CN105674330A - Single-tube combustor device of ground combustion gas turbine - Google Patents
Single-tube combustor device of ground combustion gas turbine Download PDFInfo
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- CN105674330A CN105674330A CN201610054669.8A CN201610054669A CN105674330A CN 105674330 A CN105674330 A CN 105674330A CN 201610054669 A CN201610054669 A CN 201610054669A CN 105674330 A CN105674330 A CN 105674330A
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- hole
- inner liner
- casing
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- askew
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention provides a single-tube combustor device of a ground combustion gas turbine. The single-tube combustor device of the ground combustion gas turbine comprises a casing and a flame tube arranged in the casing. A natural gas inlet pipeline is arranged on the top of the flame tube in an externally connected mode. A first-stage beveling hole whirlcone and a second-stage radial whirlcone which are opposite in rotation direction are arranged in the neck position of the flame tube sequentially from top to bottom. The first-stage beveling hole whirlcone is of a circular truncated cone structure and provided with a through hole enabling the side wall and the bottom face to communicate. The two stages of whirlcones are each provided with a Venturi tube. An igniter assembly, a main combustion hole and a mixing hole are formed in the side wall of the flame tube sequentially from top to bottom. A plurality of tiny full-coverage air film cooling holes are formed in the surface of the flame tube. A pair of symmetrical air inlets are formed in the side wall of the casing, and a convergence outlet is formed in the tail of the flame tube. By arranging the two stages of whirlcones on the neck of the flame tube and arranging the main combustion hole, the mixing hole and the tiny cooling holes in the flame tube, reasonable distribution of a combustion flow field, outlet temperature and wall temperature and reasonable temperature rise of a combustor can be achieved, and the service life of the flame tube is prolonged.
Description
Technical field
The invention belongs to ground gas turbine field, relate to a kind of with natural gas for fuel, cut sth. askew the isostructural ground gas turbine can burner in radial swirler, primary holes, blending hole and wall cooling hole with twin-stage.
Background technology
Abroad, domestic the use value of ground gas turbine is fully proved nearly ten years, and its application direction is rich promising. Along with the increase day by day of energy resource consumption, distributed power source obtains attention gradually. Distributed power supply have need not remote conveying controller switching equipment, utilize the energy nearby, require conveniently realize heat-electricity-refrigerate co-operation and meet the advantage such as power and need for electricity of application circumstances according to user. And ground gas turbine is one of energy conversion device with high power density the most quickly, stably and easily that the chemical energy of fuel is changed into electric energy. Ground gas turbine can be operating on gaseous fuel and liquid fuel, and wherein gaseous fuel is with natural gas for many, and liquid fuel includes diesel oil and heavy oil etc. The development of ground gas turbine technology and application are subject to aircraft engine technology and the excitation of the development of theory, the development of ground combustion machine self-technique, the development of related discipline technology and the market demand.
The domestic research to ground gas-turbine combustion chamber at present, the technology that Primary Reference is comparatively ripe abroad. Gaseous fuel is different from liquid and solid fuel, and combustion process comprises three phases: fuel mixes with air, mix gas heating catches fire and complete combustion chemistry and react. Gas-turbine combustion chamber adopts diffusion type to burn mostly, mixed fuel gas is that outer portion incendiary source is lighted, for anti-anti-avulsion fire, stop working, except spouting velocity and flame propagation velocity except should ensure that gas adapts, also should be taken that the strong incendiary source of composition, the heat by self producing realizes the burning of continuous-stable. In order to improve the overall performance of ground gas turbine, its combustor is generally adopted high-temperature alloy material, the mode adopting Multi-stage spiral forms recirculating zone and stablizes flame, comparatively uniform outlet temperature field is formed in conjunction with primary holes and blending hole, adopt rational type of cooling cooling flame tube wall surface, thus ensureing the life-span of burner inner liner.For ground gas turbine, mostly adopt the combustor of backflow annular and baffling form, size is longer relative to aero-gas turbine combustor, has the advantages such as blower outlet flow field is insensitive and outlet temperature is comparatively uniform, and need not too consider labyrinth and the weight of combustor. The shortcomings such as but reverse-flow can type combustor also exists, and burner inner liner film-cooled heat is big, turning additional pressure drops and non-uniform flow. Especially the ground gas turbine being fuel with natural gas, owing to the methane equal size of the natural gas of different regions is not quite similar, which results in the parameters such as the calorific value of fuel and have certain change, this just requires that its combustor should have the fuel value adaptability of one fixed width. The design process of ground gas turbine combustor should taking into full account, These characteristics is designed, and plays its strong point, overcomes its weakness.
Summary of the invention
Goal of the invention: in order to solve above-mentioned the deficiencies in the prior art, the present invention provides a kind of ground gas turbine can burner device, it is possible to produces rational Combustion Flow Field, Exit temperature distribution, wall surface temperature distribution and combustor temperature rise etc., meets design requirement.
Technical scheme: a kind of ground gas turbine can burner device, including casing and the burner inner liner being arranged in casing, the top of described burner inner liner is provided with external Imported gas pipeline, the neck location of described burner inner liner is from top to bottom disposed with one-level and cuts sth. askew hole cyclone and two grades of radial swirlers, and described one-level hole cyclone of cutting sth. askew is contrary with the direction of rotation of described two grades of radial swirlers; Described one-level hole cyclone of cutting sth. askew is the through hole that round table-like structure and hole cyclone of cutting sth. askew are provided with UNICOM's side wall surface and bottom surface; Described one-level hole cyclone of cutting sth. askew connects the first Venturi tube, and described two grades of radial swirlers connect the second Venturi tube; Described burner inner liner sidewall is from top to bottom sequentially provided with lighter mounting assembly, primary holes, blending hole, and described burner inner liner surface is provided with more than one evenly distributed all standing gaseous film control aperture; Described casing sidewall is provided with the air intlet of a pair symmetry, and described flame drum tail is provided with outlet.
Further, end cap, casing flange are also included; Described casing top is bolted described end cap, is provided with corrugated sheet between described casing and described end cap; The afterbody of described burner inner liner is provided with gripper shoe, and described gripper shoe supports described burner inner liner by casing flange.
Further, one end that described Imported gas pipeline is positioned at burner inner liner is provided with natural gas combustion nozzle.
Beneficial effect: the invention provides a kind of ground gas turbine can burner device, cut sth. askew hole cyclone by being provided with the one-level in some holes of cutting sth. askew at the cervical region of burner inner liner, two grades of radial swirlers, air is entered from two-stage cyclones, it is sufficiently mixed with the natural gas of burner ejection, under two-stage vortex gas-flow effect, form stable recirculating zone, after lighter is lighted on wall, form stable combustion flame; Air enters main flow area from primary holes, blocks head high temperature recirculation zone by the jet of primary holes, thus controlling reflux area length, and supplementary fresh air, make the natural gas that burner sprays burn completely; The air entered from blending hole can regulate Exit temperature distribution, improves the life-span of turbine; Enter the air in burner inner liner from aperture on burner inner liner internal face, form all standing air film, improve the burner inner liner life-span.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention;
Fig. 2 is ground gas turbine combustor hydrocyclone structure schematic diagram;
Wherein, Fig. 2 a is the sectional view of combustor cyclone, and Fig. 2 b is the structural representation of one-level cyclone, and Fig. 2 c is the structural representation of second cyclone;
Fig. 3 is that one-level is cut sth. askew hole cyclone tomograph;
Wherein, Fig. 3 a and Fig. 3 b is one-level and cuts sth. askew the tomograph of hole cyclone.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is further illustrated.
As shown in Figure 1, a kind of ground gas turbine can burner device, including casing 16 and the burner inner liner being arranged in casing 16, the top of burner inner liner is provided with external Imported gas pipeline 1, the neck location of burner inner liner is from top to bottom disposed with one-level and cuts sth. askew hole cyclone 4 and two grades of radial swirlers 5, one-level hole cyclone 4 of cutting sth. askew is contrary with the direction of rotation of two grades of radial swirlers 5, and the helical blade scope of two grades of radial swirlers 5 covers one-level and cuts sth. askew the through hole position on hole cyclone 4 bottom surface; One-level cuts sth. askew hole cyclone 4 in round table-like structure, and hole cyclone of cutting sth. askew is provided with the through hole of UNICOM's side wall surface and bottom surface; One-level hole cyclone 4 of cutting sth. askew connects the first Venturi tube 19, and two grades of radial swirlers 5 connect the second Venturi tube 20; Burner inner liner sidewall is from top to bottom sequentially provided with lighter mounting assembly 17, primary holes 15, blending hole 13, and burner inner liner surface is provided with more than one evenly distributed all standing gaseous film control aperture 7; Casing 16 sidewall is provided with the air intlet 14 of a pair symmetry, and flame drum tail is provided with outlet 12. Also include end cap 2, casing flange 11; Casing 16 top is bolted end cap 2, is provided with corrugated sheet 3 between casing 16 and end cap 2; The afterbody of burner inner liner is provided with gripper shoe 10, and gripper shoe 10 supports burner inner liner by casing flange 11. Imported gas pipeline 1 is positioned at one end of burner inner liner and is provided with natural gas combustion nozzle 18.
Embodiment:
Cut sth. askew 4, two grades of radial swirlers 5 of hole cyclone by natural gas combustion nozzle 18, one-level in the ground gas turbine can burner of present invention design, casing 16 and burner inner liner composition, and burner inner liner is made up of in the middle part of burner inner liner head 6, burner inner liner 8 and flame drum tail 9. From the gases at high pressure of centrifugal compressor after monosymmetric air intlet 14 enters can burner, it is divided into five partial flowpafh to enter combustion chamber flame drums, is flow through one-level to cut sth. askew all standing gaseous film control aperture 7 on the primary holes 15 on hole cyclone 4, two grades of radial swirlers 5, burner inner liners, blending hole 13 and burner inner liner wall respectively. End cover of combustion chamber 2 and gas turbine casing 16 are bolted; The Imported gas pipeline 1 of head is tapped, is conveniently connected with natural gas line, it is ensured that seal, it is prevented that gas leakage, and Imported gas pipeline 1 is welded to connect with end cover of combustion chamber 2, it is ensured that seal, it is prevented that the combustion gas in combustor spills; Due to whole gas turbine general design requirement, whole Combustion chamber design is vertically place, it is thus desirable to consider the bearing member design of its mechanical stress and thermal stress, mainly fixed by the corrugated sheet 3 of head and the burner inner liner gripper shoe 10 of afterbody, wherein the burner inner liner gripper shoe 10 of afterbody is main stressed member, and the gravity of whole burner inner liner is passed to casing flange 11 by burner inner liner gripper shoe and bears; And corrugated sheet 3 is cut sth. askew one-level 4, two grades of radial swirlers 5 of hole cyclone by bolt, casing 16 is fixing together with end cover of combustion chamber 2 to be connected, corrugated sheet 3 is enclosed within natural gas combustion nozzle and has certain void space, and there is certain axial distance between corrugated sheet 3 and end cover of combustion chamber 2, when burner inner liner expanded by heating, burner inner liner gripper shoe 10 maintains static, and corrugated sheet 3 can move up certain axial distance, thus eliminating the thermal stress of combustion chamber flame drum.Considering burner inner liner expanded by heating and component processing and alignment error, in the middle part of burner inner liner, the leading portion design of 8 has lighter mounting assembly 17, and lighter mounting assembly 17 circumferentially can all have certain mobile space in 360 ° of directions, thus facilitating lighter to install.
Major part air enters burner inner liner from primary holes 15, blending hole 13 and one-level 4, two grades of radial swirlers 5 of hole cyclone of cutting sth. askew, for organizing burning and air to blend, surplus air cools down aperture 7 from wall all standing and enters combustor, for cooling flame tube wall surface. The primary structure of head of combustion chamber is two-stage cyclones structure, cut sth. askew including one-level hole swirler assembly 4 and two grades of radial swirler assemblies 5, two-stage cyclones is respectively provided with first Venturi tube the 19, second Venturi tube 20, one-level hole cyclone 4 of cutting sth. askew connects the first Venturi tube 19, two grades of radial swirlers 5 connect the second Venturi tube 20, and Venturi tube is both designed as first shrinking, and expands afterwards, thus ensureing that air-flow accelerates flowing in Venturi tube, it is prevented that tempering. One-level hole cyclone 4 of cutting sth. askew is designed to multiple pore structure of cutting sth. askew, two grades of radial vortexs 5 are designed to radial swirler, its blade is spiral vane, and the air inlet of two-stage cyclones is oppositely oriented, blend mutually in the first Venturi tube 19 exit, form shear layer, it is ensured that natural gas mixes rapidly and uniformly with air. Cut sth. askew after the air that cyclone 4, two grades of radial swirlers 5 in hole flow out flows out first Venturi tube the 19, second Venturi tube 20 from one-level and start rapidly outwards high speed rotating expansion, thus causing burner inner liner centre pressure to reduce, cause that gas flow counterflow supplements below, thus forming stable recirculating zone at head of combustion chamber, provide aerodynamic conditions for forming stable incendiary source; Mixed gas burns rapidly after ignitor assembly 17 is lighted at head of combustion chamber, discharges heat, and air-flow accelerates, and exports 12 ejections at a high speed from combustion chamber flame drum, promotes the turbine acting after combustor, is mechanical energy by thermal energy.
One-level hole cyclone 4 of cutting sth. askew can be processed by one piece casting or machining mode, two grades of radial swirlers 5 can be processed by modes such as overall machining, one piece casting or welding, the parts such as swirler blades can be attached with cyclone baffle plate and Venturi tube by welding manner, by being welded to connect between two-stage cyclones; Cut sth. askew 4, two grades of radial swirlers of hole cyclone 5 and corrugated sheet 3, end cover of combustion chamber 2 and combustion box 16 of one-level is connected through bolt by flange; By being welded to connect between 8 and flame drum tail 9 in the middle part of burner inner liner head 6, burner inner liner; All standing cooling aperture 7 on burner inner liner wall is processed by laser drilling, and the relatively larger hole such as primary holes 15 and blending hole 13 can be processed by the mode of machining. Burner inner liner gripper shoe 10 is connected with flame drum tail 9 by welding manner so that burner inner liner entirety load-bearing is passed through on the flange 11 that gripper shoe 10 is sitting on casing below.
The aperture of natural gas combustion nozzle 18 is between 0.6～1.5mm, quantity is between 6～20, and the angle of burner injection is between 30 °～120 °, or even the version of nozzle all can carry out suitable adjustment according to required duty, thus the fuel reaching injection is mixed homogeneously with air as early as possible. What one-level cut sth. askew hole cyclone 4 cuts sth. askew hole 23 eddy flow angle between 30 °～80 °, cut sth. askew the quantity in hole 23 between 6～20, all can make suitable adjustment, air-flow rotation direction can be clockwise or counter-clockwise along airflow direction, and the shrinkage expansion section of the first Venturi tube 19 that hole cyclone 4 of cutting sth. askew with one-level is connected can effectively prevent tempering;Two grades of radial swirlers 5 are designed as radial blade formula cyclone, swirler blades 24 is welded on second cyclone baffle plate 22, swirler blades 24 setting angle is between 30 °～80 °, and swirler blades 24 number, between 10～25, all can make suitable adjustment. The air-flow of two-stage cyclones is oppositely oriented, it is possible to form stronger air-flow shear layer, is conducive to fuel to mix with the quick of air; In the middle part of burner inner liner head 6, burner inner liner, the angle between 8 and flame drum tail 9 all standing gaseous film control aperture 7 and incoming flow wall above is between 15 °～45 °, carries out suitable adjustment according to practical situation, thus reaching best cooling effect.
The air capacity of head of combustion chamber accounts for about the 12%～30% of import total air, the cooling air volume cooling down aperture 7 of hole cyclone 4 and the air inflow of two grades of radial swirlers 5, burner inner liner head of cutting sth. askew including one-level; Head of combustion chamber is fuel-rich combustion generally partially, thus ensureing there is good combustion stability.
The air of about 10%～30% is entered from two-stage cyclones, is sufficiently mixed with the natural gas of burner ejection, forms stable recirculating zone, after lighter is lighted on wall, form stable combustion flame under two-stage vortex gas-flow effect; The air of about 15%～40% enters main flow area from primary holes, blocks head high temperature recirculation zone by the jet of primary holes, thus controlling reflux area length, and supplementary fresh air, make the natural gas that burner sprays burn completely; The air of about 15%～40% enters from blending hole, regulates Exit temperature distribution so that it is temperature field meets turbine design requirement, thus improving the life-span of turbine; Surplus air enters from all standing gaseous film control aperture burner inner liner, forms all standing air film, thus improving the burner inner liner life-span on burner inner liner internal face; The high temperature and high speed combustion gas of combustor exit enters turbine, promotes turbine acting.
Finally should be noted that: above example is merely to illustrate the technical scheme of the application but not the restriction to its protection domain; technical field of the present invention has usually intellectual; without departing from the spirit and scope of the present invention, when doing various changes and retouching. Therefore, protection scope of the present invention is when being as the criterion depending on those as defined in claim.
Claims (3)
1. a ground gas turbine can burner device, it is characterized in that: include casing (16) and the burner inner liner being arranged in casing (16), the top of described burner inner liner is provided with external Imported gas pipeline (1), the neck location of described burner inner liner is from top to bottom disposed with one-level and cuts sth. askew hole cyclone (4) and two grades of radial swirlers (5), and described one-level hole cyclone (4) of cutting sth. askew is contrary with the direction of rotation of described two grades of radial swirlers (5); Described one-level cut sth. askew hole cyclone (4) in round table-like structure and hole cyclone of cutting sth. askew be provided with the through hole of UNICOM's side wall surface and bottom surface; Described one-level hole cyclone (4) of cutting sth. askew connects the first Venturi tube (19), and described two grades of radial swirlers (5) connect the second Venturi tube (20); Described burner inner liner sidewall is from top to bottom sequentially provided with lighter mounting assembly (17), primary holes (15), blending hole (13), and described burner inner liner surface is provided with more than one evenly distributed all standing gaseous film control aperture (7); Described casing (16) sidewall is provided with the air intlet (14) of a pair symmetry, and described flame drum tail is provided with outlet (12).
2. a kind of ground gas turbine can burner according to claim 1 device, it is characterised in that: also include end cap (2), casing flange (11);Described casing (16) top is bolted described end cap (2), is provided with corrugated sheet (3) between described casing (16) and described end cap (2); The afterbody of described burner inner liner is provided with gripper shoe (10), and described gripper shoe (10) supports described burner inner liner by casing flange (11).
3. a kind of ground gas turbine can burner according to claim 1 device, it is characterised in that: one end that described Imported gas pipeline (1) is positioned at burner inner liner is provided with natural gas combustion nozzle (18).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610054669.8A CN105674330B (en) | 2016-01-27 | 2016-01-27 | A kind of ground gas turbine can burner device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610054669.8A CN105674330B (en) | 2016-01-27 | 2016-01-27 | A kind of ground gas turbine can burner device |
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| CN105674330A true CN105674330A (en) | 2016-06-15 |
| CN105674330B CN105674330B (en) | 2018-07-17 |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106247402A (en) * | 2016-08-12 | 2016-12-21 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of burner inner liner |
| CN106287814A (en) * | 2016-09-29 | 2017-01-04 | 南京航空航天大学 | A kind of ground gas turbine can burner of axial admission |
| CN106482154A (en) * | 2016-10-31 | 2017-03-08 | 南京航空航天大学 | The lean premixed preevaporated low contamination combustion chamber that a kind of main is atomized with splashing type |
| CN107036128A (en) * | 2017-05-09 | 2017-08-11 | 上海泛智能源装备有限公司 | A kind of gas-turbine combustion chamber |
| CN107062306A (en) * | 2017-05-09 | 2017-08-18 | 上海泛智能源装备有限公司 | A kind of combustion chamber and gas turbine |
| CN107062307A (en) * | 2017-05-09 | 2017-08-18 | 上海泛智能源装备有限公司 | A kind of gas-turbine combustion chamber |
| CN107101225A (en) * | 2017-05-16 | 2017-08-29 | 上海泛智能源装备有限公司 | A kind of cyclone structure of burner, burner and combustion gas turbine |
| CN107101224A (en) * | 2017-05-23 | 2017-08-29 | 上海泛智能源装备有限公司 | A kind of can burner and gas turbine |
| CN107314399A (en) * | 2017-07-03 | 2017-11-03 | 上海泛智能源装备有限公司 | A kind of pre-mixing apparatus of gas turbine and combustion chamber |
| CN111043624A (en) * | 2019-12-31 | 2020-04-21 | 新奥能源动力科技（上海）有限公司 | Combustion chamber and gas turbine |
| CN112050254A (en) * | 2020-09-18 | 2020-12-08 | 中国航发四川燃气涡轮研究院 | Flame tube head |
| CN113137629A (en) * | 2021-04-19 | 2021-07-20 | 中国航发湖南动力机械研究所 | Double-stage integral swirler and flame tube head structure |
| CN113154450A (en) * | 2021-04-15 | 2021-07-23 | 中国航发湖南动力机械研究所 | Novel fuel atomization device and flame tube head structure with same |
| CN114486273A (en) * | 2021-12-27 | 2022-05-13 | 国网浙江省电力有限公司电力科学研究院 | Park flexibility reforms transform unit hydrogen and burns test device thoughtlessly |
| CN114646076A (en) * | 2022-03-18 | 2022-06-21 | 中国航空发动机研究院 | Adjustable cyclone assembly and multistage cyclone |
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| CN106247402B (en) * | 2016-08-12 | 2019-04-23 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of burner inner liner |
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| CN106287814A (en) * | 2016-09-29 | 2017-01-04 | 南京航空航天大学 | A kind of ground gas turbine can burner of axial admission |
| CN106482154A (en) * | 2016-10-31 | 2017-03-08 | 南京航空航天大学 | The lean premixed preevaporated low contamination combustion chamber that a kind of main is atomized with splashing type |
| CN107036128A (en) * | 2017-05-09 | 2017-08-11 | 上海泛智能源装备有限公司 | A kind of gas-turbine combustion chamber |
| CN107062307A (en) * | 2017-05-09 | 2017-08-18 | 上海泛智能源装备有限公司 | A kind of gas-turbine combustion chamber |
| CN107062306A (en) * | 2017-05-09 | 2017-08-18 | 上海泛智能源装备有限公司 | A kind of combustion chamber and gas turbine |
| CN107036128B (en) * | 2017-05-09 | 2023-07-18 | 新奥能源动力科技（上海）有限公司 | Combustion chamber of gas turbine |
| CN107062307B (en) * | 2017-05-09 | 2023-06-20 | 新奥能源动力科技（上海）有限公司 | Combustion chamber of gas turbine |
| CN107101225A (en) * | 2017-05-16 | 2017-08-29 | 上海泛智能源装备有限公司 | A kind of cyclone structure of burner, burner and combustion gas turbine |
| CN107101224A (en) * | 2017-05-23 | 2017-08-29 | 上海泛智能源装备有限公司 | A kind of can burner and gas turbine |
| CN107101224B (en) * | 2017-05-23 | 2023-01-10 | 新奥能源动力科技（上海）有限公司 | Single-tube combustion chamber and gas turbine |
| CN107314399A (en) * | 2017-07-03 | 2017-11-03 | 上海泛智能源装备有限公司 | A kind of pre-mixing apparatus of gas turbine and combustion chamber |
| CN111043624A (en) * | 2019-12-31 | 2020-04-21 | 新奥能源动力科技（上海）有限公司 | Combustion chamber and gas turbine |
| CN112050254A (en) * | 2020-09-18 | 2020-12-08 | 中国航发四川燃气涡轮研究院 | Flame tube head |
| CN113154450B (en) * | 2021-04-15 | 2022-08-09 | 中国航发湖南动力机械研究所 | Fuel oil atomization device and flame tube head structure with same |
| CN113154450A (en) * | 2021-04-15 | 2021-07-23 | 中国航发湖南动力机械研究所 | Novel fuel atomization device and flame tube head structure with same |
| CN113137629B (en) * | 2021-04-19 | 2022-11-04 | 中国航发湖南动力机械研究所 | Double-stage integral swirler and flame tube head structure |
| CN113137629A (en) * | 2021-04-19 | 2021-07-20 | 中国航发湖南动力机械研究所 | Double-stage integral swirler and flame tube head structure |
| CN114486273A (en) * | 2021-12-27 | 2022-05-13 | 国网浙江省电力有限公司电力科学研究院 | Park flexibility reforms transform unit hydrogen and burns test device thoughtlessly |
| CN114646076A (en) * | 2022-03-18 | 2022-06-21 | 中国航空发动机研究院 | Adjustable cyclone assembly and multistage cyclone |
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|---|---|
| CN105674330B (en) | 2018-07-17 |
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