A porous hydrogen-doped combustion nozzle for a gas turbine and a gas turbine

Abstract

The embodiment of the present disclosure provides a porous hydrogen-doped combustion nozzle suitable for a gas turbine and the gas turbine, the nozzle comprising: a nozzle body, internally provided with a pre-combustion stage channel and a main combustion stage channel, the pre-combustion stage channel being provided with a plurality of pre-combustion stage injection holes at an outlet end of the nozzle body; and the main combustion stage channel being provided with a plurality of main combustion stage injection holes at an outlet end of the nozzle body, the main combustion stage injection holes being annularly arranged outside a periphery of the pre-combustion stage injection holes. In the present application, the double-stage porous structure of the main combustion stage injection holes and the pre-combustion stage injection holes effectively suppresses the risk of rapid backfire of hydrogen fuel.

Description

Technical Field

[0001] The embodiments disclosed herein belong to the field of gas equipment technology, specifically relating to a multi-hole hydrogen-blended combustion nozzle suitable for gas turbines and a gas turbine. Background Technology

[0002] With the accelerated advancement of dual-carbon goals and the rapid transformation of the energy structure, gas turbine power generation technology needs to shift towards a clean and low-carbon direction. Therefore, hydrogen blending combustion in gas turbines is the future development direction of advanced gas turbine technology.

[0003] However, compared to traditional natural gas fuel, hydrogen fuel has characteristics such as higher adiabatic flame temperature, shorter ignition delay time, and faster flame propagation speed, which makes it very easy for backfire to occur in gas turbines during the combustion of hydrogen-fuel mixtures.

[0004] Therefore, how to solve the above problems has become a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] The embodiments disclosed herein aim to at least solve one of the technical problems existing in the prior art, and provide a porous hydrogen-blended combustion nozzle and a gas turbine suitable for gas turbines.

[0006] A first aspect of the embodiments of this disclosure provides a porous hydrogen-infused combustion nozzle suitable for a gas turbine, comprising: The nozzle body has a pre-combustion stage channel and a main combustion stage channel inside. The outlet end of the pre-combustion stage channel has multiple pre-combustion stage nozzle holes on the outlet surface of the nozzle body. The outlet end of the main combustion stage channel has multiple main combustion stage nozzle holes arranged around the periphery of the multiple pre-combustion stage nozzle holes on the outlet surface.

[0007] Optionally, the plurality of pre-combustion stage nozzles and the plurality of main combustion stage nozzles are arranged alternately on the outlet surface.

[0008] Optionally, the diameter of the pre-combustion stage nozzle is smaller than the diameter of the main combustion stage nozzle.

[0009] Optionally, the pre-combustion stage channel is used to introduce a first fuel, and the main combustion stage channel is used to introduce a second fuel; wherein the hydrogen blending ratio of the first fuel is lower than that of the second fuel.

[0010] Optionally, the pre-combustion stage nozzle includes a central pre-combustion nozzle and a plurality of outer ring pre-combustion nozzles arranged around the central pre-combustion nozzle.

[0011] Optionally, the outlet edge of the pre-combustion stage nozzle is further provided with a turbulence protrusion for disrupting the flame flow field.

[0012] Optionally, the turbulence protrusion is arc-shaped.

[0013] Furthermore, it also includes a hydrogen delivery pipeline connected to the inlet of the pre-combustion stage channel, and a natural gas-hydrogen mixed delivery pipeline connected to the inlet of the main combustion stage channel.

[0014] Optionally, the hydrogen delivery pipeline is equipped with a flow regulating valve for adjusting the hydrogen flow rate.

[0015] A second aspect of the embodiments of this disclosure provides a gas turbine including a porous hydrogen-infused combustion nozzle as described above.

[0016] The beneficial effects of the embodiments of this disclosure include: In this application, a two-stage porous structure of main combustion stage nozzle 11 + pre-combustion stage nozzle 12 is adopted, which effectively suppresses the risk of rapid backfire of hydrogen fuel. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of a porous hydrogen-infused combustion nozzle suitable for a gas turbine, according to an embodiment of the present disclosure.

[0018] In the figure, 1 is the nozzle body; 11 is the main combustion stage nozzle; 12 is the pre-combustion stage nozzle; 13 is the turbulence boss; 14 is the outlet surface; 121 is the outer ring pre-combustion hole; and 122 is the center pre-combustion hole. Detailed Implementation

[0019] To enable those skilled in the art to better understand the technical solutions of this disclosure, the disclosure will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0020] The embodiments of this application will be further described in detail below with reference to the accompanying drawings and examples. The detailed descriptions and accompanying drawings of the following embodiments are used to exemplarily illustrate the principles of this application, but should not be used to limit the scope of this application; that is, this application is not limited to the described embodiments. In the description of this application, it should be noted that, unless otherwise stated, "a plurality of" means two or more; the terms "upper," "lower," "left," "right," "inner," "outer," etc., indicating orientation or positional relationships are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. "Vertical" is not strictly vertical, but within the allowable error range. "Parallel" is not strictly parallel, but within the allowable error range.

[0021] In the description of this application, it should also be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this application depending on the specific circumstances.

[0022] like Figure 1 As shown, a multi-hole hydrogen-blending combustion nozzle suitable for gas turbines includes: The nozzle body 1 has a pre-combustion stage channel and a main combustion stage channel inside. The outlet end of the pre-combustion stage channel has a plurality of pre-combustion stage nozzle holes 12 on the outlet surface 14 of the nozzle body 1. The outlet end of the main combustion stage channel has a plurality of main combustion stage nozzle holes 11 arranged around the periphery of the plurality of pre-combustion stage nozzle holes 12 on the outlet surface 14.

[0023] In this application, a two-stage porous structure of main combustion stage nozzle 11 + pre-combustion stage nozzle 12 is adopted, which effectively suppresses the risk of rapid backfire of hydrogen fuel.

[0024] In some embodiments, the plurality of pre-combustion stage nozzles 12 and the plurality of main combustion stage nozzles 11 are arranged alternately on the outlet surface 14. This design can enhance fuel mixing and suppress the risk of backfire.

[0025] In some embodiments, the diameter of the pre-combustion stage nozzle 12 is smaller than the diameter of the main combustion stage nozzle 11. This design can refine fuel staged injection and optimize mixing and backfire prevention.

[0026] In some embodiments, the pre-combustion stage channel is used to introduce a first fuel, and the main combustion stage channel is used to introduce a second fuel. The hydrogen blending ratio of the first fuel is lower than that of the second fuel. This design allows for staged control of the combustion process, with low-hydrogen flame stabilization, high-hydrogen main combustion, and reduced risk of backfire.

[0027] In some embodiments, the pre-combustion stage nozzle 12 includes a central pre-combustion nozzle and a plurality of outer ring pre-combustion nozzles arranged around the periphery of the central pre-combustion nozzle.

[0028] In some embodiments, the outlet edge of the pre-combustion nozzle 12 is further provided with a turbulence protrusion 13 for disrupting the flame flow field.

[0029] In some embodiments, the turbulence protrusion 13 is arc-shaped.

[0030] In some embodiments, the system also includes a hydrogen delivery pipeline connected to the inlet of the pre-combustion stage channel and a natural gas-hydrogen mixed delivery pipeline connected to the inlet of the main combustion stage channel.

[0031] In some embodiments, the hydrogen delivery pipeline is equipped with a flow regulating valve for adjusting the flow rate of hydrogen.

[0032] In this application, the pre-combustion stage nozzle 12 and the main combustion stage nozzle 11 constitute a two-stage multi-hole staged injection. Combined with the turbulence protrusion 13 structure, it can realize the stratified mixing and combustion of hydrogen and natural gas, and reduce the risk of backfire.

[0033] A second aspect of the embodiments of this disclosure provides a gas turbine including a porous hydrogen-infused combustion nozzle as described above.

[0034] Specifically, this application designs the nozzle body 1 as a two-stage porous structure consisting of a main combustion stage nozzle and a pre-combustion stage nozzle. The pre-combustion stage nozzle 12 is designed with fine holes for injecting hydrogen (low hydrogen blending ratio), while the main combustion stage nozzle 11 is designed with coarse holes for injecting a natural gas-hydrogen mixture (high hydrogen blending ratio). The pre-combustion stage nozzle 12 and the main combustion stage nozzle 11 are arranged concentrically, with the pre-combustion stage nozzle 12 located inside the main combustion stage nozzle 11. A turbulence-delaying protrusion 13 is provided at the outlet of the pre-combustion stage nozzle 12 to delay the hydrogen flame propagation speed.

[0035] The nozzle body 1 is cylindrical, and its outlet surface 14 is provided with a pre-combustion stage nozzle 12 (inner layer) and a main combustion stage nozzle 11 (outer layer), which are arranged coaxially.

[0036] The pre-combustion stage channel adopts a small-diameter design. Four outer ring pre-combustion nozzles 121 are arranged in a ring on the outlet face 14 of the nozzle body 1. The central pre-combustion nozzle 122 is coaxially aligned with the nozzle body 1 and located at the center of the outlet face 14. The pre-combustion stage channel is connected to a hydrogen delivery pipeline, which is equipped with a flow regulating valve. The fuel within the pre-combustion stage channel uses a low hydrogen blending ratio to ensure stable combustion.

[0037] The main combustion stage channel has eight coarse injection holes 11 evenly distributed on the outlet surface 14. The main combustion stage injection holes 11 and the pre-combustion stage injection holes 12 are arranged alternately. The main combustion stage channel is connected to the natural gas-hydrogen mixed transportation pipeline.

[0038] Four arc-shaped baffles 13 are set at the edge of the pre-combustion stage nozzle 12 outlet to disrupt the hydrogen flame flow field of the pre-combustion stage, prevent the flame from sticking to the wall and back, and avoid the flame from directly entering the main combustion stage channel and causing backfire. At the same time, it enhances the fuel mixing ability and can effectively uniformize the temperature field.

[0039] This application employs a multi-hole injection method to mix fuel and oxidizer within a micro-scale channel. The micro-scale jet exhibits a flame quenching effect, and the micro-scale nozzles significantly increase the jet velocity at the nozzle exit, thus effectively reducing the risk of backfire. Simultaneously, the enhanced mixing near the nozzle can reduce NOx emissions to some extent.

[0040] It is understood that the above embodiments are merely exemplary embodiments used to illustrate the principles of this disclosure, and this disclosure is not limited thereto. For those skilled in the art, various modifications and improvements can be made without departing from the spirit and substance of this disclosure, and these modifications and improvements are also considered to be within the scope of protection of this disclosure.

Claims

1. A multi-hole hydrogen-blending combustion nozzle suitable for gas turbines, characterized in that, include: The nozzle body has a pre-combustion stage channel and a main combustion stage channel inside. The outlet end of the pre-combustion stage channel has multiple pre-combustion stage nozzle holes on the outlet surface of the nozzle body. The outlet end of the main combustion stage channel has multiple main combustion stage nozzle holes arranged around the periphery of the multiple pre-combustion stage nozzle holes on the outlet surface.

2. The porous hydrogen-doped combustion nozzle according to claim 1, characterized in that, The pre-combustion stage nozzles and the main combustion stage nozzles are arranged alternately on the outlet surface.

3. The porous hydrogen-doped combustion nozzle according to claim 1, characterized in that, The diameter of the pre-combustion stage nozzle is smaller than the diameter of the main combustion stage nozzle.

4. The porous hydrogen-doped combustion nozzle according to claim 1, characterized in that, The pre-combustion stage channel is used to introduce a first fuel, and the main combustion stage channel is used to introduce a second fuel; wherein the hydrogen blending ratio of the first fuel is lower than that of the second fuel.

5. The porous hydrogen-doped combustion nozzle according to claim 1, characterized in that, The pre-combustion stage nozzle includes a central pre-combustion nozzle and a plurality of outer ring pre-combustion nozzles arranged around the central pre-combustion nozzle.

6. The porous hydrogen-doped combustion nozzle according to claim 1, characterized in that, The exit edge of the pre-combustion nozzle is also provided with a turbulence protrusion for disrupting the flame flow field.

7. The porous hydrogen-doped combustion nozzle according to claim 6, characterized in that, The turbulence protrusion is arc-shaped.

8. The porous hydrogen-doped combustion nozzle according to claim 1, characterized in that, It also includes a hydrogen delivery pipeline connected to the inlet of the pre-combustion stage channel, and a natural gas-hydrogen mixed delivery pipeline connected to the inlet of the main combustion stage channel.

9. The porous hydrogen-doped combustion nozzle according to claim 8, characterized in that, The hydrogen delivery pipeline is equipped with a flow regulating valve for adjusting the flow rate of hydrogen.

10. A gas turbine, characterized in that, Includes the porous hydrogen-doped combustion nozzle as described in any one of claims 1 to 9.

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