A twodimensional finite difference program for thermal analysis of rocket thrust chambers
 1987
 2.72 MB
 913 Downloads
 English
National Aeronautics and Space Administration, For sale by the National Technical Information Service , [Washington, DC], [Springfield, Va
Space vehicles  Propulsion systems., Rocket eng
Other titles  Two dimensional finite difference program for thermal analysis of rocket thrust chambers. 
Statement  Mohammad H. Naraghi. 
Series  NASA technical memorandum  100191. 
Contributions  United States. National Aeronautics and Space Administration. 
The Physical Object  

Format  Microform 
Pagination  1 v. 
ID Numbers  
Open Library  OL14662323M 
A TWODIMENSIONAL FINITE DIFFERENCE PROGRAM FOR THERMAL ANALYSIS OF ROCKET THRUST CHAMBERS Mohammad H. Naraghi * National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio SUMMARY A twodimensional finite difference computer model for thermal analysis The of rocket thrust chambers has been developed.
A numerical model for the three dimensional thermal analysis of rocket thrust chambers and nozzles has been developed. The input to the model consists of the composition of the fuel/oxidant. Get this from a library. A twodimensional finite difference program for thermal analysis of rocket thrust chambers.
[Mohammad H Naraghi; United States. National Aeronautics and Space Administration.]. A numerical model for the three dimensional thermal analysis of rocket thrust chambers and nozzles has been developed. The input to the model consists of the composition of the fuel/oxidant mixture and flow rates, chamber pressure, coolant entrance temperature and pressure, dimensions of the engine, materials and the number of nodes in File Size: KB.
RTE performs 2D and 3D thermal analysis of regeneratively cooled rocket thrust chambers and nozzles. The program uses GASP (GAS Properties) and CET (Chemical Equilibrium with Transport Properties) for evaluation of the coolant and hot gas properties, respectively.
At each station a twodimensional finite element model is used to determine. Two dimensional analysis (2D) Heat transfer analysis of regeneratively cooled thrust chamber has been carried out using two dimensional finite difference method.
The computational domain consists of half the channel width and half the rib width because of axisymmetry and its repetitive : B.T. Kuzhiveli, S.C. Ghosh, G.K. Kuruvila, V.G.
Gandhi. In this paper we propose an analysis of the heat transfer problem between cooling channels and thrust chamber of a liquid rocket engine. The approach consists in coupling the system analysis tool. the nozzle heat transfer problem using finite difference method. Lee4 has obtained temperature distribution inside a nozzle of a solid rocket motor employing finite difference method.
Henderson) has computed indepth temperature response by solving heat conduction equation with temperaturedependent thermal by: 2. Model documentation is presented for a twodimensional (areal) heattransport model capable of simulating both water and vapor dominated geothermal reservoirs that conform with the assumptions of the model.
Finitedifference techniques are used to solve for the dependent variables pressure and enthalpy. The program is designedCited by: Heat Transfer and Thermal Stress Analysis of Circular Plate Due to Radiation Using FEM Keywords: Heat transfer analysis, Finite element method, Finite difference method, Thermal stresses analysis.
INTRODUCTION To our knowledge no one has developed finite element model for heat transfer and thermal stress analysis due to.
multiple dimensions,32,33 However, even with a multidimensional finite difference tool, there is little computational synergy between the process of heatshield design and a finite difference analysis. Most of the current finite difference tools require the user to simplify the geometry, generate the mesh by hand, and run the analysis.
The two dimensional Finite Element Analysis model of LIM has been designed with the specifications shown in Table 1. The geometry overview of LIM is shown in Fig 1Manna. S et al, ). FE Model of Mosebach (Chemfered) LIM The concept of the virtual primary core that we have introduced in our model basically generates drag force and.
Models and methods used in RPA Thrust chamber thermal analysis Gasside heat transfer – Convective heat transfer Ievlev method Bartz method Boundary layer and film cooling Loss in specific impulse due to friction in boundary layer – – Radiation heat transfer RPA library for thermodynamic analysis is used to obtain hot gas transport.
provides a holistic analysis and design tool for twodimensional structures. With today’s availability of powerful virtual 3D and parametric environments, the following question arises: can a fully threedimensional version of thrustline analysis provide the same freedom to explore the infinite equilibriumFile Size: 2MB.
Finite element analysis results are also compared with existing analytical solutions for cylindrical grains reinforced by metallic casing under thermal, vertical storage and internal pressure loads. Finite element analysis has been performed on several practical complex grain Cited by: Thus it was seen that each coolingheating cycle produced the same temperature response and that thermal analysis of a single cycle accurately represented any cycle during the life of a thrust chamber.
THERMAL ANALYSIS MODELS The 3D thermal analysis mndel Is illustrated in Figure Thrust chamber modelling for the analysis of liquid rocket engine transients Marco Leonardi 1, Francesco Di Matteoy2, Johan Steelantz2, Francesco Nasutix1, and Marcello Onofri{1 1University of Rome “La Sapienza”, eria Meccanica e Aerospaziale, Rome, Italy 2ESAESTEC, Aerothermodynamic & Propulsion Analysis Section, Noordwijk, The Netherlands.
This work is aiming to present an analytical method to study the dynamic behavior of thermoelastic stresses in a finitelength functionally graded (FG) thick hollow cylinder under thermal shock loading.
The thermomechanical properties are assumed to vary continuously through the radial direction as a nonlinear power function. Using Laplace transform and series solution, the thermoelastic Cited by: Twodimensional Analysis of Triple Coupled Physics of Structural Mechanics, Diffusion and Heat Transfer in a Gas Pipe M.
HaghighiYazdi1 and P. LeeSullivan*1 1Department of Mechanical and Mechatronics Engineering, University of Waterloo *Corresponding author: Department of Mechanical and Mechatronics Engineering, University of Waterloo.
(FE) analysis in simulating an actual design case. Then, to present the real model, a twodimensional (2D) axisymmetric model for a nonuniform disc was analysed using FE analysis.
The stresses and deformations developed as a result of the disc operating conditions at high rotational speeds and thermal gradients were evaluated using twoFile Size: 2MB.
Finite Element Analysis of. Transient BallisticDiffusive Heat Transfer. in TwoDimensional Structures. COMSOL Conference, Boston, MA OctoberThermal etching. Thermal deposition • Fourier equation Energy conservation + Fourier’s heat flux approximation.
Three dimensional thermal analysis of rocket thrust chambers.
Description A twodimensional finite difference program for thermal analysis of rocket thrust chambers PDF
NARAGHI and An adaptive remeshing method for finite element thermal analysis. EARL THORNTON and A twodimensional transient liquid metal heat pipe model. TILTON. Conservation equations for compressible and incompressible flows are the prime theme. The text concentrates on finite difference and finite volume methods and mostly treats twodimensional flows, while it also keeps key arguments general enough to apply to the threedimensional case as well.
() Twodimensional timedomain finitedifference modeling for viscoelastic seismic wave propagation. Geophysical Journal International() Numerical BlowUp of Nonlinear Parabolic IntegroDifferential Equations on Unbounded by: A numerical model for twodimensional flow around an airfoil undergoing prescribed heaving motions in a viscous flow is presented.
The model is used to examine the flow characteristics and power coefficients of a symmetric airfoil heaving sinusoidally over Cited by: 2.
Details A twodimensional finite difference program for thermal analysis of rocket thrust chambers FB2
Thrust Network Analysis The ThrustNetwork Analysis method presented in this paper is inspired by O’Dwyer’s work on funicular analysis of vaulted masonry structures [2]. It is extended by adding the concept of duality between geometry and the inplane internal forces of networks [3,4].Cited by: A few other NTP programs followed including the Space Nuclear Thermal Propulsion (SNTP) program in the early 's.
The NTP concept is similar to a liquid chemical propulsion system, except instead of combustion in the thrust chamber, a monopropellant is heated with a fission reactor (heat exchanger) in the thrust chamber and exposes the. Full text of "THRUST CHAMBER COOLING TECHNIQUES FOR SPACECRAFT ENGINES, VOLUME II" See other formats.
Steel, A Iron based alloy, D6AC Steel, Haynes was done. Further, thermal analysis has been carried out with ANSYS for the material which had been selected after structural analysis. Modeling was done by AUTOCAD. The design of rocket Motor Casing is done using ASME section VIII methods for the given input Size: 1MB.
Rocket Propulsion Elements, 7th Ed. George P. Sutton and Oscar Biblarz Contents: 1. Classification 2. Definitions and Fundamentals 3. Nozzle Theory and Thermodynamic Performance relations 4. Flight Performance 5. Chemical Rocket Propellant Analysis 6.
Liquid Propellant Rocket Engine fundamentals 7. Liquid Propellants 8. Thrust Chambers 9. () Finiteelement thermal analysis of flows on moving domains with application to modeling of a hydraulic arresting gear.
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Journal of Thermal Analysis and Calorimetry 7. () An effective approach for topological design to the acoustic–structure interaction systems with infinite acoustic by: TwoDimensional Model for LiquidRocket Transverse Combustion Instability William A.
Sirignano∗ and Pavel P. Popov† University of California, Irvine, California DOI: /1.J Nonlinear, transversemode, liquidpropellantrocketmotor combustion instability is examined with a two.Keywords: High area ratio rocket nozzle, Fluidthermal coupled analysis, Numerical simulation, Gas separation, Ground test 1.
Main text Nozzle design constitutes an important phase of rocket development. The performance of a rocket depends heavily on its nozzle’s effectiveness in converting thermal energy to kinetic energy. To increase theAuthor: Haifeng Hu, Futing Bao, Qiang Cai.











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