Fuel nozzle, combustor, gas turbine, and method of preventing fuel coking in fuel nozzle

Abstract

The invention relates to a fuel nozzle, a combustion chamber, a gas turbine and a method for preventing fuel coking in the fuel nozzle. Wherein the fuel nozzle comprises a nozzle rod core and a nozzle casing surrounding the nozzle rod core, the nozzle casing has a first casing for being arranged in the core compartment, a second casing for being arranged in the casing, and a connection with the casing. The middle casing fitted with the mounting hole, the radial gap between the nozzle casing and the nozzle rod core provides a cooling channel on the outer peripheral side of the nozzle rod core, the first casing has a cylindrical flow-around flow surface, The surface of the cylindrical flow-around flow pattern has a windward side and a leeward side relative to the air flow in the core compartment, the air intake holes of the cooling flow channel are arranged on the windward side, and the exhaust holes of the cooling flow channel are arranged on the leeward side. hole. The above-mentioned fuel nozzle has the advantages of simple structure, good cooling effect, low design and processing cost and the like.

Description

technical field [0001] The invention relates to a fuel nozzle, a combustion chamber, a gas turbine and a method for preventing fuel coking in the fuel nozzle. Background technique [0002] With the development of high-performance and high-pressure ratio aero-engines, the demand for using fuel as a coolant to cool the engine device increases rapidly, making the temperature of the fuel before entering the fuel nozzle rise as high as 100-140°C; at the same time, as the engine pressure ratio increases The air temperature at the inlet of the combustion chamber is also further increased, and the air temperature at the inlet of the combustion chamber of the first-stage engine with a thrust-to-weight ratio of 10 reaches above 800K, so that the oil temperature in the fuel nozzle and the wall temperature of the oil pipe continue to increase, resulting in The fuel is seriously deposited and coked, and attached to the inner wall. In severe cases, the nozzle will be partially blocked and...

AI Technical Summary

Problems solved by technology

[0002] With the development of high-performance and high-pressure ratio aero-engines, the demand for using fuel as a coolant to cool the engine device increases rapidly, making the temperature of the fuel before entering the fuel nozzle rise as high as 100-140°C; at the same time, as the engine pressure ratio increases The air temperature at the inlet of the combustion chamber is also further increased, and the air temperature at the inlet of the combustion chamber of the first-stage engine with a thrust-to-weight ratio of 10 reaches above 800K, so that the oil temperature in the fuel nozzle and the wall temperature of the oil pipe continue to increase, resulting in The fuel is seriously deposited and coked, and attached to the inner wall. In severe cases, it will partially block the nozzle and prevent the formation of the spray cone, resulting in a sharp deterioration in the quality of the fuel injection atomization.

Poor fuel atomization and unstable atomization quality will lead to difficulty and irregularity of combustion chamber ignition and joint flame, as well as reduction of combustion efficiency. Sometimes the instability of the fuel concentration field will lead to instability and deterioration of the gas temperature distribution at the outlet of the combustion chamber. In severe cases, it may cause burns to the flame tube, turbine guide and rotor blades

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