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Interstage combustor with integrated diversion and trapped vortex

A combustion chamber and interstage technology, which is applied in the direction of gas turbine devices, machines/engines, mechanical equipment, etc., can solve the problems of high turbulence pulsation and large air flow velocity, so as to improve the power of the whole machine, increase the temperature rise, and improve the function of gas force effect

Active Publication Date: 2016-04-06
XIAMEN UNIV +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The interstage combustor can solve the difficulties of high-pressure turbine outlet air flow velocity and high turbulent pulsation, and can solve the technical problems of combustion stability and device cooling protection

Method used

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  • Interstage combustor with integrated diversion and trapped vortex
  • Interstage combustor with integrated diversion and trapped vortex
  • Interstage combustor with integrated diversion and trapped vortex

Examples

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Embodiment Construction

[0030] see Figure 1-11 , the interstage combustor integrated with guide and vortex integration described in this embodiment is provided with a casing 2, a front guide vane 4, a rear guide vane 9 and a tail cone 10; the casing 2 and the front guide vane 4, the rear guide vane 9 and The coccyx 10 is arranged with the central axis and is an integral structure.

[0031] The shell 2 is provided with an axial center through hole, the front of the shell 2 has a trumpet shape with a small front and a large rear, the middle of the shell 2 has a flat cylindrical shape, and the inner cavity of the middle of the shell 2 is provided with a sandwich wall 21 of a bending structure. The interlayer wall 21 of the structure forms an annular cavity 8, the rear part of the housing 2 is in the shape of a waisted column, and the cooling air inlet holes 5 are evenly distributed on the same circumference of the front part of the housing 2.

[0032] The front guide vane 4 is provided with a front gu...

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Abstract

The invention discloses a diversion and standing vortex integrated interstage combustion chamber, and relates to a gas turbine. The diversion and standing vortex integrated interstage combustion chamber comprises a shell, front diversion blades, rear diversion blades and a caudal vertebra, wherein the shell, the front diversion blades, the rear diversion blades and the caudal vertebra are coaxially arranged and are of an integrated structure; an annular concave cavity is formed in the shell; cooling air inlets are uniformly distributed at intervals in one same circumference of the wall of front part of the shell; cooling air flowing holes are formed in different blades of the front diversion blades; an inner duct is formed between a front diversion hollow main body and a sleeve wall; an outer duct is formed between the sleeve wall and the shell; standing vortex is formed inside the concave cavity; fuel oil inside the concave cavity is mixed with air and is ready for stable combustion; a low-pressure turbine behind is impacted by air flow generated from combustion to act up, so that thermal circulation power can be increased, and the thrust of the fuel engine can be increased. The difficulties that a high-pressure turbine outlet is large in air flow velocity and hard in turbulent fluctuation and the technical problems of combustion stability and device cooling protection can be solved.

Description

technical field [0001] The invention relates to a gas turbine, in particular to an interstage combustor applied between a high-pressure turbine and a low-pressure turbine of the gas turbine. Background technique [0002] In order to improve the power performance of aero-engines, there are usually methods such as increasing the boost ratio of the compressor and increasing the temperature before the turbine. However, due to the concentration of related research, the development potential has been very small. [0003] The interstage combustor increases the power of the engine by adding a combustor between the high-pressure and low-pressure turbines of the aero-engine to increase the heat circulation. According to the public literature, this method can not only increase the thrust of the gas turbine, but also improve the fuel combustion efficiency. However, since the combustion chamber is arranged after the high-pressure turbine, its inlet airflow temperature, velocity and turb...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C3/16
Inventor 黄玥邢菲阮灿刘晨林志伟张统一
Owner XIAMEN UNIV
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