Method and structure for improving ignition performance of combustion chamber in low-temperature environment

Abstract

The invention provides a method and structure for improving ignition performance of a combustion chamber in a low-temperature environment, and belongs to the technical field of gas turbines.The method adopts a multi-nozzle annular combustion chamber which comprises an annular fuel oil main pipe and a first nozzle connected with the fuel oil main pipe; one or more ignition electric nozzles are arranged in the axial direction close to the first nozzle, the second nozzles are arranged on the two sides of each ignition electric nozzle respectively, the atomization performance of the second nozzles is higher than that of the first nozzle, and the ignition performance of the combustion chamber in the low-temperature environment is improved by improving the atomization quality of the fuel nozzles close to the ignition electric nozzles.

Description

Technical Field

[0001] The present application belongs to the field of gas turbines, and in particular relates to a method and structure for improving the ignition performance of a combustion chamber under a low temperature environment. Background Art

[0002] For the combustion chamber of the gas engine of a modified aircraft ship that uses diesel, since the freezing point of diesel is lower than that of aviation kerosene and the viscosity is greater, it causes difficulty in ignition of the combustion chamber under low temperature conditions.

[0003] In order to solve the above problems, there are usually two solutions in the prior art. One is to heat the fuel, and the other is to set a flow-enhancing nozzle near the ignition nozzle to improve the ignition performance and make ignition easier.

[0004] Among them, for the fuel heating technical solution, it is necessary to set up an additional fuel heating device, usually an electric heating device, which will increase the cost. For ships, the fuel heating device will also occupy the limited space on the ship and increase the power of the ship's generator. These problems make the fuel heating technical solution very inconvenient to use on ships; in addition, due to the limitations of the power of the generator and the capacity of the heating device, the amount of fuel heating is generally small, which results in poor improvement of the ignition performance by fuel heating.

[0005] With regard to the technical solution of setting a flow-enhancing nozzle near the ignition nozzle, the setting of the flow-enhancing nozzle will lead to uneven circumferential distribution of the fuel flow in the fuel main pipe, especially in the low-operating range of the gas turbine, where the uneven circumferential distribution of the fuel flow in the fuel main pipe is more serious, resulting in a larger high-temperature area at the combustion chamber outlet, causing the problem of ablation of the turbine blades, and affecting the safe operation of the gas turbine. Summary of the invention

[0006] The purpose of the present application is to provide a method and structure for improving the ignition performance of a combustion chamber in a low temperature environment, so as to solve or alleviate at least one problem in the background technology.

[0007] On the one hand, the technical solution of the present application is: a method for improving the ignition performance of a combustion chamber under a low temperature environment, the method adopts a multi-nozzle annular combustion chamber, the multi-nozzle annular combustion chamber includes an annular fuel main pipe and a first nozzle connected to the fuel main pipe, one or more ignition nozzles are arranged in the axial direction near the first nozzle, and second nozzles are arranged on both sides of the ignition nozzle respectively, the atomization performance of the second nozzle is stronger than that of the first nozzle, and the ignition performance of the combustion chamber under a low temperature environment is improved by improving the atomization quality of the fuel nozzle near the ignition nozzle.

[0008] In a preferred embodiment of the present application, a vortex finder is provided inside the nozzle of the second nozzle, and a plurality of grooves are provided in the circumferential direction of the vortex finder, and the flow area of ​​the grooves is 70% to 90% of the flow area of ​​the first nozzle.

[0009] In a preferred embodiment of the present application, a circular hole is provided at the nozzle of the second nozzle, and the diameter of the circular hole is 50% to 80% of the flow area of ​​the first nozzle 13 .

[0010] On the other hand, the technical solution of the present application is: a structure for improving the ignition performance of a combustion chamber under a low temperature environment, comprising a multi-nozzle annular combustion chamber, wherein the multi-nozzle annular combustion chamber comprises an annular fuel manifold and a plurality of first nozzles connected to the fuel manifold, and one or more ignition electric nozzles are arranged axially near the first nozzles on the multi-nozzle annular combustion chamber, and a second nozzle with better atomization quality than the first nozzle is arranged on both sides of each ignition electric nozzle.

[0011] In a preferred embodiment of the present application, the end of the second nozzle forms a nozzle, a vortexer is provided inside the nozzle, and a plurality of grooves are provided in the circumferential direction of the vortexer, the axis of the groove does not pass through the center of the swirler, and the flow area of ​​the groove is 70% to 90% of the flow area of ​​the first nozzle.

[0012] In a preferred embodiment of the present application, a circular hole is provided at the nozzle of the second nozzle, and the diameter of the circular hole is 50% to 80% of the flow area of ​​the first nozzle.

[0013] The method and structure provided in the present application do not require the addition of additional equipment such as a fuel heating device, will not increase costs, and will not cause the problem of turbine blade ablation due to local high temperature at the combustion chamber outlet, thereby ensuring the safe operation of the gas turbine. By improving the atomization quality of the fuel nozzle near the ignition nozzle, the ignition performance of the combustion chamber under low-temperature conditions can be improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0015] Figure 1 Schematic diagram of the annular combustion chamber structure in this application

[0016] Figure 2 This is the fuel main pipe and nozzle structure in this application.

[0017] Figure 3 This is a diagram of the nozzle vortexer and nozzle structure in this application.

[0018] Figure 4 This is the distribution diagram of the channels on the nozzle vortex finder in this application.

[0019] Reference numerals:

[0020] 10-Multi-nozzle annular combustion chamber

[0021] 11-Ignition

[0022] 12-Fuel main pipe

[0023] 13-First nozzle

[0024] 14-Second nozzle

[0025] 15- Nozzle

[0026] 16-round hole

[0027] 17-Vortex

[0028] 18-Slot DETAILED DESCRIPTION

[0029] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0030] In order to solve the problem of difficulty in combustion chamber ignition under low temperature environment conditions, without adding additional equipment such as fuel heating devices, and also without the problem of high local temperature at the combustion chamber outlet causing turbine blade ablation, the present application provides a method and structure for improving the ignition performance of the combustion chamber under low temperature environment conditions.

[0031] The method provided in the present application for improving the ignition performance of a combustion chamber under low temperature environment conditions comprises the following contents: a multi-nozzle annular combustion chamber 10 is adopted, wherein the multi-nozzle annular combustion chamber 10 comprises an annular fuel main pipe 12 and a first nozzle 13 connected to the fuel main pipe 12, wherein one or more ignition electric nozzles 11 are arranged near the axial direction of the first nozzle 13; second nozzles 14 are arranged on both sides of the ignition electric nozzle 11, respectively, and the atomization performance of the second nozzle 14 is stronger than that of the first nozzle 13, and the ignition performance of the combustion chamber under low temperature environment is improved by improving the atomization quality of the fuel nozzle near the ignition electric nozzle.

[0032] Furthermore, a vortex finder 16 is provided inside the nozzle 15 of the second nozzle 14 . The vortex finder 16 is provided with a plurality of grooves 18 in the circumferential direction. The flow area of ​​the grooves is 70% to 90% of the flow area of ​​the first nozzle 13 .

[0033] Furthermore, the nozzle 15 of the second nozzle 14 is provided with a circular hole 17 , and the diameter of the circular hole 17 is 50% to 80% of the flow area of ​​the first nozzle 13 .

[0034] On this basis, if Figure 1 and Figure 2As shown, the structure for improving the ignition performance of the combustion chamber under low temperature environment provided by the present application includes: a multi-nozzle annular combustion chamber 10, the multi-nozzle annular combustion chamber 10 includes an annular fuel main pipe 12 and a plurality of first nozzles 13 connected to the fuel main pipe 12, the first nozzle 13 is a conventional nozzle, and one or more ignition electric nozzles 11 are arranged near the axial direction of the first nozzle 13. A second nozzle 14 with better atomization quality than the first nozzle 13 is arranged on both sides of each ignition electric nozzle 11.

[0035] like Figure 3 As shown, the end of the second nozzle 14 forms a nozzle 15, and a vortex finder 16 is arranged inside the nozzle 15. The vortex finder 16 is provided with a plurality of grooves 18 in the circumferential direction. The axis of the groove 18 does not pass through the center of the swirler. The flow area of ​​the groove 18 is 70% to 90% of the flow area of ​​the first nozzle 13. Therefore, compared with the conventional first nozzle 13, the flow area of ​​the groove (6) on the vortex finder (5) of the second nozzle 14 with better atomization quality is reduced by 10% to 30%.

[0036] like Figure 4 As shown, the nozzle 15 of the second nozzle 14 is provided with a circular hole 17, the diameter of which is 50% to 80% of the flow area of ​​the first nozzle 13, so that the diameter of the circular hole 17 on the nozzle 15 of the second nozzle 14 with better atomization quality is reduced by 20% to 50%.

[0037] The method and structure provided in the present application do not require the addition of additional equipment such as a fuel heating device, will not increase costs, and will not cause the problem of turbine blade ablation due to local high temperature at the combustion chamber outlet, thereby ensuring the safe operation of the gas turbine. By improving the atomization quality of the fuel nozzle near the ignition nozzle, the ignition performance of the combustion chamber under low-temperature conditions can be improved.

[0038] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for improving the ignition performance of a combustion chamber under a low temperature environment, characterized in that: The method adopts a multi-nozzle annular combustion chamber, wherein the multi-nozzle annular combustion chamber (10) comprises an annular fuel main pipe (12) and a first nozzle (13) connected to the fuel main pipe (12), one or more ignition nozzles (11) are arranged in the axial direction close to the first nozzle (13), and second nozzles (14) are arranged on both sides of the ignition nozzle (11), respectively, and the atomization performance of the second nozzle (14) is stronger than that of the first nozzle (13). By improving the atomization quality of the fuel nozzle near the ignition nozzle (11), the ignition performance of the combustion chamber in a low temperature environment is improved.

2. The method for improving the ignition performance of a combustion chamber under a low temperature environment according to claim 1, characterized in that: A vortex finder (16) is provided inside the nozzle (15) of the second nozzle (14). The vortex finder (16) is provided with a plurality of grooves (18) in the circumferential direction. The flow area of ​​the grooves is 70% to 90% of the flow area of ​​the first nozzle (13).

3. The method for improving the ignition performance of a combustion chamber under a low temperature environment as claimed in claim 2, characterized in that: The nozzle (15) of the second nozzle (14) is provided with a circular hole (17), and the diameter of the circular hole (17) is 50% to 80% of the flow area of ​​the first nozzle (13).

4. A structure for improving the ignition performance of a combustion chamber under low temperature conditions, characterized in that: The structure comprises a multi-nozzle annular combustion chamber (10), wherein the multi-nozzle annular combustion chamber (10) comprises an annular fuel main pipe (12) and a plurality of first nozzles (13) connected to the fuel main pipe (12); one or more ignition nozzles (11) are arranged axially close to the first nozzles (13) on the multi-nozzle annular combustion chamber (10); and a second nozzle (14) having a better atomization quality than the first nozzle (13) is arranged on both sides of each ignition nozzle (11).

5. The structure for improving the ignition performance of the combustion chamber under low temperature environment as claimed in claim 4, characterized in that: The end of the second nozzle (14) forms a nozzle (15), and a vortex finder (16) is provided inside the nozzle (15). The vortex finder (16) is provided with a plurality of grooves (18) in the circumferential direction, and the axis of the groove (18) does not pass through the center of the vortex finder. The flow area of ​​the groove (18) is 70% to 90% of the flow area of ​​the first nozzle (13).

6. The structure for improving the ignition performance of the combustion chamber under low temperature environment as claimed in claim 5, characterized in that: The nozzle (15) of the second nozzle (14) is provided with a circular hole (17), and the diameter of the circular hole (17) is 50% to 80% of the flow area of ​​the first nozzle (13).

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