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Turbine stator blade with interstage combustor

A turbine stator and combustion chamber technology, applied in the direction of combustion chambers, continuous combustion chambers, combustion methods, etc., can solve the problems of high temperature, large inlet airflow velocity, and reduce blocking ratio, etc., achieve simple structure, improve machine power and weight add small effect

Inactive Publication Date: 2013-08-28
XIAMEN UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

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

Method used

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  • Turbine stator blade with interstage combustor
  • Turbine stator blade with interstage combustor
  • Turbine stator blade with interstage combustor

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Embodiment Construction

[0029] see Figure 1-7 , the embodiment of the present invention is provided with outer ring 1, guide vane body guide vane body 2, guide vane cover 3, inner ring 4, 2 ignition devices (including ignition seat 7 and ignition nozzle (not shown in the figure)) and 8 spray rod devices 6 are formed.

[0030] The outer ring 1 is provided with a cooling chamber 11 , and the cooling chamber 11 is provided with an air inlet 5 . The guide vane is arranged between the inner ring 4 and the outer ring 1 , the guide vane is provided with a guide vane main body 2 and a guide vane cover 3 , and the guide vane cover 3 is arranged on the upper end surface of the guide vane main body 2 . The main body 2 of the guide vane is provided with an oil injection cavity 201 at the front, a return flow cavity 204 at the middle and a cooling cavity 205 at the rear; there is a spray bar slot 207 inside the oil injection cavity 201, and a baffle 202 is provided at the end of the oil injection cavity 201 , ...

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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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/02F02C3/14F23R3/00
Inventor 邢菲方骁远王培勇邢盼徐磊磊
Owner XIAMEN UNIV
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