CN115405949B - Ignition device, ignition method, combustion chamber and gas turbine - Google Patents
Ignition device, ignition method, combustion chamber and gas turbine Download PDFInfo
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- CN115405949B CN115405949B CN202211000141.4A CN202211000141A CN115405949B CN 115405949 B CN115405949 B CN 115405949B CN 202211000141 A CN202211000141 A CN 202211000141A CN 115405949 B CN115405949 B CN 115405949B
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 68
- 238000000034 method Methods 0.000 title claims abstract description 26
- 239000000446 fuel Substances 0.000 claims abstract description 92
- 239000007788 liquid Substances 0.000 claims abstract description 12
- 239000007789 gas Substances 0.000 description 42
- 239000003921 oil Substances 0.000 description 25
- 238000010892 electric spark Methods 0.000 description 11
- 239000000203 mixture Substances 0.000 description 11
- 239000002737 fuel gas Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000000889 atomisation Methods 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 3
- 238000009413 insulation Methods 0.000 description 3
- 238000004080 punching Methods 0.000 description 3
- 238000004088 simulation Methods 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000007789 sealing 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
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000010791 quenching Methods 0.000 description 1
- 230000000171 quenching effect Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spray-Type Burners (AREA)
Abstract
The invention discloses an ignition device, an ignition method, a combustion chamber and a gas turbine. Comprising the following steps: a prefilming fuel nozzle, an ignition nozzle and a fuel-air mixing cavity; the prefilming fuel nozzle comprises an oil inlet channel, a nozzle spout, an air inlet and an annular prefilming cavity, wherein the oil inlet channel is communicated with the nozzle spout, the nozzle spout is communicated with the annular prefilming cavity, and the air inlet is used for forming an air layer in front of the end face of the ignition electric nozzle; the annular prefilming cavity is positioned between the end face of the ignition electric nozzle and the oil-gas mixing cavity, the other side of the annular prefilming cavity is communicated with the oil-gas mixing cavity, and the annular prefilming cavity is used for forming a circular liquid film; the ignition electric nozzle is embedded in the prefilming 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 current ignition device of the combustion chamber of the 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 arranged on the outer casing of the gas turbine, and the flame tube is inserted into the outer casing of the flame tube of the combustion chamber, so that electric sparks released by the electric nozzle can ignite an oil-gas mixture in the flame tube. The ignition mode of the fuel near the prior electric spark ignition electric nozzle to form a flame kernel and then the flame kernel propagates to the fuel near the nozzle to ignite the fuel in the backflow area can be called indirect ignition. FIG. 1 is a schematic diagram of a reverse flow combustor, which is used primarily in medium and small gas turbines. As can be seen from fig. 1, the ignition tips are located in the outer ring position of the cartridge and the fuel nozzles are located in the head of the cartridge. The ignition implementation of the combustion chamber in fig. 1 and the process are as follows: 1) The fuel is sprayed out from the fuel nozzle, and a fuel-gas mixture is formed near the ignition electric nozzle by being mixed with the strong swirl air at the head part; 2) The ignition nozzle releases electric spark 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 function, and the oil-gas mixture at the outlet of the nozzle is further ignited; 4) A large amount of the oil-gas mixture is ignited, thereby forming a stable turbulent combustion flame, and the combustion chamber is successfully ignited.
The main disadvantages of the above technology are as follows: 1) Because the ignition nozzle and the fuel nozzle are mutually independent and the installation position distance of the ignition nozzle and the fuel nozzle is long, fuel is mixed by a large amount of air after being sprayed out by the fuel nozzle, and fuel steam with a certain concentration is difficult to form near the ignition nozzle, so that the electric spark released by the nozzle is difficult to ensure that the nearby fuel steam can be ignited and an initial flame kernel is formed; 2) Even if the electric spark successfully ignites the fuel vapor near the electric nozzle and forms an initial flame kernel, the flame kernel still needs to enter the backflow area to ignite the oil-gas mixture near the outlet of the nozzle through the transportation process, and because the flame kernel can be quenched and cooled in the transportation process, the flame kernel is difficult to ensure that the flame kernel can successfully ignite the oil-gas mixture near the outlet of the nozzle so as to form stable turbulent flame. 3) The ignition nozzle is required to extend into the flame tube, so that the ignition nozzle is directly contacted with high-temperature fuel gas and is ablated by the high-temperature fuel gas for a long time, and the service life of the ignition nozzle is short.
Disclosure of Invention
In order to solve the problems, the invention provides an ignition device, an ignition method, a combustion chamber and a gas turbine.
The embodiment of the invention provides an ignition device, which comprises:
a prefilming fuel nozzle, an ignition nozzle and a fuel-air mixing cavity;
the prefilming fuel nozzle comprises an oil inlet channel, a nozzle spout, an air inlet and an annular prefilming cavity, wherein the oil inlet channel is communicated with the nozzle spout, the nozzle spout is communicated with the annular prefilming cavity, and the air inlet is used for forming an air layer in front of the end face of the ignition electric nozzle; the annular prefilming cavity is positioned between the end face of the ignition electric nozzle and the oil-gas mixing cavity, the other side of the annular prefilming cavity is communicated with the oil-gas mixing cavity, and the annular prefilming cavity is used for forming a circular liquid film;
the ignition electric nozzle is embedded in the prefilming 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.
Optionally, the prefilled fuel nozzle further comprises an oil collecting ring, wherein the oil collecting ring is arranged between the oil inlet channel and the nozzle spout and is respectively communicated with the oil inlet channel and the nozzle spout.
Optionally, the ignition electrode tip is connected with the prefilming fuel nozzle through a thread structure.
Optionally, the prefilming fuel nozzle is a groove structure, the fuel inlet channel, the nozzle spout, the air inlet hole and the annular prefilming cavity are located on the side surface of the groove structure, and the annular prefilming cavity forms a circular liquid film on the bottom surface of the groove structure.
Optionally, the end face of the ignition electrode is parallel to the bottom face of the prefilming fuel nozzle.
Optionally, the ignition device provided by the embodiment of the invention further comprises a chamfer hole vortex device, wherein the chamfer hole vortex device is in sealing connection with the outer wall of the prefilming fuel nozzle, the chamfer hole vortex device is of a first annular structure, and the middle of the first annular structure forms the oil-gas mixing cavity.
Optionally, the chamfer hole swirler further comprises a chamfer hole for introducing air into the oil-gas mixing cavity.
Optionally, the ignition device provided by the embodiment of the invention further comprises a radial vane type swirler, wherein the radial vane type swirler is of a second annular structure and is connected with the chamfer hole swirler.
Based on the same inventive concept, the embodiment of the invention also provides an ignition method, which uses the ignition device to perform 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 also 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 process related to a series of traditional ignition modes such as fuel and fuel core transportation is 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 prefilled pneumatic atomizing nozzle and an ignition electric nozzle, and the ignition electric nozzle and the fuel nozzle are integrated, so that a series of parts such as an electric nozzle mounting seat, an electric nozzle heat insulation lining and the like do not need to be arranged on a combustion chamber casing, and in addition, 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 structure is more compact.
3. The ignition performance is high. The ignition performance of the invention can be improved by 30% compared with that of a conventional combustion chamber by carrying out ignition simulation and experimental study on a three-head combustion chamber test piece of a new generation turboshaft engine.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be apparent from the description, or may be learned by 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 thereof as well as the appended drawings.
The technical scheme of the invention is further described in detail through the drawings and the embodiments.
Drawings
The accompanying drawings 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, without limitation, the embodiments of 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 block diagram of a combustion chamber in an embodiment of the invention;
FIG. 4 is a schematic view of a gas turbine engine including a combustor in accordance with 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 chamfer hole vortex; 46. radial vane turbulators; 48. a swirler vane; 52. a central axis; 54. a nozzle is started; 56. a thread structure; 58. igniting the end face of the nozzle; 60. prefilled fuel nozzles; 61. an oil inlet passage; 62. oil collecting ring; 63. a nozzle spout; 64. an air inlet hole; 65. annular prefilming cavity wall surface; 68. an annular prefilming cavity; 70. an oil-gas mixing cavity; 74. and chamfering 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 solution of the present invention may be embodied in various forms and should not be limited to 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, a method, a combustion chamber, and a gas turbine.
The embodiment of the present invention provides an ignition device 42, where the ignition device 42 is a combined ignition device, and the structure of the ignition device is shown in fig. 2, and includes:
prefilled fuel nozzle 60, ignition nozzle 54, and oil and gas mixing chamber 70; the fuel vapor may be ignited by an electric spark, thereby forming an initial core and a high temperature fuel mass containing the core near the ignition tip face 58;
the prefilming fuel nozzle 60 comprises an oil inlet channel 61, a nozzle spout 63, an air inlet 64 and an annular prefilming cavity 68, the prefilming fuel nozzle 60 is specifically a prefilming 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 prefilming cavity 68. The air inlet holes 64 are used for forming an air layer in front of the end face 58 of the ignition electrode 54, so that the ignition and the fuel combustion are facilitated to be sufficient; the annular prefilming cavity 68 is located between the end face 58 of the ignition electric nozzle 54 and the oil-gas mixing cavity 70, the other side of the annular prefilming cavity 68 is communicated with the oil-gas mixing cavity 70, and the annular prefilming cavity 68 is used for forming a circular liquid film; the fuel enters from the fuel inlet channel 61 and is sprayed out from the nozzle spout 63 into the annular prefilming cavity 68 to form an annular liquid film.
The ignition tip 54 is embedded in the prefilled fuel nozzle 60, the ignition tip 54 is used to form an initial flame, and the air-fuel mixture chamber 70 is used to mix air and fuel.
Optionally, the prefilled fuel nozzle 60 further comprises an oil collecting ring 62, wherein the oil collecting ring 62 is communicated with the oil inlet channel 61 and the nozzle spout 63 between the oil inlet channel 61 and the nozzle spout 63, respectively. The oil collecting ring 62 enables the nozzle ports 63 to synchronously spray fuel everywhere, and a circular liquid film is easier to form.
Optionally, the ignition electrode 54 is connected to the prefilled fuel nozzle 60 by a threaded structure 56, which facilitates the fixed replacement.
Optionally, the prefilming fuel nozzle 60 is a groove structure, the fuel inlet channel 61, the nozzle spout 63, the air inlet 64 and the annular prefilming cavity 68 are located at the side surface of the groove structure, and the annular prefilming cavity 68 forms a circular liquid film at the bottom surface of the groove structure.
Optionally, the end face 58 of the ignition nozzle 54 is parallel to the bottom surface of the prefilled fuel nozzle 60.
In some alternative embodiments, combustion chamber head structure 40 includes an ignition device 42, and an ignition device 42 further includes a chamfer hole swirler 44 and a radial vane swirler 46.
Optionally, the ignition device provided by the embodiment of the present invention further includes a chamfer hole vortex device 44, where the chamfer hole vortex device 44 is connected with the outer wall of the prefilming fuel nozzle 60 in a sealing manner, the chamfer hole vortex device 44 is of a first annular structure, and the middle of the first annular structure forms the oil-gas mixing cavity 70.
Optionally, the chamfer hole swirler 44 further includes chamfer holes 74, wherein the chamfer holes 74 are used for introducing air into the oil-gas mixing cavity 70 to promote the full combustion of fuel.
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 chamfer hole swirler 44. The radial vane swirler 46 is provided with swirler vanes 48.
The technical scheme of the invention is different from that of the traditional combustion chamber ignition device and the mode, as shown in fig. 1, the traditional ignition device is independent electrical equipment, the ignition electric nozzle and the fuel nozzle are two independent parts, the installation positions are far apart, and the ignition device can only form electric sparks on the end face of the ignition electric nozzle, so that the electric sparks can not be ensured to ignite fuel steam and form stable flame. In addition, the traditional ignition mode needs to enable fuel oil liquid drops and steam to move to the vicinity of an ignition nozzle, an initial flame kernel is formed on the end face of the ignition nozzle, then the flame kernel also needs to flow back to the vicinity of a nozzle outlet to form stable turbulent flame, the ignition mode is complex in process, the fuel oil and the flame kernel are affected by a series of factors including quenching, turbulent flow and the like in the transportation process, and the ignition reliability is difficult to be ensured. The technical scheme of the invention combines and integrates the traditional ignition device and the fuel nozzle, 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 flame kernel and high-temperature fuel gas clusters directly form stable turbulent flame in the backflow area. Therefore, the ignition 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 prefilled fuel nozzle 60 and an ignition tip 54. The firing nozzle 54 is embedded in the fuel nozzle 60, which are connected by a threaded structure 56. The fuel enters the nozzle 60 through the fuel manifold and then enters an oil collecting ring 62 through an oil inlet channel 61, the fuel enters a nozzle spout 63 from the oil collecting ring 62 and then is injected to form a cylindrical jet into an annular prefilming cavity 68, the fuel jet directly impacts an annular prefilming cavity wall surface 65 to form a ring-shaped liquid film, and the ring-shaped liquid film flows along the annular prefilming cavity wall surface 65 and then leaves the fuel nozzle 60 to enter a fuel-air mixing cavity 70. This air-fuel mixture chamber 70 is cylindrical and has a central axis 52, and the central axis 52 is also the central axis of the ignition tip 54, the end face 58 of the ignition tip 54, and the annular prefilming chamber 68. The air from the oil and gas mixing chamber 70 comes from 2 streams, 1 stream entering the oil and gas mixing chamber 70 through the inlet holes 64 on the fuel nozzle 60, and a portion entering the mixing chamber through the chamfer holes 74 of the chamfer 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 and oil-gas mixing of the fuel oil. The end face 58 of the firing nozzle 54 may release the spark plug to ignite the fuel-air mixture formed in the mixing chamber to form an initial flame kernel that heats the air in the mixing chamber 70 and further forms a high temperature fuel mass that moves downstream with the air flow to ignite the fuel vapor in the recirculation zone and form a stable turbulent 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 process related to a series of traditional ignition modes such as fuel and fuel core transportation is 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 prefilled pneumatic atomizing nozzle and an ignition electric nozzle, and the ignition electric nozzle and the fuel nozzle are integrated, so that a series of parts such as an electric nozzle mounting seat, an electric nozzle heat insulation lining and the like do not need to be arranged on a combustion chamber casing, and in addition, 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 structure is more compact.
3. The ignition performance is high. The ignition performance of the invention can be improved by 30% compared with that of a conventional combustion chamber by carrying out ignition simulation and experimental study on a three-head combustion chamber test piece of a new generation turboshaft engine.
Based on the same inventive concept, the embodiment of the present invention also provides an ignition method for performing ignition using the ignition device 42 as described above. According to the method, the prefilled pneumatic atomizing nozzle is used for enabling oil gas to be rapidly mixed, and the electric spark is directly released near the outlet of the nozzle to further ignite fuel steam to form an initial fire core and a high-temperature fuel gas group, so that the fuel and fire core transportation process is greatly simplified, and the ignition success rate is improved.
Based on the same inventive concept, the embodiment of the present invention further provides a combustion chamber 3, the structure of which is shown in fig. 3, including an annular combustion chamber body 30, a liner outer ring 32, a liner inner ring 34 and a combustion chamber head structure 40, wherein the combustion chamber head structure 40 includes the ignition device 42 as described above. In some alternative embodiments, combustion chamber head structure 40 includes an ignition device 42, and an ignition device 42 further includes a chamfer 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, flame kernel generation, turbulent flame propagation and the like are directly completed in the mixing cavity positioned at the head, so that the fuel and flame kernel transportation processes are greatly simplified, and the ignition reliability is further improved. Fig. 3 is a central sectional view of the combustion chamber 3 applied 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 liner outer ring 32 circumscribes the outer ring boundary of the annular combustion chamber 30 and the liner inner ring 34 circumscribes the inner ring boundary of the annular combustion chamber 30. The inner and outer combustion rings 32, 34 are embedded in the annular combustion casing and form an inner and outer ring passage 35, 37 respectively with the casing. The combustion chamber 3 also includes an annular header assembly 40 mounted upstream of the outer and inner burner rings 32, 34 for fuel injection atomization, oil and gas 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, comprising 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, wherein the combustion chamber 3 further comprises an ignition device as described above, and the ignition device is installed at the head of the combustion chamber 3. In some alternative embodiments, combustion chamber head structure 40 includes an ignition device 42, and an ignition device 42 further includes a chamfer hole swirler 44 and a radial vane swirler 46. Fig. 4 shows a schematic diagram of a gas turbine 10, comprising 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. When the gas turbine operates, air flows pass through the high-pressure compressor 1 and the low-pressure compressor 2, are compressed into high-pressure gas and enter the combustion chamber 3, and the high-temperature high-pressure gas formed by combustion in the combustion chamber 3 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 process related to a series of traditional ignition modes such as fuel and fuel core transportation is 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 prefilled pneumatic atomizing nozzle and an ignition electric nozzle, and the ignition electric nozzle and the fuel nozzle are integrated, so that a series of parts such as an electric nozzle mounting seat, an electric nozzle heat insulation lining and the like do not need to be arranged on a combustion chamber casing, and in addition, 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 structure is more compact.
3. The ignition performance is high. The ignition performance of the invention can be improved by 30% compared with that of a conventional combustion chamber by carrying out ignition simulation and experimental study on a three-head combustion chamber test piece of a new generation turboshaft engine.
Any modification, supplement, equivalent replacement, etc. within the principle of the technical solution of the present invention should still fall within the scope of patent coverage of the technical solution of the present invention.
Claims (11)
1. An ignition device, comprising:
a prefilled fuel nozzle (60), an ignition nozzle (54), and a fuel-air mixing chamber (70);
the prefilming fuel nozzle (60) comprises an oil inlet channel (61), a nozzle spout (63), an air inlet hole (64) and an annular prefilming cavity (68), wherein the oil inlet channel (61) is communicated with the nozzle spout (63), the nozzle spout (63) is communicated with the annular prefilming cavity (68), and the air inlet hole (64) is used for forming an air layer in front of the end face (58) of the ignition electric nozzle (54); the annular prefilming 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 prefilming cavity (68) is communicated with the oil-gas mixing cavity (70), and the annular prefilming cavity (68) is used for forming a circular liquid film;
the ignition electrode (54) is embedded in the prefilming fuel nozzle (60), the ignition electrode (54) is used for forming an initial flame, and the oil-gas mixing cavity (70) is used for mixing air and fuel.
2. The device according to claim 1, characterized in that the prefilled fuel nozzle (60) further comprises an oil collecting ring (62), said oil collecting ring (62) being in communication with said oil inlet channel (61) and said nozzle spout (63), respectively, between said oil inlet channel (61) and said nozzle spout (63).
3. The device according to claim 1, characterized in that the ignition tip (54) is connected to the prefilled fuel nozzle (60) by means of a screw structure (56).
4. A device according to any one of claims 1-3, characterized in that the prefilming fuel nozzle (60) is of a groove structure, the fuel inlet channel (61), nozzle spout (63), air inlet (64) and annular prefilming chamber (68) are located at the sides of the groove structure, and the annular prefilming chamber (68) forms a circular liquid film at the bottom of the groove structure.
5. The device according to claim 4, characterized in that the end face (58) of the ignition nozzle (54) is parallel to the bottom face of the prefilled fuel nozzle (60).
6. The apparatus of any of claims 1-5, further comprising a chamfer hole swirler (44), the chamfer hole swirler (44) being sealingly connected to an outer wall of the prefilled fuel nozzle (60), the chamfer hole swirler (44) being of a first annular configuration, a middle of the first annular configuration forming the fuel-air mixing chamber (70).
7. The apparatus of claim 6, wherein the chamfer bore swirler (44) further comprises a chamfer bore (74), the chamfer bore (74) for passing air into the oil and gas 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 coupled to the chamfer bore swirler (44).
9. A method of ignition, characterized in that ignition is performed using an ignition device as claimed in any one of claims 1-8.
10. A combustion chamber characterized by 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 comprising 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 1-8.
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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115405949A CN115405949A (en) | 2022-11-29 |
| CN115405949B true CN115405949B (en) | 2023-12-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211000141.4A Active CN115405949B (en) | 2022-08-19 | 2022-08-19 | Ignition device, ignition method, combustion chamber and gas turbine |
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| CN118423717B (en) * | 2024-07-04 | 2024-10-29 | 中国航发湖南动力机械研究所 | Long-life backflow combustion chamber |
Citations (5)
| 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 |
| 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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| US9890690B2 (en) * | 2015-10-06 | 2018-02-13 | Woodward, Inc. | Passive prechamber direct injection combustion |
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Patent Citations (5)
| 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 |
| 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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