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Novel catalytic soft combustion method

A combustion method and catalytic combustion technology, applied in the direction of combustion methods, combustion chambers, combustion equipment, etc., can solve the problems of low emission characteristics and the inability to take into account the high performance of gas turbines at the same time, to achieve low emission characteristics, reduce pollutant content, and uniform combustion Effect

Inactive Publication Date: 2018-06-01
SHANGHAI JIAO TONG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The research on the application of catalytic combustion in the field of gas turbines is mainly reflected in the research of catalytic combustion micro gas turbine technology using low calorific value fuels, but the technical solutions disclosed in the prior art cannot take into account the high performance and low emission characteristics of gas turbines at the same time

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0027] For heavy-duty gas turbines, the fuel working medium is methane (or natural gas), the temperature of the air from the compressor is about 350°C, the pressure is about 25 atmospheres, and the main fuel (primary fuel) accounts for the composition of the mixture The proportion of methane in the combustion gas is about 2.5%. The present invention works through the following steps:

[0028](1) During the start-up phase, the air from the compressor enters the premix chamber through the pores along the air passage between the outer and outer casings of the staged combustor. At the same time, the fuel inlet is opened, and the fuel and air flowing into the premixing chamber are combusted under the action of the igniter, and the staged combustion chamber is heated to make the temperature of the catalytic combustion chamber reach the ignition temperature required for the reaction. Then the starting fuel inlet is closed, the main fuel (primary fuel) inlet is opened, and the stable...

Embodiment 2

[0032] For medium-sized gas turbines, the fuel working medium is methane (or natural gas), the air temperature from the compressor is about 250°C, the pressure is about 12 atmospheres, and the main fuel (primary fuel) accounts for the composition of the mixture The ratio is about 2.5%, and the proportion of methane entering the rear catalytic / gas phase reaction zone from the secondary fuel port is about 1.5% in the gas. The present invention works through the following steps:

[0033] (1) During the start-up phase, the air from the compressor enters the premix chamber through the pores along the air passage between the outer and outer casings of the staged combustor. At the same time, the fuel inlet is opened, and the fuel and air flowing into the premixing chamber are combusted under the action of the igniter, and the staged combustion chamber is heated to make the temperature of the catalytic combustion chamber reach the ignition temperature required for the reaction. Then ...

Embodiment 3

[0037] For the situation applicable to micro gas turbines, the fuel working medium is methane (or natural gas), the air temperature from the compressor is about 150°C, and the pressure is about 6 atmospheres. The methane entering the premix chamber from the main fuel port is in the mixture The proportion of the methane in the gas is about 2%, and the proportion of the methane entering the rear catalytic / gas phase reaction zone from the secondary fuel port is about 1%. The present invention works through the following steps:

[0038] (1) During the start-up phase, the air from the compressor enters the premix chamber through the pores along the air passage between the outer and outer casings of the staged combustor. At the same time, the fuel inlet is opened, and the fuel and air flowing into the premixing chamber are combusted under the action of the igniter, and the staged combustion chamber is heated to make the temperature of the catalytic combustion chamber reach the ignit...

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PUM

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Abstract

The invention relates to a novel catalytic soft combustion method. By adopting the mode of the hierarchical concept, catalytic combustion and post-catalytic combustion (gas phase reaction) are combined, and efficient clean combustion of fuel in a combustion chamber is achieved by means of three areas comprising the premixing area, the catalytic combustion area and the gas phase combustion area (post-catalytic combustion area) of the hierarchical combustion chamber. Compared with the prior art, the performance is reliable, the NOx and hydrocarbon content in combustion products can be reduced, the combustion efficiency is high, and environmental pollution is reduced. Meanwhile, by means of no-flame combustion, the thermoacoustic oscillation phenomenon in the combustion chamber of a gas turbine can be effectively reduced or eliminated.

Description

technical field [0001] The invention relates to a combustion method, in particular to a novel catalytic soft combustion method combining catalytic combustion and post-catalytic combustion (gas phase reaction). Background technique [0002] As an important heat-to-power conversion device, gas turbines are increasingly widely used in the fields of ships, power generation and chemical industry, and have an irreplaceable role and status in national economy and national defense construction. The improvement of the gas turbine cycle efficiency mainly depends on the increase of the exhaust temperature of the combustion chamber, and the contradiction is that the NO in the combustion chamber X The emissions will also increase with the increase of exhaust temperature. At the same time, the working environment of the heavy-duty gas turbine combustor is very harsh, with the characteristics of large heat load, high temperature and high speed, high excess air coefficient and complex flow ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/40F02C9/26
CPCF23R3/40F02C9/26
Inventor 翁一武
Owner SHANGHAI JIAO TONG UNIV