Premium
Analysis of Particle Laden Flow and Heat Transfer in Cascade and Rocket Nozzle
Author(s) -
CHO H. H.,
KIM W. S.,
YU M. S.,
BAE J. C.
Publication year - 2001
Publication title -
annals of the new york academy of sciences
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 1.712
H-Index - 248
eISSN - 1749-6632
pISSN - 0077-8923
DOI - 10.1111/j.1749-6632.2001.tb05855.x
Subject(s) - nozzle , solid fuel rocket , mechanics , particle (ecology) , heat transfer , cascade , rocket engine nozzle , materials science , rocket engine , discharge coefficient , rocket (weapon) , particle size , particle velocity , chemistry , thermodynamics , aerospace engineering , physics , propellant , engineering , geology , oceanography , chromatography
A bstract : This paper presents results for the calculation of particle trajectories in a cascade and a rocket nozzle using a Lagrangian method. When the floating particles collide to the components, the component surface is damaged severely. The surface erosion rate is strongly dependent on a particle size, a particle impact angle and a surface material. For a compressor cascade, the particle impact rate increases proportionally with the flow inlet angle and the erosion rate on the pressure side surface of blade are related to the surface or coating materials. For a solid rocket nozzle, the particle free zone in the nozzle divergent section increases quickly with increasing particle size and the maximum heat transfer density occurs at the starting region of nozzle convergent section. The Al 2 O 3 droplet breaks up around the nozzle throat due to the high velocity difference between the droplet and gas stream, resulting in the big change of particle free zone.