Three dimensional thermal analysis of rocket thrust chambers
Conference
·
OSTI ID:5828969
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 different parts of the engine. The model allows for temperature variation in three dimensions: axial, radial and circumferential directions and by implementing an iterative scheme, it provides nodal temperature distribution, rates of heat transfer, hot gas and coolant thermal and transport properties.
- Research Organization:
- National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
- OSTI ID:
- 5828969
- Report Number(s):
- N-89-21025; NASA-TM-101973; E-4673; NAS-1.15:101973; CONF-880676-
- Resource Relation:
- Conference: Conference on thermophysics, plasma dynamics and lasers, San Antonio, TX, USA, 27-29 Jun 1988
- Country of Publication:
- United States
- Language:
- English
Similar Records
Two-dimensional finite difference program for thermal analysis of rocket thrust chambers
Engine-cycle analysis for a particle-bed reactor nuclear rocket. Final report, May-Jul 90
Study of the Effects of Materials Selection for the Closeout Structure on the Service Life of a Liquid Rocket Engine Thrust Chamber
Technical Report
·
Tue Sep 01 00:00:00 EDT 1987
·
OSTI ID:5828969
Engine-cycle analysis for a particle-bed reactor nuclear rocket. Final report, May-Jul 90
Technical Report
·
Fri Mar 01 00:00:00 EST 1991
·
OSTI ID:5828969
Study of the Effects of Materials Selection for the Closeout Structure on the Service Life of a Liquid Rocket Engine Thrust Chamber
Journal Article
·
Sat Jun 15 00:00:00 EDT 2019
· Journal of Materials Engineering and Performance
·
OSTI ID:5828969