Gas nozzle and gas nozzle detection and early warning method

Abstract

The embodiment of the invention discloses a gas nozzle and a gas nozzle detection early warning method. The gas nozzle comprises a nozzle shell, a first hydrogen fuel pipe, a second hydrogen fuel pipe assembly, a first premixer, a second premixer and an airflow annular piece, wherein the first hydrogen fuel pipe is coaxially fixed at the central axis position of the nozzle shell; the airflow annular piece surrounds the first hydrogen fuel pipe and is coaxially fixed in the nozzle shell; the first premixer is fixed in a cavity between the first hydrogen fuel pipe and the airflow annular piece; the second premixer is fixed in a cavity between the airflow annular piece and the outer shell of the nozzle shell; the second hydrogen fuel pipe assembly is fixedly connected to the edge of the top face of the nozzle shell. According to the embodiment, emission of oxynitride can be effectively reduced, flame can be prevented from moving up and down, and the backfire risk is avoided.

Description

Technical Field

[0001] The embodiments of the present disclosure relate to the field of gas turbines, and in particular to a gas nozzle and a gas nozzle detection and early warning method. Background Art

[0002] As an energy source to replace traditional fossil fuels, hydrogen fuel has the characteristics of low density, wide flammable range, fast combustion speed, high adiabatic flame temperature, and abundant storage resources. It can effectively reduce carbon emissions and is of great significance to alleviating global climate change and protecting the environment. It has received extensive attention and research in the field of gas turbines.

[0003] The nitrogen oxides produced by hydrogen combustion are mainly thermal, mainly produced by high-temperature combustion. The combustion temperature is the most sensitive parameter affecting the generation of thermal nitrogen oxides, and is exponentially related to the nitrogen oxide generation rate. The existing low-pollution combustion technology of hydrogen fuel mainly adopts micro-mixing combustion technology, which mainly uses a large number of simple micro nozzles to replace traditional large-diameter nozzles, converting large-scale flames into multiple small-scale flames, enhancing the local mixing intensity of air and hydrogen, and improving the mixing uniformity. At the same time, the small-scale flame can greatly shorten the residence time of nitrogen in the high-temperature zone, thereby reducing the generation of nitrogen oxides.

[0004] The world's mainstream gas turbine manufacturers are vigorously promoting the use of hydrogen-blended fuel and pure hydrogen fuel. However, the physical and chemical properties of hydrogen are significantly different from those of traditional hydrocarbon fuels, resulting in huge challenges for hydrogen combustion technology. For example, hydrogen fuel requires a higher fuel flow rate to achieve the same heat load as traditional fuels, resulting in a large pressure loss in the combustion chamber, which in turn affects the performance of the entire machine. And with the widespread increase in the use of aviation and ground combustion turbines and the increasingly stringent emission standards, low nitrogen oxide emission technology has become the core competitiveness of gas turbine production.

[0005] However, the inventors have found that when the calibration plate is placed in the above manner, the following technical problems often occur:

[0006] The diameter of the existing micro-mixing tubes for micro-mixed premixed combustion is mostly a single diameter. Although it can effectively reduce the emission of nitrogen oxides from hydrogen combustion, the activity of hydrogen in the premixing reaction and the higher flame speed make the flame front thinner, making it easier for the flame to move upstream, which increases the risk of flashback.

[0007] The above information disclosed in this Background section is only for enhancement of understanding of the background of the inventive concept and therefore it may contain information that does not form the prior art that is already known in this country to a person of ordinary skill in the art. Summary of the invention

[0008] The content of this disclosure is used to introduce concepts in a brief form, which will be described in detail in the detailed implementation section below. The content of this disclosure is not intended to identify the key features or essential features of the technical solution claimed for protection, nor is it intended to limit the scope of the technical solution claimed for protection.

[0009] Some embodiments of the present disclosure propose a gas nozzle and a gas nozzle detection and early warning method to solve the technical problems mentioned in the above background technology section.

[0010] In a first aspect, some embodiments of the present disclosure provide a gas nozzle, characterized in that the gas nozzle comprises: a nozzle housing, a first hydrogen fuel pipe, a second hydrogen fuel pipe assembly, a first premixer, a second premixer, an airflow ring and a second hydrogen fuel pipe ventilation pipe, wherein: the first hydrogen fuel pipe is coaxially fixed to the center axis position of the nozzle housing, wherein the nozzle housing is a cylindrical hollow double-layer housing, the first hydrogen fuel pipe is a double-layer pipe, the sandwich space of the double-layer pipe is a first hydrogen fuel channel, a circle of vent holes is provided at the bottom end of the outer layer pipe of the first hydrogen fuel pipe, and the hydrogen in the first hydrogen fuel channel flows into the fuel chamber of the first premixer through the vent holes; the air inlet end of the first hydrogen fuel pipe is provided with an air inlet hole, and in the working state, hydrogen is transported to the sandwich space of the first hydrogen fuel pipe through the air inlet hole; the airflow ring is coaxially fixed around the first hydrogen fuel pipe in the nozzle housing, and is used to isolate the fuel chamber of the second premixer from that of the first premixer. chamber; the first premixer is fixed in the chamber between the first hydrogen fuel pipe and the air flow ring; the second premixer is fixed in the chamber between the air flow ring and the outer shell of the nozzle housing, wherein the first premixer and the second premixer are both composed of a plurality of micro-mixing tubes arranged layer by layer around the central axis of the nozzle housing, and each layer is composed of a plurality of micro-mixing tubes of different diameters, so as to pass the gas from the air inlet end to the air outlet end under working conditions; the second hydrogen fuel pipe assembly is fixedly connected to the top surface edge of the nozzle housing, and the second hydrogen fuel pipe ventilation pipe is fixedly connected to the second hydrogen fuel pipe assembly, wherein each second hydrogen fuel pipe in the second hydrogen fuel pipe assembly transports hydrogen to the hollow chamber of the nozzle housing through the fixedly connected second hydrogen fuel pipe ventilation pipe, and the second hydrogen fuel pipe assembly is interconnected with the hollow chamber of the nozzle housing, so as to pass the hydrogen to the hollow chamber under working conditions, and then pass the hydrogen from the hollow chamber to the fuel chamber of the second premixer.

[0011] Optionally, the first premixer and the second premixer are separated into an outer chamber and an inner chamber by a partition, wherein: each micro-mixing tube in the first premixer and the second premixer is provided with an air vent at the position of the inner chamber, so as to flow the gas introduced into the inner chamber of the first premixer and the second premixer to the micro-mixing tube in a working state, and the inner chamber of the first premixer and the second premixer is separated by the air flow annular member; in a working state, air is introduced into the air inlet end of the first premixer and the second premixer for mixing with the hydrogen in each micro-mixing tube and the chamber, and then the gas flows out through the air outlet end.

[0012] Optionally, a vent hole is provided on the air flow ring at the position of the outer chamber, wherein: the outer chambers of the first premixer and the second premixer are interconnected through the vent hole on the air flow ring, which is used to flow the cooling gas flowing into the internal space of the air flow ring into the outer chambers of the first premixer and the second premixer under working conditions, so as to cool the micro-mixing tube and the gas nozzle at the outer chamber position.

[0013] Optionally, the micro-mixing tubes in the first premixer and the second premixer are arranged around the central axis of the gas nozzle in one layer, and the micro-mixing tubes in adjacent layers have different inclination directions to form a cross arrangement.

[0014] Optionally, the air inlet end faces of the first premixer and the second premixer are configured as rounded corners, and the air inlet end of the air flow annular member is configured as rounded corners.

[0015] Optionally, the outer chambers of the first premixer and the second premixer are provided with thermal barrier coatings, and the end surfaces where the thermal barrier coatings are located are provided with air outlet holes corresponding to each micro-mixing tube, and the end surfaces where the thermal barrier coatings are located are provided with cold air exhaust holes for exhausting the cooling air input into the outer chamber.

[0016] In a second aspect, some embodiments of the present disclosure provide a gas nozzle detection and early warning method for the above-mentioned first aspect, the gas nozzle detection and early warning method comprising: controlling a thermocouple element to perform temperature measurement on an injection surface of a gas nozzle in a working state at a plurality of preset angles respectively, so as to generate a temperature measurement information sequence, wherein each temperature measurement information in the above-mentioned temperature measurement information sequence comprises: a measurement angle and a measurement temperature value corresponding to the above-mentioned injection surface when the above-mentioned thermocouple element is measuring, wherein each jet hole on the injection surface of the above-mentioned gas nozzle is provided with a corresponding jet hole coordinate area and a jet hole identifier; when the above-mentioned thermocouple element measurement is finished, controlling a preset infrared temperature measuring sensor to measure the flame temperature distribution information of the above-mentioned injection surface; and The flame temperature distribution information is positionally calibrated with the temperature measurement information sequence to generate calibrated flame temperature distribution information and a converted measured temperature value sequence; the calibrated flame temperature distribution information is data calibrated using the converted measured temperature value sequence to generate gas nozzle temperature distribution information; the gas nozzle temperature distribution information is temperature-divided according to the jet coordinates of each jet hole on the injection surface to generate a jet hole temperature value set corresponding to each jet hole identifier; in response to determining that there is a jet hole temperature value exceeding a preset temperature range in the jet hole temperature value set, the jet coordinate corresponding to the jet hole temperature value exceeding the preset temperature range is used as warning information, and the warning device is controlled to issue a warning operation of jet hole blockage.

[0017] The above-mentioned various embodiments of the present disclosure have the following beneficial effects: through the gas nozzle for pure hydrogen gas turbine of some embodiments of the present disclosure, the risk of flashback in the gas turbine can be avoided. Specifically, the reason for the increased risk of flashback is that the diameter of the micro-mixing tube of the existing micro-mixed premixed combustion is mostly a single diameter. Although it can effectively reduce the emission of nitrogen oxides from hydrogen combustion, the activity of hydrogen in the premixed reaction and the higher flame speed make the flame front thinner, making it easier for the flame to move upstream. Based on this, the gas nozzle for pure hydrogen gas turbine of some embodiments of the present disclosure includes: a nozzle housing, a first hydrogen fuel pipe, a second hydrogen fuel pipe assembly, a first premixer, a second premixer, an airflow ring and a second hydrogen fuel pipe ventilation duct. The above-mentioned first hydrogen fuel pipe is coaxially fixed to the center axis position of the above-mentioned nozzle housing. Among them, the nozzle shell is a cylindrical hollow double-layer shell, the first hydrogen fuel pipe is a double-layer pipe, the interlayer space of the double-layer pipe is the first hydrogen fuel channel, and a circle of vents is provided at the bottom end of the outer tube of the first hydrogen fuel pipe, through which the hydrogen in the first hydrogen fuel channel flows into the fuel chamber of the first premixer. The air inlet end of the first hydrogen fuel pipe is provided with an air inlet hole, and in the working state, hydrogen is transported to the interlayer space of the first hydrogen fuel pipe through the air inlet hole. Secondly, the air flow annular member is coaxially fixed in the nozzle shell around the first hydrogen fuel pipe, and is used to isolate the second premixer from the fuel chamber of the first premixer; the first premixer is fixed in the chamber between the first hydrogen fuel pipe and the air flow annular member. The second premixer is fixed in the chamber between the air flow annular member and the outer shell of the nozzle shell. Wherein, the first premixer and the second premixer are both composed of multiple layers of micro-mixing tubes arranged layer by layer around the central axis of the nozzle housing, and each layer is composed of multiple micro-mixing tubes of different diameters, so as to pass the gas from the air inlet end to the air outlet end in the working state. The second hydrogen fuel pipe assembly is fixedly connected to the top edge of the nozzle housing, and the second hydrogen fuel pipe ventilation pipe is fixedly connected to the second hydrogen fuel pipe assembly. Wherein, each second hydrogen fuel pipe in the second hydrogen fuel pipe assembly transports hydrogen to the hollow chamber of the nozzle housing through the fixedly connected second hydrogen fuel pipe ventilation pipe, and the second hydrogen fuel pipe assembly is interconnected with the hollow chamber of the nozzle housing, so as to circulate hydrogen into the hollow chamber in the working state, and then circulate from the hollow chamber to the fuel chamber of the second premixer. Setting adjacent cylindrical micro-mixing tubes to different diameters will form inharmonic waves, which will further affect the propagation of sound waves and reduce the thermal acoustic instability of combustion. In addition, the uneven array of micro-mixing tubes of different diameters will affect the mixing uniformity of the fuel near the exhaust side of the nozzle, allowing the fuel to burn more fully and evenly, thereby effectively eliminating local high-temperature areas and hot spots in the flame tube of the combustion chamber, which can not only effectively reduce the emission of nitrogen oxides, but also prevent the flame from moving up and down and avoid the risk of flashback. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The above and other features, advantages and aspects of the embodiments of the present disclosure will become more apparent with reference to the following detailed description in conjunction with the accompanying drawings. Throughout the accompanying drawings, the same or similar reference numerals represent the same or similar elements. It should be understood that the drawings are schematic and that components and elements are not necessarily drawn to scale.

[0019] Figure 1 is a schematic overall cross-sectional view of a gas nozzle according to some embodiments of the gas nozzle disclosed herein;

[0020] Figure 2 is a schematic cross-sectional view of a first hydrogen fuel pipe according to some embodiments of the gas nozzle of the present disclosure;

[0021] Figure 3 is a schematic diagram of a micro-mixing tube arrangement structure according to some embodiments of a gas nozzle disclosed herein;

[0022] Figure 4 is a partial cross-sectional schematic diagram of a gas nozzle according to other embodiments of the gas nozzle disclosed herein;

[0023] Figure 5 is a front cross-sectional view of a gas nozzle according to other embodiments of the gas nozzle disclosed herein;

[0024] Figure 6 is a schematic cross-sectional view of an airflow ring member according to other embodiments of a gas nozzle disclosed herein;

[0025] Figure 7 is a front view of a gas outlet surface of a gas nozzle according to other embodiments of the gas nozzle disclosed herein;

[0026] Figure 8 The following is a flow chart of some embodiments of the gas nozzle detection and early warning method according to the present disclosure. DETAILED DESCRIPTION

[0027] Embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although certain embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be construed as being limited to the embodiments set forth herein. On the contrary, these embodiments are provided to provide a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are only for exemplary purposes and are not intended to limit the scope of protection of the present disclosure.

[0028] It should also be noted that, for ease of description, only the parts related to the invention are shown in the drawings. In the absence of conflict, the embodiments and features in the embodiments of the present disclosure can be combined with each other.

[0029] It should be noted that the concepts such as "first" and "second" mentioned in the present disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0030] It should be noted that the modifications of "one" and "plurality" mentioned in the present disclosure are illustrative rather than restrictive, and those skilled in the art should understand that unless otherwise clearly indicated in the context, it should be understood as "one or more".

[0031] The names of the messages or information exchanged between multiple devices in the embodiments of the present disclosure are only used for illustrative purposes and are not used to limit the scope of these messages or information.

[0032] The present disclosure will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0033] First, see Figure 1 , Figure 1 FIG. 1 is a schematic diagram of an overall cross-section of a gas nozzle according to some embodiments of the gas nozzle disclosed herein. Figure 1 As shown, the gas nozzle comprises: a nozzle housing 1, a first hydrogen fuel pipe 2, a second hydrogen fuel pipe assembly 3, a first premixer 4, a second premixer 5, an airflow ring 6 and a second hydrogen fuel pipe ventilation pipe 7, wherein:

[0034] The first hydrogen fuel pipe 2 is coaxially fixed to the center axis of the nozzle housing 1. The nozzle housing 1 is a cylindrical hollow double-layer housing, the first hydrogen fuel pipe 2 is a double-layer pipe, the interlayer space of the double-layer pipe is the first hydrogen fuel channel 23, and a circle of vent holes 22 are arranged at the bottom end of the outer layer of the first hydrogen fuel pipe 2, and the hydrogen in the first hydrogen fuel channel 23 flows into the fuel chamber of the first premixer 4 through the vent holes.

[0035] As an example, Figure 2 As shown, Figure 2 A circle of vent holes 22 is arranged at the bottom end of the outer tube of the first hydrogen fuel tube 22 .

[0036] The air inlet end of the first hydrogen fuel pipe 2 is provided with an air inlet hole 21. In the working state, hydrogen is transported to the interlayer space of the first hydrogen fuel pipe 2 through the air inlet hole 21.

[0037] The airflow annular member 6 is coaxially fixed in the nozzle housing 1 around the first hydrogen fuel pipe 2 , and is used to isolate the fuel chambers of the second premixer 5 and the first premixer 4 .

[0038] The first premixer 4 is fixed in a chamber between the first hydrogen fuel pipe 2 and the airflow annular member 6 .

[0039] The second premixer 5 is fixed in the chamber between the airflow annular member 6 and the shell of the nozzle housing 1. The first premixer 4 and the second premixer 5 are both composed of multiple layers of micro-mixing tubes arranged layer by layer around the central axis of the nozzle housing 1, and each layer is composed of multiple micro-mixing tubes of different diameters, which are used to pass the gas from the inlet end to the outlet end in the working state. Here, the inlet end can be Figure 1 The upper surface of the gas nozzle. The gas outlet can be Figure 1 The lower surface of the gas nozzle.

[0040] As an example, Figure 3 shown. Figure 3 In the schematic diagram of the micro-mixing tube arrangement structure shown in , the micro-mixing tubes are arranged crosswise with two different diameters (r1 and r2, and r1 is less than r2). In addition, micro-mixing tubes of two different diameters can also be arranged in a repeated cross form. For example, the arrangement is expressed in diameter as [r1, r1, r2, r1, r1, r2, r1, r1, r2…]. Or it can be expressed as [r1, r1, r2, r2, r1, r1, r2, r2, r1, r1 r2, r2,…], etc. No specific limitation is made here. In practice, the diameter of the micro-mixing tube can take any value greater than zero. That is, it can be an integer or a floating point number (for example, 1.3 mm, 2.4 mm, 5.6 mm, etc.). For another example, it can be 3 mm and 4 mm in diameter, or it can be 3.5 mm and 6 mm in diameter, etc. The diameter can be adjusted according to the process technology and actual needs, without specific limitation.

[0041] The second hydrogen fuel pipe assembly 3 is fixedly connected to the top edge of the nozzle housing 1. The second hydrogen fuel pipe ventilation pipe 7 is fixedly connected to the second hydrogen fuel pipe assembly 3. Among them, each second hydrogen fuel pipe in the second hydrogen fuel pipe assembly 3 transports hydrogen to the hollow chamber of the nozzle housing through the fixedly connected second hydrogen fuel pipe ventilation pipe 7. The second hydrogen fuel pipe assembly 3 is interconnected with the hollow chamber of the nozzle housing 1, and is used to circulate hydrogen into the hollow chamber in the working state, and then circulate from the hollow chamber to the fuel chamber of the second premixer 5.

[0042] In practice, the ratio of the total amount of hydrogen introduced into the air inlet 21 of the first hydrogen fuel pipe 2 to the total amount of hydrogen introduced into the second hydrogen fuel pipe vent 7 is a preset hydrogen ratio, so as to facilitate sufficient mixing of hydrogen and air. For example, the preset hydrogen ratio may be 1:3.

[0043] The above-mentioned various embodiments of the present disclosure have the following beneficial effects: the risk of flashback in the gas turbine can be avoided by the gas nozzle of some embodiments of the present disclosure. Specifically, the reason for the increased risk of flashback is that the diameter of the micro-mixing tube of the existing micro-mixed premixed combustion is mostly a single diameter. Although it can effectively reduce the emission of nitrogen oxides from hydrogen combustion, the activity of hydrogen in the premixed reaction and the higher flame speed make the flame front thinner, making it easier for the flame to move upstream. Based on this, the gas nozzle for a pure hydrogen gas turbine of some embodiments of the present disclosure includes: a nozzle housing, a first hydrogen fuel pipe, a second hydrogen fuel pipe assembly, a first premixer, a second premixer, an airflow ring and a second hydrogen fuel pipe ventilation duct. The above-mentioned first hydrogen fuel pipe is coaxially fixed to the center axis position of the above-mentioned nozzle housing. Among them, the nozzle shell is a cylindrical hollow double-layer shell, the first hydrogen fuel pipe is a double-layer pipe, the interlayer space of the double-layer pipe is the first hydrogen fuel channel, and a circle of vents is provided at the bottom end of the outer tube of the first hydrogen fuel pipe, through which the hydrogen in the first hydrogen fuel channel flows into the fuel chamber of the first premixer. The air inlet end of the first hydrogen fuel pipe is provided with an air inlet hole, and in the working state, hydrogen is transported to the interlayer space of the first hydrogen fuel pipe through the air inlet hole. Secondly, the air flow annular member is coaxially fixed in the nozzle shell around the first hydrogen fuel pipe, and is used to isolate the second premixer from the fuel chamber of the first premixer; the first premixer is fixed in the chamber between the first hydrogen fuel pipe and the air flow annular member. The second premixer is fixed in the chamber between the air flow annular member and the outer shell of the nozzle shell. Wherein, the first premixer and the second premixer are both composed of multiple layers of micro-mixing tubes arranged around the central axis of the nozzle housing, and the diameters of adjacent micro-mixing tubes in each layer of micro-mixing tubes are different, so as to pass the gas from the air inlet end to the air outlet end in the working state. The second hydrogen fuel pipe assembly is fixedly connected to the top edge of the nozzle housing, and the second hydrogen fuel pipe ventilation pipe is fixedly connected to the second hydrogen fuel pipe assembly. Wherein, each second hydrogen fuel pipe in the second hydrogen fuel pipe assembly transports hydrogen to the hollow chamber of the nozzle housing through the fixedly connected second hydrogen fuel pipe ventilation pipe, and the second hydrogen fuel pipe assembly is interconnected with the hollow chamber of the nozzle housing, so as to circulate hydrogen into the hollow chamber in the working state, and then circulate from the hollow chamber to the fuel chamber of the second premixer. Setting adjacent cylindrical micro-mixing tubes to different diameters will form inharmonic waves, which will further affect the propagation of sound waves and reduce the thermal acoustic instability of combustion. In addition, the uneven array of micro-mixing tubes of different diameters will affect the mixing uniformity of the fuel near the exhaust side of the nozzle, allowing the fuel to burn more fully and evenly, thereby effectively eliminating local high-temperature areas and hot spots in the flame tube of the combustion chamber, which can not only effectively reduce the emission of nitrogen oxides, but also prevent the flame from moving up and down and avoid the risk of flashback.

[0044] Second, see Figure 4 , Figure 4 FIG. 2 is a partial cross-sectional schematic diagram of a gas nozzle according to other embodiments of the gas nozzle disclosed herein. Figure 4 As shown, the first premixer 4 and the second premixer 5 are separated into an outer chamber 9 and an inner chamber 8 by a partition. Among them, each micro-mixing tube 10 in the first premixer 4 and the second premixer 5 is provided with a vent hole 11 at the position of the inner chamber 8, so as to circulate the gas entering the inner chamber 8 of the first premixer 4 and the second premixer 5 to the micro-mixing tube 10 in the working state, and the inner chamber 8 of the first premixer 4 and the second premixer 5 is separated by the air flow annular member 6.

[0045] In the working state, air is introduced into the air inlet ends of the first premixer 4 and the second premixer 5 to mix with the hydrogen in each micro-mixing tube and the chamber, and then the gas flows out through the air outlet ends.

[0046] In practice, a pure hydrogen inlet hole is provided on the micro-mixing tube 10 to enhance the mixing degree of hydrogen and air, eliminate local high temperature areas, and thus reduce the emission of nitrogen oxides.

[0047] As an example, see Figure 5 The gas inlet (inlet arrow) and outlet (outlet arrow) are marked in the figure. The gas mixture ratio can be

[0048] Next, please participate Figure 6 , Figure 6 Schematic diagram of the cross section of the airflow ring 6 according to other embodiments of the gas nozzle disclosed in the present invention. A vent hole 61 is provided at the position of the outer chamber 9 on the airflow ring 6. The outer chambers 9 of the first premixer 4 and the second premixer 5 are connected to each other through the vent hole on the airflow ring 6, which is used to flow the cooling gas flowing into the inner space of the airflow ring 6 into the outer chambers 9 of the first premixer 4 and the second premixer 5 in the working state, so as to cool the micro-mixing tube 10 and the gas nozzle at the position of the outer chamber 9.

[0049] In the process of adopting the above technical solutions to solve the technical problems in the background technology, the following technical problem is often accompanied: a large number of micro nozzles with simple structures are used to replace traditional large-diameter nozzles to convert large-scale flames into multiple small-scale flames. Although this can enhance the local mixing intensity of air and hydrogen and improve the mixing uniformity, due to its small size, the micro-mixed premixed combustion has obvious thermoacoustic instability, which induces structural resonance, thereby easily damaging the nozzle structure and reducing the service life of the nozzle.

[0050] Therefore, in response to the above-mentioned technical problem 2, combined with the existing gas turbine design reconstruction technology, the following solution can be determined.

[0051] Then, see further Figure 7 , Figure 7 Schematic diagram of the arrangement structure of the micro-mixing tubes 10 of other embodiments of the gas nozzle according to the present disclosure. The micro-mixing tubes 10 in the first premixer 4 and the second premixer 5 are arranged around the central axis of the gas nozzle in one layer, and the micro-mixing tubes 10 in adjacent layers have different inclination directions to form a cross arrangement.

[0052] As an example, Figure 3 As shown, the first cylindrical micro-mixing tube 10 on the first ring (first layer) can be tilted clockwise, and the angle between its central axis and the central axis of the nozzle is 30°. The second cylindrical micro-mixing tube 10 on the second ring is tilted counterclockwise. Among them, the angle between the central axis and the central axis of the nozzle is 30°.

[0053] Optionally, the micro-mixing tube can also be set to 3 or more different diameters. Specifically, different diameters can be set according to process technology and actual needs, and no specific limitation is made.

[0054] Optionally, the air inlet end faces of the first premixer 4 and the second premixer 5 are rounded, and the air inlet end of the airflow ring 6 is rounded. The rounded design of the inlet end faces of the micro-mixing tube 10 and the airflow ring 6 channel can avoid turbulent dissipation caused by air velocity disturbance, ensure air intake uniformity, and increase the mixing effect of air and pure hydrogen.

[0055] Optionally, the central axis of the micro-mixing tube 10 can be set to other inclination angles to ensure that the angle with the central axis of the nozzle is an acute angle (such as within 5°-85°). On the one hand, the length of the micro-mixing tube 10 can be increased by inclination without increasing the height of the micro-mixing tube 10, and the head size of the combustion chamber can be reduced. On the other hand, the purpose of fully mixing hydrogen and air can be achieved, local high temperature areas can be eliminated, thermoacoustic oscillations can be avoided, and the uniformity of outlet temperature distribution can be improved.

[0056] The above-mentioned implementation mode and its related contents, as an inventive point of the embodiment of the present disclosure, solve the above-mentioned technical problem 2 "how to improve the service life of the gas nozzle". The factors that lead to the reduction of the service life of the nozzle are often as follows: using a large number of micro nozzles with simple structures to replace the traditional large-diameter nozzles, converting the large-scale flame into multiple small-scale flames, although it can enhance the local mixing intensity of air and hydrogen and improve the mixing uniformity, but due to the small size, the micro-mixed premixed combustion has obvious thermoacoustic instability, which induces structural resonance, thus easily destroying the nozzle structure. If the above factors are solved, the service life of the gas nozzle can be improved. In order to achieve this effect, first, by setting the micro-mixing tubes in opposite inclination directions, the propagation direction of the sound wave will be changed, and the transmission vibration frequency and amplitude of each other's sound waves will be weakened. Then, the tube diameter is different, the turbulent flow is different, and the sound wave frequency and amplitude are different. Setting adjacent cylindrical micro-mixing tubes to different diameters will form inharmonic waves, which will further affect the propagation of sound waves and reduce combustion thermoacoustic instability. In addition, the uneven array of micro-mixing tubes with different diameters will affect the mixing uniformity of the fuel near the exhaust side of the nozzle, so that the fuel can be burned more fully and evenly. Thus, the local high temperature area and hot spots in the flame tube of the combustion chamber are effectively eliminated, thereby reducing the emission of nitrogen oxides and improving the uniformity of the temperature distribution at the combustion chamber outlet, thereby reducing the emission of nitrogen oxides. At the same time, the cross-tilted arrangement can form a reverse weak swirl structure, which affects the propagation direction of the sound wave and reduces the oscillation frequency and amplitude. This avoids the structural resonance phenomenon, thereby greatly extending the service life of the gas nozzle.

[0057] Finally, see Figure 8 , Figure 8 1 is a front view of the gas outlet surface of the gas nozzle according to other embodiments of the gas nozzle of the present disclosure. The gas outlet end surface of the outer chamber 9 of the first premixer 4 and the second premixer 5 is provided with a thermal barrier coating 12. The end surface of the thermal barrier coating 12 is provided with gas outlet holes 13 corresponding to each micro-mixing tube 10. And the end surface of the thermal barrier coating 12 is provided with air film holes 121 for discharging the air input into the outer chamber 9.

[0058] In practice, air film holes are set on the exhaust side end face of the nozzle and air cooling is used to effectively avoid cracks in the nozzle structure at the exhaust end due to excessive thermal stress on the exhaust side, thereby reducing the risk of fuel leakage.

[0059] See below Figure 8 , Figure 8 A flowchart 800 is shown of some embodiments of a gas nozzle detection early warning method according to the present disclosure.

[0060] In the process of using the above technical solutions to solve the technical problems in the background technology, the following technical problem three is often accompanied: how to detect the blockage of the gas nozzle's air holes based on the temperature of the gas nozzle. For the above technical problem three, the usual solution is: measure the temperature of the gas nozzle in the working state through a single thermocouple element; and if you want to measure more accurately, measure the temperature of different parts of the gas nozzle multiple times through a single thermocouple element; or measure by setting multiple thermocouple elements. In addition, you can also measure the temperature by setting a temperature measuring paint, and judge whether there is a blockage by the measured temperature. However, the above method still has the following technical problems: First, the measurement range of the thermocouple element is relatively limited, and a single measurement takes a long time. Even if multiple thermocouple elements are set to measure at the same time, it is difficult to measure the overall temperature distribution of the gas nozzle. Second, because the gas nozzle's air holes are set small and dense, although the temperature measuring paint can measure the temperature distribution, the measurement result is easy to form an overall temperature distribution, making it impossible to distinguish the granularity of the temperature distribution and difficult to distinguish the local temperature. Even if part of the air hole is blocked, it is covered by the nearby flame temperature. Therefore, it is difficult to determine whether the air jet hole is blocked based on the measurement results.

[0061] Therefore, in response to the above-mentioned technical problem three, combined with the measurement equipment and measurement-related technologies available, the following solution can be determined.

[0062] The gas nozzle detection and early warning method for the gas nozzle of a pure hydrogen gas turbine comprises the following steps:

[0063] Step 801 : Controlling the thermocouple element to measure the temperature of the injection surface of the gas nozzle in the working state at a plurality of preset angles respectively, so as to generate a temperature measurement information sequence.

[0064] In some embodiments, the execution subject of the gas nozzle detection and early warning method can control the thermocouple element to respectively detect the injection surface (such as Figure 8 The temperature of the injection surface is measured by measuring the outer flame of the injection surface to generate a temperature measurement information sequence. Each temperature measurement information in the temperature measurement information sequence may include: the measurement angle and the measured temperature value corresponding to the injection surface when the thermocouple element is measured. Each injection hole of the injection surface of the gas nozzle is provided with a corresponding injection hole coordinate area and injection hole identification.

[0065] As an example, the multiple preset angles may be "0 degrees, 90 degrees, 180 degrees, 270 degrees", or "30 degrees, 90 degrees, 150 degrees, 230 degrees, 270 degrees, 330 degrees", etc. Here, the preset angle is the angle corresponding to the injection surface. The angle between a fixed ray passing through the center of the injection surface and another variable ray passing through the center of the circle. The position of the other ray is the measurement position of the probe on the thermocouple element. Each measured temperature value can represent the average temperature value of the gas nozzle at the corresponding position of the thermocouple element. In addition, a jet hole identifier is pre-set for each jet hole.

[0066] Step 802, when the thermocouple element measurement is finished, control the preset infrared temperature sensor to measure the flame temperature distribution information of the injection surface.

[0067] In some embodiments, the execution subject may control a preset infrared temperature sensor to measure the flame temperature distribution information of the injection surface when the thermocouple element measurement is completed. The thermocouple element may be removed when the thermocouple element measurement is completed, and then the preset infrared temperature sensor may be controlled to measure the flame temperature distribution information of the injection surface. Here, the flame temperature distribution information may characterize the flame temperature distribution of the injection surface.

[0068] Step 803: Positionally calibrate the flame temperature distribution information and the temperature measurement information sequence to generate calibrated flame temperature distribution information and a converted measured temperature value sequence.

[0069] In some embodiments, the execution entity may perform position calibration on the flame temperature distribution information and the temperature measurement information sequence to generate calibrated flame temperature distribution information and a converted measured temperature value sequence.

[0070] In some optional implementations of some embodiments, the execution subject performs position calibration on the flame temperature distribution information and the temperature measurement information sequence to generate calibrated flame temperature distribution information and a converted measured temperature value sequence, which may include the following steps:

[0071] The first step is to convert the flame temperature distribution information to the target coordinate system to obtain the calibrated temperature distribution information. The target coordinate system is established with the center of the injection surface of the gas nozzle as the origin, and the jet hole coordinate area of ​​each jet hole is the coordinate area in the target coordinate system. The horizontal axis of the target coordinate system can be a ray fixed by the thermocouple element during the measurement process, and the vertical axis can be a vertical ray through the center of the circle to establish the coordinate system. Here, each coordinate in the flame temperature distribution information can be converted to the target coordinate system through the relative conversion matrix between the infrared temperature sensor coordinate system and the target coordinate system measured in advance. In addition, a range of the same size as the injection surface area (such as a circular formula of the same size as the injection surface) can be limited in the target coordinate system.

[0072] The second step is to determine the coordinates of the measurement angles included in each temperature measurement information in the temperature measurement information sequence in the target coordinate system to obtain a measurement coordinate group, wherein the intersection coordinates of the ray of each measurement angle and the edge of the injection surface in the target coordinate system can be determined as the measurement coordinates.

[0073] The third step is to add the measured temperature values ​​included in each temperature measurement information in the temperature measurement information sequence to the positions of the corresponding measurement coordinates in the measurement coordinate group to obtain a converted measured temperature value sequence.

[0074] Step 804, using the converted measured temperature value sequence, data calibration is performed on the calibrated flame temperature distribution information to generate gas nozzle temperature distribution information.

[0075] In some embodiments, the execution entity may utilize the converted measured temperature value sequence to perform data calibration on the calibrated flame temperature distribution information to generate gas nozzle temperature distribution information.

[0076] In some optional implementations of some embodiments, the execution subject uses the converted measured temperature value sequence to perform data calibration on the calibrated flame temperature distribution information to generate the gas nozzle temperature distribution information, which may include the following steps:

[0077] In the first step, the nozzle area in the target coordinate system is divided into regions according to the measurement coordinate group and the measurement angles included in each temperature measurement information in the temperature measurement information sequence to obtain a divided region group. The circular region corresponding to the ejection surface in the target coordinate system can be evenly divided with each measurement angle as the center to obtain a plurality of sector-shaped regions as the divided region group.

[0078] The second step is to determine the average temperature value in each divided area in the divided area group in the calibrated flame temperature distribution information to obtain a temperature average value group. The average temperature value of each coordinate in each divided area in the divided area group can be determined as the temperature average value.

[0079] The third step is to adjust the data of the calibrated flame temperature distribution information according to the above-mentioned temperature average value group and the above-mentioned converted measured temperature value sequence to generate the gas nozzle temperature distribution information. Among them, for each temperature average value and the converted measured temperature value corresponding to the same area, the difference between the average temperature value and the converted measured temperature value can be determined as the measured temperature difference. Then, the temperature value of each coordinate in the area where the above-mentioned temperature average value is located in the above-mentioned calibrated flame temperature distribution information can be subtracted from the above-mentioned measured temperature difference to obtain the adjusted temperature value. In this way, the data adjustment of the temperature value of each coordinate in the circumferential area corresponding to the injection surface in the target coordinate system is completed to obtain the gas nozzle temperature distribution information.

[0080] Step 805 , dividing the temperature distribution information of the gas nozzle according to the jet coordinates of each jet hole on the jet surface, so as to generate a jet hole temperature value set corresponding to each jet hole identifier.

[0081] In some embodiments, the execution entity may perform temperature division on the gas nozzle temperature distribution information according to the jet coordinates of each jet hole on the jet surface to generate a jet hole temperature value set corresponding to each jet hole identifier.

[0082] In some optional implementations of some embodiments, the execution subject divides the temperature distribution information of the gas nozzle according to the jet coordinates of each jet hole on the injection surface to generate a jet hole temperature value set corresponding to each jet hole identifier, which may include the following steps:

[0083] The first step is to determine the temperature distribution values ​​of each coordinate position in each jet hole coordinate area in the above-mentioned gas nozzle temperature distribution information according to the jet hole coordinate area corresponding to each jet hole, and obtain a set of temperature distribution value groups. For each jet hole coordinate area, the temperature distribution values ​​corresponding to each coordinate in the area can be determined.

[0084] In the second step, the mean of each temperature distribution value in each temperature distribution value group in the above temperature distribution value group set is determined as the jet hole temperature value to obtain the jet hole temperature value set.

[0085] Step 806, in response to determining that there is a jet hole temperature value exceeding the preset temperature range in the jet hole temperature value set, the jet coordinates corresponding to the jet hole temperature value exceeding the preset temperature range are used as warning information, and the warning device is controlled to issue a warning operation of jet hole blockage.

[0086] In some embodiments, the execution subject may respond to the determination that there is a jet hole temperature value exceeding a preset temperature range in the jet hole temperature value set, use the jet coordinates corresponding to the jet hole temperature value exceeding the preset temperature range as warning information, and control the warning device to issue a warning operation of jet hole blockage. The warning device may include a voice device or a display device. The warning operation may be a voice prompt or display of warning information to remind the operator of the jet hole blockage.

[0087] The above steps 801-806 and their related contents, as an inventive point of an embodiment of the present disclosure, solve the above-mentioned technical problem three "how to detect the pore blockage of the gas nozzle based on the temperature of the gas nozzle". The factors that make it difficult to perform pore blockage detection well are often as follows: measuring the temperature of the gas nozzle in the working state through a single thermocouple element; and if you want to measure more accurately, measure the temperature of different parts of the gas nozzle multiple times through a single thermocouple element; or measure by setting multiple thermocouple elements. In addition, you can also set a temperature measuring paint to measure the temperature, and judge whether there is a blockage by the measured temperature. However, the above method still has the following technical problems: First, the measurement range of the thermocouple element is relatively limited, and a single measurement takes a long time. Even if multiple thermocouple elements are set to measure at the same time, it is difficult to measure the overall temperature distribution of the spray surface of the gas nozzle. Second, because the gas nozzle's jet holes are set small and dense, although the measurement of the temperature measuring paint can measure the temperature distribution, the measurement result is easy to form an overall temperature distribution, making it impossible to distinguish the granularity of the temperature distribution and difficult to distinguish the local temperature. Even if part of the jet hole is blocked, it is covered by the temperature of the nearby flame. Therefore, it is difficult to determine whether the jet hole is blocked based on the measurement results. If the above factors are solved, the pore blockage detection can be accurately performed. In order to achieve this effect, first of all, it is considered that although a single thermocouple element measures the gas nozzle accurately, it is difficult to measure the range. Therefore, by controlling the thermocouple element to measure the temperature of the injection surface of the gas nozzle in the working state at multiple preset angles, a temperature measurement information sequence is obtained. In order to accurately identify the specific blocked jet hole, the jet hole is marked in advance. At the same time, at the end of the measurement of the above thermocouple element, the flame temperature distribution information of the above injection surface is measured by controlling the preset infrared temperature sensor, thereby obtaining the entire temperature distribution of the injection surface of the gas nozzle. Then, in order to merge the two types of information, the two types of information can be converted into the same coordinate system through position calibration to generate the calibrated flame temperature distribution information and the converted measured temperature value sequence. In practice, although the measurement range of the thermocouple element is limited, the measurement accuracy is high. Although the infrared temperature sensor can measure the temperature distribution, there is a large measurement error. Therefore, the above-mentioned embodiment of the present application uses the data measured by the thermocouple element as the standard reference temperature to calibrate the measurement results of the infrared temperature sensor to improve the accuracy of the temperature distribution information of the gas nozzle. In this way, high-precision temperature distribution information of the entire injection surface of the gas nozzle is measured. Then, through temperature division, it can be used to determine the temperature values ​​corresponding to each coordinate in each jet hole coordinate area in the target coordinate system. Therefore, it can be used to distinguish the temperature conditions of each jet hole. Finally, it is determined whether the jet hole is blocked by judging whether the temperature value of each jet hole area exceeds the preset temperature range.Thus, the gas nozzle pore blockage detection is completed based on the temperature of the gas nozzle. Then, an early warning can be given in time according to the detection result for the maintenance of the gas nozzle. This avoids the gas nozzle from being blocked for a long time and causing damage, and also prolongs the service life of the gas nozzle.

[0088] The above descriptions are only some preferred embodiments of the present disclosure and an explanation of the technical principles used. Those skilled in the art should understand that the scope of the invention involved in the embodiments of the present disclosure is not limited to the technical solutions formed by a specific combination of the above-mentioned technical features, but should also cover other technical solutions formed by any combination of the above-mentioned technical features or their equivalent features without departing from the above-mentioned inventive concept. For example, the above-mentioned features are replaced with the technical features with similar functions disclosed in the embodiments of the present disclosure (but not limited to) and the technical solutions formed.

Claims

1. A gas nozzle for a pure hydrogen gas turbine, characterized in that: The gas nozzle comprises: a nozzle housing, a first hydrogen fuel pipe, a second hydrogen fuel pipe assembly, a first premixer, a second premixer, an air flow ring, and a second hydrogen fuel pipe ventilation pipe, wherein: The first hydrogen fuel pipe is coaxially fixed to the center axis of the nozzle housing, wherein the nozzle housing is a cylindrical hollow double-layer housing, the first hydrogen fuel pipe is a double-layer pipe, the interlayer space of the double-layer pipe is the first hydrogen fuel channel, and a circle of vent holes is arranged at the bottom end of the outer layer of the first hydrogen fuel pipe, and the hydrogen in the first hydrogen fuel channel flows into the fuel chamber of the first premixer through the vent holes; The air inlet end of the first hydrogen fuel pipe is provided with an air inlet hole, and in a working state, hydrogen is transported to the interlayer space of the first hydrogen fuel pipe through the air inlet hole; The airflow annular member is coaxially fixed in the nozzle housing around the first hydrogen fuel pipe and is used to isolate the fuel chamber of the second premixer from that of the first premixer; The first premixer is fixed in the chamber between the first hydrogen fuel pipe and the airflow annular member; The second premixer is fixed in a chamber between the airflow annular member and the outer shell of the nozzle housing, wherein the first premixer and the second premixer are both composed of multiple layers of micro-mixing tubes arranged layer by layer around the central axis of the nozzle housing, and each layer is composed of multiple micro-mixing tubes of different diameters, so as to pass the gas from the air inlet end to the air outlet end in a working state; The second hydrogen fuel pipe assembly is fixedly connected to the top edge of the nozzle housing, and the second hydrogen fuel pipe ventilation pipe is fixedly connected to the second hydrogen fuel pipe assembly, wherein each second hydrogen fuel pipe in the second hydrogen fuel pipe assembly transports hydrogen to the hollow chamber of the nozzle housing through the fixedly connected second hydrogen fuel pipe ventilation pipe, and the second hydrogen fuel pipe assembly is interconnected with the hollow chamber of the nozzle housing, and is used to flow hydrogen into the hollow chamber in the working state, and then flow from the hollow chamber to the fuel chamber of the second premixer.

2. The gas nozzle according to claim 1, characterized in that: The first premixer and the second premixer are separated into an outer chamber and an inner chamber by a partition, wherein: Each micro-mixing tube in the first premixer and the second premixer is provided with a vent hole at the position of the inner chamber, so as to allow the gas introduced into the inner chamber of the first premixer and the second premixer to flow into the micro-mixing tube in the working state, and the inner chamber of the first premixer and the second premixer is isolated by the air flow annular member; In the working state, air is introduced into the air inlet ends of the first premixer and the second premixer to mix with the hydrogen in each micro-mixing tube and the chamber, and then the gas flows out through the air outlet ends.

3. The gas nozzle according to claim 2, characterized in that: The airflow annular member is provided with a vent hole at the position of the outer chamber, wherein: The outer chambers of the first premixer and the second premixer are connected to each other through the vent holes on the airflow ring, and are used to flow the cooling gas flowing into the internal space of the airflow ring into the outer chambers of the first premixer and the second premixer in the working state, so as to cool the micro-mixing tubes and the gas nozzles at the outer chamber positions.

4. The gas nozzle according to claim 1, characterized in that: The air inlet end faces of the first premixer and the second premixer are configured as rounded corners, and the air inlet end of the air flow annular member is configured as rounded corners.

5. The gas nozzle according to claim 1, characterized in that: The air outlet end faces of the outer chambers of the first premixer and the second premixer are provided with thermal barrier coatings, and the end faces where the thermal barrier coatings are located are provided with air outlet holes corresponding to each micro-mixing tube, and the end faces where the thermal barrier coatings are located are provided with cold air exhaust holes for exhausting the cooling air input into the outer chamber.

6. A gas nozzle detection and early warning method as described in any one of claims 1 to 5, comprising: Controlling the thermocouple element to measure the temperature of the injection surface of the gas nozzle in the working state at a plurality of preset angles respectively, so as to generate a temperature measurement information sequence, wherein each temperature measurement information in the temperature measurement information sequence includes: a measurement angle and a measurement temperature value corresponding to the injection surface when the thermocouple element is measuring, and each injection hole on the injection surface of the gas nozzle is provided with a corresponding injection hole coordinate area and an injection hole identifier; When the thermocouple element measurement is finished, controlling a preset infrared temperature sensor to measure the flame temperature distribution information of the injection surface; Performing position calibration on the flame temperature distribution information and the temperature measurement information sequence to generate calibrated flame temperature distribution information and a converted measured temperature value sequence; Using the converted measured temperature value sequence, data calibration is performed on the calibrated flame temperature distribution information to generate gas nozzle temperature distribution information; According to the jet coordinates of each jet hole on the jet surface, the temperature distribution information of the gas nozzle is divided into temperature values ​​to generate a jet hole temperature value set corresponding to each jet hole identifier; In response to determining that there is a jet hole temperature value exceeding a preset temperature range in the jet hole temperature value set, the jet coordinates corresponding to the jet hole temperature value exceeding the preset temperature range are used as warning information, and the warning device is controlled to issue a warning operation of jet hole blockage.

Images