Estimation of heat loss in a closed vessel

Power cartridges are designed and developed for use in military aircraft in association with High Energy Materials Research Laboratory, Pune. During development, the cartridge is fired in a closed vessel to generate basic design parameters. When the cartridge is fired, the heat is lost to the walls of the vessel due to conduction, convection, radiation, and to some extent, by expansion of the vessel. An attempt has been made to estimate the heat loss from the vessel and the surrounding. The aim of this study was to lay down the technical results theoretically and their validation through experiments.

A

Surface area of the vessel

Co-volume of gas

Charge weight of propellant

Specific heat at constant volume

Specific heat at constant pressure

Mean molar heat capacities of gaseous products

Internal dia of vessel

Force constant of propellant

Overall heat transfer coefficient

Heat loss by propellant

Thermal conductivity

Length of closed vessel

Molecular weight

Mass of gaseous products

Number of moles of gas per unit mass

Maximum pressure obtained from P-t curve, when propellant is burned inside the closed vessel

Absolute pressure of gas

Amount of heat generated by propellant

Gas constant for products of combustion

Temperature of propellant gas

Ambient temperature

Adiabatic flame temperature of propellant

Time when propellant burns

Temperature difference

Volume of gas

Specific volume of gas

Constant, 3.147

Ratio of specific heat for propellant gases