CN115405949A - Ignition device and method, combustion chamber and gas turbine - Google Patents
Ignition device and method, combustion chamber and gas turbine Download PDFInfo
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- CN115405949A CN115405949A CN202211000141.4A CN202211000141A CN115405949A CN 115405949 A CN115405949 A CN 115405949A CN 202211000141 A CN202211000141 A CN 202211000141A CN 115405949 A CN115405949 A CN 115405949A
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 69
- 238000000034 method Methods 0.000 title claims abstract description 24
- 239000000446 fuel Substances 0.000 claims abstract description 88
- 239000007788 liquid Substances 0.000 claims abstract description 10
- 238000007789 sealing Methods 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 44
- 239000003921 oil Substances 0.000 description 22
- 238000010892 electric spark Methods 0.000 description 11
- 239000000203 mixture Substances 0.000 description 9
- 239000000243 solution Substances 0.000 description 4
- 238000000889 atomisation Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 3
- 238000004088 simulation Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000004080 punching Methods 0.000 description 2
- 238000004146 energy storage Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 210000002445 nipple Anatomy 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23Q—IGNITION; EXTINGUISHING-DEVICES
- F23Q3/00—Igniters using electrically-produced sparks
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/38—Nozzles; Cleaning devices therefor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/40—Mixing tubes or chambers; Burner heads
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23Q—IGNITION; EXTINGUISHING-DEVICES
- F23Q3/00—Igniters using electrically-produced sparks
- F23Q3/006—Details
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/58—Cyclone or vortex type combustion chambers
Abstract
The invention discloses an ignition device, an ignition method, a combustion chamber and a gas turbine. The method comprises the following steps: a pre-film type fuel nozzle, an ignition electric nozzle and an oil-gas mixing cavity; the pre-film type fuel nozzle comprises an oil inlet channel, a nozzle spout, an air inlet hole and an annular pre-film cavity, wherein the oil inlet channel is communicated with the nozzle spout, the nozzle spout is communicated with the annular pre-film cavity, and the air inlet hole is used for forming an air layer in front of the end surface of the ignition electric nozzle; the annular pre-film cavity is positioned between the end face of the ignition electric nozzle and the oil-gas mixing cavity, the other side of the annular pre-film cavity is communicated with the oil-gas mixing cavity, and the annular pre-film cavity is used for forming an annular liquid film; the ignition electric nozzle is embedded into the pre-film type fuel nozzle, the ignition electric nozzle is used for forming an initial fire core, and the oil-gas mixing cavity is used for mixing air and fuel. The technical scheme disclosed by the invention has the advantages of high ignition reliability, compact structure and high ignition performance.
Description
Technical Field
The invention relates to the technical field of engines, in particular to an ignition device, an ignition method, a combustion chamber and a gas turbine.
Background
The ignition device of the combustion chamber of the current gas turbine is generally independent electrical equipment and consists of an ignition electric nozzle, an ignition coil and an energy storage device. The ignition electric nozzle is generally mounted on a casing outside the combustion stage turbine and is inserted into a flame tube from the outer ring of the flame tube of a combustion chamber, so that electric sparks released by the electric nozzle can ignite an oil-gas mixture in the flame tube. The ignition mode that the fuel near the electric spark ignition electric nozzle forms a fire core and then is transmitted to the fuel in the ignition backflow area near the nozzle from the fire core can be called indirect ignition. Fig. 1 is a schematic structural diagram of a backflow type combustion chamber, which is mainly used for small and medium-sized gas turbines. As can be seen from FIG. 1, the ignition nozzle is located at the outer ring of the flame tube, and the fuel nozzle is located at the head of the flame tube. The ignition of the combustion chamber in fig. 1 is realized as follows: 1) Fuel is sprayed out from the fuel nozzle, and forms a combustible oil-gas mixture near the ignition electric nozzle by mixing with the head strong-swirl air; 2) The ignition electric nozzle releases electric sparks so as to ignite the oil-gas mixture, and the ignited oil-gas mixture forms an initial fire core and starts to spread all around; 3) The fire core enters a central backflow area of the combustion chamber through the transportation effect, and further ignites an oil-gas mixture at the outlet of the nozzle; 4) A large amount of oil-gas mixture is ignited, so that a stable turbulent combustion flame is formed, and the combustion chamber is successfully ignited.
The main disadvantages of the above technology are as follows: 1) Because the ignition electric nozzle and the fuel nozzle are mutually independent and the installation positions of the ignition electric nozzle and the fuel nozzle are long in distance, fuel is mixed with a large amount of air after being sprayed out of the fuel nozzle, fuel steam with certain concentration is difficult to form near the ignition electric nozzle, and therefore electric sparks released by the electric nozzle are difficult to ensure to ignite the near fuel steam and form an initial fire core; 2) Even if the electric spark successfully ignites the fuel steam near the electric nozzle and forms an initial fire core, the fire core still needs to enter the backflow area to ignite the oil-gas mixture near the outlet of the electric nozzle through the transportation process, and because the fire core can be quenched and cooled in the transportation process, the fire core is difficult to ensure to successfully ignite the oil-gas mixture near the outlet of the electric nozzle, so that stable turbulent flame is formed. 3) The ignition electric nozzle is required to extend into the flame tube, so that the ignition electric nozzle is in direct contact with high-temperature gas and is ablated by the high-temperature gas for a long time, and the service life of the ignition electric nozzle is short.
Disclosure of Invention
To solve the above problems, the present invention provides an ignition device, a method, a combustion chamber and a gas turbine.
An embodiment of the present invention provides an ignition device, including:
a pre-film type fuel nozzle, an ignition electric nozzle and an oil-gas mixing cavity;
the pre-film type fuel nozzle comprises an oil inlet channel, a nozzle spout, an air inlet hole and an annular pre-film cavity, wherein the oil inlet channel is communicated with the nozzle spout, the nozzle spout is communicated with the annular pre-film cavity, and the air inlet hole is used for forming an air layer in front of the end surface of the ignition electric nozzle; the annular pre-film cavity is positioned between the end face of the ignition electric nozzle and the oil-gas mixing cavity, the other side of the annular pre-film cavity is communicated with the oil-gas mixing cavity, and the annular pre-film cavity is used for forming an annular liquid film;
the ignition electric nozzle is embedded into the pre-film type fuel nozzle and used for forming an initial fire core, and the oil-gas mixing cavity is used for mixing air and fuel.
Optionally, the pre-film fuel nozzle further comprises an oil collecting ring, and the oil collecting ring is arranged between the oil inlet channel and the nozzle and is respectively communicated with the oil inlet channel and the nozzle.
Optionally, the ignition electric nozzle is connected with the prefilming fuel nozzle through a thread structure.
Optionally, the pre-film type fuel nozzle is of a groove structure, the oil inlet channel, the nozzle, the air inlet hole and the annular pre-film cavity are located on the side face of the groove structure, and the annular pre-film cavity is located on the bottom face of the groove structure to form an annular liquid film.
Optionally, the end face of the ignition nozzle is parallel to the bottom face of the prefilming fuel nozzle.
Optionally, the ignition device provided by the embodiment of the present invention further includes a chamfered hole swirler, the chamfered hole swirler is hermetically connected to the outer wall of the pre-film fuel nozzle, the chamfered hole swirler is of a first annular structure, and the oil-gas mixing cavity is formed in the middle of the first annular structure.
Optionally, the chamfered hole swirler further includes a chamfered hole, and the chamfered hole is used for introducing air into the oil-gas mixing chamber.
Optionally, the ignition device provided by the embodiment of the present invention further includes a radial vane swirler, where the radial vane swirler is a second annular structure and is connected to the chamfered hole swirler.
Based on the same inventive concept, the embodiment of the invention also provides an ignition method, which uses the ignition device for ignition.
Based on the same inventive concept, the embodiment of the invention also provides a combustion chamber, which comprises an annular combustion cavity, a flame tube outer ring, a flame tube inner ring and a combustion chamber head structure, wherein the combustion chamber head structure comprises the ignition device.
Based on the same inventive concept, the embodiment of the invention also provides a gas turbine, which comprises a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine, wherein the combustion chamber further comprises the ignition device.
The technical scheme provided by the embodiment of the invention has the beneficial effects that at least:
1. the ignition reliability is high. The ignition electric nozzle and the fuel nozzle are combined and integrated, so that the intermediate processes related to a series of traditional ignition modes such as fuel and fire core transportation are greatly simplified, and the ignition reliability and the ignition performance under extreme conditions are improved by adopting a direct ignition mode.
2. The structure is compact. Ignition contains a pneumatic atomizing nozzle of pre-filming formula and an ignition electric nozzle, and through will igniteing electric nozzle and fuel nozzle integration, can need not set up a series of parts such as electric nozzle mount pad, electric nozzle thermal-insulated bush on the combustion chamber machine casket, also need not punch in addition on flame tube and machine casket and install the ignition electric nozzle for the combustion chamber structure is more compact.
3. The ignition performance is high. Ignition simulation and experimental research are carried out on a three-head combustion chamber test piece of a new generation of turboshaft engine, and the ignition performance of the three-head combustion chamber test piece is proved to be improved by 30% compared with that of a conventional combustion chamber.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by the practice of the embodiments of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic view of a reverse flow combustor;
FIG. 2 is a block diagram of an ignition device according to an embodiment of the present invention;
FIG. 3 is a view showing the structure of a combustion chamber in the embodiment of the present invention;
FIG. 4 is a schematic view of a gas turbine engine including a combustor in an embodiment of the present invention.
Reference numerals: 1. a low pressure compressor; 2. a high pressure compressor; 3. a combustion chamber; 4. a high pressure turbine; 5. a low pressure turbine; 10. a gas turbine; 30. an annular combustion chamber; 32. an outer ring of the flame tube; 34. an inner ring of the flame tube; 35. an inner ring channel; 37. an outer ring channel; 40. a combustion chamber head structure; 42. an ignition device; 44. a chamfered hole swirler; 46. a radial vane swirler; 48. a swirler vane; 52. a central axis; 54. an ignition electric nozzle; 56. a thread structure; 58. the end surface of the ignition electric nozzle; 60. a pre-film type fuel nozzle; 61. an oil inlet channel; 62. an oil collecting ring; 63. a nozzle spout; 64. an air intake; 65. the wall surface of the annular pre-filming cavity; 68. an annular pre-filming cavity; 70. an oil-gas mixing cavity; 74. and (5) obliquely cutting the hole.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the technical solutions of the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
In order to solve the problems in the prior art, embodiments of the present invention provide an ignition device, an ignition method, a combustion chamber and a gas turbine.
An embodiment of the present invention provides an ignition device 42, where the ignition device 42 is a combined ignition device, and its structure is shown in fig. 2, and includes:
a pre-film type fuel nozzle 60, an ignition electric nozzle 54 and an oil-gas mixing cavity 70; the fuel steam can be ignited by electric sparks, so that an initial fire core and a high-temperature gas mass containing the fire core are formed near the end surface 58 of the ignition nozzle;
the pre-film type fuel nozzle 60 comprises an oil inlet channel 61, a nozzle spout 63, an air inlet 64 and an annular pre-film cavity 68, the pre-film type fuel nozzle 60 is specifically a pre-film type pneumatic atomizing nozzle, the oil inlet channel 61 is communicated with the nozzle spout 63, and the nozzle spout 63 is communicated with the annular pre-film cavity 68. The air inlet holes 64 are used for forming an air layer in front of the end surface 58 of the ignition electric nozzle 54, so that ignition and fuel oil combustion are facilitated; the annular pre-film cavity 68 is located between the end surface 58 of the ignition nozzle 54 and the oil-gas mixing cavity 70, the other side of the annular pre-film cavity 68 is communicated with the oil-gas mixing cavity 70, and the annular pre-film cavity 68 is used for forming an annular liquid film; the fuel enters from the fuel inlet channel 61, is sprayed out from the nozzle 63 and is sprayed into the annular pre-film cavity 68 to form an annular liquid film.
The ignition plug 54 is inserted into the pre-film fuel nozzle 60, the ignition plug 54 is used for forming an initial flame kernel, and the air-fuel mixing chamber 70 is used for mixing air and fuel.
Optionally, the pre-film type fuel nozzle 60 further includes an oil collecting ring 62, and the oil collecting ring 62 is located between the oil inlet channel 61 and the nozzle 63 and is respectively communicated with the oil inlet channel 61 and the nozzle 63. The oil collecting ring 62 enables the nozzle jet 63 to synchronously jet fuel oil at all positions, and a circular liquid film is more easily formed.
Optionally, the ignition nozzle 54 is connected with the prefilming fuel nozzle 60 through a thread structure 56, so that fixation and replacement are facilitated.
Optionally, the pre-film fuel nozzle 60 is of a groove structure, the oil inlet channel 61, the nozzle spout 63, the air inlet 64 and the annular pre-film cavity 68 are located on the side surface of the groove structure, and the annular pre-film cavity 68 forms an annular liquid film on the bottom surface of the groove structure.
Optionally, the end surface 58 of the ignition tip 54 is parallel to the bottom surface of the pre-film fuel nozzle 60.
In alternative embodiments, the combustion chamber head structure 40 includes an ignition device 42, an ignition device 42 further including a chamfered hole swirler 44 and a radial vane swirler 46.
Optionally, the ignition device provided by the embodiment of the present invention further includes a chamfered hole swirler 44, the chamfered hole swirler 44 is connected to an outer wall of the pre-film fuel nozzle 60 in a sealing manner, the chamfered hole swirler 44 is a first annular structure, and the middle of the first annular structure forms the oil-gas mixing chamber 70.
Optionally, the chamfered hole swirler 44 further includes a chamfered hole 74, and the chamfered hole 74 is used for introducing air into the air-fuel mixing chamber 70 to promote sufficient fuel combustion.
Optionally, the ignition device provided by the embodiment of the present invention further includes a radial vane swirler 46, where the radial vane swirler 46 is a second annular structure and is connected to the chamfered hole swirler 44. The radial vane swirler 46 is provided with swirler vanes 48.
The technical scheme of the invention is different from the traditional combustion chamber ignition device and the mode, as shown in figure 1, the traditional ignition device is independent electrical equipment, an ignition electric nozzle and a fuel nozzle are two independent parts, the installation positions are far away, the ignition device can only form electric sparks on the end surface of the ignition electric nozzle, and the electric sparks can not be ensured to ignite fuel steam and form stable flame. In addition, in the traditional ignition mode, fuel droplets and steam need to move to the vicinity of the ignition electric nozzle, an initial fire core is formed on the end face of the ignition electric nozzle, and then the fire core needs to flow back to the vicinity of the outlet of the nozzle to form stable turbulent flame. According to the technical scheme, the traditional ignition device and the fuel nozzle are combined and integrated, the ignition electric nozzle is embedded into the fuel nozzle, the electric spark directly ignites fuel steam at the outlet of the nozzle, and the formed fire core and high-temperature fuel gas clusters directly form stable turbulent flame in a backflow area. The ignition electric nozzle and the fuel nozzle are combined and integrated, so that the structure is more compact, the oil gas transportation process and the fire core transportation process in the traditional ignition process are simplified, the uncertainty of the ignition process is reduced, and the ignition reliability of the combustion chamber is improved.
Specifically, referring to FIG. 2, the ignition device 42 includes a pre-film fuel injector 60 and an ignition nozzle 54. The ignition nipple 54 is inserted into the fuel nozzle 60 and the two are connected by a threaded structure 56. Fuel enters the injector nozzle 60 through the fuel manifold and then enters an oil collection ring 62 through the fuel inlet passage 61, the fuel passes from the oil collection ring 62 into the injector nozzle orifice 63 and is then injected as a cylindrical jet into an annular prefilming chamber 68, the fuel jet impinges directly on the annular prefilming chamber wall 65 to form a ring of annular liquid film which flows along the annular prefilming chamber wall 65 and then exits the fuel injector nozzle 60 into an air-fuel mixing chamber 70. The air-fuel mixing chamber 70 is cylindrical and has a central axis 52, and the central axis 52 is also the central axis of the ignition plug 54, the end surface 58 of the ignition plug 54, and the annular prefilming chamber 68. The air in the air mixing chamber 70 comes from 2 air flows, 1 air flow enters the air mixing chamber 70 through the air inlet holes 64 on the fuel nozzle 60, and a part of air flows enters the air mixing chamber through the inclined hole 74 of the inclined hole swirler 44. The two air flows wrap the annular oil film to form a sandwich oil-gas structure, which is beneficial to the rapid atomization of fuel oil and the oil-gas mixing. The end face 58 of the ignition torch 54 is configured to discharge spark and thereby ignite the mixture of fuel and air formed in the mixing chamber to form an initial flame kernel which heats the air in the mixing chamber 70 and further forms a high temperature plume which moves downstream with the air flow to initiate a turbulent flame from igniting the fuel vapor in the recirculation zone and forming a stable flame in the downstream recirculation zone.
The technical effects of the ignition device of the embodiment include:
1. the ignition reliability is high. The ignition electric nozzle and the fuel nozzle are combined and integrated, so that the intermediate processes related to a series of traditional ignition modes such as fuel and fire core transportation are greatly simplified, and the ignition reliability and the ignition performance under extreme conditions are improved by adopting a direct ignition mode.
2. The structure is compact. The ignition device comprises a pre-film type pneumatic atomizing nozzle and an ignition electric nozzle, and the ignition electric nozzle is integrated with the fuel nozzle, so that a series of parts such as an electric nozzle mounting seat and an electric nozzle heat-insulating lining do not need to be arranged on a combustion chamber casing, and the ignition electric nozzle does not need to be installed by punching holes on a flame tube and the casing, so that the combustion chamber is more compact in structure.
3. The ignition performance is high. Ignition simulation and experimental research are carried out on a three-head combustion chamber test piece of a new generation of turboshaft engine, and the ignition performance of the three-head combustion chamber test piece is proved to be improved by 30% compared with that of a conventional combustion chamber.
Based on the same inventive concept, the embodiment of the present invention further provides an ignition method, which uses the ignition device 42 as described above to perform ignition. The method uses the pre-film type pneumatic atomizing nozzle to enable oil and gas to be mixed quickly, electric sparks are directly released near the outlet of the nozzle to ignite fuel steam to form initial fire nuclei and high-temperature fuel gas clusters, the transportation process of the fuel and the fire nuclei is greatly simplified, and the success rate of ignition is improved.
Based on the same inventive concept, the embodiment of the present invention further provides a combustion chamber 3, which is configured as shown in fig. 3, and includes an annular combustion cavity 30, a liner outer ring 32, a liner inner ring 34, and a combustion chamber head structure 40, where the combustion chamber head structure 40 includes the ignition device 42 as described above. In alternative embodiments, the combustion chamber head structure 40 includes an ignition device 42, an ignition device 42 further including a chamfered hole swirler 44 and a radial vane swirler 46. According to the technical scheme, the fuel nozzle and the ignition electric nozzle are combined and integrated to form the combined ignition device, the ignition device is arranged at the head of the combustion chamber, and a series of ignition intermediate processes such as fuel atomization, oil-gas mixing, electric spark release, fire kernel generation, turbulent flame propagation and the like are directly completed in a mixing cavity positioned at the head, so that the transportation process of fuel and fire kernels is greatly simplified, and the ignition reliability is improved. Fig. 3 is a central sectional view of a combustion chamber 3 used in the gas turbine 10. The combustion chamber 3 is a combustion chamber based on combined ignition, and mainly comprises an annular combustion cavity 30, a flame tube outer ring 32 and a flame tube inner ring 34. The outer liner ring 32 circumscribes the outer annular boundary of the annular combustion chamber 30, and the inner liner ring 34 circumscribes the inner annular boundary of the annular combustion chamber 30. The combustor inner ring 32 and the combustor outer ring 34 are embedded in an annular combustor casing and form an inner ring channel 35 and an outer ring channel 37, respectively, with the casing. The combustion chamber 3 also comprises an annular head 40 mounted upstream of the outer ring 32 and the inner ring 34 of the liner, this head being used for fuel injection atomisation, air-fuel mixing and ignition.
Based on the same inventive concept, the embodiment of the present invention further provides a gas turbine 10, the structure of which is shown in fig. 4, and the gas turbine includes a low-pressure compressor 1, a high-pressure compressor 2, a combustion chamber 3, a high-pressure turbine 4 and a low-pressure turbine 5, the combustion chamber 3 further includes the ignition device as described above, and the ignition device is mounted at the head of the combustion chamber 3. In alternative embodiments, the combustion chamber head structure 40 includes an ignition device 42, an ignition device 42 further including a chamfered hole swirler 44 and a radial vane swirler 46. Fig. 4 is a schematic view of a gas turbine 10, which includes a low-pressure compressor 1, a high-pressure compressor 2, a combustor 3, a high-pressure turbine 4, and a low-pressure turbine 5. When the gas turbine operates, airflow passes through the high-pressure compressor 1 and the low-pressure compressor 2, is compressed into high-pressure gas, enters the combustion chamber 3, and is combusted in the combustion chamber 3 to form high-temperature high-pressure gas, and the high-temperature high-pressure gas sequentially enters the high-pressure turbine 4 and the low-pressure turbine 5 to perform expansion work.
The method and the device provided by the embodiment of the invention have the following technical effects:
1. the ignition reliability is high. The ignition electric nozzle and the fuel nozzle are combined and integrated, so that the intermediate processes related to a series of traditional ignition modes such as fuel and fire core transportation are greatly simplified, and the ignition reliability and the ignition performance under extreme conditions are improved by adopting a direct ignition mode.
2. The structure is compact. The ignition device comprises a pre-film type pneumatic atomizing nozzle and an ignition electric nozzle, and the ignition electric nozzle is integrated with the fuel nozzle, so that a series of parts such as an electric nozzle mounting seat and an electric nozzle heat-insulating lining do not need to be arranged on a combustion chamber casing, and the ignition electric nozzle does not need to be installed by punching holes on a flame tube and the casing, so that the combustion chamber is more compact in structure.
3. The ignition performance is high. Ignition simulation and experimental research are carried out on a three-head combustion chamber test piece of a new generation of turboshaft engine, and the ignition performance of the three-head combustion chamber test piece is proved to be improved by 30% compared with that of a conventional combustion chamber.
Any modification, supplement and equivalent substitution made within the principle scope of the technical solution of the present invention shall still fall within the patent coverage scope of the technical solution of the present invention.
Claims (11)
1. An ignition device, comprising:
the device comprises a pre-film type fuel nozzle (60), an ignition electric nozzle (54) and a fuel-air mixing cavity (70);
the pre-film type fuel nozzle (60) comprises an oil inlet channel (61), a nozzle spout (63), an air inlet hole (64) and an annular pre-film cavity (68), wherein the oil inlet channel (61) is communicated with the nozzle spout (63), the nozzle spout (63) is communicated with the annular pre-film cavity (68), and the air inlet hole (64) is used for forming an air layer in front of the end surface (58) of the ignition electric nozzle (54); the annular pre-film cavity (68) is positioned between the end face (58) of the ignition electric nozzle (54) and the oil-gas mixing cavity (70), the other side of the annular pre-film cavity (68) is communicated with the oil-gas mixing cavity (70), and the annular pre-film cavity (68) is used for forming an annular liquid film;
the ignition electric nozzle (54) is embedded into the pre-film type fuel nozzle (60), the ignition electric nozzle (54) is used for forming an initial fire core, and the air-fuel mixing cavity (70) is used for mixing air and fuel.
2. The arrangement as claimed in claim 1, characterized in that the prefilming fuel nozzle (60) further comprises an oil collecting ring (62), the oil collecting ring (62) communicating with the oil inlet channel (61) and the nozzle orifice (63) between the oil inlet channel (61) and the nozzle orifice (63), respectively.
3. The apparatus of claim 1 wherein said ignition burner (54) is connected to said prefilmer fuel nozzle (60) by a threaded structure (56).
4. The device according to any one of claims 1-3, characterized in that the pre-film type fuel nozzle (60) is a groove structure, the oil inlet channel (61), the nozzle spout (63), the air inlet hole (64) and the annular pre-film cavity (68) are positioned at the side surface of the groove structure, and the annular pre-film cavity (68) forms an annular liquid film at the bottom surface of the groove structure.
5. The device as claimed in claim 4, characterized in that the end face (58) of the ignition nozzle (54) is parallel to the bottom face of the pre-film fuel nozzle (60).
6. The device as claimed in any one of claims 1-5, further comprising a chamfered hole swirler (44), wherein the chamfered hole swirler (44) is in sealing connection with an outer wall of the pre-film fuel nozzle (60), and the chamfered hole swirler (44) is of a first annular structure, and the middle of the first annular structure forms the fuel-air mixing chamber (70).
7. The apparatus of claim 6, wherein the chamfered hole swirler (44) further comprises a chamfered hole (74), the chamfered hole (74) for passing air into the air mixing chamber (70).
8. The apparatus of claim 7 further comprising a radial vane swirler (46), the radial vane swirler (46) being a second annular structure connected to the chamfered hole swirler (44).
9. An ignition method characterized by using the ignition device according to any one of claims 1 to 8 for ignition.
10. A combustion chamber, comprising an annular combustion chamber (30), a liner outer ring (32), a liner inner ring (34) and a combustion chamber head structure (40), said combustion chamber head structure (40) comprising said ignition device (42) according to any one of claims 1-8.
11. A gas turbine engine, characterized in that it comprises a low-pressure compressor (1), a high-pressure compressor (2), a combustion chamber (3), a high-pressure turbine (4) and a low-pressure turbine (5), said combustion chamber (3) further comprising an ignition device (42) according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211000141.4A CN115405949B (en) | 2022-08-19 | 2022-08-19 | Ignition device, ignition method, combustion chamber and gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211000141.4A CN115405949B (en) | 2022-08-19 | 2022-08-19 | Ignition device, ignition method, combustion chamber and gas turbine |
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| CN115405949A true CN115405949A (en) | 2022-11-29 |
| CN115405949B CN115405949B (en) | 2023-12-15 |
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Citations (6)
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| CN202253758U (en) * | 2011-08-11 | 2012-05-30 | 中国航空动力机械研究所 | Air swirler |
| CN102980204A (en) * | 2012-11-27 | 2013-03-20 | 哈尔滨工程大学 | Fuel-atomizing integrated igniter |
| US20170096932A1 (en) * | 2015-10-06 | 2017-04-06 | Woodward, Inc. | Passive prechamber direct injection combustion |
| CN109441643A (en) * | 2018-09-27 | 2019-03-08 | 北京航空航天大学 | Micro turbojet engine and gas-turbine combustion chamber igniter |
| CN209053698U (en) * | 2018-09-26 | 2019-07-02 | 中国航发商用航空发动机有限责任公司 | Ignition electric nozzle component, combustion chamber and the gas turbine of combustion chamber |
| CN114753932A (en) * | 2021-01-08 | 2022-07-15 | 中国航发商用航空发动机有限责任公司 | Oil collecting ring, fuel nozzle, combustion chamber, gas turbine engine and thermal protection method |
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2022
- 2022-08-19 CN CN202211000141.4A patent/CN115405949B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202253758U (en) * | 2011-08-11 | 2012-05-30 | 中国航空动力机械研究所 | Air swirler |
| CN102980204A (en) * | 2012-11-27 | 2013-03-20 | 哈尔滨工程大学 | Fuel-atomizing integrated igniter |
| US20170096932A1 (en) * | 2015-10-06 | 2017-04-06 | Woodward, Inc. | Passive prechamber direct injection combustion |
| CN209053698U (en) * | 2018-09-26 | 2019-07-02 | 中国航发商用航空发动机有限责任公司 | Ignition electric nozzle component, combustion chamber and the gas turbine of combustion chamber |
| CN109441643A (en) * | 2018-09-27 | 2019-03-08 | 北京航空航天大学 | Micro turbojet engine and gas-turbine combustion chamber igniter |
| CN114753932A (en) * | 2021-01-08 | 2022-07-15 | 中国航发商用航空发动机有限责任公司 | Oil collecting ring, fuel nozzle, combustion chamber, gas turbine engine and thermal protection method |
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| CN115405949B (en) | 2023-12-15 |
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