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Axial classification combustor

A staged combustion and secondary combustion technology, which is applied in combustion chambers, combustion methods, combustion equipment, etc., can solve the problems of inability to meet NOx emission standards and increase emissions, and achieve shortened residence time, low NOx emissions, and improved air uniformity Effect

Pending Publication Date: 2021-07-16
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For higher-level gas turbines, the outlet temperature of the combustion chamber is close to 1700°C. At this time, the thermal NO x Emissions have increased sharply, and conventional DLN combustion technology has been unable to reduce NO x Emission compliance

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0040] figure 1 A structural view of the axially staged combustor provided by the embodiment of the present invention is schematically shown. Such as figure 1 As shown, the axially staged combustor 10 may include:

[0041] The combustion chamber includes a main combustion zone 17 and a secondary combustion zone 18. The main combustion zone 17 is arranged in the upstream section of the combustion chamber, surrounded by its front wall 19 and a primary cylindrical wall 20 . The secondary combustion zone 18 is arranged in the downstream section of the combustion chamber, adjacent to the main combustion zone 17 in the axial direction, and surrounded by the secondary cylindrical wall surface 21 . The rear end of the secondary combustion zone 18 communicates with a transition section 22 .

[0042] In a feasible mode of this embodiment, the primary equivalent ratio of the main combustion zone 17 can adopt, for example, a lean premixed combustion mode, and the high-temperature flue...

Embodiment 2

[0053] The secondary nozzle of the axially staged combustor provided in this implementation adopts a micro-mixing nozzle structure. figure 2 A schematic diagram of the structure of the secondary nozzle provided by this embodiment is shown. Such as figure 2 As shown, the secondary nozzle 23 is provided with a nozzle structure outlet 26 towards the secondary combustion zone 18, and the cross section of the nozzle structure outlet 26 is circular (such as figure 2 Shown in A-A), its diameter D is the amount in millimeters. In a feasible manner of this embodiment, the specific range may be, for example, 1mm≤D≤20mm, preferably 5mm≤D≤20mm, which is not limited in the present invention.

[0054] Secondary nozzle 23 is provided with nozzle fuel inlet 27 and nozzle air inlet 28, and the cross-section of nozzle fuel inlet 27 structure is as follows image 3 As shown, the cross-section of the nozzle fuel inlet 27 structure is as Figure 4 As shown, the nozzle fuel inlet 27 and the ...

Embodiment 3

[0062] In this implementation, an axially staged burner with specific numerical operating parameters and structural parameters is selected for combustion tests.

[0063] Specifically, in a feasible mode of this embodiment, the total equivalent ratio is 0.727, the primary air flow rate is 900SLM, the primary fuel flow rate is 66.2SLM, the secondary load ratio FS is 30%, and the secondary equivalent ratio Φ 2 Take 0.8, the equivalent ratio of the main combustion zone Φ 1 Take 0.7. The secondary nozzle 23 is arranged vertically to the centerline of the classification system, θ is 90°, the diameter D of the secondary nozzle 23 is 5 mm, and the number of secondary nozzles 23 is 8. At this time, the jet flux ratio J is about 20. The overall length L of the secondary nozzle 23 is 7D, and the length L between the nozzle fuel inlet 27 and the nozzle air inlet 28 1 Take 2D, the length L between the nozzle air inlet 28 and the secondary nozzle outlet 26 section 2 Take 5D. Number N of...

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Abstract

The invention discloses an axial classification combustor. The axial classification combustor (10) comprises a combustion chamber, wherein the combustion chamber comprises a main combustion area (17) and a secondary combustion area (18); the main combustion area (17) is arranged at the upstream section of the combustion chamber; the secondary combustion area (18) is arranged at the downstream section of the combustion chamber and is axially connected with the main combustion area (17); a main nozzle (16) is formed at one end, away from the secondary combustion area (18), of the main combustion area (17); the main nozzle (16) faces the main combustion area (17) and is connected with a primary fuel and air mixed channel (15); a secondary nozzle (23) having at least one micro-mixed nozzle structure is arranged on the wall face of the secondary combustion area (18) in the radial direction; the secondary nozzle (23) is connected with a secondary air pipeline (24) and a secondary fuel pipeline (25); and the change trend of a secondary equivalence ratio of the secondary combustion area (18) and the change trend of a secondary load ratio are contrary. According to the axial classification combustor disclosed by the invention, emission of low NOx under the high load is realized, and the flexibility of load adjustment is improved.

Description

technical field [0001] The invention relates to the technical field of low-pollution combustion under high load of a combustion chamber of a gas turbine, in particular to an axial staged burner. Background technique [0002] As the main device that consumes natural gas energy, gas turbine is an indispensable power source in industrial production. As the level of gas turbines is getting higher and higher, gas turbines are constantly developing towards high efficiency and wide load adjustment range, and the method to improve cycle efficiency is mainly achieved by increasing combustion temperature and pressure. Low emission combustion is an important performance goal for gas turbine combustors. NO among pollutants produced by gas turbines fueled by natural gas x As an important component of pollutants, how to solve or balance the contradiction between combustion temperature and NOx emissions is a key issue in the development of gas turbine combustors. [0003] dry low NO x ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/34F23R3/28
CPCF23R3/346F23R3/286
Inventor 邵卫卫王子叶刘勋伟张哲巅肖云汉
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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