CN105674330B - A kind of ground gas turbine can burner device - Google Patents
A kind of ground gas turbine can burner device Download PDFInfo
- Publication number
- CN105674330B CN105674330B CN201610054669.8A CN201610054669A CN105674330B CN 105674330 B CN105674330 B CN 105674330B CN 201610054669 A CN201610054669 A CN 201610054669A CN 105674330 B CN105674330 B CN 105674330B
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- Prior art keywords
- inner liner
- burner inner
- level
- hole
- burner
- Prior art date
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Classifications
-
- 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
Abstract
The present invention provides a kind of ground gas turbine can burner devices, including casing and the burner inner liner being arranged in casing, the top of burner inner liner is equipped with external Imported gas pipeline, the neck location of burner inner liner is from top to bottom disposed with the opposite level-one beveling hole cyclone in direction of rotation and two level radial swirler, level-one chamfers hole cyclone structure in a circular table shape, and beveling hole cyclone is equipped with the through-hole of unicom side wall surface and bottom surface；Two-stage cyclones are respectively provided with Venturi tube；Burner inner liner side wall is from top to bottom equipped with ignitor assembly, primary holes, blending hole successively, and burner inner liner surface is equipped with several all standing gaseous film control apertures；Casing side wall is equipped with a pair of symmetrical air intlet, and flame drum tail is equipped with convergence and exports.By burner inner liner neck be arranged primary holes on two-stage cyclones and burner inner liner, blending hole, cooling aperture arrangement, can generate that rational Combustion Flow Field, outlet temperature and wall surface temperature distribution, burn room temperature liter, the raising burner inner liner service life.
Description
Technical field
The invention belongs to ground gas turbine field, be related to it is a kind of using natural gas as fuel, it is radial with twin-stage beveling
Cyclone, primary holes, the isostructural ground gas turbine can burner of blending hole and wall cooling hole.
Background technology
It is external, domestic nearly ten years, the use value of ground gas turbine is fully proved that application direction is
It is rich promising.With the increasingly increase of energy consumption, distributed generation resource is gradually paid attention to.Distributed power supply does not need
Remote conveying controller switching equipment requires to facilitate and realizes heat-electricity-refrigerate co-operation and meet special answer using the energy, according to user nearby
The advantages that with the power and power demand of environment.And ground gas turbine is that the chemical energy of fuel is changed into the fastest of electric energy
Speed, one of the energy conversion device for stablizing and easily having high power density.Ground gas turbine can use gas combustion
Material and liquid fuel, wherein gaseous fuel is more with natural gas, and liquid fuel includes diesel oil and heavy oil etc..Ground gas turbine skill
The development of art developed with application by aircraft engine technology and theory, the developing of ground combustion machine self-technique, related discipline skill
The development of art and the excitation of the market demand.
The domestic research to ground gas-turbine combustion chamber at present, the external more mature technology of Primary Reference.Gas fires
Material is different from liquid and solid fuel, and combustion process includes three phases：Fuel mixes with air, mixed gas heating is caught fire and
Complete combustion chemistry reaction.Gas-turbine combustion chamber mostly uses greatly diffusion type burning, and mixed fuel gas is to lean on external point
Burning things which may cause a fire disaster is lighted, de- fiery, flame-out in order to prevent, other than the spouting velocity and flame propagation velocity that should ensure that gas are adapted, also
It should be taken that and constitute strong incendiary source, the heat generated by itself realizes the burning of continuous-stable.In order to improve ground
The overall performance of face gas turbine, combustion chamber are generally used high-temperature alloy material, are formed reflux by the way of Multi-stage spiral
Area stablizes flame, forms more uniform outlet temperature field in conjunction with primary holes and blending hole, is cooled down using the rational type of cooling
Burner inner liner wall surface, to ensure the service life of burner inner liner.For ground gas turbine, backflow ring shape and baffling form are mostly used greatly
Combustion chamber, size is longer for aero-gas turbine combustion chamber, has the outlet and insensitive to blower outlet flow field
The advantages that temperature is more uniform, and labyrinth and weight without excessively considering combustion chamber.But reverse-flow can type combustor exists
The shortcomings of big burner inner liner film-cooled heat, turning additional pressure drops and non-uniform flow.Especially using natural gas as the ground of fuel
Face gas turbine, since the methane equal size of the natural gas of different regions is not quite similar, which results in the ginsengs such as the calorific value of fuel
Number has certain variation, and this requires its combustion chambers should be with the fuel value adaptability of one fixed width.In ground gas wheel
It should fully consider that These characteristics are designed, and play its strong point in the design process of machine combustion chamber, overcome its weakness.
Invention content
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 single tube combustion
Chamber device is burnt, rational Combustion Flow Field, Exit temperature distribution, wall surface temperature distribution and burning room temperature liter etc. can be generated, met
Design requirement.
Technical solution：A kind of ground gas turbine can burner device, including casing and the flame that is arranged in casing
Cylinder, the top of the burner inner liner are equipped with external Imported gas pipeline, and the neck location of the burner inner liner is from top to bottom successively
It is provided with level-one beveling hole cyclone and two level radial swirler, the level-one beveling hole cyclone and the two level radial vortex
The direction of rotation of device is opposite；The level-one chamfers hole cyclone structure in a circular table shape and beveling hole cyclone is equipped with unicom
The through-hole of side wall surface and bottom surface；The level-one beveling hole cyclone connects the first Venturi tube, the two level radial swirler connection
Second Venturi tube；The burner inner liner side wall is from top to bottom equipped with igniter mounting assembly, primary holes, blending hole, the fire successively
Flame cylinder surface is equipped with more than one evenly distributed all standing gaseous film control aperture；The casing side wall is equipped with a pair of symmetrical empty
Gas import, the flame drum tail are equipped with outlet.
Further, further include end cap, casing flange；The end cap, the machine is bolted at the top of the casing
Corrugated sheet is equipped between casket and the end cap；The tail portion of the burner inner liner is equipped with support plate, and the support plate passes through casing method
Orchid supports the burner inner liner.
Further, the Imported gas pipeline is located at one end of burner inner liner equipped with natural gas combustion nozzle.
Advantageous effect：The present invention provides a kind of ground gas turbine can burner devices, pass through the neck in burner inner liner
Portion is provided with the level-one beveling hole cyclone in several beveling holes, two level radial swirler, and air is entered from two-stage cyclones, with
The natural gas that burner sprays is sufficiently mixed, and stable recirculating zone is formed under the effect of two-stage vortex gas-flow, through point on wall surface
After firearm is lighted, stable combustion flame is formed；Air enters main flow area from primary holes, and head is blocked by the jet stream of primary holes
Portion high temperature recirculation zone to control reflux area length, and supplements fresh air, the natural gas completely burned for making burner spray；From
The air that blending hole enters can adjust Exit temperature distribution, improve the service life of turbine；Enter the air in burner inner liner from aperture
All standing air film is formed on burner inner liner internal face, improves the burner inner liner service life.
Description of the drawings
Fig. 1 is the structural diagram of the present invention；
Fig. 2 is ground gas turbine combustion chamber hydrocyclone structure schematic diagram；
Wherein, Fig. 2 a are the sectional view of combustion chamber cyclone, and Fig. 2 b are the structural schematic diagram of level-one cyclone, and Fig. 2 c are two
The structural schematic diagram of grade cyclone；
Fig. 3 is that level-one chamfers hole cyclone tomograph；
Wherein, Fig. 3 a and Fig. 3 b are the tomograph of level-one beveling hole cyclone.
Specific implementation mode
The present invention will be further described below with reference to the drawings.
As shown in Figure 1, a kind of ground gas turbine can burner device, including casing 16 and it is arranged in casing 16
The top of burner inner liner, burner inner liner is equipped with external Imported gas pipeline 1, and the neck location of burner inner liner is from top to bottom set gradually
There are level-one beveling hole cyclone 4 and two level radial swirler 5, level-one to chamfer the rotation of hole cyclone 4 and two level radial swirler 5
Direction is on the contrary, the through-hole institute on 4 bottom surface of helical blade range covering level-one beveling hole cyclone of two level radial swirler 5 is in place
It sets；Level-one chamfers 4 structure in a circular table shape of hole cyclone, and beveling hole cyclone is equipped with the logical of unicom side wall surface and bottom surface
Hole；Level-one chamfers hole cyclone 4 and connects the first Venturi tube 19, and two level radial swirler 5 connects the second Venturi tube 20；Burner inner liner side
Wall is from top to bottom equipped with igniter mounting assembly 17, primary holes 15, blending hole 13 successively, and burner inner liner surface is equipped with more than one
The all standing gaseous film control aperture 7 of even arrangement；16 side wall of casing is equipped with a pair of symmetrical air intlet 14, and flame drum tail is equipped with
Outlet 12.Further include end cap 2, casing flange 11；End cap 2 is bolted in 16 top of casing, is set between casing 16 and end cap 2
There is corrugated sheet 3；The tail portion of burner inner liner is equipped with support plate 10, and support plate 10 supports burner inner liner by casing flange 11.Natural gas
One end that inlet pipeline 1 is located at burner inner liner is equipped with natural gas combustion nozzle 18.
Embodiment：
The ground gas turbine can burner that the present invention designs chamfers hole cyclone 4, two by natural gas combustion nozzle 18, level-one
Grade radial swirler 5, casing 16 and burner inner liner composition, burner inner liner is by the middle part of flame tube head 6, burner inner liner 8 and flame drum tail 9
Composition.High pressure gas from centrifugal compressor is divided into five after monosymmetric air intlet 14 enters can burner
Partial flowpafh enters combustion chamber flame drum, is to flow through level-one beveling hole cyclone 4, two level radial swirler 5, on burner inner liner respectively
Primary holes 15, all standing gaseous film control aperture 7 on blending hole 13 and burner inner liner wall surface.End cover of combustion chamber 2 and combustion gas wheel
Machine casing 16 is bolted；The Imported gas pipeline 1 on head is tapped, convenient to be connect with natural gas line, can be with
Ensure sealing, prevent gas leakage, and Imported gas pipeline 1 is welded to connect with end cover of combustion chamber 2, ensures sealing, prevent combustion chamber
Interior combustion gas leaks out；Due to entire gas turbine general design requirement, entire Combustion chamber design is vertical places, it is therefore desirable to be examined
The bearing member design for considering its mechanical stress and thermal stress, mainly by the burner inner liner support plate 10 of the corrugated sheet on head 3 and tail portion
It fixes, the burner inner liner support plate 10 of wherein tail portion is main stressed member, the gravity of entire burner inner liner is supported by burner inner liner
Plate passes to casing flange 11 to bear；And level-one is chamfer hole cyclone 4, two level radial vortex by corrugated sheet 3 by bolt
Device 5, casing 16 are fixedly connected together with end cover of combustion chamber 2, and corrugated sheet 3 is sleeved on natural gas combustion nozzle and has certain gap
Space, and have certain axial distance between corrugated sheet 3 and end cover of combustion chamber 2, when burner inner liner expanded by heating, burner inner liner
Support plate 10 is fixed, and corrugated sheet 3 can move up certain axial distance, to eliminate the heat of combustion chamber flame drum
Stress.In view of burner inner liner expanded by heating and component processing and installation error, 8 leading portion is designed with igniter in the middle part of burner inner liner
Mounting assembly 17, igniter mounting assembly 17 can have certain mobile space with circumferentially 360 ° of directions, to facilitate igniting
Device is installed.
Most of air enters from primary holes 15, blending hole 13 and level-one beveling hole cyclone 4, two level radial swirler 5
Burner inner liner, for tissue burning and air blending, surplus air enters combustion chamber from wall surface all standing cooling aperture 7, for cold
But burner inner liner wall surface.The primary structure of head of combustion chamber is two-stage cyclones structure, including level-one beveling 4 He of hole swirler assembly
Two level radial vortex device assembly 5, two-stage cyclones are respectively provided with the first Venturi tube 19, the second Venturi tube 20, and level-one chamfers Kong Xuan
It flowing device 4 and connects the first Venturi tube 19, two level radial swirler 5 connects the second Venturi tube 20, and Venturi tube is both designed as first shrinking, after
Expansion accelerates flowing to ensure air-flow in Venturi tube, prevents from being tempered.Level-one beveling hole cyclone 4 is designed to multiple bevelings
Pore structure, two level radial vortex 5 are designed to radial swirler, and blade is spiral vane, and the air inlet of two-stage cyclones
It is oppositely oriented, it is mutually blended in 19 exit of the first Venturi tube, forms shear layer, ensure that natural gas is rapidly and uniformly mixed with air
It closes.The air flowed out from level-one beveling hole cyclone 4, two level radial swirler 5 flows out the first Venturi tube 19, the second Venturi tube 20
After start rapid high speed rotation expansion outward, to cause the pressure reduction of burner inner liner centre, cause below gas flow counterflow come
Supplement, to form stable recirculating zone in head of combustion chamber, the incendiary source to form stable provides aerodynamic conditions；Mixed gas exists
Head of combustion chamber burns rapidly after ignitor assembly 17 is lighted, and discharges heat, and air-flow accelerates, from combustion chamber flame drum outlet 12
High speed sprays, and pushes the turbine acting behind combustion chamber, is mechanical energy by thermal energy.
Level-one beveling hole cyclone 4 can be processed by way of monoblock cast or mechanical processing, two level radial vortex
Device 5 can be processed by modes such as whole mechanical processing, monoblock cast or welding, and the components such as swirler blades can pass through
Welding manner is attached with cyclone baffle and Venturi tube, by being welded to connect between two-stage cyclones；Level-one chamfers Kong Xuan
Flow device 4, two level radial swirler 5 is connected by flange by bolt with corrugated sheet 3, end cover of combustion chamber 2 and combustion box 16
It connects；By being welded to connect between 8 and flame drum tail 9 in the middle part of flame tube head 6, burner inner liner；All standing on burner inner liner wall surface
Cooling aperture 7 is processed by laser drilling, and the bigger hole such as primary holes 15 and blending hole 13 can pass through machinery
The mode of processing is processed.Burner inner liner support plate 10 is connect by welding manner with flame drum tail 9 so that burner inner liner is whole
Load-bearing is sitting on casing by support plate 10 on subsequent flange 11.
The aperture of natural gas combustion nozzle 18 between 0.6~1.5mm, quantity between 6~20 and burner injection angle
Degree is between 30 °~120 °, and even the structure type of nozzle can carry out adjustment appropriate according to required working condition,
Fuel to reach injection is uniformly mixed with air as early as possible.Level-one chamfers the 23 eddy flow angle of beveling hole of hole cyclone 4 at 30 °
Between~80 °, the quantity in hole 23 is chamfer between 6~20, can make adjustment appropriate, air-flow rotation direction is along airflow direction
Can be clockwise or counter-clockwise, the shrinkage expansion section for chamferring the first Venturi tube 19 that hole cyclone 4 is connect with level-one can have
Effect prevents from being tempered；Two level radial swirler 5 is designed as radial blade formula cyclone, and swirler blades 24 are welded on two level eddy flow
On device baffle 22,24 setting angle of swirler blades between 30 °~80 °, 24 number of swirler blades between 10~25,
Adjustment appropriate can be made.The air-flow of two-stage cyclones is oppositely oriented, can form stronger air-flow shear layer, be conducive to
Fuel is mixed with the quick of air；All standing gaseous film control above flame tube head 6, burner inner liner middle part 8 and flame drum tail 9
Angle between aperture 7 and incoming wall surface carries out adjustment appropriate between 15 °~45 °, according to actual conditions, to reach most
Good cooling effect.
The air capacity of head of combustion chamber accounts for 12%~30% or so of import total air, including level-one chamfers hole eddy flow
The cooling air volume of the cooling aperture 7 of the air inflow of device 4 and two level radial swirler 5, flame tube head；Head of combustion chamber is overall
For inclined fuel-rich combustion, to ensure there is preferable combustion stability.
10%~30% or so air is entered from two-stage cyclones, and the natural gas sprayed with burner is sufficiently mixed,
Stable recirculating zone is formed under the effect of two-stage vortex gas-flow, after igniter is lighted on wall surface, forms stable combustion flame；
15%~40% or so air enters main flow area from primary holes, and head high temperature recirculation zone is blocked by the jet stream of primary holes,
To control reflux area length, and fresh air is supplemented, the natural gas completely burned for making burner spray；15%~40% or so
Air enters from blending hole, adjusts Exit temperature distribution, so that its temperature field is met turbine design requirement, to improve the longevity of turbine
Life；Surplus air enters from all standing gaseous film control aperture on burner inner liner, and all standing air film is formed on burner inner liner internal face,
To improve the burner inner liner service life；The high temperature and high speed combustion gas of combustor exit enters turbine, pushes turbine acting.
Finally it should be noted that:Above example is merely to illustrate the technical solution of the application rather than to its protection domain
Limitation, have usually intellectual in technical field of the present invention, without departing from the spirit and scope of the present invention, when can make
Various changes and retouching.Therefore, the scope of protection of the present invention is defined by those of the claims.
Claims (2)
1. a kind of ground gas turbine can burner device, it is characterised in that：Including casing (16) and it is arranged in casing (16)
Interior burner inner liner, the top of the burner inner liner are equipped with external Imported gas pipeline (1), the neck location of the burner inner liner by
Level-one beveling hole cyclone (4) and two level radial swirler (5) are disposed under above, the level-one chamfers hole cyclone
(4) opposite with the direction of rotation of two level radial swirler (5)；Level-one beveling hole cyclone (4) structure in a circular table shape,
And beveling hole cyclone is equipped with the through-hole of unicom side wall surface and bottom surface；The level-one beveling hole cyclone (4) connects first
Venturi tube (19), the two level radial swirler (5) connect the second Venturi tube (20)；The burner inner liner side wall is from top to bottom successively
Equipped with igniter mounting assembly (17), primary holes (15), blending hole (13), the burner inner liner surface is equipped with more than one and uniformly arranges
The all standing gaseous film control aperture (7) of row；Casing (16) side wall is equipped with a pair of symmetrical air intlet (14), the flame
Cylinder tail portion is equipped with outlet (12)；
Further include end cap (2), casing flange (11)；The end cap (2), the machine is bolted at the top of the casing (16)
Corrugated sheet (3) is equipped between casket (16) and the end cap (2)；The tail portion of the burner inner liner is equipped with support plate (10), the branch
Fagging (10) supports the burner inner liner by casing flange (11).
2. a kind of ground gas turbine can burner device according to claim 1, it is characterised in that：The natural gas
One end that inlet pipeline (1) is located at burner inner liner is equipped with natural gas combustion nozzle (18).
Priority Applications (1)
| 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 |
Applications Claiming Priority (1)
| 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105674330A CN105674330A (en) | 2016-06-15 |
| CN105674330B true CN105674330B (en) | 2018-07-17 |
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| CN201610054669.8A Expired - Fee Related CN105674330B (en) | 2016-01-27 | 2016-01-27 | A kind of ground gas turbine can burner device |
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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 |
| CN106287814B (en) * | 2016-09-29 | 2019-04-19 | 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 |
| 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 |
| 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 |
| CN107101225B (en) * | 2017-05-16 | 2023-01-10 | 新奥能源动力科技（上海）有限公司 | Swirl structure of combustor, combustor 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 |
| 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 |
| 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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| CN105674330A (en) | 2016-06-15 |
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