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A Multistage Partitioned Combustion Structure for Gas Turbine

A technology of gas turbine and combustion structure, applied in the direction of combustion chamber, combustion method, combustion equipment, etc., can solve the problems that combustion stability and low emission can not be well balanced, achieve flame extinguishing performance and low emission, ensure the prevention of ablation, Guaranteed efficient combustion

Active Publication Date: 2021-11-30
成都中科翼能科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the problem that the combustion stability and low emission cannot be well balanced in the combustion process of gas turbines in the prior art, this solution provides a multi-stage partitioned combustion structure for gas turbines. The combustion area of ​​the combustion chamber Multi-level zoning and fine zoning control are carried out to realize the combustion of most of the gas under the requirements of reasonable and low emission standards, to achieve efficient and stable combustion while reducing NOx emissions in the combustion chamber, and to achieve a good balance between combustion stability and low emissions

Method used

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  • A Multistage Partitioned Combustion Structure for Gas Turbine
  • A Multistage Partitioned Combustion Structure for Gas Turbine
  • A Multistage Partitioned Combustion Structure for Gas Turbine

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Embodiment 1

[0039] Such as Figure 1-Figure 7 As shown, this embodiment designs a multi-stage partitioned combustion structure for a gas turbine, including a combustor casing 8, a flame tube 5, a plurality of swirlers and a flow divider 6 and other structures.

[0040] There is an annular groove cavity 84 inside the combustor casing 8; the outlet of the groove cavity 84 faces the rear side of the gas turbine. And the combustion chamber casing 8 is used for the installation of the flame tube 5 .

[0041] The flame tube 5 is arranged in the cavity 84 of the combustor casing 8 , and the flame tube 5 has an annular groove-shaped combustion chamber. The combustion outlet 54 of the combustion chamber faces the same as the outlet of the groove cavity 84 of the combustion chamber casing 8; after the gas burns in the flame tube 5, the exhaust gas is ejected from the combustion outlet 54.

[0042] The combustion chamber of the swirler is used to introduce air and gas into the combustion chamber; ...

Embodiment 2

[0052] This embodiment designs a variety of working modes for the multi-stage partitioned combustion structure used in the gas turbine in the first embodiment, which are the ignition state working mode, the small state working mode, the transition state working mode and the heavy load state working mode, four The first working mode is that the working mode of each cyclone group is divided according to the starting power.

[0053] In the working mode of the ignition state, each swirler group is only supplied with gas by the second gas channel 14 of its on-duty swirler 1 for diffusion combustion; the principle of the working mode of the ignition state is: in this working mode, the gas supply And the intake air volume is small, and the emission standard has no regulations and requirements on the emission of the ignition state, all the gas is concentrated at the duty swirler 1, and is injected by the second gas channel 14 of the duty swirler 1, using the diffusion The advantage of...

Embodiment 3

[0058] Such as Figure 1-Figure 7 As shown, on the basis of the structure of the first embodiment, this embodiment refines the structures of the flame tube 5 and the casing main body 82 .

[0059] The flame tube 5 includes a cylinder rear section 52 and a cylinder front section 51, the cylinder front section 51 is a double-layer structure, the inner layer is the front section inner wall 512, the outer layer is the front section outer wall 513, and there is a sandwich channel between the front section inner wall 512 and the front section outer wall 513 514. An impingement cooling hole 511 is provided on the outer wall of the front section 51 of the cylinder, and a mounting portion 53 for installing a swirler is provided at the inner bottom of the front section 51 of the cylinder.

[0060] A slot is arranged on the inner side of the rear section 52 of the cylinder, and the slot faces the combustion outlet 54. A slot cooling hole 521 connected to the outside of the rear section ...

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Abstract

The invention belongs to the technical field of gas turbines, and specifically relates to a multi-stage partitioned combustion structure for gas turbines, which includes a combustion chamber casing, a flame tube, a plurality of swirlers and flow dividers, and the swirlers are divided into on-duty swirlers, The flame transfer swirler, the first and the second main combustion swirlers, each swirler is provided with a first gas channel, and the first gas channel transports the gas used for premixed combustion; at the duty swirler A second gas channel is also provided, and the second gas channel transports the gas used for diffusion combustion; the installation angles of the swirler blades are different, and the swirling air flow fields generated by each swirler are relatively independent, so that each swirler The streamer participates in the combustion of independent zones. In this scheme, the multi-stage partition combustion technology uses four different cyclones combined with diverters to form a multi-stage partition organization combustion in the form of graded fuel supply, which meets the needs of all working conditions and ensures the combustion chamber ignition performance and combustion stability. , to achieve the demand for low emission of nitrogen oxides.

Description

technical field [0001] The invention belongs to the technical field of gas turbines, and in particular relates to a multi-stage partitioned combustion structure for gas turbines. Background technique [0002] Gas turbine is a device with good cleanliness and high efficiency. It has the advantages of small size and low weight. It is widely used in power generation, independent energy system, mechanical drive and other fields. However, during the operation of the gas turbine, nitrogen oxides (NO x ), carbon monoxide (CO) and incompletely combusted hydrocarbons (UHC). related. [0003] In recent years, low-emission combustion technology has developed rapidly, and various new technologies have emerged continuously. A number of low-emission combustion technologies have been developed, and various low-pollution combustion chambers have been developed. Lean-burn premixed combustion technology is a representative of various low-pollution combustion technologies. Its main idea is ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/38F23R3/42F23R3/16F23R3/28
CPCF23R3/16F23R3/283F23R3/38F23R3/42
Inventor 刘宝琪范珍涔颜腾冲王龙陈柳君代茂林杨治王梁丞赵汝伟
Owner 成都中科翼能科技有限公司
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