Gas turbine main combustion chamber multi-channel diffuser with intelligently adjustable diffusion ratio

Abstract

The invention discloses a gas turbine main combustion chamber multi-channel diffuser with the intelligently adjustable diffusion ratio, and belongs to the technical field of gas turbine combustion. The diffusion ratio flowing through an inner diffusion channel and an outer diffusion channel can be intelligently set by adjusting the expansion angle of a cone located in a diffuser casing, the target diffusion ratio of each channel is set according to different working conditions, so that the sum of friction loss and separation loss of the diffuser is minimum; in addition, the multi-channel diffuser guides two air flows to a designated area of the head of the double-ring-cavity combustion chamber, the air flows of the main combustion stage and the pre-combustion stage of the double-ring-cavity combustion chamber can be intelligently distributed by adjusting the position of a flow dividing cone located in a diffuser casing, according to different working conditions, the set oil-gas ratio of each area is obtained, so that high combustion characteristics and low pollution emission are realized.

Description

technical field [0001] The invention belongs to the technical field of gas turbine combustion, in particular to a multi-channel diffuser for a main combustion chamber of a gas turbine with an intelligently adjustable diffusion ratio. Background technique [0002] Staged and stratified combustion technology is the main technical means to achieve low-pollution combustion. The double-annular combustion chamber adopts radial classification, and the flame tube is divided into two internal and external combustion areas by the annular center body, namely the main combustion stage and the pre-combustion stage. The characteristic of organizational combustion is not to change the air distribution ratio, but to adjust the fuel distribution from one zone to another according to the engine operating conditions to change the fuel-air ratio, thereby controlling the combustion temperature. Radial staging causes the radial height of the double-annular combustor to be much larger than that of...

AI Technical Summary

Problems solved by technology

[0003] The total pressure loss of the traditional aerodynamic diffuser is small, but its length is too long, and the flow stability of the diffuser is sensitive to the change of the inlet velocity distribution, which limits its application scenarios; Short and insensitive to the flow field at the outlet of the compressor, it is widely used in aviation gas turbine combustors. However, the sudden diffuser diffuser applied to the double-annular combustor has too large pressure loss in the outer ring area, resulting in an unacceptable total pressure loss. At the same time Air separation occurs at high thrust-to-weight ratios

In addition, in the middle working condition between the high and low working conditions of the double-annular combustion chamber, since the two-stage combustion zones deviate from their optimal design points, it is difficult to ensure the uniformity of the temperature field at the exit of the combustion chamber, which reduces the performance of low pollution emissions.

The existing combustor diffuser structure can no longer meet the needs of modern high-performance aeroengines for combustor diffusers, so designing a new type of diffuser has great practical significance

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