Ignition electric nozzle integrated with fuel nozzle at head of combustion chamber of gas turbine

Abstract

The invention belongs to the technical field of gas turbine combustion chamber design, and particularly relates to an ignition electric nozzle of a gas turbine combustion chamber head integrated fuel nozzle, which comprises an ignition electric nozzle mounting cylinder, a plurality of fuel injection holes inclined outwards, fuel injection holes inclined inwards and a plurality of ignition electric nozzles, each outward inclined fuel spray hole is positioned on the outer side of the inward inclined fuel spray hole; the fuel connecting nozzle is connected to the side wall of the front end of the sparking plug mounting cylinder, and the outward inclined fuel spraying holes and the inward inclined fuel spraying holes are communicated through fuel channels in the side wall of the sparking plug mounting cylinder; and the ignition electric nozzle is connected in the front end of the ignition electric nozzle mounting cylinder, and the end part extends into the rear end of the ignition electric nozzle mounting cylinder.

Description

Technical Field

[0001] The present application belongs to the technical field of gas turbine combustion chamber design, and in particular relates to an ignition nozzle with an integrated fuel nozzle in the head of a gas turbine combustion chamber. Background Art

[0002] In order to reduce pollutant emissions, gas turbine combustion chambers generally adopt the technical solution of lean premixed staged combustion. The combustion chamber flame tube is larger in size, and the combustion chamber ignition of the conventional ignition nozzle arrangement scheme is more difficult. In this regard, at present, the ignition nozzle is mostly set on the wall of the flame tube, perpendicular to the axis of the swirler at the head of the combustion chamber. This technical solution design still has the problem that the fuel is difficult to diffuse to the vicinity of the ignition nozzle for flame tubes with larger cross-sectional dimensions, the fuel concentration near the ignition nozzle is low, and ignition is not easy to succeed. In addition, the end of the ignition nozzle is in direct contact with the hot combustion gas in the flame tube and is easily burned.

[0003] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0004] The purpose of the present application is to provide an ignition nozzle with an integrated fuel nozzle in a combustion chamber head of a gas turbine, so as to overcome or alleviate at least one of the technical defects of the known ones.

[0005] The technical solution of this application is:

[0006] An ignition nozzle with an integrated fuel nozzle in the head of a gas turbine combustion chamber, comprising:

[0007] The nozzle mounting cylinder has a plurality of outwardly inclined fuel spray holes and inwardly inclined fuel spray holes distributed along the circumferential direction at the rear end, and each outwardly inclined fuel spray hole is located outside the inwardly inclined fuel spray hole;

[0008] A fuel nozzle is connected to the side wall at the front end of the nozzle mounting tube, and is connected to each outwardly inclined fuel spray hole and the inwardly inclined fuel spray hole through a fuel channel in the side wall of the nozzle mounting tube;

[0009] The ignition nozzle is connected to the front end of the nozzle mounting tube, and the end portion extends to the rear end of the nozzle mounting tube.

[0010] Optionally, in the above-mentioned ignition nozzle with integrated fuel nozzle in the combustion chamber head of the gas turbine, the front end outer wall of the nozzle mounting tube has an annular connecting edge.

[0011] Optionally, in the above-mentioned ignition nozzle with integrated fuel nozzle in the combustion chamber head of the gas turbine, the outwardly inclined fuel spray holes and the inwardly inclined fuel spray holes on the rear end of the nozzle mounting tube are staggered in the circumferential direction.

[0012] Optionally, in the above-mentioned ignition nozzle of the integrated fuel nozzle in the combustion chamber head of the gas turbine, an annular limit platform is provided inside the rear end of the nozzle mounting tube, the inner side of the annular limit platform has a plurality of radial cooling holes distributed along the circumferential direction, the outer side of the annular limit platform has a plurality of axial cooling holes distributed along the circumferential direction, and the inner side of the annular limit platform has an annular cooling cavity connecting the radial cooling holes and the axial cooling holes;

[0013] An air vent is provided on the outer wall of the nozzle installation tube, and the air vent is connected to the annular cooling cavity through a cooling channel in the side wall of the nozzle installation tube.

[0014] Optionally, in the above-mentioned ignition nozzle with integrated fuel nozzle in the gas turbine combustion chamber head, the ignition nozzle is threadedly connected to the front end of the nozzle mounting tube, cooperates with the stopper between the end of the nozzle mounting tube, and a gasket is arranged at the stopper position. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of an ignition nozzle of an integrated fuel nozzle in a combustion chamber head of a gas turbine provided in an embodiment of the present application;

[0016] Figure 2 It is a partial schematic diagram of an ignition nozzle of an integrated fuel nozzle in a combustion chamber head of a gas turbine provided in an embodiment of the present application;

[0017] Figure 3 yes Figure 2 lateral view of;

[0018] in:

[0019] 1-Electric nozzle mounting tube; 2-Fuel nozzle; 3-Ignition electric nozzle; 4-Gasket;

[0020] A-outwardly inclined fuel spray hole; B-inwardly inclined fuel spray hole; C-radial cooling hole; D-axial cooling hole; E-vent hole.

[0021] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0022] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0023] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0024] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0025] An ignition nozzle with an integrated fuel nozzle in the combustion chamber head of a gas turbine, such as Figure 1 As shown, it includes an electric nozzle mounting tube 1, a fuel nozzle 2, an ignition electric nozzle 3, and a gasket 4.

[0026] The front end outer wall of the nozzle mounting tube 1 has an annular connecting edge.

[0027] The rear end of the nozzle mounting tube 1 has a plurality of outwardly inclined fuel spray holes A and inwardly inclined fuel spray holes B distributed along the circumferential direction, each outwardly inclined fuel spray hole A is located outside the inwardly inclined fuel spray hole B, and each outwardly inclined fuel spray hole A and inwardly inclined fuel spray hole B are staggered in the circumferential direction, such as Figure 2-Figure 3 shown.

[0028] The rear end of the nozzle mounting tube 1 is provided with an annular stopper, the inner side of the annular stopper has a plurality of radial cooling holes C distributed along the circumferential direction, the outer side of the annular stopper has a plurality of axial cooling holes D distributed along the circumferential direction, and the inner side of the annular stopper has an annular cooling cavity connecting the radial cooling holes C and the axial cooling holes D, such as Figure 2-Figure 3 shown.

[0029] An air vent E is provided on the outer wall of the nozzle mounting tube 1 , and the air vent E is connected to the annular cooling cavity through a cooling channel in the side wall of the nozzle mounting tube 1 .

[0030] The fuel nozzle 2 is connected to the side wall of the front end of the nozzle mounting tube 1, and is connected to each outwardly inclined fuel spray hole A and the inwardly inclined fuel spray hole B through a fuel channel in the side wall of the nozzle mounting tube 1.

[0031] The ignition nozzle 3 is threadedly connected to the front end of the nozzle mounting tube 1, and is matched with the stopper between the end of the nozzle mounting tube 1, and a gasket 4 is arranged at the stopper position, and the axial clearance between the ignition nozzle 3 and the annular limit platform can be controlled by the gasket 4 of different thicknesses, such as Figure 2 shown.

[0032] The ignition nozzle with integrated fuel nozzle in the combustion chamber head of the gas turbine disclosed in the above embodiment has a fuel nozzle integrated in the ignition nozzle. In specific applications, it can be set in the combustion chamber head. Specifically, the rear end of the nozzle mounting tube 1 passes through the mounting hole at the front end of the combustion chamber casing and extends into the mounting hole at the front end of the flame tube. The front end is exposed outside the front end of the combustion chamber casing and is connected to the front end of the combustion chamber casing by an annular connecting edge. The vent E is located between the combustion chamber casing and the front end of the flame tube, and multiple vents can be arranged along the circumferential direction of the combustion chamber head. When working, fuel can flow in through the fuel nozzle 2, and the fuel in the side wall of the nozzle mounting tube 1 can be discharged. The fuel is sprayed through each outwardly inclined fuel nozzle A and inwardly inclined fuel nozzle B, wherein the fuel sprayed through each outwardly inclined fuel nozzle A can be sprayed to the recirculation zone in the flame tube to increase the fuel concentration in the recirculation zone, and the fuel sprayed through each inwardly inclined fuel nozzle B will increase the fuel concentration near the end of the ignition nozzle 3, thereby improving the ignition success rate of the ignition nozzle 3, and easily igniting the recirculation zone to organize combustion. In addition, the fuel sprayed from each outwardly inclined fuel nozzle A has little effect on the shape of the recirculation zone in the flame tube, which can ensure the stability of the recirculation zone in the flame tube and the stability of the flame.

[0033] The ignition nozzle with integrated fuel nozzle in the combustion chamber head of the gas turbine disclosed in the above embodiment, when working, the air in the combustion chamber casing can flow in through the vent hole E on the side wall of the nozzle mounting tube 1, pass through the fuel channel in the side wall and the annular cooling cavity, and be ejected from the radial cooling hole C and the axial cooling hole D. The air ejected from the radial cooling hole C can be provided to the ignition nozzle 3 for ignition ionization, and can cool the end of the ignition nozzle 3 to prevent the end of the ignition nozzle 3 from being burned. The air ejected from the axial cooling hole D can blow the flame in the flame tube backwards, thereby further cooling the end of the ignition nozzle 3 to prevent the end of the ignition nozzle 3 from being burned.

[0034] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. An ignition nozzle with an integrated fuel nozzle in the combustion chamber head of a gas turbine, characterized in that: include: The nozzle mounting cylinder (1) has a rear end portion having a plurality of outwardly inclined fuel spray holes (A) and inwardly inclined fuel spray holes (B) distributed along the circumferential direction, wherein each outwardly inclined fuel spray hole (A) is located outside the inwardly inclined fuel spray hole (B); A fuel nozzle (2) is connected to the side wall at the front end of the nozzle mounting tube (1) and is connected to each outwardly inclined fuel spray hole (A) and the inwardly inclined fuel spray hole (B) through a fuel channel in the side wall of the nozzle mounting tube (1); The ignition nozzle (3) is connected to the front end of the nozzle mounting tube (1), and the end portion extends to the rear end of the nozzle mounting tube (1).

2. The ignition nozzle of the integrated fuel nozzle in the combustion chamber head of the gas turbine according to claim 1, characterized in that: The front end outer wall of the nozzle mounting tube (1) is provided with an annular connecting edge.

3. The ignition nozzle of the integrated fuel nozzle in the combustion chamber head of the gas turbine according to claim 1, characterized in that: The outwardly inclined fuel spray holes (A) and the inwardly inclined fuel spray holes (B) on the rear end of the nozzle mounting tube (1) are staggeredly distributed in the circumferential direction.

4. The ignition nozzle of the integrated fuel nozzle in the combustion chamber head of the gas turbine according to claim 1, characterized in that: The rear end of the nozzle mounting tube (1) is provided with an annular stopper, the inner side of the annular stopper is provided with a plurality of radial cooling holes (C) distributed along the circumferential direction, the outer side of the annular stopper is provided with a plurality of axial cooling holes (D) distributed along the circumferential direction, and the inner side of the annular stopper is provided with an annular cooling cavity connecting the radial cooling holes (C) and the axial cooling holes (D); An air vent (E) is provided on the outer wall of the nozzle mounting cylinder (1), and the air vent (E) is connected to the annular cooling cavity through a cooling channel in the side wall of the nozzle mounting cylinder (1).

5. The ignition nozzle of the integrated fuel nozzle in the combustion chamber head of the gas turbine according to claim 1, characterized in that: The ignition nozzle (3) is threadedly connected to the front end of the nozzle mounting tube (1) and is matched with a stopper at the end of the nozzle mounting tube (1), and a gasket (4) is arranged at the stopper.

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