Combustion chamber capable of automatically adjusting mixed intake air

Abstract

The invention provides a combustion chamber capable of automatically adjusting mixed intake air, which is connected with a last-stage guide vane of a gas compressor and comprises a flame tube and a diffuser, and the diffuser is arranged at the downstream of the last-stage guide vane of the gas compressor; the combustion chamber also comprises a mixing gas inlet assembly, the inlet end of the mixing gas inlet assembly communicates with the last-stage guide vane of the gas compressor, the outlet end of the mixing gas inlet assembly communicates with the flame tube, and the mixing gas inlet assembly can directly introduce gas at the last-stage guide vane of the gas compressor into the flame tube. The combustion chamber has the advantages that by arranging the mixing air inlet assembly, partial flow division of the inlet flow of the combustion chamber is achieved, and the Mach number of the inlet of the combustion chamber is reduced, so that the total pressure loss of the diffuser is reduced, and the total pressure recovery coefficient and the combustion efficiency of the combustion chamber are improved. Meanwhile, the combustion chamber outlet temperature field is actively regulated and controlled, the outlet temperature field distribution quality is improved, and the service life of a turbine is further prolonged.

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 combustor's basic performance and structure have reached a fairly high level. However, for modern high-performance gas turbine engine combustors, there are still a lot of problems and challenges. The development and application of new concepts, new structures, new materials and new processes is the source to ensure its continuous progress. [0003] Modern civil gas turbine engines are developing towards high bypass ratio turbofan engines, and the requirements for low cost, low pollution, low noise and high reliability are constantly increasing. important topics for research. Since 1994, GE Aero Engines has employed several improved low-emission combustors on new aircraft gas turbine engines, including the CFM56-5B an...

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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