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Integrated pressure rotational flow atomizing nozzle of gas turbine and combustor with nozzle

A swirling atomizing nozzle and gas turbine technology, which is applied in the combustion chamber, combustion method, combustion equipment, etc., can solve the problems of application limitation, large overall structure and volume, and achieve compact overall size, stable combustion temperature, and reduction of nitrogen oxides. The effect of emissions

Pending Publication Date: 2022-03-25
中国船舶重工集团公司第七0三研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, since pressure swirl atomization must require structures such as swirlers and swirl chambers, its overall structural volume has always been large, so its application in lean-burn premixed pre-evaporation technology has been limited.

Method used

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  • Integrated pressure rotational flow atomizing nozzle of gas turbine and combustor with nozzle
  • Integrated pressure rotational flow atomizing nozzle of gas turbine and combustor with nozzle
  • Integrated pressure rotational flow atomizing nozzle of gas turbine and combustor with nozzle

Examples

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Effect test

Embodiment 1

[0022] to combine Figure 1-3 , the nozzle as a whole adopts an integrated structure, including the nozzle head and the nozzle tail; the front end of the nozzle head is provided with a fuel nozzle 3, and the nozzle head is provided with a swirl chamber 4, and the fuel nozzle 3 communicates with the front end of the swirl chamber 4; There is a fuel channel 1 in the tail of the nozzle, and the fuel channel 1 communicates with the rear end of the swirl chamber 4 through the swirl hole 2; the fuel enters the cavity in the nozzle head through the fuel channel 1, and then enters through the swirl hole 2 The swirl chamber 4 is finally sprayed out in the form of oil mist through the fuel nozzle 3 .

Embodiment 2

[0024] Further, the swirl holes 2 are tangent to the inner diameter of the swirl chamber 4, and the swirl holes 2 are distributed in single or multiple rows; the number of swirl holes in each row is 2 or 3 or 4 or 6; When the flow holes 4 are distributed in multiple rows, a staggered arrangement method is adopted, and the range of the staggered angle is 0-180°.

[0025] The invention integrates the fuel channel, the swirler and the fuel nozzle, and can adjust the fuel spray pattern by changing the diameter of the swirl aperture, the number of holes, the hole position and the diameter of the fuel nozzle; due to the compact overall size, it can be conveniently used for multiple applications. in the burner. Through multi-group or multi-point arrangement, good atomization of fuel oil under different working conditions of the gas turbine can be satisfied.

Embodiment 3

[0027] Figure 4(a), Figure 4(b), Figure 5 An example of the use of the present invention is given, the example is a dual-fuel gas turbine combustor, integrated pressure swirl atomizing nozzles (invention) are installed in groups on the 2nd stage air radial swirler of the combustor (16 pieces in total, Figure 4); the fuel channel 1 is installed on the burner in the form of a plug-in connection, and communicates with the inside of the fuel main pipe; the air heat insulation tube is set on the shell at the end of the nozzle to prevent the fuel from Channel 1 carbon deposits. The fuel nozzle 3 is located at the outlet of the second-stage air radial swirler; when the dual-fuel gas turbine burner uses liquid fuel and works in a higher working condition, the high-pressure fuel from the fuel pump passes through the fuel main pipe, fuel channel 1, swirl The orifice 2 and the swirl chamber 4 are injected from the fuel nozzle 3 to the downstream of the air flow channel of the second-st...

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Abstract

The invention belongs to the technical field of gas turbines, and particularly relates to an integrated pressure rotational flow atomizing nozzle of a gas turbine and a dual-fuel gas turbine combustor with the nozzle. The nozzle provided by the invention adopts the integrated design of the fuel channel, the swirler and the fuel nozzle, is compact in overall size, can be conveniently applied to various combustors, and can meet good fuel atomization of a gas turbine under different working conditions through multi-group or multi-point arrangement; high-pressure fuel oil is jetted to the downstream of an air flowing channel of the second-stage air radial swirler through a nozzle and mixed with strong swirling air to form uniform mixed oil gas to be combusted in the combustion chamber, the combustion temperature in the combustion chamber can be effectively controlled by adjusting the swirling degree and the air flow of the two-stage swirler, combustion is stable, and the combustion efficiency is improved. And the purpose of reducing emission of nitrogen oxides is achieved.

Description

technical field [0001] The invention belongs to the technical field of gas turbines, and in particular relates to a gas turbine integrated pressure swirl atomization nozzle and a dual-fuel gas turbine burner with the nozzle. Background technique [0002] When the gas turbine is working, the fuel is atomized through the nozzle and enters the combustion chamber of the gas turbine for combustion; in order to improve the combustion efficiency of the fuel and widen the stable combustion range, it is generally required to have strict distribution rules for the atomization of the fuel. Due to the complexity of the atomization process and insufficient understanding of the atomization phenomenon and mechanism, fuel atomization technology has become the bottleneck of engine development. As the key device of atomization formation, the nozzle plays an extremely important role in the atomization process. Compared with other nozzles, pressure swirl nozzles are widely used in combustion c...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/38F23R3/12
CPCF23R3/38F23R3/12
Inventor 杨强林枫李名家李雅军冉军辉曹天泽任艳平杜秋丽
Owner 中国船舶重工集团公司第七0三研究所
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