Flame stabilizing device for TBCC subsonic combustion ramjet engine combustion chamber

Abstract

The invention provides a flame stabilizing device for a TBCC subsonic combustion ramjet engine combustion chamber. The flame stabilizing device for the TBCC subsonic combustion ramjet engine combustion chamber comprises a supporting plate, a cover hood and an on-duty fuel injector bar. The supporting plate and the cover hood are connected together to form a cavity, the on-duty fuel injector bar is arranged in the cavity, the supporting plate has an upper surface and a lower surface, the lower surface has a concave cavity while the upper surface has a convex cavity, the supporting plate has a front cavity and a back cavity, the front cavity is located between the cavity and the back cavity, the front cavity is used for introducing cooling gas, a primary oil way fuel injector bar is arranged in the back cavity, a cooling gas round channel communicating the front cavity with the back cavity is formed between the front cavity and the back cavity, and a cooling gas round channel communicating the front cavity with the cavity is formed between the front cavity and the cavity. By reasonably arranging the fuel supply positions of the on-duty fuel injector bar and the primary oil way and improving the atomizing effect by way of various modes such as pressure atomization, pneumatic atomization and colliding atomization, the ignition property of the TBCC subsonic combustion ramjet engine combustion chamber is improved, the combustion property in a wide range is considered, and the integral property of the TBCC subsonic combustion ramjet engine combustion chamber is improved.

Description

technical field [0001] The present invention relates to flame stabilization devices for engine combustion chambers. In particular, the present invention relates in particular to a flame stabilization device for a TBCC (Turbine-based combined cycle) sub-combustion ramjet combustor. Background technique [0002] The working starting point of the TBCC sub-combustion ramjet engine is set at Mach number 2.5, and the total temperature of the corresponding combustion chamber is about 486K, the pressure is close to the standard atmospheric pressure, but the air flow Mach number can reach 0.28, which has a great impact on the reliable ignition and flame stability of the combustion chamber. great challenge. At the same time, the TBCC sub-combustion ramjet engine also needs to achieve stable and efficient combustion in a wide range of Mach numbers ranging from 2.5 to 4, which is another problem faced by the combustion chamber. [0003] The traditional blunt-body flame stabilizer with...

AI Technical Summary

Problems solved by technology

But for the combustion chamber of TBCC sub-combustion ramjet engine, the inflow temperature at the starting point of work is only about 486K, the atomization and evaporation of fuel oil are greatly affected, and the process of atomization and evaporation of fuel oil must be strengthened in various ways to ensure ignition probability of success

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