Nozzle device for adapting to the change of gaseous fuel usage and gas turbine having the same

Abstract

The present invention discloses a nozzle device for adapting to the change of gaseous fuel use and a gas turbine having the same, including: a first adapter, a second adapter and a dual-fuel nozzle. An air extraction cavity, an inner flow channel and an outer flow channel are provided in the dual-fuel nozzle. The injection end of the dual-fuel nozzle has a nozzle head, and a plurality of inner flow channel spray holes and outer flow channel spray holes are formed in the nozzle head. The dual-fuel nozzle is used to adaptively select to connect the first adapter or the second adapter according to the type of gaseous fuel. Fuel channels and air extraction channels are provided in both of them. The fuel channel in the first adapter is used to communicate with the outer flow channel, and the air extraction channel in the first adapter communicates the air extraction cavity and the inner flow channel. The fuel channel in the second adapter communicates with the inner flow channel, and the air extraction channel in the second adapter communicates the air extraction cavity and the outer flow channel. For the device of the present invention, when the types of gaseous fuel are different, only by replacing the corresponding adapter to make the gaseous fuel enter the pre-set flow channel, the combustion requirements of the gas turbine can be met.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular, to a nozzle device for adapting to the change of gaseous fuel use. In addition, the present invention also relates to a gas turbine including the above nozzle device for adapting to the change of gaseous fuel use. Background Art

[0002] The compatibility of ground gas turbines and aero-engines with multiple fuels can bring great economic benefits: ground gas turbines can select the most economical fuel according to market prices to reduce operating costs, reduce dependence on a single fuel, avoid shutdown risks caused by supply interruptions or price fluctuations, and in addition, it is suitable for areas with diverse fuel resources and improves equipment utilization; aero-engines can use multiple fuels (such as aviation kerosene, diesel, or synthetic fuels) to improve mission adaptability in specific situations (such as remote areas). In addition, when fuel supply is restricted, multi-fuel compatibility can ensure the continuous operation of the aircraft.

[0003] At present, ground gas turbines and aero-engines rarely have the function of compatible multi-fuel continuous combustion. If you want to change the fuel, you need to disassemble the ground gas turbine and aero-engine in the factory, replace the combustion components suitable for other fuels, and then assemble them. The change cycle is too long, and there are technical risks in the disassembly and assembly process, which may introduce factors that cause the deterioration of the gas turbine state. After retrieval, it is found that ground gas turbines and aero-engines rarely have the technology of compatible multi-fuels, especially for the solutions that can change fuels. Now, the technical solutions of existing gas turbines burning multi-fuels retrieved are briefly described:

[0004] Patent 1: CN206890575U, a multi-fuel nozzle, a fuel injection system, and a turbine engine thereof; the multi-fuel nozzle includes a nozzle body, and a first fuel flow channel and a second fuel flow channel are arranged in the nozzle body. In a cross-section perpendicular to the fuel flow direction, the first fuel flow channel is arranged in the middle, and a plurality of the second fuel flow channels are arranged in the circumferential direction of the first fuel flow channel. A variety of fuel flow channels are arranged in the nozzle body. According to the type of fuel and the combustion requirements of the turbine engine, the fuel can be proportionally distributed into different fuel flow channels and ejected by using a fluid distribution device, so as to meet the combustion requirements of a variety of fuels.

[0005] Patent Two: CN103930725B, an improved multi-fuel nozzle and a method for modifying a dual-fuel nozzle, which is a multi-fuel nozzle for a gas turbine. The nozzle includes: an annular body including a plurality of gas channels, all of the gas channels being circumferentially arranged around the longitudinal axis of the body; an annular fuel body placed in the annular body and including a central oil channel coaxial with the longitudinal axis of the body; an annular cooling air channel located between the annular body and the fuel body; and a discrete cooling air body including a guide member, the guide member being supported independently of the downstream end of the body and configured to radially and inwardly direct the cooling air traveling downstream in the annular cooling air channel to a directly downstream position downstream of the downstream end of the central oil channel.

[0006] 1) Patent One only provides a nozzle structure for simultaneously supplying multiple fuels to a turbine engine for combustion in a certain proportion, rather than a solution for enabling a turbine engine to still operate after changing the fuel used.

[0007] 2) Patent Two also provides a nozzle structure for simultaneously supplying multiple fuels to a turbine engine for combustion in a certain proportion. Its innovation lies in that liquid fuel is supplied in the center of the nozzle, and gaseous fuel is supplied around the center of the nozzle. The normal-temperature gaseous fuel is used to cool the high-temperature nozzle, preventing the liquid fuel from carbonizing due to high temperature at the nozzle head and affecting the nozzle performance. At the same time, the thermal stress of the nozzle is reduced to increase its service life. It is also not a solution for enabling a turbine engine to still operate after changing the fuel used. Summary of the Invention

[0008] The present invention provides a nozzle device for adapting to the change of gaseous fuel used and a gas turbine having the same, so as to solve the technical problems that the existing engine disassembly and replacement have a too long change cycle, and there are technical risks in the disassembly and assembly processes, which may introduce factors leading to the deterioration of the gas turbine state, and the existing nozzle structure cannot achieve a solution for enabling a turbine engine to still operate after changing the fuel used.

[0009] The technical solution adopted by the present invention is as follows:

[0010] A nozzle device for adapting to the change of use of gaseous fuel, comprising: a first adapter, a second adapter and a dual-fuel nozzle; the dual-fuel nozzle is provided with an induced air cavity for connecting the airflow to the engine combustion chamber, an inner flow channel for guiding the flow and an outer flow channel arranged in a ring outside the inner flow channel, the injection end of the dual-fuel nozzle has a nozzle head, and the nozzle head is provided with a plurality of inner flow channel spray holes connecting the inner flow channel and a plurality of outer flow channel spray holes connecting the outer flow channel; the dual-fuel nozzle is used to adaptively select and connect the first adapter or the second adapter according to the type of gas fuel, both the first adapter and the second adapter are provided with a fuel channel for conveying gas fuel and an induced air channel for conveying airflow, the fuel channel in the first adapter is used to communicate with the outer flow channel, the induced air channel in the first adapter is used to connect the induced air cavity and the inner flow channel, the fuel channel in the second adapter is used to communicate with the inner flow channel, and the induced air channel in the second adapter is used to connect the induced air cavity and the outer flow channel.

[0011] Furthermore, the injection end of the nozzle head has a number of regularly arranged spray holes; the outer flow channel gradually transitions from an annular cavity in the nozzle head to form an irregular and single-chamber outer flow air cavity, and a number of outer flow channel spray holes extending along the axial direction of the nozzle head are provided at the bottom of the outer flow air cavity, and the outer flow channel spray holes connect the outer flow air cavity and the corresponding spray holes on the injection end of the nozzle head; the inner flow channel first gradually transitions from a single cavity in the axial direction of the nozzle head to form a plurality of inner flow air channels that are not connected to each other, and then gradually transitions from a plurality of inner flow air channels to form an irregular and single-chamber inner flow air cavity, and a number of inner flow channel spray holes extending along the axial direction of the nozzle head are provided at the bottom of the inner flow air cavity, and the inner flow channel spray holes connect the inner flow air cavity and the corresponding spray holes on the injection end of the nozzle head.

[0012] Furthermore, the plurality of spray holes are arranged in concentric rings on the injection end face, and each concentric ring has a plurality of spray holes evenly spaced along the circumferential direction, and the diameter of the spray holes on each concentric ring gradually increases along the radial direction.

[0013] Furthermore, the dual-fuel nozzle also includes a connecting head and a nozzle tube; the connecting head is used to be detachably connected to the first adapter or the second adapter, and an air induction cavity is provided in the adapter; the two ends of the nozzle tube are respectively connected to the connecting head and the nozzle head, and the inner flow channel and the outer flow channel extend along the length direction of the nozzle tube and are arranged in the nozzle tube.

[0014] Furthermore, the connector includes a connector body which is hollow and open at one end and closed at the other end, and a mounting ear seat fixedly connected to the outer circle of the connector body; the inner cavity of the connector body forms an adapter mounting hole and an air inlet cavity which are arranged in sequence along its length direction, and the first adapter or the second adapter is inserted into the adapter mounting hole from the open end of the connector body and then disassembled to connect the dual-fuel nozzle, and an air inlet which is arranged through the wall is opened on the side wall of the air inlet cavity; an inner flow channel inlet connected to the inner flow channel and an outer flow channel inlet connected to the outer flow channel are provided on the closed end of the connector body.

[0015] Furthermore, the dual-fuel nozzle is formed by an additive manufacturing process.

[0016] Furthermore, both the first adapter and the second adapter include an adapter body for detachably fixing to the connector body. The fuel passage in the first adapter includes a first fuel passage formed by inwards concave extension from the top end of the adapter body, and a plurality of adapter passages that communicate with the blind end of the first fuel passage and extend downwards and then penetrate through the outer wall surface at the bottom end of the adapter body. The adapter passages are used to communicate the first fuel passage and the outer flow passage inlet. The air intake passage in the first adapter penetrates through the bottom end of the adapter body to communicate the air intake cavity and the inner flow passage inlet, and the adapter passages and the air intake passage are arranged circumferentially offset. The fuel passage in the second adapter is a second fuel passage that axially penetrates through the adapter body to communicate the inner flow passage inlet. The air intake passage in the second adapter penetrates through the bottom end of the adapter body to communicate the air intake cavity and the outer flow passage inlet.

[0017] Furthermore, the adapter body includes an external mounting head, a hexagonal platform, a connecting column, an air intake column, and a sealing head that are sequentially connected along the axis. The adapter body is axially inserted into the connector body so that the connecting column is threadedly connected to the adapter mounting hole. The air intake column corresponds to the air intake cavity, and the outer diameter of the air intake column is smaller than the inner diameter of the air intake cavity to form an annular air intake groove with the air intake cavity. The sealing head is used to tightly press against the bottom surface of the air intake cavity to cut off the direct communication between the inner flow passage inlet and the outer flow passage inlet and the air intake groove, and both the air intake passage and the adapter passage are arranged on the sealing head.

[0018] Furthermore, the outer wall surface of the external mounting head is provided with an external thread for detachably connecting to an external connecting pipe. The cross-section of the hexagonal platform is polygonal for receiving force during the installation of the adapter body. The sealing head is conical to cooperate with the conical surface at the bottom of the air intake cavity to seal the communication between the inner flow passage inlet and the outer flow passage inlet and the air intake groove.

[0019] According to another aspect of the present invention, a gas turbine is also provided, which is internally provided with a nozzle device for adapting to the change of gaseous fuel use as described in any one of the above.

[0020] The present invention has the following beneficial effects:

[0021] The present invention relates to a nozzle device for adapting to the change of gaseous fuel use. When designing, the number of inner flow path spray holes and the layout of the inner flow path spray holes on the injection end face of the nozzle head are correspondingly set according to the type of gaseous fuel to be flowed in the inner flow path to meet the combustion requirements, and the number of outer flow path spray holes and the layout of the outer flow path spray holes on the injection end face of the nozzle head are correspondingly set according to the type of gaseous fuel to be flowed in the outer flow path to meet the combustion requirements. Thus, when the types of gaseous fuels are different, only by replacing the corresponding adapter to make the gaseous fuel enter the pre-set flow path can the combustion requirements of the gas turbine be met. Since only by replacing the adapter after the equipment is shut down can the purpose of the gas turbine burning another gaseous fuel be achieved without returning to the factory to disassemble the engine body, the replacement efficiency is greatly improved, the risks existing in the replacement process and the labor intensity of the replacement operation are reduced; compared with the prior art nozzle schemes in which a variety of fuels are supplied to the turbine engine for combustion in a certain proportion at the same time, most of the fuels are liquid fuels, and the combustion efficiency is lower than that of gaseous fuels. There is an essential difference compared with the function of the nozzle device of the present invention that can be compatible with a variety of gaseous fuels for continuous combustion. The device of the present invention can further improve the combustion efficiency of the fuel, and can select the most economical gaseous fuel according to the market price to reduce the operation cost, reduce the dependence on a certain specific gaseous fuel, and avoid the shutdown risk caused by supply interruption or price fluctuation;

[0022] For the gas turbine of the present invention, when the types of gaseous fuels are different, only by replacing the corresponding adapter to make the gaseous fuel enter the pre-set flow path can the combustion requirements of the gas turbine be met. And since only by replacing the adapter after the equipment is shut down can the purpose of the gas turbine burning another gaseous fuel be achieved without returning to the factory to disassemble the engine body, the replacement efficiency is greatly improved, the risks existing in the replacement process and the labor intensity of the replacement operation are reduced; compared with the prior art nozzle schemes in which a variety of fuels are supplied to the turbine engine for combustion in a certain proportion at the same time, most of the fuels are liquid fuels, and the combustion efficiency is lower than that of gaseous fuels. There is an essential difference compared with the function of the nozzle device of the present invention that can be compatible with a variety of gaseous fuels for continuous combustion. The device of the present invention can further improve the combustion efficiency of the fuel, and can select the most economical gaseous fuel according to the market price to reduce the operation cost, reduce the dependence on a certain specific gaseous fuel, and avoid the shutdown risk caused by supply interruption or price fluctuation.

[0023] In addition to the purposes, features and advantages described above, the present invention has other purposes, features and advantages. The following will refer to the drawings for a further detailed description of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The drawings forming a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0025] Figure 1 It is a schematic diagram of the spatial structure of the nozzle device for adapting to the change of gaseous fuel use in the preferred embodiment of the present invention;

[0026] Figure 2 is Figure 1 a schematic diagram of the spatial structure of the dual-fuel nozzle in;

[0027] Figure 3 is Figure 2 the first sectional structure diagram of;

[0028] Figure 4 is Figure 2 the second sectional structure diagram of;

[0029] Figure 5 is Figure 3 a schematic diagram of the cross-section at position a in;

[0030] Figure 6 is Figure 3 a schematic diagram of the cross-section at position b in;

[0031] Figure 7 is Figure 3 a schematic diagram of the cross-section at position c in;

[0032] Figure 8 is Figure 1 a schematic diagram of the spatial structure of the second adapter in;

[0033] Figure 9 is the first sectional structure diagram of the first adapter;

[0034] Figure 10 is the second sectional structure diagram of the first adapter;

[0035] Figure 11 is the sectional structure diagram of the second adapter;

[0036] Figure 12 is Figure 9 a schematic diagram of the assembly of the first adapter and the dual-fuel nozzle in;

[0037] Figure 13 is Figure 10 a schematic diagram of the assembly of the first adapter and the dual-fuel nozzle in;

[0038] Figure 14 is Figure 11 a schematic diagram of the assembly of the second adapter and the dual-fuel nozzle in.

[0039] Legend:

[0040] 1. First adapter; 101. First fuel channel; 102. Transfer channel;

[0041] 2. Second adapter; 201. Second fuel passage

[0042] 120. Bleed air passage; 121. External mounting head; 122. Hexagonal platform; 123. Connecting column; 124. Bleed air column; 125. Sealing head

[0043] 3. Dual fuel nozzle

[0044] 31. Connector body; 311. Adapter mounting hole; 312. Bleed air chamber; 313. Bleed air hole; 314. Inlet of internal flow path; 315. Inlet of external flow path

[0045] {32. Mounting ear seat; 321. Mounting hole}

[0046] 33. Nozzle tube; 331. Internal flow path; 332. External flow path

[0047] 34. Nozzle head; 341. Spray hole of internal flow path; 342. Spray hole of external flow path; 343. External bleed air chamber; 344. Internal bleed air passage; 346. Internal bleed air chamber Detailed implementation mode

[0048] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways defined and covered by the following.

[0049] Refer to Figure 1 、 Figure 3 、 Figure 9 、 Figure 10 、 Figure 11 、 Figure 12 、 Figure 13 and Figure 14A preferred embodiment of the present invention provides a nozzle device for adapting to the use of gaseous fuels, comprising a first adapter 1, a second adapter 2, and a dual-fuel nozzle 3. The dual-fuel nozzle 3 includes an air bleed cavity 312 for connecting airflow to the engine combustion chamber, an inner flow channel 331 for directing airflow, and an outer flow channel 332 surrounding the inner flow channel 331. The injection end of the dual-fuel nozzle 3 includes a nozzle head 34, which is provided with a plurality of inner flow channel spray holes 341 communicating with the inner flow channel 331 and a plurality of outer flow channel spray holes 342 communicating with the outer flow channel 332. The dual-fuel nozzle 3 is used to adaptively select and connect the first adapter 1 or the second adapter 2 according to the type of gas fuel. Both the first adapter 1 and the second adapter 2 are provided with a fuel channel for conveying gas fuel and an air bleed channel 120 for conveying air flow. The fuel channel in the first adapter 1 is used to communicate with the outer flow channel 332, and the air bleed channel 120 in the first adapter 1 is used to connect the air bleed cavity 312 and the inner flow channel 331. The fuel channel in the second adapter 2 is used to communicate with the inner flow channel 331, and the air bleed channel 120 in the second adapter 2 is used to connect the air bleed cavity 312 and the outer flow channel 332.

[0050] The working principle of the nozzle device of the present invention is as follows:

[0051] When the first adapter 1 is installed, the fuel channel is connected to the outer flow channel 332 of the dual-fuel nozzle 3. After the gas fuel passes through the fuel channel and the outer flow channel 332 in turn, it is gathered and stabilized in the nozzle head 34 and then ejected outward through the outer flow channel nozzle hole 342 to participate in combustion; the two air flows in the engine combustion chamber enter the air induction cavity 312, and enter the inner flow channel 331 of the dual-fuel nozzle 3 through the air induction channel 120. After being gathered and stabilized in the nozzle head 34, it is ejected outward from the inner flow channel nozzle hole 341, thereby assisting combustion and cooling the nozzle device at the same time.

[0052] When the second adapter 2 is installed, the fuel channel is connected to the inner flow channel 331 of the dual-fuel nozzle 3. After the gas fuel passes through the fuel channel and the inner flow channel 331 in turn, it is gathered and pressure-stabilized in the nozzle head 34 and then ejected outward through the inner flow channel spray hole 341 to participate in combustion; the two air flows in the engine combustion chamber enter the bleed cavity 312, and enter the outer flow channel 332 of the dual-fuel nozzle 3 through the bleed channel 120. After being gathered and pressure-stabilized in the nozzle head 34, it is ejected outward from the outer flow channel spray hole 342, thereby assisting combustion and cooling the nozzle device at the same time.

[0053] The present invention relates to a nozzle device for adapting to the change of gaseous fuel used. During the design, the number of inner flow channel spray holes 341 and the layout of the inner flow channel spray holes 341 on the spraying end surface of the nozzle head 34 are correspondingly set according to the type of gaseous fuel to be circulated in the inner flow channel 331 to meet the combustion requirements, and the number of outer flow channel spray holes 342 and the layout of the outer flow channel spray holes 342 on the spraying end surface of the nozzle head 34 are correspondingly set according to the type of gaseous fuel to be circulated in the outer flow channel 332 to meet the combustion requirements. Thus, when the type of gaseous fuel is different, only by replacing the corresponding adapter to make the gaseous fuel enter the pre-set flow channel can the combustion requirements of the gas turbine be met. Since the purpose of making the gas turbine burn another gaseous fuel can be achieved only by replacing the adapter after the equipment is shut down, without the need to return to the factory to disassemble the engine body, the replacement efficiency is greatly improved, and the risks and labor intensity during the replacement process are reduced. Compared with the prior art nozzle schemes in which a variety of fuels are supplied to the turbine engine for combustion in a certain proportion, and the fuels are mostly liquid fuels with lower combustion efficiency than gaseous fuels, there is an essential difference compared with the function of the nozzle device of the present invention that can be compatible with the continuous combustion of a variety of gaseous fuels. The device of the present invention can further improve the combustion efficiency of the fuel, and can select the most economical gaseous fuel according to the market price to reduce the operating cost, reduce the dependence on a certain specific gaseous fuel, and avoid the shutdown risk caused by supply interruption or price fluctuation.

[0054] Optionally, as Figure 3 , Figure 5 , Figure 6 and Figure 7 shown, the spraying end of the nozzle head 34 has a number of regularly arranged spray holes; the outer flow channel 332 gradually transitions from an annular cavity in the nozzle head 34 to form a special-shaped and single-chamber outer flow gas cavity 343. A number of outer flow channel spray holes 342 extending along the axial direction of the nozzle head 34 are opened at the bottom of the outer flow gas cavity 343. The outer flow channel spray holes 342 communicate the outer flow gas cavity 343 with the corresponding spray holes on the spraying end of the nozzle head 34; the inner flow channel 331 first gradually transitions from a single-hole cavity in the axial direction of the nozzle head 34 to form a number of non-connected inner flow air channels 344, and then gradually transitions from the number of inner flow air channels 344 to form a special-shaped and single-chamber inner flow gas cavity 346. A number of inner flow channel spray holes 341 extending along the axial direction of the nozzle head 34 are opened at the bottom of the inner flow gas cavity 346. The inner flow channel spray holes 341 communicate the inner flow gas cavity 346 with the corresponding spray holes on the spraying end of the nozzle head 34.

[0055] In this alternative solution, the outer flow channel 332 is first an annular cavity that is annularly arranged outside the inner flow channel 331 in the air flow direction, and then gradually transitions from the annular cavity to form a special-shaped and single-chamber outer flow air cavity 343. The outer flow air cavity 343 is then connected to the corresponding nozzles at the injection end through a number of outer flow channel nozzles 342; similarly, the inner flow channel 331 is first a single-hole cavity located at the center of the outer flow channel 332 in the air flow direction, and then gradually transitions from the single-hole cavity to form a number of non-connected inner flow air channels 344. Then, the number of non-connected inner flow air channels 344 gradually transitions to form a special-shaped and single-chamber inner flow air cavity 346. Finally, the inner flow air cavity 346 is connected to the corresponding nozzles at the injection end through a number of inner flow channel nozzles 341. This design uses the single-chamber outer flow air cavity 343 and inner flow air cavity 346 to collect and stabilize the air flow respectively, so as to improve the injection uniformity and injection effect of the fuel gas and air. Moreover, this structural change of the inner flow channel 331 also helps the air flow in the outer flow channel 332 to first form a special-shaped single pressure-stabilizing cavity corresponding to the corresponding nozzles.

[0056] Preferably, as Figure 7 shown, a number of nozzles are arranged in concentric rings on the injection end face, and each concentric ring has a number of nozzles evenly spaced circumferentially, and the diameters of the nozzles on each concentric ring increase gradually in the radial direction. Moreover, the number of nozzles corresponding to the outer flow air cavity 343 and the outer flow air channel in the nozzle head 34 remains unchanged, and the number of nozzles corresponding to the inner flow air channel 344 and the inner flow air cavity 346 also remains unchanged. That is to say, the nozzle head 34 is used to distribute the fluid in the inner flow channel 331 and the outer flow channel 332 into the nozzles with a specified number and specified positions; in addition, the positions and numbers of the nozzles connected to the inner flow air cavity 346 and the outer flow air cavity 343 are different according to the type of fuel. The specific positions, aperture diameters and numbers should be obtained through combustion simulation calculations according to the type of gaseous fuel.

[0057] Optionally, as Figure 2 、 Figure 3 and Figure 4 shown, the dual-fuel nozzle 3 further includes a connection head and a nozzle pipe 33. The connection head is used for detachable connection with the first adapter 1 or the second adapter 2, and an air guide cavity 312 is provided in the adapter. The two ends of the nozzle pipe 33 are respectively connected to the connection head and the nozzle head 34, and the inner flow channel 331 and the outer flow channel 332 are arranged in the nozzle pipe 33 along the length direction of the nozzle pipe 33. In this alternative solution, as Figure 3 shown, the nozzle pipe 33 is bent, and the bending direction is the vertical backward direction of the through hole on the side wall of the air guide cavity 312.

[0058] In this alternative solution, as Figure 2 、 Figure 3 and Figure 4As shown in the figure, the connector includes a connector body 31 that is hollowly arranged with one end open and the other end closed, and mounting lugs 32 fixedly connected to the outer circumference of the connector body 31. An installation hole 321 that penetrates through is provided on the mounting lugs 32 for fixing the nozzle device. The inner cavity of the connector body 31 forms an adapter installation hole 311 and an air intake cavity 312 that are arranged in sequence along its length direction. The first adapter 1 or the second adapter 2 is inserted into the adapter installation hole 311 from the open end of the connector body 31 and then detachably connected to the dual-fuel nozzle 3. An air intake hole 313 that penetrates the wall surface is provided on the side wall of the air intake cavity 312. An inner flow channel inlet 314 that communicates with the inner flow channel 331 and an outer flow channel inlet 315 that communicates with the outer flow channel 332 are provided on the closed end of the connector body 31. In a specific embodiment of this alternative solution, as Figure 2 shown, the adapter installation hole 311 is a threaded hole structure, its outer circumferential surface is cylindrical, and a symmetric plane for anti-torsion is machined during the screwing of the adapter thread.

[0059] Preferably, since the overall structure of the dual-fuel nozzle 3 is complex, in the present invention, the dual-fuel nozzle 3 is formed by an additive manufacturing process.

[0060] Optionally, as Figure 9 、 Figure 10 and Figure 11 shown, both the first adapter 1 and the second adapter 2 include an adapter body, and the adapter body is used for detachably fixing to the connector body 31. The fuel channel in the first adapter 1 includes a first fuel channel 101 formed by inwards concave extension from the top end of the adapter body, and a plurality of transfer channels 102 that communicate with the blind end of the first fuel channel 101 and extend downwards and then penetrate through the outer wall surface of the bottom end of the adapter body. The transfer channels 102 are used for communicating the first fuel channel 101 and the outer flow channel inlet 315. The air intake channel 120 in the first adapter 1 penetrates through the bottom end of the adapter body for communicating the air intake cavity 312 and the inner flow channel inlet 314, and the transfer channels 102 and the air intake channel 120 are arranged in a circumferential dislocation manner. The fuel channel in the second adapter 2 is a second fuel channel 201 that axially penetrates through the adapter body for communicating the inner flow channel inlet 314. The air intake channel 120 in the second adapter 2 penetrates through the bottom end of the adapter body for communicating the air intake cavity 3,12 and the outer flow channel inlet 315.

[0061] In this alternative solution, as Figure 9 、 Figure 10 and Figure 11 shown, the number of the transfer channels 102 is multiple, and the multiple transfer channels 102 are evenly spaced along the circumference; the number of the air intake channels 120 is also multiple, and the multiple air intake channels 120 are evenly spaced along the circumference, and the multiple transfer channels 102 and the multiple air intake channels 120 are arranged in a circumferential one-to-one dislocation manner.

[0062] In this alternative solution, as Figure 8 shown, the adapter body includes an external mounting head 121, a hexagonal platform 122, a connecting column 123, an air guiding column 124, and a sealing head 125 that are sequentially connected along the axial direction. The adapter body is axially inserted into the connector body 31 so that the connecting column 123 is threadedly connected to the adapter mounting hole 311. The air guiding column 124 is arranged corresponding to the air guiding cavity 312, and the outer diameter of the air guiding column 124 is smaller than the inner diameter of the air guiding cavity 312 to form an annular air guiding groove with the air guiding cavity 312. The sealing head 125 is used to tightly press against the bottom surface of the air guiding cavity 312 to cut off the direct connection between the inner flow channel inlet 314 and the outer flow channel inlet 315 and the air guiding groove, and both the air guiding channel 120 and the transfer channel 102 are arranged on the sealing head 125.

[0063] In this alternative solution, as Figure 8 shown, the outer wall surface of the external mounting head 121 is provided with an external thread for detachably connecting with an external connecting pipe. The cross-section of the hexagonal platform 122 is polygonal for the adapter body to be stressed during installation. The sealing head 125 is conical to cooperate with the conical surface at the bottom of the air guiding cavity 312 to seal the connection between the inner flow channel inlet 314 and the outer flow channel inlet 315 and the air guiding groove.

[0064] The preferred embodiment of the present invention further relates to a gas turbine, which is internally provided with a nozzle device for adapting to the change of gaseous fuel use as described in any one of the above. For the gas turbine of the present invention, when the types of gaseous fuels are different, only by replacing the corresponding adapter to make the gaseous fuel enter the pre-set flow channel, the combustion requirements of the gas turbine can be met. And since only by replacing the adapter after the equipment is shut down can the purpose of the gas turbine burning another gaseous fuel be achieved, without the need to return to the factory to disassemble the engine body, thus greatly improving the replacement efficiency, reducing the risks existing in the replacement process and the labor intensity of the replacement operation; compared with the prior art nozzle solutions in which a variety of fuels are supplied to the turbine engine for combustion in a certain proportion, and the fuels are mostly liquid fuels with lower combustion efficiency than gaseous fuels, there is an essential difference compared with the function of the nozzle device of the present invention that can be compatible with the continuous combustion of a variety of gaseous fuels. The device of the present invention can further improve the combustion efficiency of the fuel, and can select the most economical gaseous fuel according to the market price to reduce the operating cost, reduce the dependence on a certain specific gaseous fuel, and avoid the shutdown risk caused by supply interruption or price fluctuation.

[0065] The above are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A nozzle device for adapting to the change of gaseous fuel use, characterized in that Comprising: A first adapter (1), a second adapter (2) and a dual-fuel nozzle (3); An air extraction cavity (312) for connecting the airflow of the engine combustion chamber, an internal flow channel (331) for guiding the flow, and an external flow channel (332) annularly arranged outside the internal flow channel (331) are provided in the dual-fuel nozzle (3). The injection end of the dual-fuel nozzle (3) has a nozzle head (34), and a plurality of internal flow channel injection holes (341) communicating with the internal flow channel (331) and a plurality of external flow channel injection holes (342) communicating with the external flow channel (332) are formed on the nozzle head (34); The dual-fuel nozzle (3) is used to adaptively select to connect the first adapter (1) or the second adapter (2) according to the type of gaseous fuel. Fuel channels for transporting gaseous fuel and air extraction channels (120) for transporting airflow are provided in both the first adapter (1) and the second adapter (2). The fuel channel in the first adapter (1) is used to communicate with the external flow channel (332), the air extraction channel (120) in the first adapter (1) is used to connect the air extraction cavity (312) and the internal flow channel (331), the fuel channel in the second adapter (2) is used to communicate with the internal flow channel (331), and the air extraction channel (120) in the second adapter (2) is used to connect the air extraction cavity (312) and the external flow channel (332); The injection end of the nozzle head (34) has a plurality of regularly arranged injection holes; the external flow channel (332) gradually transitions from an annular cavity in the nozzle head (34) to form a special-shaped and single-chamber external air flow cavity (343). A plurality of external flow channel injection holes (342) extending along the axial direction of the nozzle head (34) are formed at the bottom of the external air flow cavity (343), and the external flow channel injection holes (342) communicate the external air flow cavity (343) and the corresponding injection holes on the injection end of the nozzle head (34); the internal flow channel (331) first gradually transitions from a single-hole cavity in the axial direction of the nozzle head (34) to form a plurality of non-connected internal air flow channels (344), and then gradually transitions from the plurality of internal air flow channels (344) to form a special-shaped and single-chamber internal air flow cavity (346). A plurality of internal flow channel injection holes (341) extending along the axial direction of the nozzle head (34) are formed at the bottom of the internal air flow cavity (346), and the internal flow channel injection holes (341) communicate the internal air flow cavity (346) and the corresponding injection holes on the injection end of the nozzle head (34).

2. The nozzle device for adapting to the change of gaseous fuel use according to claim 1, characterized in that A plurality of injection holes are arranged in concentric rings on the injection end surface, and a plurality of injection holes are evenly spaced along the circumferential direction on each ring of concentric rings, and the diameters of the injection holes on each ring of concentric rings gradually increase in the radial direction.

3. The nozzle device for adapting to the change of gaseous fuel use according to claim 1, characterized in that The dual-fuel nozzle (3) further includes a connection head and a nozzle tube (33); The connection head is used for detachably connecting with the first adapter (1) or the second adapter (2), and an air extraction cavity (312) is provided in the adapter. Both ends of the nozzle tube (33) are respectively connected to the connector and the nozzle head (34), and the inner flow channel (331) and the outer flow channel (332) are arranged in the nozzle tube (33) along the length direction of the nozzle tube (33).

4. The nozzle device for adapting to the change of gaseous fuel use according to claim 3, characterized in that The connector includes a connector body (31) that is hollowly arranged with one end open and one end closed, and a mounting ear seat (32) fixedly connected to the outer circle of the connector body (31); The inner cavity of the connector body (31) forms an adapter installation hole (311) and an air introduction cavity (312) arranged in sequence along its length direction. The first adapter (1) or the second adapter (2) is inserted into the adapter installation hole (311) from the open end of the connector body (31) and then detachably connected to the dual-fuel nozzle (3). An air introduction hole (313) is provided on the side wall of the air introduction cavity (312) and penetrates the wall surface; On the closed end of the connector body (31), there are provided an inner flow channel inlet (314) communicating with the inner flow channel (331) and an outer flow channel inlet (315) communicating with the outer flow channel (332).

5. The nozzle device for adapting to the change of gaseous fuel use according to claim 1, characterized in that The dual-fuel nozzle (3) is formed by an additive manufacturing process.

6. The nozzle device for adapting to the change of gaseous fuel use according to claim 4, characterized in that Both the first adapter (1) and the second adapter (2) include an adapter body, and the adapter body is used for detachably fixing to the connector body (31); The fuel channel in the first adapter (1) includes a first fuel channel (101) formed by concave extension from the top end of the adapter body, and a plurality of blind ends communicating with the first fuel channel (101) and extending downward and penetrating the outer wall surface of the bottom end of the adapter body. The transfer channel (102) is used for communicating the first fuel channel (101) and the outer flow channel inlet (315); The air introduction channel (120) in the first adapter (1) penetrates the bottom end of the adapter body for communicating the air introduction cavity (312) and the inner flow channel inlet (314), and the transfer channel (102) and the air introduction channel (120) are arranged circumferentially offset; The fuel channel in the second adapter (2) is a second fuel channel (201) that axially penetrates the adapter body. The second fuel channel (201) is used for communicating the inner flow channel inlet (314). The air introduction channel (120) in the second adapter (2) penetrates the bottom end of the adapter body for communicating the air introduction cavity (312) and the outer flow channel inlet (315).

7. The nozzle device for adapting to the change of gaseous fuel use according to claim 6, characterized in that The adapter body includes an external installation head (121), a hexagonal platform (122), a connecting column (123), an air introduction column (124) and a sealing head (125) connected in sequence along the axis; The adapter body is axially inserted into the connector body (31) so that the connecting column (123) is threadedly connected to the adapter installation hole ( The air guiding column (124) is arranged corresponding to the air guiding cavity (312), and the outer diameter of the air guiding column (124) is smaller than the inner diameter of the air guiding cavity (312), so as to form an annular air guiding groove with the air guiding cavity (312). The sealing head (125) is used to tightly press against the bottom surface of the air guiding cavity (312) to cut off the direct connection between the inner flow channel inlet (314) and the outer flow channel inlet (315) and the air guiding groove, and both the air guiding channel (120) and the transfer channel (102) are arranged on the sealing head (125).

8. The nozzle device for adapting to the change of gaseous fuel use according to claim 7, characterized in that The outer wall surface of the external mounting head (121) is provided with an external thread for detachably connecting with an external connecting pipe. The cross section of the hexagonal platform (122) is polygonal for bearing force during the installation of the adapter body. The sealing head (125) is conical and is matched with the conical surface at the bottom of the air guiding cavity (312) to seal the connection between the inner flow channel inlet (314) and the outer flow channel inlet (315) and the air guiding groove.

9. A gas turbine, characterized in that, It is internally provided with the nozzle device for adapting to the change of gaseous fuel use according to any one of claims from 1 to 8.

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