Turbine stator blade with interstage combustor

Abstract

The invention discloses a turbine stator blade with an interstage combustor, and relates to turbine stator blades of aero-engines or gas turbines. The turbine stator blade comprises an inner ring, an outer ring and multiple guide blades, wherein the guide blades are provided with a guide blade main body and a guide blade cover; the guide blade cover is arranged on the upper end of the guide blade main body, and the guide blade main body is provided with a front oil injection cavity, a middle backflow cavity and a rear cooling cavity; another cooling cavity is formed at the rear of the guide blade cover, and the oil injection cavity is internally provided with a spraying rod slot; the cooling cavity of the guide blade main body and the cooling cavity of the guide blade cover respectively have cooling holes; the turbine stator blade is also provided with ignition devices and multiple spraying rod devices, and the ignition devices are provided with ignition bases and ignition electric nozzles; the spraying rod devices are arranged on the guide blades, the outer ends of the spraying rod devices pass through and are exposed of the outer ring, and the inner ends of the spraying rod devices stretch into oil injection cavities of the guide blades; and the spraying rod devices are provided with oil pipes, gas pipes and nozzles, oil spraying ports and multiple gas spraying ports are formed in the nozzles, and the oil pipes and the air pipes are respectively connected with an oil supplying pipe and a gas supplying pipe.

Description

technical field [0001] The invention relates to a turbine stator blade of an aeroengine or a gas turbine, in particular to a turbine stator blade with an interstage combustion chamber. Background technique [0002] In order to improve the power performance of aeroengines or gas turbines, there are usually methods such as increasing the boost ratio of the compressor and increasing the temperature before the turbine, but the potential for such research to be tapped is already small. [0003] The Interstage Turbine Burner (ITB) has been proposed as a new idea in recent years. It increases the heat circulation by adding a combustion chamber between the high-pressure and low-pressure turbines of the aeroengine, thereby increasing the engine power. Since the combustion chamber is arranged between two turbine stages, compared with the main combustion chamber, its inlet airflow temperature and velocity are higher, and it has higher requirements for flame stabilization; compared with...

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Problems solved by technology

[0007] The purpose of the present invention is to provide a device that can overcome the difficulties caused by the high flow rate and high temperature of the inlet airflow, solve the problems of lean combustion, stable flame and blade cooling, etc., has good lean oil flameout characteristics, can significantly improve the atomization effect, and reduce clogging. A Turbine Stator Blade with Interstage Combustion Chamber

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