Combustion chamber with automatic adjustment of the intake air

Abstract

The invention provides a combustion chamber capable of automatically adjusting the mixed intake air, which is connected to the final stage guide vane of the compressor. The combustion chamber capable of automatically adjusting the mixed intake air includes: a flame tube and a diffuser, and the diffuser is arranged at Downstream of the final stage guide vane of the compressor; the mixed air intake assembly, the inlet end is communicated with the final stage guide vane of the compressor, the outlet end of the mixed air intake assembly is communicated with the flame tube, and the mixed air intake assembly can connect the end of the compressor. The gas at the stage guide vanes is introduced directly into the flame tube. The beneficial effect of the present invention is that, in this embodiment, the inlet flow of the combustion chamber is partially divided by the provision of the mixed intake air assembly, and the Mach number at the inlet of the combustion chamber is reduced, thereby reducing the total pressure loss of the diffuser and improving the combustion chamber. Total pressure recovery factor and combustion efficiency. At the same time, the active control of the temperature field at the outlet of the combustion chamber is realized, the distribution quality of the outlet temperature field is improved, and the life of the turbine is further increased.

Description

technical field [0001] The invention relates to the field of aero-engines, in particular to a combustion chamber capable of automatically adjusting mixed intake air. Background technique [0002] As one of the three core components of a gas turbine engine, the basic performance and structure of the combustion chamber have reached a very high level. However, for the modern high-performance gas turbine engine combustion chamber, there are still a lot of problems and challenges. The development and application of new concepts, new structures, new materials and new processes are the source of ensuring its continuous progress. [0003] Modern civil gas turbine engines are developing in the direction of turbofan engines with large bypass ratios. The requirements for low cost, low pollution, low noise and high reliability are constantly increasing. Major aero-engine companies have taken the reduction of combustion chamber pollution emissions and fuel consumption as a priority. Res...

AI Technical Summary

Problems solved by technology

As the combustion chamber rises significantly, if the OTDF value increases slightly, the hot spot temperature at the exit of the combustion chamber will increase sharply, which will bring great difficulty and challenges to the design of turbine blades

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