Gas turbine low-emission combustion chamber using gas fuels

A gas fuel, gas turbine technology, applied in the direction of combustion chamber, continuous combustion chamber, combustion method, etc., can solve the problems of lack of adaptability of gas fuel, engine combustion chamber damage, prone to spontaneous combustion and backfire, etc., to achieve stable combustion and prevent Good effect of tempering and mixing

Inactive Publication Date: 2019-08-16
SHENYANG AEROSPACE UNIVERSITY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] 1. The flammable limit is narrow, especially when the engine is under low operating conditions, it is prone to flameout;
[0005] 2. Spontaneous combustion and tempering problems are prone to occur during the premixing process, resulting in damag

Method used

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  • Gas turbine low-emission combustion chamber using gas fuels
  • Gas turbine low-emission combustion chamber using gas fuels
  • Gas turbine low-emission combustion chamber using gas fuels

Examples

Experimental program
Comparison scheme
Effect test

Example Embodiment

[0032] Example 1

[0033] like Figure 1-Figure 4 As shown, a gas turbine low-emission combustor using gas fuel, the combustor head includes a duty stage and a main combustion stage arranged in a concentric manner, and the duty stage is in the center, and the main combustion stage is arranged at the periphery of the duty stage. Combustion stability and low emissions when using gaseous fuel is achieved by adjusting the fuel distribution of the duty stage, the main combustion stage including the first-stage axial swirler 6 and the duty stage fuel nozzles and the coordination between the different nozzles , the first-stage axial swirler 6 is installed in the central hole of the head of the flame tube 12, the outer casing 14 of the flame tube is installed outside the flame tube 12, and the flame tube 12 is arranged coaxially with the outer casing 14 of the flame tube, The outer casing 14 of the flame cylinder is respectively provided with a No. 1 duty fuel tank 24 and a No. 2 dut...

Example Embodiment

[0038] Example 2

[0039] like Figure 5 and Image 6 As shown, the outer casing 14 of the flame tube is located in the outer ring part of the high-pressure igniter 7 and close to one end of the first-stage axial swirler 6. The No. 2 duty fuel nozzles 3 are evenly arranged in the circumferential direction, and the No. The axial angle between the axis of the nozzle 3 and the first-stage axial swirler 6 is 60°. Other structures and connection methods are the same as those in Embodiment 1.

Example Embodiment

[0040] Example 3

[0041] The installation angle between the center line of the flame tube 12 and the engine center line is 30°. Other structures and connection methods are the same as those in Embodiment 1 or Embodiment 2.

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Abstract

The invention discloses a gas turbine low-emission combustion chamber using gas fuels, and belongs to the technical field of gas turbines. The combustion chamber comprises an on-duty grade, a main combustion grade, a high-pressure igniter, a mixing hole, an exhaust outlet, a bearing machine box, a flame cylinder, the flame cylinder outer machine box, a flange, a first on-duty grade gas fuel pipeline, a main combustion grade gas fuel pipeline, a main combustion grade fuel main pipe, a first on-duty grade fuel main pipe, a pipeline bracket, a second on-duty grade fuel main pipe, a second on-dutygrade gas fuel pipeline, an air conditioning device, a first on-duty grade fuel tank, a second on-duty grade fuel tank and a main combustion grade fuel tank; when a gas turbine is started in low-loadstates, only the on-duty grade works; when the gas turbine is started in high-load states, the on-duty grade and the main combustion grade work together; and through diffusion combustion of on-duty grade fuels, a stable ignition source is provided to a main combustion area, so that the low emission requirement is guaranteed, the combustion stability and the combustion efficiency are fully considered, and the performance requirements of the combustion chamber are comprehensively met.

Description

technical field [0001] The invention belongs to the technical field of gas turbine combustion chambers, and in particular relates to a gas turbine low-emission combustion chamber using gas fuel. Background technique [0002] Gas turbine originated in the 1960s. It can use various fuels such as gas fuel and liquid fuel. countries' attention. It is a power machine widely used in aviation, shipbuilding, electric power and many other industrial fields, and plays a vital role in the development of the national economy. Compared with other engines, gas turbines have many advantages, such as fuel consumption rate, noise, emission, vibration, etc. They can be used for traditional distributed power generation, and can also be used for grid-connected power generation and other way, it is suitable for both urban and remote areas. And because of its clean and reliable advantages, it is highly praised by the industry and society. In recent years, gas turbines have been widely used as...

Claims

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Application Information

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IPC IPC(8): F23R3/28F23R3/38
CPCF23R3/286F23R3/38
Inventor 刘爱虢李昱泽陈炫任曾文刘凯
Owner SHENYANG AEROSPACE UNIVERSITY
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