Heat transfer in the cavity of a gas turbine liquid rocket engine

The subject of the study is the theoretical research of the process in consideration with heat emission in the cavity rotation between the rotor and the stator of a gas turbine. For the result of the dependency which allows to make a calculation of the local heat emission coefficient in the wall of a rotation disk (rotor) and the fixed wall of the framework (stator), the method of the integral ratios is used. As a result of the performed work, the dependency has been brought out. Realization of the dependency into the software will make the calculation of the heat currents in the axial elements of the construction of a gas turbine. The comparative analysis with the theories of different authors along with the calculation of the local heat emission coefficient into the wall of the rotation disk has given the satisfactory convergence. The comparative analysis of the dependency showed higher coefficient of the heat emission from a rotating flow in the cavern into the wall of the stator than the rotor did.