A commonly cited advantage of pulse combustors is a high rate of heat transfer in the tail pipe. Past research on these rates of heat transfer is inconclusive regarding the amount of heat transfer enhancement and how various flow parameters affect this enhancement. This article reports an experimental heat transfer study in the tail pipe of a pulse combustor. The pulsation frequency, pulsation ...

The response of a valved pulse combustor to changes in the relative timing between the resonant pressure wave and the instantaneous energy release rate has been examined. Experiments were designed to examine the pulse combustor's response to independent changes in the experimental conditions that resulted in nearly independent changes in the fluid dynamic species mixing time, the fluid dynamic ...

Original scientific paper Numerical simulations of four combustion processes in a dual-fuel combustor of chemically recuperated gas turbine (CRGT) were carried out in this work. The fuels in the four combustion processes were liquid fuel, liquid fuel + steam, liquid fuel + reformed gas and reformed gas, respectively. The mathematical models adopted for different fuels combustion consist of real...

Coupling model for two-dimensional mixed-compression supersonic inlet with Mach number of 2.5 at design point and pulse detonation combustor was established, three working schemes were designed to investigate multi cycle process by using unsteady numerical simulation chemical reaction. The results show that the following two measurements can both restrain back-propagating compression wave broad...

A technology program was started in 1994 within the framework of the German Aeronautics Research Program to develop axial staged combustor technology up to a core engine demonstrator. The objective was to demonstrate a 50% NOx reduction against the ICAO CAEP II limit without any compromise on the CO, UHC and smoke emission level compared to the latest single annular combustor technology. All ot...

Flame stability inside a cylindrical micro-combustor was studied. Considering occurrence of heat recirculation, the respective relations were written and with parameters such as motion speed of reactants, flame propagation speed and thermal conductivity of the combustor’s wall, flame stability and its location inside micro-combustor were studied. It was found that for each thermal conductivity ...

The influence of the in-stream pylon and strut on the performance of scramjet combustor was experimentally and numerically investigated. The experiments were conducted with a direct-connect supersonic model combustor equipped with multiple cavities. The entrance parameter of combustor corresponds to scramjet flight Mach number 4.0 with a total temperature of 947 K. The research results show tha...