Dual-fuel integrated igniter nozzle and gas turbine

Abstract

The present invention discloses a dual-fuel integrated igniter nozzle and a gas turbine, comprising: a nozzle body, a first fuel pipe and a second fuel pipe connected to the internal space of the nozzle body, and an air inlet hole provided on the nozzle body; an igniter provided in the nozzle body, and the igniter located on the central axis of the nozzle body. Through the above arrangement, the present invention integrates the igniter into the nozzle body, isolating the igniter from the external environment, and can effectively solve the problems of unsuccessful ignition during startup, restarting after flameout, and ignition under harsh working conditions of the gas turbine. At the same time, the dual-fuel arrangement can also make the nozzle of the present invention more adaptable to the rich and diverse energy types of the contemporary era; the overall structure is compact and lightweight, and can better adapt to micro gas turbines.

Description

Technical Field

[0001] The present invention belongs to the technical field of gas turbines, and in particular relates to a dual-fuel integrated igniter nozzle and a gas turbine. Background Art

[0002] Gas turbines have the advantages of high efficiency, small size, light weight, simple maintenance, good maneuverability, high degree of automation and low cost. Therefore, they are widely used in aviation, land-based power generation, natural gas transportation, petroleum, railway and shipbuilding industries.

[0003] Traditional gas turbines have poor fuel adaptability in their combustion chamber nozzles and cannot match the diverse energy types of today. They are not suitable for hydrogen, ammonia, or even a large amount of industrial by-product gas, oilfield associated gas, and biomass energy, resulting in serious energy waste.

[0004] When the gas turbine is started, restarted after flameout, or ignited under severe working conditions, problems such as ignition failure may occur, affecting normal use;

[0005] At the same time, the further improvement of environmental protection standards has also placed higher requirements on gas turbines, requiring the efficiency of gas turbines to be improved and pollutant emissions to be reduced. Summary of the Invention

[0006] The object of the present invention is to solve at least one problem in the above-mentioned background technology, and to provide a dual-fuel integrated igniter nozzle and a gas turbine.

[0007] To achieve the above objectives, the present invention provides a dual-fuel integrated igniter nozzle, comprising:

[0008] a nozzle body, a first fuel pipe and a second fuel pipe communicating with an interior space of the nozzle body, and an air inlet hole provided on the nozzle body;

[0009] An igniter is provided in the nozzle body and is located on the central axis of the nozzle body.

[0010] Preferably, the nozzle body is provided with a first fuel channel and a second fuel channel which are independent of each other, and a mixing channel which is in communication with the first fuel channel and the second fuel channel;

[0011] The first fuel channel is in communication with the first fuel pipe, and the second fuel channel is in communication with the second fuel pipe;

[0012] An igniter mounting plate is provided in the nozzle body;

[0013] The first fuel channel and the second fuel channel are separated from the mixing channel by the igniter mounting plate;

[0014] The igniter is fixed to the igniter mounting plate, and one end of the igniter is located in the first fuel channel, and the other end is located in the mixing channel;

[0015] The igniter mounting plate is provided with a first incident air hole communicating with the first fuel channel and the mixing channel, and a second incident air hole communicating with the second fuel channel and the mixing channel;

[0016] The second incident air hole is arranged close to the inner wall of the nozzle body;

[0017] The air inlet hole is in communication with the mixing channel;

[0018] The air inlet holes include first air inlet holes and second air inlet holes that are evenly arranged in the circumference, and the first air inlet holes are arranged close to the igniter mounting plate;

[0019] The opening area of ​​the first air inlet hole is larger than the opening area of ​​the second air inlet hole;

[0020] The opening of the second air inlet hole is configured as a radial oblique opening.

[0021] Preferably, the bevel angle of the radial bevel opening is less than or equal to 45°.

[0022] Preferably, the second air inlet holes are configured as key-shaped holes and are evenly arranged along the circumference of the side wall of the nozzle body.

[0023] Preferably, the first incident air hole is arranged close to the inner wall of the nozzle body.

[0024] Preferably, the second air inlet hole is arranged close to the ignition position of the igniter.

[0025] Preferably, the first incident air hole and the second incident air hole are located on the same horizontal plane.

[0026] Preferably, the igniter comprises an ignition rod wrapped with a ceramic material.

[0027] Preferably, a mounting flange is further provided on the side wall of the nozzle body.

[0028] To achieve the above objectives, the present invention further provides a gas turbine comprising any one of the dual-fuel integrated igniter nozzles described above.

[0029] Based on this, the beneficial effects of the present invention are:

[0030] 1. The present invention's solution, by installing the igniter inside the nozzle body, provides the nozzle with higher ignition reliability and better control of the ignition equivalence ratio. This not only alleviates the ignition failure problem of traditional igniters and achieves efficient combustion, but also adapts to ignition in harsh operating conditions such as high altitude, high humidity, and low temperatures, ensuring stable operation of the gas turbine.

[0031] 2. The present invention incorporates independent first and second fuel channels within the nozzle body. This allows the first and second fuels, after entering the nozzle body through the first and second fuel pipes, to stabilize within the two channels before being ejected through the inlet holes in the two channels. This ensures good initial uniformity for both ejected gaseous fuels. Furthermore, the ejected gas flow is stable, ensuring stable combustion and preventing flashback.

[0032] 3. According to the solution of the present invention, the nozzle body is provided with a first air inlet hole and a second air inlet hole. The opening area of ​​the first air inlet hole is larger than the opening area of ​​the second air inlet hole. The first air inlet hole is located close to the fuel channel. This allows the fuel ejected through the incident air hole to be mixed with a large amount of air immediately, thereby improving the mixing effect.

[0033] 4. The present invention utilizes a key-shaped radially oblique opening as the second air inlet, allowing high-pressure air to form a swirling flow after entering the nozzle body. This not only solves the stratification problem caused by density differences in conventional natural gas-hydrogen blending, but also improves the mixing efficiency of the first fuel, second fuel, and air.

[0034] 5. Through the solution of the present invention, the nozzle has a compact overall structure, simple process, light weight, small flow loss, uniform and stable outlet flow field, and can better meet the requirements of gas turbine size and lightweight installation. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 A perspective view schematically showing a dual-fuel integrated igniter nozzle according to one embodiment of the present invention;

[0036] Figure 2 A top view schematically showing a dual-fuel integrated igniter nozzle according to one embodiment of the present invention;

[0037] Figure 3 Schematically shows an embodiment of the present invention Figure 2 Cross-sectional view along the A-A' direction;

[0038] Description of the drawings: nozzle body 10, first fuel channel 101, second fuel channel 102, mixing channel 103, first fuel pipe 20, second fuel pipe 30, air inlet hole 40, first air inlet hole 401, second air inlet hole 402, igniter 50, igniter mounting plate 60, first incident air hole 601, second incident air hole 602, mounting flange 70. DETAILED DESCRIPTION

[0039] The present invention will now be discussed with reference to exemplary embodiments. It should be understood that the embodiments discussed are only intended to enable those skilled in the art to better understand and implement the present invention, rather than to imply any limitation on the scope of the present invention.

[0040] As used herein, the term "including" and variations thereof are to be interpreted as open-ended terms meaning "including, but not limited to." The term "based on" is to be interpreted as "based, at least in part, on." The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment."

[0041] Figure 1 A perspective view schematically showing a dual-fuel integrated igniter nozzle according to one embodiment of the present invention, Figure 2 A top view schematically showing a dual-fuel integrated igniter nozzle according to one embodiment of the present invention, Figure 3 Schematically shows an embodiment of the present invention Figure 2 The cross-sectional view in the A-A' direction is as follows: Figure 1-3 As shown, a dual-fuel integrated igniter nozzle of the present invention comprises:

[0042] The nozzle body 10, a first fuel pipe 20 and a second fuel pipe 30 communicating with the interior space of the nozzle body 10, and an air inlet hole 40 provided on the nozzle body 10;

[0043] An igniter 50 is provided in the nozzle body 10 and is located on the central axis of the nozzle body 10 .

[0044] Traditional technologies have poor fuel adaptability for gas turbine combustor nozzles, which cannot match the diverse energy sources of today. Besides natural gas, they are also incompatible with hydrogen, ammonia, and even a large amount of industrial by-product gas, oilfield associated gas, and biomass energy, resulting in serious energy waste.

[0045] Based on the above problems, the present invention is provided with a first fuel pipe 20 and a second fuel pipe 30 on the nozzle body 10, which can be used for dual fuel mixing. It is suitable for the mixed supply of multiple fuels with natural gas as the main fuel and hydrogen, ammonia and other clean energy sources as the secondary fuel, so that the nozzle has more reliable multi-fuel adaptability and provides the possibility of installing an igniter 50 in the subsequent nozzle.

[0046] At the same time, in traditional technologies, the igniter is plug-in type, with part of it exposed to the outside world. When the gas turbine is started, restarted after flameout, or ignited under harsh operating conditions, it is often easily affected by external environmental factors, resulting in problems such as ignition failure, affecting the normal use of the gas turbine;

[0047] The present invention integrates the igniter 50 into the nozzle body 10 and isolates the igniter 50 from the external environment through the shell of the nozzle body 10, making the igniter 50 less susceptible to environmental influences. This ensures the ignition success rate of the gas turbine even in harsh environments without affecting normal use.

[0048] The nozzle of the present invention realizes the dual functions of mixing and ignition, has a compact overall structure, and is more adaptable to the requirements of gas turbine size and lightweight installation.

[0049] like Figure 3 As shown, in the embodiment of the present invention, the first fuel pipe 20 and the second fuel pipe 30 are arranged perpendicular to each other. Of course, they can also be arranged parallel to each other.

[0050] Furthermore, the nozzle body 10 is provided with a first fuel channel 101 and a second fuel channel 102 which are independent of each other, and a mixing channel 103 which is in communication with the first fuel channel 101 and the second fuel channel 102;

[0051] The first fuel passage 101 is in communication with the first fuel pipe 20 , and the second fuel passage 102 is in communication with the second fuel pipe 30 .

[0052] Specifically, the nozzle body 10 is configured to be cylindrical, and the first fuel channel 101 and the second fuel channel 102 are coaxially arranged;

[0053] During operation, the first fuel enters the internal space of the nozzle body 10 through the first fuel pipe 20, stabilizes the airflow in the first fuel channel 101, and then is ejected into the mixing channel 103 through the first fuel channel 101. Similarly, the second fuel enters the internal space of the nozzle body 10 through the second fuel pipe 30, stabilizes the airflow in the second fuel channel 102, and then is ejected into the mixing channel 103 through the second fuel channel 102. At the same time, air enters the nozzle body 10 from the air inlet hole 40, thereby enabling the first fuel, the second fuel and the air to be mixed in the mixing channel 103.

[0054] Through the above-mentioned setting, the first fuel channel 101 and the second fuel channel 102 are coaxially arranged, and the first fuel and the second fuel can be stabilized in the two channels respectively. On the one hand, it can better control the ignition equivalence ratio and realize efficient combustion, and can effectively avoid the phenomenon of fuel being directly ejected from the pipeline in traditional technology, so as to avoid this method resulting in a small fuel flow rate and inability to achieve good fuel mixing, resulting in the fuel airflow entering the mixing channel 103 being itself uneven and asymmetric, affecting the stability of combustion; on the other hand, since the nozzle of the present invention is suitable for gas fuel, and gas fuel requires a certain distance to stabilize the airflow, the setting of the first fuel channel 101 and the second fuel channel 102 can avoid the backfire problem caused by the direct ejection and mixing of the airflow and unstable combustion.

[0055] At the same time, the first fuel channel 101, the second fuel channel 102 and the nozzle body 10 are all arranged horizontally, and the air inlet hole 40 is arranged on the side wall of the nozzle body 10, so that the flow directions of the first fuel, the second fuel and the air are perpendicular to each other, so that the air and fuel are staggered, making the mixing faster and more uniform.

[0056] Furthermore, an igniter mounting plate 60 is provided within the nozzle body 10;

[0057] The first fuel channel 101 and the second fuel channel 102 are separated from the dilution channel 103 by the igniter mounting plate 60 .

[0058] The igniter 50 is fixed on the igniter mounting plate 60 , and one end of the igniter 50 is located in the first fuel channel 101 , and the other end of the igniter 50 is located in the mixing channel 103 .

[0059] Specifically, the igniter mounting plate 60 is a circular plate with a certain thickness. A through hole is set at its center. The size of the through hole is consistent with the cross-sectional size of the igniter 50. The igniter 50 penetrates the igniter mounting plate 60 through the through hole. Part of it is located in the first fuel channel 101, and the other part is located in the mixing channel 103, thereby fixing the igniter 50.

[0060] With this arrangement, the igniter mounting plate 60 divides the internal space of the nozzle body 10, so that the nozzle has better smoothness and mixing effects, improves internal fuel distribution, enhances combustion stability, and also increases the structural strength of the nozzle.

[0061] Furthermore, the igniter mounting plate 60 is provided with a first air inlet 601 communicating with the first fuel channel 101 and the mixing channel 103 , and a second air inlet 602 communicating with the second fuel channel 102 and the mixing channel 103 ;

[0062] The second incident air hole 602 is disposed close to the inner wall of the nozzle body 10 .

[0063] Specifically, a first incident air hole 601 is provided on the igniter mounting plate 60. The first incident air hole 601 is specifically located on the projection area of ​​the first fuel channel 101 projected onto the igniter mounting plate 60. The second incident air hole 602 is similarly located on the projection area of ​​the second fuel channel 102 projected onto the igniter mounting plate 60.

[0064] At the same time, the second incident air hole 602 is arranged close to the edge of the igniter mounting plate 60, that is, close to the inner wall of the nozzle body 10. Through this arrangement, when the second fuel is ejected from the second incident air hole 602, it can be mixed with the air entering from the air inlet hole 40 earlier, thereby improving the mixing effect.

[0065] At the same time, the first incident air hole 601 can also be arranged close to the inner wall of the nozzle body 10, so that the first fuel can be mixed with the air earlier after being sprayed out through the first incident air hole 601, thereby improving the mixing effect.

[0066] Furthermore, the air inlet hole 40 is connected to the mixing channel 103, so that the mixing of fuel and air occurs in the mixing channel 103, ensuring the initial uniformity of the two fuels and facilitating the user to control the flow rate of each component.

[0067] Furthermore, the air inlet hole 40 includes a first air inlet hole 401 and a second air inlet hole 402 , and the first air inlet hole 401 is disposed near the igniter mounting plate 60 ;

[0068] The opening area of ​​the first air inlet hole 401 is larger than the opening area of ​​the second air inlet hole 402 .

[0069] Specifically, a plurality of first air inlet holes 401 are provided, preferably approximately circular, but may also be of other shapes. The first air inlet holes 401 are evenly arranged circumferentially along the side wall of the nozzle body 10 to form a cross jet to meet the air volume requirement;

[0070] At the same time, the first air inlet hole 401 and the second air inlet hole 402 are arranged at a certain angle away from the fuel outlet, which can reduce the impact of air on the fuel, thereby ensuring the mixing effect.

[0071] The first air inlet hole 401 is arranged close to the igniter mounting plate 60, so that air can first enter the nozzle body 10 in large quantities through the larger opening, so that the first fuel, the second fuel and the air are fully mixed to meet the air demand for mixing, avoiding the traditional technology of only setting one air inlet, or setting a smaller air inlet close to the fuel nozzle, and the phenomenon of insufficient air volume, resulting in incomplete mixing or uneven mixing, resulting in more pollutants after combustion, and polluting the environment after discharge.

[0072] Furthermore, the opening of the second air inlet hole 402 is configured as a radially beveled opening.

[0073] In conventional technology, in order to achieve faster and better mixing of air and fuel, a swirler is separately provided in the mixing section to cause the gas to swirl, thereby achieving a "stirring" effect, accelerating the mixing rate, and improving the mixing effect of air and fuel. However, the separately provided swirler increases the weight of the igniter nozzle, makes the safety structure inside the nozzle more complicated, reduces the reliability of the product, and increases the manufacturing cost.

[0074] In the present invention, however, the second air inlet hole 402 is designed as a radially beveled opening. This allows high-pressure air from outside the nozzle to enter the nozzle body 10 along the radially beveled surface, forming a swirling flow within the nozzle around the axis. In other words, the second air inlet hole 402, through its own structure, can produce the same swirling effect as a swirler. This simplifies the nozzle structure, reduces nozzle weight, improves nozzle reliability, and lowers manufacturing and maintenance costs. It also solves the stratification problem caused by density differences in traditional natural gas hydrogen blending and improves the gas blending effect.

[0075] At the same time, if the number of the first air inlet holes 401 and the second air inlet holes 402 is set to be the same, the mixing effect can be further enhanced, the uniformity of the fuel at the nozzle outlet can be ensured, and better smoothness performance can be obtained.

[0076] Furthermore, the bevel angle of the radial bevel opening of the second air inlet hole 402 is less than or equal to 45°, preferably 30°. The swirl generated within this range can achieve the best mixing effect of air and fuel.

[0077] Furthermore, the second air inlet holes 402 are configured as key-shaped holes and are evenly arranged along the circumference of the side wall of the nozzle body 10 .

[0078] By setting the second air inlet holes 402 as key-shaped holes, the area occupied by the second air inlet holes 402 in the circumferential direction of the side wall of the nozzle body 10 is reduced, thereby increasing the number of second air inlet holes 402 and thereby increasing the amount of air entering the nozzle body 10. At the same time, more beveled second air inlet holes 402 can also provide a better swirl flow field effect, thereby enhancing the mixing effect of air and fuel.

[0079] Furthermore, the second air inlet hole 402 is provided close to the ignition position of the igniter 50 .

[0080] Specifically, the second air inlet hole 402 is arranged on the upstream side of the ignition position of the igniter 50. With this arrangement, the fuel and air are well mixed before the ignition position of the igniter 50, and the mixture has a higher mixing uniformity when it moves to the ignition position, making it easier for the mixture to ignite.

[0081] Furthermore, the igniter 50 may be specifically an ignition rod wrapped by a ceramic material. The ceramic material has good high temperature resistance and good tolerance to harsh environments, which enables the nozzle to better adapt to the environment and improve the ignition success rate.

[0082] Furthermore, in the above scheme, the first incident air hole 501 and the second incident air hole 502 are on the same horizontal plane, thereby ensuring that the first fuel and the second fuel ejected through the first incident air hole 501 and the second incident air hole 502 can be at the same initial position and can be mixed with the air almost synchronously, avoiding the problem of uneven mixing caused by one fuel being mixed with the air before the other fuel is ejected.

[0083] Furthermore, a mounting flange 70 is provided on the side wall of the nozzle body 10 to facilitate the connection between the nozzle and the gas turbine.

[0084] Furthermore, the present invention also provides a gas turbine comprising the above-mentioned dual-fuel integrated igniter nozzle.

[0085] In summary, the solution of the present invention, by installing the igniter 50 inside the nozzle body 10, makes the nozzle of the present invention have higher ignition reliability. It can not only improve the problem of unsuccessful ignition of traditional igniters, but also adapt to ignition in harsh working conditions such as high altitude, high humidity, cold and low temperature environments, thereby ensuring the stable operation of the gas turbine.

[0086] The nozzle body 10 is provided with a first fuel channel 101 and a second fuel channel 102, which are independent of each other. After the first fuel and the second fuel enter the nozzle body 10 through the first fuel pipe 20 and the second fuel pipe 30, they are stabilized in the two channels respectively before being ejected through the incident air holes on the two channels. This ensures that both ejected gas fuels have good initial uniformity. At the same time, the ejected airflow is stable, which can ensure combustion stability and avoid flashback problems.

[0087] The nozzle body 10 is provided with a first air inlet hole 401 and a second air inlet hole 402. The opening area of ​​the first air inlet hole 401 is larger than the opening area of ​​the second air inlet hole 402. The first air inlet hole 401 is arranged close to the fuel channel, so that the fuel ejected through the incident air hole can be mixed with a large amount of air immediately, thereby improving the mixing effect.

[0088] The second air inlet hole 402 is configured as a key-shaped radial oblique opening, so that air can form a swirl after entering the nozzle body 10, "stirring" the gas in the nozzle body 10, accelerating the mixing rate of the first fuel, the second fuel and the air, improving the mixing effect, and thus reducing emission pollution;

[0089] The overall structure and process are simple, the flow loss is small, and the flow field at the nozzle outlet is uniform and stable, which is conducive to subsequent combustion.

[0090] The above description is merely a preferred embodiment of the present application and an illustration of the technical principles employed. Those skilled in the art should understand that the scope of the invention herein is not limited to the technical solutions formed by the specific combination of the above-mentioned technical features, but also encompasses other technical solutions formed by any combination of the above-mentioned technical features or their equivalents without departing from the inventive concept. For example, a technical solution formed by replacing the above-mentioned features with (but not limited to) technical features having similar functions disclosed in this application.

[0091] It should be understood that the size of the serial numbers of each step in the content of the invention and the embodiments of the present invention does not absolutely mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of the present invention.

Claims

1. A dual-fuel integrated igniter nozzle, characterized in that: include: a nozzle body, a first fuel pipe and a second fuel pipe communicating with an interior space of the nozzle body, and an air inlet hole provided on the nozzle body; An igniter is provided in the nozzle body, and the igniter is located on the central axis of the nozzle body; The nozzle body is provided with a first fuel channel and a second fuel channel which are independent of each other, and a mixing channel which is in communication with the first fuel channel and the second fuel channel; the first fuel channel is in communication with the first fuel pipe, and the second fuel channel is in communication with the second fuel pipe; An igniter mounting plate is provided in the nozzle body; the first fuel channel and the second fuel channel are separated from the mixing channel by the igniter mounting plate; the igniter is fixed to the igniter mounting plate, and one end of the igniter is located in the first fuel channel and the other end is located in the mixing channel; a first incident air hole connecting the first fuel channel and the mixing channel, and a second incident air hole connecting the second fuel channel and the mixing channel are provided on the igniter mounting plate; the second incident air hole is provided near the inner wall of the nozzle body; The air inlet hole is connected to the mixing channel; the air inlet hole includes a first air inlet hole and a second air inlet hole uniformly arranged along the circumference of the side wall of the nozzle body, the first air inlet hole is arranged near the igniter mounting plate; the opening area of ​​the first air inlet hole is larger than the opening area of ​​the second air inlet hole; The opening of the second air inlet hole is configured as a radial oblique opening.

2. A dual-fuel integrated igniter nozzle according to claim 1, characterized in that: The bevel angle of the radial bevel opening is less than or equal to 45°.

3. The dual-fuel integrated igniter nozzle according to claim 1, characterized in that: The second air inlet hole is configured as a key-shaped hole.

4. The dual-fuel integrated igniter nozzle according to claim 1, characterized in that: The first incident air hole is arranged close to the inner wall of the nozzle body.

5. The dual-fuel integrated igniter nozzle according to claim 1, characterized in that: The second air inlet hole is arranged close to the ignition position of the igniter.

6. The dual-fuel integrated igniter nozzle according to claim 1, characterized in that: The first incident air hole and the second incident air hole are located on the same horizontal plane.

7. The dual-fuel integrated igniter nozzle according to claim 1, characterized in that: The igniter includes an ignition rod wrapped with ceramic material.

8. The dual-fuel integrated igniter nozzle according to claim 1, characterized in that: A mounting flange is also provided on the side wall of the nozzle body.

9. A gas turbine, characterized in that: The invention comprises the dual-fuel integrated igniter nozzle according to any one of claims 1 to 8.

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