CN112460632A

CN112460632A - Radial grading partial premixing type gas fuel nozzle

Info

Publication number: CN112460632A
Application number: CN202011161297.1A
Authority: CN
Inventors: 张国强; 孙鹏; 任艳平; 冉军辉; 李雅军; 齐秀龙; 程旭
Original assignee: 703th Research Institute of CSIC
Current assignee: 703th Research Institute of CSIC
Priority date: 2020-10-27
Filing date: 2020-10-27
Publication date: 2021-03-09

Abstract

The invention aims to provide a radial grading partial premixing type gas fuel nozzle which comprises a main combustion path nozzle, a pilot combustion path nozzle, a flow guide cover and an extruder, wherein the pilot combustion path nozzle is fixed inside the main combustion path nozzle, the end part of the flow guide cover is installed on the end part of the extruder, one part of the main combustion path nozzle is arranged in a shell space formed by the flow guide cover and the extruder, the main combustion path nozzle is provided with a hole, a first-stage swirler and a second-stage swirler are arranged on the main combustion path nozzle behind the hole, the first-stage swirler and the second-stage swirler are positioned in the extruder, circumferential fuel holes are circumferentially distributed at an outlet of the pilot combustion path nozzle, and axial fuel holes with the same size are axially distributed at the outlet of the pilot combustion path nozzle. The fuel of the invention is supplied to the combustion area in two independent channels, which can better avoid the problems of fuel gas channel blockage and the like. The venturi can prevent the failure of the nozzle from being ablated by the tempering in the main combustion area. The secondary swirler improves the fuel consumption rate of the nozzle and provides help for the development of a large high-power gas turbine.

Description

Radial grading partial premixing type gas fuel nozzle

Technical Field

The invention relates to a gas turbine, in particular to a fuel nozzle of the gas turbine.

Background

With the rapid development of industrial modernization and diversification of energy types, gas turbine power devices are widely applied in the fields of ship propulsion, petrochemical industry, energy and power, oil and gas exploitation, distributed energy and the like. In recent years, due to the large amount of mining of fossil energy such as coal and petroleum, the problem of environmental pollution is becoming more severe, and the market demand for low-emission gas turbines has been promoted. The gas fuel has unique advantages, carbon dioxide and water are generated after combustion, and the gas fuel belongs to clean fuel, so most of low-emission gas turbines use the gas fuel, a combustion chamber is used as one of three major components of the gas turbine, the combustion chamber has the function of converting chemical energy of the fuel into heat energy, and the performance of the gas turbine can directly influence the performance of the whole engine. Fuel supply is an important ring for stable combustion of a combustion chamber of a gas turbine, and a fuel nozzle is an important link in the design of a low-emission combustion chamber for not only stably inputting fuel but also ensuring pulse-free combustion of the combustion chamber.

Disclosure of Invention

The invention aims to provide a radial grading partial premixing type gas fuel nozzle which can effectively reduce pollutant discharge and ensure pulse-free combustion so as to realize good combustion stability under low working conditions and can realize ultra-low discharge requirements under high working conditions.

The purpose of the invention is realized as follows:

the invention relates to a radial grading partial premixing type gas fuel nozzle, which is characterized in that: including burning way nozzle mainly, the way nozzle of igniting, the kuppe, the extruder, the way nozzle of igniting is fixed and is burning inside the way nozzle mainly, the tip of kuppe is installed on the tip of extruder, it sets up in the casing space that kuppe and extruder are constituteed to burn partly of way nozzle mainly, it sets up the hole on the way nozzle to burn mainly, set up first order swirler and second grade swirler on the way nozzle of burning mainly of hole rear, first order swirler and second grade swirler are located the extruder, the circumference fuel hole that distributes in the exit circumference of the way nozzle of igniting, the axial in its exit arranges the axial fuel hole of equidimension simultaneously.

The present invention may further comprise:

1. the air guide sleeve adopts a tapered spray pipe structure, and the extruder adopts a venturi tube structure.

2. The blades of the first-stage swirler and the second-stage swirler are arranged in a staggered mode, and blade fuel holes are uniformly distributed on the blades in a linear mode.

3. The non-premixed zone of the pilot fuel nozzle supplies fuel for diffusion combustion and the premixed zone of the main fuel nozzle supplies fuel for lean premixed combustion.

The invention has the advantages that: the fuel of the invention is supplied to the combustion area in two independent channels, the diameter of the fuel hole is larger, the fuel channel is convenient to clean, and the problems of fuel gas channel blockage and the like can be better avoided. The use of the venturi can better prevent the occurrence of the failure of the nozzle ablated by the tempering in the main combustion area. The use of the secondary swirler greatly improves the fuel consumption rate of the nozzle, which can provide beneficial help for the development of large and high-power gas turbines.

Drawings

FIG. 1 is a schematic structural view of the present invention;

fig. 2 is a left side view of the present invention.

Detailed Description

The invention will now be described in more detail by way of example with reference to the accompanying drawings in which:

referring to FIGS. 1-2, a radially staged partially premixed gas fuel nozzle of the present invention comprises: the gas fuel nozzle comprises a pilot fuel nozzle 1, a main fuel nozzle 2, a flow guide cover 3, a first-stage swirler 4, a second-stage swirler 5, an extruder 6 and the like. The matching surfaces between the pilot burner 1 and the main burner 2 are welded and assembled into a whole, and can be fixedly connected by other structures during specific use.

The gas fuel nozzle has 2 fuel gas delivery passages.

The non-premixed zone of pilot nozzle 1 is supplied with fuel, and the non-premixed fuel is used for diffusion combustion. The fuel holes are circumferentially distributed at the outlet of the

pilot combustor nozzle

1, 1 fuel hole with the same size is axially arranged, the purpose of setting diffusion combustion can ensure pulse-free combustion of the combustion chamber, and the temperature of a main combustion area of the combustion chamber is effectively reduced, so that the emission is reduced.

Fuel is supplied to the premixed zone of the main fuel nozzle 2, and the premixed fuel is used for lean premixed combustion. A certain number of fuel holes are linearly and uniformly distributed on the I-level swirler 4 and the II-level swirler 5, so that gas fuel and air can be premixed, the heat efficiency of the fuel is improved, and the fuel is fully combusted.

Generally, diffusion combustion can improve combustion stability under low operating conditions, while premixed combustion can improve combustion efficiency. The two combustion modes are matched with each other to ensure the stable combustion of the combustion chamber of the gas turbine.

The dome 3 constitutes an oxidant delivery channel. The air guide sleeve 3 adopts a tapered nozzle structure, and the flowing speed of gas is increased when the subsonic flow oxidant flows through the tapered nozzle, so that the effect of accelerating mixing with fuel is achieved.

The extruder 6 adopts a venturi structure for accelerating the flow rate of the fuel-oxidizer admixture and for another purpose of preventing flame flashback in the center region.

Claims

1. A radially staged partially premixed gas fuel nozzle, characterized by: including burning way nozzle mainly, the way nozzle of igniting, the kuppe, the extruder, the way nozzle of igniting is fixed and is burning inside the way nozzle mainly, the tip of kuppe is installed on the tip of extruder, it sets up in the casing space that kuppe and extruder are constituteed to burn partly of way nozzle mainly, it sets up the hole on the way nozzle to burn mainly, set up first order swirler and second grade swirler on the way nozzle of burning mainly of hole rear, first order swirler and second grade swirler are located the extruder, the circumference fuel hole that distributes in the exit circumference of the way nozzle of igniting, the axial in its exit arranges the axial fuel hole of equidimension simultaneously.

2. A radially staged partially premixed gas fuel nozzle as claimed in claim 1, wherein: the air guide sleeve adopts a tapered spray pipe structure, and the extruder adopts a venturi tube structure.

3. A radially staged partially premixed gas fuel nozzle as claimed in claim 2, wherein: the blades of the first-stage swirler and the second-stage swirler are arranged in a staggered mode, and blade fuel holes are uniformly distributed on the blades in a linear mode.

4. A radially staged partially premixed gas fuel nozzle as claimed in claim 3, wherein: the non-premixed zone of the pilot fuel nozzle supplies fuel for diffusion combustion and the premixed zone of the main fuel nozzle supplies fuel for lean premixed combustion.