greater depth with edges filleted coolant channel models to establish perfect suitable shape for the coolant channels in order to maintain the entire thrust chamber within the melting point of its materials. Finite Element Method (FEM) has adopted to establish the thermal behaviour of the coolant channel's materials such as Nickel, Copper and Zirconium under the specific boundary conditions. Temperature distribution with respect to the nodal distances at thrust chamber's inlet, throat and outlet portions with four different shapes of coolant channel models under Nickel, Copper and Zirconium materials were attained and compared with each other. Finite element results reveals that the successful configuration for generatively cooled rocket thrust chamber must have the coolant passage shape of rectangular cross section with greater depth (b>d).Keywords
This publication has 11 references indexed in Scilit:
- Cyclic Stress Analysis of a Rocket Engine Thrust Chamber Using Chaboche, Voce and Creep Constitutive ModelsTransactions of the Indian Institute of Metals, 2016
- A Quasi-2-D Model for the Prediction of the Wall Temperature of Rocket Engine Cooling ChannelsNumerical Heat Transfer, Part A: Applications, 2011
- A CFD-RTE Model for Thermal Analysis of Regeneratively Cooled Rocket EnginesPublished by American Institute of Aeronautics and Astronautics (AIAA) ,2008
- A Simple Approach for Thermal Analysis of Regenerative Cooling of Rocket EnginesPublished by ASME International ,2008
- Numerical simulation and optimization on heat transfer and fluid flow in cooling channel of liquid rocket engine thrust chamberEngineering Computations, 2006
- Supercritical Flows in High Aspect Ratio Cooling ChannelsPublished by American Institute of Aeronautics and Astronautics (AIAA) ,2005
- High Temperature Thermal Analysis on Nozzle of Thrust ChamberPublished by American Institute of Aeronautics and Astronautics (AIAA) ,2002
- Cryogenic rocket calorimeter chamber experiments and heat transfer simulationsPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1998
- Experiments on heat transfer in a cryogenic engine thrust chamberJournal of Propulsion and Power, 1993
- Nonlinear structural analysis of cylindrical thrust chambers using viscoplastic modelsJournal of Propulsion and Power, 1992