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Gas turbine combustor swirling jet mixing nozzle

A technology of gas turbines and mixing nozzles, which is applied in combustion chambers, continuous combustion chambers, combustion methods, etc., can solve the problems of flat increase in nitrogen oxide emission levels, limited potential, and failure to meet emission standards, etc., to reduce pollutant emissions, The effect of suppressing the formation of nitrogen oxides and reducing the possibility of flashback

Active Publication Date: 2017-09-15
CHINA UNITED GAS TURBINE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Comparing the latest combustion chamber products in the 1990s and the present in the world, it can be seen that the average outlet temperature has increased by about 200°C. Although the combustion chamber has undergone a series of optimizations and improvements, the emission level of nitrogen oxides has remained the same or even slightly increased. This shows that the current combustor design structure has limited potential when targeting future higher parameter combustors, and faces the risk of not meeting emission standards

Method used

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  • Gas turbine combustor swirling jet mixing nozzle
  • Gas turbine combustor swirling jet mixing nozzle
  • Gas turbine combustor swirling jet mixing nozzle

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0022] refer to figure 1 and 2 As shown, the gas turbine combustor swirl jet mixing nozzle includes: a nozzle base 1 , a swirl nozzle assembly 2 and a jet nozzle assembly 3 .

[0023] The nozzle base 1 is provided with a swirl inlet passage 11 and a jet inlet passage 12 for supplying fuel to the swirl nozzle assembly 2 and the jet nozzle assembly 3 respectively.

[0024] The swirl nozzle assembly 2 includes a swirl barrel 20 , a swirl fuel pipe 21 and a plurality of swirl vanes 22 . The swirl tube 20 is a metal cylinder with openings at the front and rear ends. The front end of the swirl fuel pipe 21 is inserted into the swirl tube 20 from the rear end of the swirl tube 20 and is arranged at the center of the swirl tube 20 . The front end of the swirl fuel pipe 21 is closed, and the rear end is used to be installed on the nozzle base 1 and communicated with the swirl air intake passage 11 . A plurality of swirl vanes 22 are mounted on the swirl fuel pipe 21 and arranged bet...

Embodiment 2

[0032] refer to image 3 As shown, the gas turbine combustor swirl jet mixing nozzle includes: a nozzle base 1 , a swirl nozzle assembly 2 and a jet nozzle assembly 3 .

[0033] The nozzle base 1 is provided with a swirl inlet passage 11 and a jet inlet passage 12 for supplying fuel to the swirl nozzle assembly 2 and the jet nozzle assembly 3 respectively.

[0034]The swirl nozzle assembly 2 includes a swirl barrel 20 , a swirl fuel pipe 21 and a plurality of swirl vanes 22 . The swirl tube 20 is a metal cylinder with openings at the front and rear ends. The front end of the swirl fuel pipe 21 is inserted into the swirl tube 20 from the rear end of the swirl tube 20 and is arranged at the center of the swirl tube 20 . The front end of the swirl flow fuel pipe 21 is closed, and the rear end is installed on the nozzle base 1 and communicated with the swirl flow intake passage 11 . A plurality of swirl vanes 22 are mounted on the swirl fuel pipe 21 and connected between the swi...

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Abstract

The invention relates to the field of nozzle structures of combustion chambers of gas turbines and discloses a swirling jet mixing nozzle of the combustion chamber of the gas turbine. The swirling jet mixing nozzle of the combustion chamber of the gas turbine comprises a jet nozzle component and a swirling nozzle component, the jet nozzle component comprises a jet barrel and a jet fuel pipe, and the jet barrel is concentric with the swirling nozzle component and located at the outer side of the swirling nozzle component; a front baffle plate, a rear baffle plate and a middle baffle plate are arranged between the jet barrel and swirling nozzle component to form a front chamber and a rear chamber; the front baffle plate is provided with a first jet hole and a second jet hole, and the first jet hole is connected with the rear chamber through a jet duct; the jet fuel pipe is connected with the rear chamber, an air inlet is formed in the outer side wall of the front chamber, or the jet fuel pipe is connected with the front chamber, and an air inlet is formed in the outer side wall of the rear chamber. The swirling jet mixing nozzle of the combustion chamber of the gas turbine reduces the swirling stable flame airflow proportion, increases the jet mixture proportion, lowers the flame peak temperature, inhibits the nitrogen oxide generation and reduces the pollution gas emission.

Description

technical field [0001] The invention relates to the technical field of gas turbine combustor nozzles, in particular to a gas turbine combustor swirling jet flow mixing nozzle. Background technique [0002] For industrial heavy-duty gas turbines, the development goals for decades have always been higher average temperature of the combustion chamber outlet (standardized gas turbine technical level) and lower pollutant emissions; the above technical indicators are closely related to the combustion chamber and contradict each other, higher The average temperature at the outlet of the combustion chamber means that more fuel participates in the combustion process, and the average temperature in the combustion chamber is higher. Nitrogen oxides, which are the main pollutants in the combustion chamber, are closely related to the thermal process inside the combustion chamber. The basic function of the gas turbine combustor is to convert the chemical energy in the fuel into the therma...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/38
Inventor 李珊珊吕煊方子文王绥德陈伟
Owner CHINA UNITED GAS TURBINE TECH CO LTD