A methodological approach to calculation of combustion chamber thrust for a detonating engine as applies to conceptual design problems

Аuthors

Frolov V. N.^*, Garanin I. V.^**

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: 28474@mail.ru
**e-mail: garanin-nio203@yandex.ru

Abstract

An engineering technique is suggested to calculate a combustion chamber thrust values for pulse-jet detonating engines. This technique allows us to reduce significantly computation costs and time needed to solve the problem. The one-dimensional classical theory is used to compute a propagation of detonation wave in the chamber. A finite-element model based on the Euler equations is used also to compute non-steady flow of combustion products as well as to calculate filling of the chamber with a fuel mixture. A demonstration example is presented for the technique.

Keywords:

etonating engine, detonation, combustion chamber, thrust