Please use this identifier to cite or link to this item:
|Title:||Experimental investigation on the supersonic jet impingement|
|Authors:||Ghanegaonkar, P M|
|IPC Code:||Int.Cl.7 F15D 1/08|
|Abstract:||In order to understand the effects of supersonic jet impingement, static tests are conducted in a small-scale rocket motor loaded with a typical nitramine propellant to produce a nozzle exit Mach number of 3. This jet is made to impinge on a plate aligned vertically to the nozzle axis. The distance between the nozzle exit and the plate is varied from 2 to 6 times the nozzle exit diameter. The pressure rise due to jet impingement on the plate has been measured using pressure transducers located at ten different radial locations. The pressure - time data are analyzed to get an insight into the flow field upstream of the plate. The maximum pressure exerted on the plate is about 20-30% of the maximum pressure generated in the combustion chamber. Ten static tests are carried out to obtain the effects of nozzle divergence angle, axial distance between the nozzle exit and the plate and the chamber stagnation pressure on the flow field.|
|ISSN:||0975-1017 (Online); 0971-4588 (Print)|
|Appears in Collections:||IJEMS Vol.11(2) [April 2004]|
Items in NOPR are protected by copyright, with all rights reserved, unless otherwise indicated.