Fuel line, micro-premix combustion chamber and turbine engine

Abstract

The application discloses a fuel pipeline, a micro-premix combustion chamber and a turbine engine and relates to the technical field of aerospace. The fuel pipeline comprises a gas inlet pipe, a gas branch pipe, a gas nozzle and a combustion-supporting gas passage; a plurality of gas inlet ends of the gas branch pipe are in one-to-one communication with a plurality of gas outlets of the gas inlet pipe, and the gas branch pipe is arranged around the gas inlet pipe and forms a plurality of multi-layer polygonal micro-premix branch pipe units which are connected with each other and distributed from inside to outside; the combustion-supporting gas passage is in communication with the micro-premix combustion chamber, a plurality of gas inlet ports which are arranged at intervals are arranged on the combustion-supporting gas passage along the circumference of the combustion-supporting gas passage, each micro-premix branch pipe unit surrounds the combustion-supporting gas passage and is in one-to-one communication with the plurality of gas inlet ports on the outer periphery of the combustion-supporting gas passage through the plurality of gas nozzles. The hydrogen fuel pipeline structure of the micro-premix combustion chamber is improved, uniform gas inlet of the hydrogen fuel of the head of the micro-premix combustion chamber is realized, and the equivalence ratio of each micro-premix unit can be ensured to be neither too high nor too low.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a fuel pipeline, a micro-premixed combustion chamber and a turbine engine. BACKGROUND

[0002] Hydrogen fuel has great prospects as a clean and renewable energy source. The advantages and potential of applying hydrogen fuel to the field of aviation and gas turbine power are emerging. However, in terms of combustion performance, the hydrogen fuel has a very high mass heat value and a very high adiabatic flame temperature. Under the same equivalence ratio, the combustion temperature of the main combustion zone of a combustion chamber using hydrogen fuel is higher than that of a combustion chamber using aviation kerosene, which can result in more thermal NOx x generation.

[0003] Pre-mixed combustion is one of the suitable ways to adapt to pure hydrogen low-pollution combustion. Pre-mixed combustion can effectively reduce the generation of local hot spots. It mixes hydrogen and air before combustion, which can effectively avoid the concentration of hydrogen concentration and the generation of stoichiometric combustion zone, thereby reducing the formation of local hot spots in the combustion process and further reducing the emission of nitrogen oxides. However, due to the extremely fast flame propagation speed of pure hydrogen combustion, the pre-mixed combustion has a high risk of backfiring, which is not friendly to the aviation engine combustion chamber. Therefore, micro-premixed combustion technology emerges as the times require. It disperses hydrogen fuel into multiple streams and directly injects it without swirl.

[0004] The existing hydrogen fuel gas turbine engine combustion chamber adopts a micro-premixed combustion organization mode to reduce NOx x emission. Micro-mixed pre-combustion is a technology that achieves low NOx x combustion by reducing the mixing scale of fuel and air flow and using a large number of micro-premixed channels. For example, a typical micro-premixed combustion injector designed by NASA is composed of an air ring channel and a hydrogen fuel ring channel installed concentrically. The hydrogen injection holes are arranged in the air injection holes, and a separate hydrogen injector is arranged in each air groove to achieve symmetrical mixing of air and hydrogen. However, this structure design has disadvantages: the large number of micro-premixed channels have complex structures and cause flow uniformity problems. Due to reasons such as flow rate and flow loss, the flow rates of micro-channels at different positions are significantly different. SUMMARY

[0005] The main purpose of the present application is to provide a fuel pipeline, a micro-premixed combustion chamber and a turbine engine, which aims to reduce the structural complexity of the fuel pipeline, improve the uniformity of the flow distribution, and reduce the difference between the flow rates of the micro-channels at different positions.

[0006] To achieve the above-mentioned purpose, the present application provides a fuel pipeline, which comprises a fuel gas inlet pipe, a fuel gas branch pipe, a fuel gas injection pipe and a combustion-supporting gas channel.

[0007] The gas inlet pipe, one end of which is adapted to be connected to combustible gas, and the other end of which is provided with a plurality of spaced gas outlets along the circumference thereof;

[0008] The gas branch pipe, having a plurality of gas inlet ends, the plurality of gas inlet ends of the gas branch pipe being in one-to-one communication with the plurality of gas outlets of the gas inlet pipe, and the gas branch pipe being arranged around the gas inlet pipe to form a plurality of polygonal micro-premixed branch pipe units which are connected to each other and distributed from the inside to the outside;

[0009] The combustion-supporting gas channel, one end of which is adapted to be connected to combustion-supporting gas, and the other end of which is adapted to be connected to the micro-premixed combustion chamber, each of the combustion-supporting gas channels being provided with a plurality of spaced gas inlets along the circumference thereof, and each of the micro-premixed branch pipe units surrounding a combustion-supporting gas channel and being in one-to-one communication with the plurality of gas inlets on the outer periphery of the combustion-supporting gas channel through a plurality of gas injection pipes.

[0010] Optionally, the micro-premixed branch pipe units are regular hexagons; and / or

[0011] The number of the gas injection pipes between the innermost micro-premixed branch pipe units and the corresponding combustion-supporting gas channels is less than the number of the gas injection pipes between the micro-premixed branch pipe units of other layers and the corresponding combustion-supporting gas channels.

[0012] Optionally, the diameter of the gas inlet pipe is 4-7 mm.

[0013] Optionally, the diameter of the gas branch pipe is 1-2 mm.

[0014] Optionally, the diameter of the gas injection pipe is less than or equal to 0.6 mm.

[0015] Optionally, the gas branch pipe and the gas injection pipe are in the same axial section.

[0016] Optionally, the combustion-supporting gas channel is in the shape of a triangular prism, a hexagonal prism, a dodecahedral prism, or a cylinder.

[0017] Optionally, the cross-sectional area of the combustion-supporting gas channel is 3-5 mm2.

[0018] To achieve the above object, the present application provides a micro-premix combustion chamber, comprising a fuel pipeline as described above, the fuel pipeline comprising a fuel gas inlet pipe, a fuel gas branch pipe, a fuel gas nozzle and a combustion-supporting gas passage; the fuel gas inlet pipe, one end of which is adapted to be connected to a combustible gas, the other end of which is provided with a plurality of spaced-apart gas outlets along the periphery thereof; the fuel gas branch pipe, having a plurality of gas inlet ends, the plurality of gas inlet ends of the fuel gas branch pipe being in one-to-one communication with the plurality of gas outlets of the fuel gas inlet pipe, and the fuel gas branch pipe being arranged around the fuel gas inlet pipe and forming a plurality of multi-layer polygonal micro-premix branch pipe units which are connected to each other and distributed from the inside to the outside; the combustion-supporting gas passage, one end of which is adapted to be connected to a combustion-supporting gas, the other end of which is adapted to be connected to the micro-premix combustion chamber, each of the combustion-supporting gas passages being provided with a plurality of spaced-apart gas inlet ports along the periphery thereof, and each of the micro-premix branch pipe units surrounding one of the combustion-supporting gas passages and being in one-to-one communication with the plurality of gas inlet ports on the periphery of the combustion-supporting gas passage through the plurality of fuel gas nozzles.

[0019] To achieve the above object, the present application further provides a turbine engine comprising the micro-premix combustion chamber as described above.

[0020] In the technical scheme of the present application, the fuel pipeline comprises a fuel gas inlet pipe, a fuel gas branch pipe, a fuel gas nozzle and a combustion-supporting gas passage; the fuel gas inlet pipe, one end of which is adapted to be connected to a combustible gas, the other end of which is provided with a plurality of spaced-apart gas outlets along the periphery thereof; the fuel gas branch pipe, having a plurality of gas inlet ends, the plurality of gas inlet ends of the fuel gas branch pipe being in one-to-one communication with the plurality of gas outlets of the fuel gas inlet pipe, and the fuel gas branch pipe being arranged around the fuel gas inlet pipe and forming a plurality of multi-layer polygonal micro-premix branch pipe units which are connected to each other and distributed from the inside to the outside; the combustion-supporting gas passage, one end of which is adapted to be connected to a combustion-supporting gas, the other end of which is adapted to be connected to the micro-premix combustion chamber, each of the combustion-supporting gas passages being provided with a plurality of spaced-apart gas inlet ports along the periphery thereof, and each of the micro-premix branch pipe units surrounding one of the combustion-supporting gas passages and being in one-to-one communication with the plurality of gas inlet ports on the periphery of the combustion-supporting gas passage through the plurality of fuel gas nozzles. It can be understood that the present application improves the hydrogen fuel pipeline structure of the micro-premix combustion chamber, realizes uniform gas inlet of the fuel at the head of the micro-premix hydrogen fuel combustion chamber, and can ensure that the equivalence ratio of each micro-premix unit is not too high or too low.

[0021] In the present application, the micro-premix branch pipe units are polygonally arranged, and the deflection angle is moderate, so that the non-uniformity of the outer micro-premix branch pipe units can be effectively reduced even at a high fuel equivalence ratio, thereby effectively reducing the pollutant emission. Taking a single-head combustion chamber at an equivalence ratio of 0.5 as an example, the NOx emission of the traditional hydrogen pipeline is higher than 200 ppm, while the NOx emission of the present application is lower than 20 ppm, which significantly reduces the overall NOx emission of the combustion chamber at a high equivalence ratio. x x x

[0022] ​​​In the present application, the outermost micro-premixing branch pipe unit is connected, and the hydrogen injection pipe on the side of the hydrogen inlet pipe of the innermost unit is cancelled, so that the unit with too high equivalence ratio is avoided.

[0023] In the present application, all hydrogen fuel branch pipes and hydrogen fuel injection pipes have the same profile, so that the structure is relatively simple, the processing is more convenient, and the manufacturing cost is lower. BRIEF DESCRIPTION OF DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed to be used in the embodiments or the prior art description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor on the basis of the drawings shown.

[0025] Figure 1 It is a structural schematic diagram of an embodiment of the fuel pipeline of the present application;

[0026] Figure 2 It is a fuel flow direction schematic diagram of an embodiment of the fuel pipeline of the present application;

[0027] Figure 3 It is a front view of an embodiment of the fuel pipeline of the present application;

[0028] Figure 4 It is a sectional view of an embodiment of the fuel pipeline and the micro-premixing combustion chamber having the same of the present application; Figure 1 ;

[0029] Figure 5 It is a sectional view of an embodiment of the fuel pipeline and the micro-premixing combustion chamber having the same of the present application; Figure 2 ;

[0030] Figure 6 It is a structural schematic diagram of an embodiment of the fuel pipeline and the micro-premixing combustion chamber having the same of the present application; Figure 1 ;

[0031] Figure 7 It is a structural schematic diagram of an embodiment of the fuel pipeline and the micro-premixing combustion chamber having the same of the present application; Figure 2 .

[0032] EXPLANATION OF DRAWINGS:

[0033] 10, gas inlet pipe; 20, gas branch pipe; 30, gas injection pipe; 40, combustion-supporting gas passage; 10a, gas outlet; 210, micro-premixing branch pipe unit; 100, micro-premixing combustion chamber; 40a, gas inlet.

[0034] The implementation, functional features and advantages of the present application will be further described with reference to the embodiments and the drawings. DETAILED DESCRIPTION

[0035] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all the other embodiments obtained by a person of ordinary skill in the art without creative effort are within the protection scope of the present application.

[0036] It should be noted that all the directionality indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present application are only used to explain the relative position relationship, movement condition, etc. between components in a certain posture (as shown in the drawings), and if the certain posture changes, the directionality indications also change accordingly.

[0037] In the description of the present application, it should be noted that unless specifically defined and limited, the terms “mounting”, “connection”, “connecting” should be understood in a broad sense, for example, can be fixed connection, can also be detachable connection, or integrally connected; can be mechanical connection, can also be electrical connection; can be directly connected, can also be indirectly connected through an intermediate medium, can be the communication inside two elements. For a person of ordinary skill in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0038] In addition, the description of “first”, “second” and the like in the present application is only for the purpose of description, and cannot be understood as indicating or implying the relative importance of the indicated technical features or implicitly indicating the number of the indicated technical features. Therefore, the features limited by “first”, “second” can explicitly or implicitly include at least one of the features. In addition, the meaning of “and / or” appearing throughout the text is to include three parallel schemes, for example, “A and / or B” includes A scheme, or B scheme, or A and B schemes are satisfied at the same time. In addition, the technical solutions of each embodiment can be combined with each other, but it must be based on the fact that a person of ordinary skill in the art can realize it, when the combination of technical solutions appears contradictory or unachievable, it should be considered that the combination of technical solutions does not exist, and is not within the protection scope required by the present application.

[0039] The present application provides a fuel pipeline.

[0040] Reference Figures 1 to 7In an embodiment of the present application, the fuel pipeline comprises a combustible gas inlet pipe 10, a combustible gas branch pipe 20, a combustible gas nozzle 30 and an auxiliary gas channel 40. The combustible gas inlet pipe 10 is adapted to be connected to a combustible gas source at one end and is provided with a plurality of gas outlets 10a at its periphery. The combustible gas branch pipe 20 has a plurality of gas inlet ends, and the gas inlet ends of the combustible gas branch pipe 20 are in one-to-one communication with the gas outlets 10a of the combustible gas inlet pipe 10. The combustible gas branch pipe 20 is arranged around the combustible gas inlet pipe 10 and forms a plurality of multi-layered polygonal micro-premixed branch pipe units 210 which are connected to each other and distributed from the inside to the outside. The auxiliary gas channel 40 is adapted to be connected to an auxiliary gas source at one end and is adapted to be in communication with the micro-premixed combustion chamber 100 at the other end. Each auxiliary gas channel 40 is provided with a plurality of auxiliary gas inlets 40a at its periphery. Each micro-premixed branch pipe unit 210 surrounds an auxiliary gas channel 40 and is in one-to-one communication with the auxiliary gas inlets 40a on the periphery of the auxiliary gas channel 40 through a plurality of combustible gas nozzles 30. In the following, the combustible gas is taken as an example of hydrogen and the auxiliary gas is taken as an example of air, and the present application is not limited to the micro-premixed condition of hydrogen and air.

[0041] In the present embodiment, the micro-premixed branch pipe unit 210 can be in the shape of a triangle, a quadrilateral, a pentagon, a hexagon, a heptagon or an octagon, and any other shape which can avoid the straight flow of hydrogen and reduce the non-uniformity of the flow rate. Preferably, the micro-premixed branch pipe unit 210 is in the shape of a regular hexagon.

[0042] It can be understood that the present application improves the hydrogen fuel pipeline structure of the micro-premixed combustion chamber 100, realizes the uniform intake of the fuel at the head of the micro-premixed hydrogen fuel combustion chamber and ensures that the equivalence ratio of each micro-premixed unit is not too high or too low.

[0043] In an embodiment, the present application mainly refers to Figures 1 to 3 The number of combustible gas nozzles 30 between the innermost micro-premixed branch pipe unit 210 and the corresponding auxiliary gas channel 40 is less than the number of combustible gas nozzles 30 between the micro-premixed branch pipe units 210 of other layers and the corresponding auxiliary gas channels 40. In this way, the difference between the flow rates of the micro-channels at different positions can be further reduced.

[0044] As shown in FIG. 1, the micro-premixed combustion chamber 100 is provided with a plurality of micro-premixed branch pipe units 210 which are arranged in a plurality of layers and are connected to each other. Each micro-premixed branch pipe unit 210 is provided with a plurality of combustible gas nozzles 30 which are in one-to-one communication with the auxiliary gas inlets 40a on the periphery of the auxiliary gas channel 40. The combustible gas nozzles 30 are arranged in a plurality of layers and are connected to each other. The number of combustible gas nozzles 30 between the innermost micro-premixed branch pipe unit 210 and the corresponding auxiliary gas channel 40 is less than the number of combustible gas nozzles 30 between the micro-premixed branch pipe units 210 of other layers and the corresponding auxiliary gas channels 40. In this way, the difference between the flow rates of the micro-channels at different positions can be further reduced. Figure 2As shown, when the micro-premixed branch pipe unit 210 is a regular hexagon, the gas flow direction is that, after the hydrogen fuel enters from the gas inlet pipe 10, it diffuses outwardly in six directions of the gas branch pipes 20, and each of the gas branch pipes 20 continues to branch into two hydrogen gas branch pipe passages with an included angle of 120° (deflection angle), and so on, until the hydrogen gas enters the corresponding combustion-supporting gas passages 40 through the gas injection pipes 30 of each layer, and finally reaches the outermost layer of the gas branch pipes 20 into the outermost layer of the gas injection pipes 30. In the combustion-supporting gas passages 40, the air is uniformly mixed with the hydrogen gas from the six gas injection pipes 30 (partly close to the center, the number of injection holes is less than 6, which aims to further reduce the difference between the flow rates of the micro-channels at different positions), and finally enters the rear chamber for combustion.

[0045] In an embodiment, referring to Figures 1 to 3 , the diameter of the gas inlet pipe 10 can be 4-7 mm, the diameter of the gas branch pipe 20 can be 1-2 mm, and the diameter of the gas injection pipe 30 can be less than or equal to 0.6 mm. In this way, the micro-premixed effect of the fuel pipeline can be further improved, and the cost is relatively low.

[0046] In an embodiment, referring to Figures 1 to 5 , the gas branch pipe 20 and the gas injection pipe 30 are in the same axial section. This arrangement can make all the hydrogen fuel branch pipes and hydrogen fuel injection pipes have the same profile, the structure is relatively simple, the processing is more convenient, and the manufacturing cost is lower.

[0047] In an embodiment, referring to Figures 1 to 3 , the shape of the combustion-supporting gas passage 40 is a triangular prism, a hexagonal prism, a dodecahedron, or a cylinder, etc., which is not limited herein. When the shape of the combustion-supporting gas passage 40 is a hexagonal prism, the cross-sectional area of the combustion-supporting gas passage 40 is preferably 3-5 mm2. In this way, it is helpful to further improve the micro-premixed effect, improve the aesthetics, and reduce the structural complexity.

[0048] In summary, the present application uses a relatively simple hydrogen fuel pipeline with a regular hexagonal structure arrangement to achieve uniform intake of fuel at the head of the micro-premixed hydrogen fuel combustion chamber, which can ensure that the equivalence ratio of each micro-premixed unit is not too high or too low. In the present application, the micro-premixed branch pipe unit 210 is polygonally arranged, and the deflection angle is moderate, which can effectively reduce the non-uniformity of the outer layer of the micro-premixed branch pipe unit 210 even at a high fuel equivalence ratio, thereby effectively reducing the pollutant emissions. Taking a single-head combustion chamber at an equivalence ratio of 0.5 as an example, the traditional hydrogen pipeline NOx emission is higher than 200 ppm, while the NOx emission of the present application is lower than 20 ppm, which significantly reduces the overall NOx emission of the combustion chamber at a high equivalence ratio. x x x ​​Discharge. The outermost micro-premixed branch pipe unit 210 is communicated with the design, and the hydrogen injection pipe on the side of the innermost unit body close to the hydrogen inlet pipe is cancelled, so that the unit body with too high equivalence ratio is avoided. All hydrogen fuel branch pipes and hydrogen fuel injection pipes are in the same profile, the structure is relatively simple, the processing is more convenient, and the manufacturing cost is lower.

[0049] The application also provides a micro-premixed combustion chamber 100, which refers to Figures 4 to 7 The micro-premixed combustion chamber 100 comprises a fuel pipeline, the specific structure of which refers to the above-mentioned embodiments. Since the micro-premixed combustion chamber 100 provided by the application comprises all the schemes of all the embodiments of the above-mentioned fuel pipeline, at least the same technical effects as the above-mentioned fuel pipeline are achieved, which will not be elaborated here.

[0050] The application also provides a turbine engine, which refers to Figures 4 to 7 The turbine engine comprises a micro-premixed combustion chamber 100, the specific structure of which refers to the above-mentioned embodiments. Since the turbine engine provided by the application comprises all the schemes of all the embodiments of the above-mentioned micro-premixed combustion chamber 100, at least the same technical effects as the above-mentioned micro-premixed combustion chamber 100 are achieved, which will not be elaborated here.

[0051] The above-mentioned is only the optional embodiment of the application, and does not limit the patent scope of the application. Any equivalent structural transformation, direct / indirect application in other related technical fields under the inventive concept of the application, and the content of the specification and the drawings are included in the patent protection scope of the application.

Claims

1. A fuel line, characterized in that The gas inlet pipe, the gas branch pipe, the gas jet pipe and the combustion-supporting gas channel; The gas inlet pipe has one end adapted to be connected to a combustible gas source and the other end provided with a plurality of gas outlets arranged at intervals along the circumference of the gas inlet pipe; The gas branch pipe has a plurality of gas inlet ends, the gas inlet ends of the gas branch pipe are in one-to-one communication with the gas outlets of the gas inlet pipe, and the gas branch pipe is arranged around the gas inlet pipe to form a plurality of multi-layer polygonal micro-premixed branch pipe units connected to each other and distributed from the inside to the outside; The combustion-supporting gas channel has one end adapted to be connected to a combustion-supporting gas source and the other end adapted to be connected to the micro-premixed combustion chamber, each combustion-supporting gas channel is provided with a plurality of gas inlet openings arranged at intervals along the circumference of the combustion-supporting gas channel, and each micro-premixed branch pipe unit surrounds a combustion-supporting gas channel and is in one-to-one communication with the plurality of gas inlet openings on the outer periphery of the combustion-supporting gas channel through a plurality of gas jet pipes.

2. The fuel line of claim 1, wherein, The micro-premixed branch pipe unit is a regular hexagon; and / or The number of gas jet pipes between the innermost micro-premixed branch pipe unit and the corresponding combustion-supporting gas channel is less than the number of gas jet pipes between the micro-premixed branch pipe units of other layers and the corresponding combustion-supporting gas channels.

3. The fuel line of claim 1, wherein, The diameter of the gas inlet pipe is 4-7 mm.

4. The fuel line of claim 1, wherein, The diameter of the gas branch pipe is 1-2 mm.

5. The fuel line of claim 1, wherein, The diameter of the gas jet pipe is less than or equal to 0.6 mm.

6. The fuel rail of claim 1, wherein, The gas branch pipe and the gas jet pipe are in the same axial section.

7. The fuel rail of claim 1, wherein, The combustion-supporting gas channel has a shape of a triangular prism, a hexagonal prism, a dodecahedral prism or a cylinder.

8. The fuel rail of claim 1, wherein, The cross-sectional area of the combustion-supporting gas passage is 3-5 mm 2 .

9. A micro-premix combustion chamber, characterized by, The fuel pipe comprises the fuel pipe according to any one of claims 1-8.

10. A turbine engine characterized by, The micro-premixed combustion chamber comprises the micro-premixed combustion chamber according to claim 9.

Images