ID#: 82
Abstract Title: Probe Method of Sampling of Combustion Products of Solid Rocket Propellant at Temperatures and Pressures Typical of Combustion Chamber of Rocket Motor
Session Title: Poster Session II
Session Date: 8/2/01
Session Start Time: 2:50 PM
Contributing Author: Korobeinichev, O.P.
Organization: Institute of Chemical Kinetics and Combustion,
Country: Russia
Authors: O.P. Korobeinichev, A.G. Tereshenko, P.A. Skovorodko, A.A. Paletsky, E.N.Volkov
Short Abstract: New probing technique for determination the composition of combustion products of composite solid rocket propellant (CSRP) at temperatures 2500-3200К and pressures 4-8 MPa typical of rocket motor is described. A two-stage probe device, which enables to freeze the sample passing main shocks inside the probe, has been designed. The first stage probe with inner opening angle of the cone 90 and pressure inside the probe ~20 torr extracts the samples from the flame, and the second stage ñ from underexpanded free jet formed inside the first stage. For estimation the probe sampling accuracy the gas flow simulation based on numerical solution of Navier-Stokes equations has been performed. By chemical kinetics equations solution it is shown that in the sampling process the concentration of the majority of stable species distorts in the range of 2 - 3%, and for Н2 and О2 ~ 12%. The simulation of sample flow through the second stage of the probe have shown, that growth of temperature and pressure due to mixing of high-enthalpy hypersonic flow with surrounding gas does not initiate the chemical reactions, which could distort the sample composition. The method allows performing additional operations after sampling, particularly, separation of CO and N2 in the sample composition with further analysis by time-of-flight mass-spectrometer. СО and СО2 concentrations in combustion products of model CSRP ñ ammonium dinitramide with polycaprolacton at pressure 4 MPa has been determined. The method can be applied for diagnostics of combustion processes in rocket motor, as well as in aircraft engine chamber and internal combustion engine.