A fuel-cooled evaporator tube structure

Abstract

The invention relates to a fuel-cooled type evaporating pipe structure. The evaporating pipe structure is applicable to engines and combustion chamber components of other burners, a closed fuel cooling cavity is formed between an evaporating pipe inner sleeve and an evaporating pipe outer sleeve, a fuel inlet pipe extends into the fuel cooling cavity in the outlet section position of the evaporating pipe, at least one row of fuel nozzles evenly distributed in the circumferential direction are arranged along the inlet section of the evaporating pipe inner sleeve, grooves communicating with one another are formed in the outer surface of the evaporating pipe inner sleeve, and fuel is delivered to the outlet section from the inlet section of the fuel cooling cavity along the grooves and is sprayed into the evaporating pipe at the inlet section. According to the structure, the fuel arrives at the fuel nozzles at the inlet section of the evaporating pipe from the inner cavity of the outlet section of the evaporating pipe and cools the wall surface of the evaporating pipe, and thermal state ablation protection of the evaporating pipe is completed; each way of fuel is preheated independently, the preheating degree of the fuel is increased, and the evaporating and premixing effect of the fuel is enhanced. By the aid of the overall design, cooling protection of the evaporating pipe is realized, and the service life is prolonged; high-intensity preheating of the fuel is realized, and the evaporating and premixing degree is increased.

Description

technical field [0001] The invention belongs to the technical field with combustion characteristics, especially the technical field of gas turbine combustion chambers, and in particular relates to a fuel-cooled evaporation tube structure suitable for gas turbine combustion chambers. Background technique [0002] At present, gas turbines using evaporator tube combustion technology have been widely used. For example, AMT in the Netherlands, Rolls-Royce in the UK, Artesjet, etc. have a series of products. The structure of a certain type of aviation gas turbine combustor is as follows: figure 2 As shown, it consists of the front wall, inner wall, outer wall, evaporation tube and fuel nozzle of the flame tube. The evaporator tube is located in the combustion high-temperature zone. During long-term use, it is found that the outlet section and the transition section of the evaporator tube are overheated or even ablated, which seriously restricts the service life. [0003] The co...

AI Technical Summary

Problems solved by technology

[0003] The commonly used evaporator tube technology designs the fuel nozzle and the evaporator tube independently. The fuel directly enters the gas flow channel of the evaporator tube without passing through the heat exchange on the wall of the evaporator tube in advance. The wall of the evaporator tube is not cooled by fuel oil, resulting in Overheating or even ablation. At the same time, this method makes the fuel preheating effect poor. When entering the air flow channel, the temperature is low and the atomization is poor, resulting in a longer flame zone, smoke, and a decrease in combustion efficiency and flameout performance.

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