CN106287814B - A kind of ground gas turbine can burner of axial admission - Google Patents
A kind of ground gas turbine can burner of axial admission Download PDFInfo
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- CN106287814B CN106287814B CN201610861437.3A CN201610861437A CN106287814B CN 106287814 B CN106287814 B CN 106287814B CN 201610861437 A CN201610861437 A CN 201610861437A CN 106287814 B CN106287814 B CN 106287814B
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- burner
- inner liner
- burner inner
- combustion chamber
- natural gas
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Classifications
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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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
Abstract
The invention discloses a kind of ground gas turbine can burner of axial admission, including combustion chamber charge pipeline, casings, combustor exit section, casing upper end is connected with combustion chamber charge pipeline, and lower end is connected with combustor exit section, is equipped with burner inner liner in combustor exit section；Burner inner liner is connect by Imported gas pipeline with combustion chamber charge pipeline；Flame tube head top is equipped with natural gas combustion nozzle, and covers level-one swirler assembly, second cyclone component on natural gas combustion nozzle；Multiple natural gas spray orifices are being set on natural gas combustion nozzle；Primary holes is installed on the upside of burner inner liner middle section, the upper end of primary holes is provided with igniter mounting assembly；Blending hole is installed on the downside of burner inner liner middle section；The invention also discloses the internal structures of swirler assembly；Combustion chamber of the invention can be conducive to the Quick uniform mixing of fuel and air, and flame tube head forms stable recirculating zone, and improves the service life of combustion chamber entirety.
Description
Technical field
The invention belongs to ground gas turbine fields, and in particular to a kind of ground gas turbine single tube burning of axial admission
Room.
Background technique
Nearly ten years, the use value and application prospect of ground gas turbine are sufficiently demonstrate,proved by scholar both domestic and external
It is bright.And with the increasingly increase of energy consumption, distributed generation resource is also gradually paid attention to.Distributed power supply does not need far
Apart from equipment for power transmission and distribution, the energy can be utilized nearby, required to facilitate according to user and realized heat-electricity-refrigerate co-operation and have energy
The advantages of enough meeting the power and power demand of application circumstances.Ground gas turbine is that the chemical energy of fuel is changed into electricity
One of the quickest, stable and convenient energy conversion device with high power density of energy.Ground gas turbine is used
Fuel can be gaseous fuel or liquid fuel, wherein gaseous fuel is more with natural gas, liquid fuel include diesel oil and
Heavy oil etc..The development of ground gas turbine technology is with application by aircraft engine technology and theoretical development, ground combustion machine itself
Development, the development of related discipline technology and the excitation of the market demand of technology.
The research to ground gas-turbine combustion chamber domestic at present, the external more mature technology of Primary Reference, wherein institute
The fuel majority used is gaseous fuel.Gaseous fuel is different from liquid and solid fuel, and combustion process includes three phases:
(1) fuel mixes with air, the heating of (2) mixed gas is caught fire, (3) complete combustion chemistry reaction.Gas-turbine combustion chamber is most
It being burnt using diffusion type, mixed fuel gas is lighted by external incendiary source, it is de- fiery, flame-out in order to prevent, in addition to that should be
Outside the spouting velocity and flame propagation velocity of gas are adapted, it also should be taken that and constitute strong incendiary source, lean on itself
The heat of generation realizes the burning of continuous-stable.In order to improve the overall performance of ground gas turbine, combustion chamber is generally used
High-temperature alloy material is formed recirculating zone by the way of Multi-stage spiral and stablizes flame, formed more in conjunction with primary holes and blending hole
Uniform outlet temperature field, using reasonable type of cooling cooling flame tube wall surface, to guarantee the service life of burner inner liner.For ground
Face gas turbine, mostly uses greatly the combustion chamber of backflow ring shape and baffling form, and size is come relative to aero-gas turbine combustion chamber
It says longer, has many advantages, such as that and outlet temperature insensitive to blower outlet flow field is more uniform, and do not have to excessively consider burning
The labyrinth and weight of room.But reverse-flow can type combustor there is burner inner liner film-cooled heats big, turning additional pressure drops and
The disadvantages of non-uniform flow.Especially using natural gas as the ground gas turbine of fuel, due to the methane of the natural gas of different regions
Equal size is not quite similar, and has certain variation which results in parameters such as the calorific values of fuel, and this requires its combustion chambers to have
There is the fuel value adaptability of one fixed width.Above-mentioned spy should be fully considered in the design process of ground gas turbine combustion chamber
Point is designed, and is played its strong point, is overcome its weakness.Therefore, a kind of service life that can be improved combustion chamber entirety is designed, together
Quick uniform blending between Shi Shixian natural gas and air draught, and flame tube head forms stable recirculating zone, favorably
In the stable combustion chamber of flame combustion chamber be always those skilled in the art's technical problem to be solved.
Summary of the invention
In view of the problems of the existing technology the present invention, proposes a kind of ground gas turbine single tube burning of axial admission
Room can be conducive to the Quick uniform mixing of fuel and air, and flame tube head forms stable reflux using cyclone
Area is conducive to flame combustion chamber stabilization and improves the service life of combustion chamber entirety.
The invention is realized in this way a kind of ground gas turbine can burner of axial admission, including combustion chamber into
Feed channel, casing, combustor exit section, which is characterized in that the casing upper end is connected with combustion chamber charge pipeline, described
Casing lower end is connected with combustor exit section, is equipped with burner inner liner in the combustor exit section；The burner inner liner passes through
Imported gas pipeline is connect with combustion chamber charge pipeline；The flame tube head top is equipped with natural gas combustion nozzle, and
Level-one swirler assembly, second cyclone component on natural gas combustion nozzle are covered, and there are gaps；When burner inner liner expanded by heating
When, natural gas combustion nozzle is fixed, and burner inner liner can move up certain axial distance, to eliminate combustion chamber flame drum
Thermal stress；Multiple natural gas spray orifices are set on the natural gas combustion nozzle；Primary holes is installed on the upside of the burner inner liner middle section,
The upper end of primary holes is provided with igniter mounting assembly；Blending hole is installed on the downside of the burner inner liner middle section；Pass through natural gas
The Quick uniform blending between natural gas and head cyclone swirling eddy may be implemented in the setting of burner and swirler assembly,
Be conducive to the tissue of head burning；The design of primary holes can effectively be truncated head recirculating zone, and supplement head oxygen
Burning is participated in, so that the natural gas completely burned that nozzle sprays；The setting of blending hole can make air and mainstream high-temperature fuel gas
Uniformly mixing, and the temperature field for meeting turbine inlet is formed, combustor exit high temperature hotspot is reduced, to improve turbine life；
Multiple blending holes are circumferentially designed on burner inner liner, to adjust combustor exit temperature distribution；Level-one swirler assembly, second level
The air of swirler assembly outflow starts rapidly high speed rotation expansion outward, so that the pressure reduction of burner inner liner centre is caused,
Cause below gas flow counterflow supplement, to form stable recirculating zone in head of combustion chamber, the incendiary source to form stable is mentioned
Aerodynamic conditions are supplied.
Further, the spray orifice has certain angle with axial；Natural gas spurt on the natural gas combustion nozzle
Aperture is 0.3~3.5mm；Quantity is 6~20；The angle of natural gas spray orifice injection on the burner is 30 °~150 °.
Further, the combustion chamber charge pipeline passes through combustion chamber suction flange and combustion chamber charge section flange and machine
Casket connection；The combustor exit section is connect by turbine inlet flange and combustor exit flange with casing.
Further, the igniter mounting assembly can move on flame drum outer wall；In view of burner inner liner be heated it is swollen
Swollen and component processing and installation error have an igniter mounting assembly in the design of flame drum outer wall, and igniter mounting assembly can be with
Circumferentially there is certain mobile space in 360 ° of directions, thus the heated free wxpansion after facilitating igniter to install and burn.
Further, the flame tube head surface is equipped with flame tube head gaseous film control aperture, segment table in burner inner liner
Face is equipped with burner inner liner middle section gaseous film control aperture, and flame drum tail surface is equipped with burner inner liner contraction section gaseous film control aperture；
All standing gaseous film control aperture is devised on burner inner liner wall surface can be improved the burner inner liner service life.
Further, described to be cooperated with Imported gas pipeline by certain gap with flame tube head；It is described
Imported gas pipeline and combustion chamber charge pipeline by be welded to connect or flanged joint；Guarantee sealing, prevents combustion chamber
Pressure-air in admission line leaks out.
Further, the junction of the combustor exit section and flame drum tail be successively arranged burner inner liner support plate and
Turbine support plate；Entire Combustion chamber design is to be placed in turbine inlet support plate vertically, is fixed by burner inner liner support plate
Burner inner liner, wherein the burner inner liner support plate of tail portion is main stressed member, and the gravity of entire burner inner liner is by burner inner liner support plate
Turbine support plate is passed to bear；It is fixed between flame tube head and natural gas combustion nozzle by certain gap, to protect
Demonstrate,prove the heated rear freely expansion upwards of burner inner liner.
The invention also discloses a kind of ground gas turbine can burner of axial admission, the level-one cyclone group
Part, second cyclone component are biaxially cyclone combination, the combination of biradial cyclone or beveling radial swirler combination.
Further, the level-one cyclone and second cyclone can also merge into single-stage axial swirler.
Further, one is separately installed on the level-one swirler assembly, second cyclone component of the can burner
Grade swirler blades, second cyclone blade；The level-one swirler blades, second cyclone blade be prismatic blade formula or
Spirally, setting angle is 20 °~80 °, and lobe numbers are 6~30.
The beneficial effect of the present invention and the prior art is:
(1) by cyclone, primary holes and the setting for blending pore structure, so that two strands of head swirling eddy enters burner inner liner
After form shear layer, be conducive to the Quick uniform mixing of fuel and air, and flame tube head forms stable recirculating zone, has
Stablize conducive to flame combustion chamber；
(2) by design natural gas combustion nozzle structure and gas spraying hole number, angle, to realize that natural gas and head revolve
The Quick uniform blending between device swirling eddy is flowed, the tissue of head burning is conducive to；
(3) size and number of primary holes and blending hole is rationally designed.Jet stream is adjusted by changing the size of primary holes
Combustion centre recirculating zone is truncated in depth, shortens burning length.Adjust Jet Penetration Depth by changing blending hole size, and with master
Stream high-temperature fuel gas uniformly mixes, and forms the temperature field for meeting turbine inlet, combustor exit high temperature hotspot is reduced, to improve whirlpool
Take turns the service life
(4) by the design of vertical placing burning room, have reasonable mechanical stress and thermal stress force mechanism, guarantee
The load of burner inner liner and heated free wxpansion, thus the gravity of entire burner inner liner by support plate that flame drum tail welds come
It bears；And the expanded by heating of whole burner inner liner, it is flexible upwards, pass through moving freely between head burner and swirler assembly
To realize heated free wxpansion.
(5) design of burner inner liner wall surface has the cooling aperture of all standing, is formed about air film in the inner wall of burner inner liner, cold
But burner inner liner wall surface reduces burner inner liner wall surface temperature and temperature gradient, to improve the service life of combustion chamber entirety.
(6) two-stage axial swirler, air-flow rotation direction phase are designed to by level-one axial swirler and second level axial swirler
Instead, stronger air-flow shear layer can be formed, is conducive to fuel and is mixed with the quick of air, so that fuel gas and air is fast
Fast uniformly mixing, head of the mixed combustible gas body after high speed rotation in burner inner liner forms stable recirculating zone, plays stabilization
The effect of flame lights fuel gas by igniter and carries out stablizing burning；Or it merges as single-stage axial swirler, guarantor
It demonstrate,proves head reflux plot structure and under the blending permanence condition of natural gas, realization can burner's head construction is simple, thus
Reduce processing cost.
Detailed description of the invention
Fig. 1 is a kind of ground gas turbine can burner structural schematic diagram of axial admission of the present invention.
Fig. 2 is a kind of ground gas turbine combustion chamber rotation of ground gas turbine can burner of axial admission of the present invention
Flow device structural schematic diagram.
Wherein, 1- combustion chamber charge pipeline, 2- natural gas air inlet pipe road, 3- level-one swirler assembly, 4- second cyclone
Component, 5- natural gas combustion nozzle, 6- igniter install aperture member, 7- primary holes, 8- burner inner liner, 9- blending hole, the support of 10- burner inner liner
Plate, 11- turbine inlet support plate, 12- combustor exit section, 13- turbine inlet flange, 14- combustor exit flange, 15- fire
Flame cylinder contraction section gaseous film control aperture, 16- casing, 17- burner inner liner middle section gaseous film control aperture, 18- flame tube head air film are cold
But aperture, the combustion chamber 19- suction flange, 20- combustion chamber charge section flange, 21- level-one swirler blades, 22- second cyclone
Blade, 23- natural gas spray orifice.
Specific embodiment
Invention will be further explained below with reference to the drawings and examples..
As shown in Figure 1, a kind of ground gas turbine can burner of axial admission of the present invention includes combustion chamber inlet duct
Road 1, casing 16,16 upper end of casing described in combustor exit section 12 are connected with combustion chamber charge pipeline 1, under the casing 16
End is connected with combustor exit section 12, and the hollow end that three is surrounded is equipped with burner inner liner 8, and the burner inner liner 8 is mounted on combustion
Burn 12 upper end of room outlet section；The burner inner liner 8 is fixed by Imported gas pipeline 2 with combustion chamber charge pipeline 1；Institute
8 apical head of burner inner liner stated is equipped with natural gas combustion nozzle 5；One end of Imported gas pipeline 2 is connected with natural gas combustion nozzle 5
It connects；Level-one swirler assembly 3,4 sets of second cyclone component on natural gas combustion nozzle 5, and there are gaps；Described is natural
Multiple natural gas spray orifices 23 are set on gas burner 5, and natural gas spray orifice and axial admission air-flow have certain angle, gas spraying
The aperture in hole 23 between 0.3~3.5mm, quantity between 6~20 and injection angle between 30 °~150 °, very
Adjustment appropriate can be carried out according to required working condition to the structure type for being nozzle, so that the fuel for reaching injection is most
It mixes with air fastly uniformly.Primary holes 7 is installed on the upside of 8 middle section of burner inner liner, the upper end of primary holes 7 is provided with igniter installation group
Part 6；Blending hole 9 is installed on the downside of 8 middle section of burner inner liner；8 head surface of burner inner liner is equipped with flame tube head gaseous film control aperture
18, section surface is equipped with burner inner liner middle section gaseous film control aperture 17 in burner inner liner 8, and 8 tail surface of burner inner liner is equipped with burner inner liner
Contraction section gaseous film control aperture 15.
High pressure gas from centrifugal compressor enters single tube after spiral case is collected, from axial combustion chambers admission line 1
Behind combustion chamber, it is divided into 4 partial flowpafhs and enters combustion chamber flame drum, is to flow through level-one swirler assembly 3, second cyclone group respectively
Primary holes 7, blending hole 9 on part 4, burner inner liner and all standing gaseous film control aperture on burner inner liner wall surface, i.e. burner inner liner are received
Contracting section gaseous film control aperture 15, middle section surface are equipped with burner inner liner middle section gaseous film control aperture 17 and flame tube head air film is cold
But aperture 18 enters burner inner liner.Combustion chamber charge pipeline 1 passes through combustion chamber suction flange 19 and combustion chamber charge section flange 20
It is connect with casing 16；Combustor exit section 12 is connected by turbine inlet flange 13 and combustor exit flange 14 and casing 16
It connects, it is ensured that sealing prevents gas leakage；The Imported gas pipeline 2 on head is equipped with screw thread, convenient to connect with natural gas line,
It can guarantee to seal, prevent gas leakage, and Imported gas pipeline 2 and combustion chamber charge pipeline 1 are welded to connect or pass through flange
Connection guarantees sealing, prevents the pressure-air in combustion chamber charge pipeline from leaking out；Since entire gas turbine master-plan is wanted
It asks, entire Combustion chamber design is to be placed in turbine inlet support plate 11 vertically, it is therefore desirable to consider that its mechanical stress and heat are answered
The bearing member of power designs, mainly by the company of the level-one swirler assembly 3 on head, second cyclone component 4 and natural gas combustion nozzle 5
It connects and the burner inner liner support plate 10 of 8 tail portion of burner inner liner is fixed, wherein the burner inner liner support plate 10 of tail portion is main stress
Component, the gravity of entire burner inner liner pass to turbine support plate 11 by burner inner liner support plate to bear；Guarantee the load of burner inner liner
With heated free wxpansion；The gravity of entire burner inner liner is born by the support plate that flame drum tail welds；And whole flame
Cylinder expanded by heating, by between the burner and swirler assembly that head is designed be free to move axially guarantee its freely it is swollen
It is swollen.
Level-one swirler assembly 3,4 sets of second cyclone component on natural gas combustion nozzle 5 and have certain void space,
When burner inner liner expanded by heating, natural gas combustion nozzle 5 is fixed, and burner inner liner 8 can move up certain axial distance, thus
Eliminate the thermal stress of combustion chamber flame drum.In view of burner inner liner expanded by heating and component processing and installation error, in burner inner liner
The leading portion design in portion has igniter mounting assembly 6, and igniter mounting assembly 6 can move on 8 outer wall of burner inner liner, and
There is certain mobile space in 360 ° of directions of circumference, so that igniter be facilitated to install.
10%~40% or so air is entered from level-one swirler assembly 3, second cyclone component 4, is sprayed with burner
Natural gas is sufficiently mixed, and forms stable recirculating zone under the effect of two-stage vortex gas-flow, after igniter is lighted on wall surface,
Form stable combustion flame；10%~40% or so air enters main flow area from primary holes, is cut by the jet stream of primary holes
Broken end portion high temperature recirculation zone, to control reflux area length, and supplements fresh air, and the natural gas for spraying burner fires completely
It burns；10%~40% or so air enters from blending hole, adjusts Exit temperature distribution, so that its temperature field is met turbine design and want
It asks, to improve the service life of turbine；The air entered from all standing gaseous film control aperture on burner inner liner, in burner inner liner inner wall
Upper formation all standing air film, to improve the burner inner liner service life.
As shown in Fig. 2, the primary structure of head of combustion chamber is two-stage cyclones structure, including 3 He of level-one swirler assembly
Second cyclone component 4, level-one swirler assembly 3 and second cyclone component 4 can be the combination of biaxially cyclone, biradial
Cyclone combination or beveling radial swirler combination.Level-one swirler assembly 3 is mainly designed as axial swirler, second level eddy flow
Device assembly 4 is designed to axial swirler, and blade is spiral vane or prismatic blade, and the air inlet rotation direction phase of two-stage cyclones
Anti- or identical, two-stage cyclones air inlet forms shear layer, guarantees that natural gas is rapidly and uniformly mixed with air.From level-one cyclone
The air that component 3, second cyclone component 4 flow out starts rapidly high speed rotation expansion outward, to cause burner inner liner central part
Position pressure reduction, cause below gas flow counterflow supplement, to form stable recirculating zone in head of combustion chamber, stablize to be formed
Incendiary source provide aerodynamic conditions；Mixed gas burns rapidly after ignitor assembly 6 is lighted in head of combustion chamber, discharges heat,
Air-flow accelerates, and it is machine by thermal energy that from 12 high speed ejection of combustion chamber flame drum outlet section, the turbine after pushing combustion chamber, which does work,
Tool energy.
Level-one swirler assembly 3 can be processed by way of monoblock cast or machining, second cyclone component 4
It can be processed by modes such as whole machining, monoblock cast or welding, the components such as swirler blades can pass through weldering
It connects mode to be attached with wall surface inside and outside cyclone, passes through welded connecting between two-stage cyclones；Level-one swirler assembly 3, two
Grade swirler assembly 4 is connected by welding with combustion chamber flame drum 8 to be connect；Burner inner liner wall surface excessive internal heat flame cylinder contraction section gaseous film control is small
Hole 15, middle section surface, which are equipped with burner inner liner middle section gaseous film control aperture 17 and flame tube head gaseous film control aperture 18, to be led to
It crosses laser boring or mechanical perforation techniques is processed, primary holes 7 and the bigger hole of blending hole 9 can pass through machining
Mode is processed；By designing the size and number of reasonable primary holes and blending hole, so that reasonable primary holes be organized to penetrate
Recirculating zone can be truncated in flow depth degree and air inflow, primary holes jet stream, occur mainly in combustion chemistry reaction in recirculating zone.Tissue
Good reasonable blending hole Jet Penetration Depth and tolerance, form the temperature field for meeting turbine inlet requirement, to reduce high temperature hotspot.Fire
Flame cylinder support plate 10 is connect by welding manner with burner inner liner outlet section 12, so that burner inner liner entirety load-bearing is sat by support plate 10
In turbine inlet support plate 11.
Level-one swirler assembly 3 is axial swirler, eddy flow angle between 20 °~80 °, blade quantity is at 6~30
Between, these settings can make adjustment appropriate, and air-flow rotation direction can be for clockwise or counter-clockwise along airflow direction；Second level
Swirler assembly 4 is also configured as bladed axial swirler, blade angle degree between 20 °~80 ° and lobe numbers 6~
Adjustment appropriate can be made between 30.Level-one swirler assembly 3, the air-flow of second cyclone component 4 are oppositely oriented, can
To form stronger air-flow shear layer, be conducive to fuel and mixed with the quick of air, and two-stage cyclones blade can be straight
Vane type or helical blade type；Burner inner liner wall surface excessive internal heat flame cylinder contraction section gaseous film control aperture 15, middle segment table above burner inner liner 8
Face is equipped between burner inner liner middle section gaseous film control aperture 17 and flame tube head gaseous film control aperture 18 and incoming flow wall surface
Angle between 15 °~45 °, compound angle between 30 °~60 °, these settings carry out adjustment appropriate according to the actual situation, from
And reach best cooling effect.
It, can also be level-one swirler assembly 3 and two in engineering in the case where guaranteeing two-stage cyclones circulation area permanence condition
Grade swirler assembly 4 merge into single-stage axial swirler, by design single-stage cyclone swirling number, and and natural gas combustion nozzle into
Row matching, guarantees that head of combustion chamber forms stable Combustion Flow Field, to realize that structure is simple, and reduces its processing cost.
The air capacity of head of combustion chamber, including level-one swirler assembly 3,4 air inflow of second cyclone component and fire
The cooling air volume of flame cylinder head cooling hole 18 accounts for 12%~40% or so of import total air, and head of combustion chamber is generally inclined
Fuel-rich combustion, to guarantee there is preferable combustion stability.
Claims (10)
1. a kind of ground gas turbine can burner of axial admission, including combustion chamber charge pipeline (1), casing (16), combustion
It burns room outlet section (12), which is characterized in that described casing (16) upper end is connected with combustion chamber charge pipeline (1), the machine
Casket (16) lower end is connected with combustor exit section (12), is equipped with burner inner liner (8) in the combustor exit section (12)；It is described
Burner inner liner (8) connect with combustion chamber charge pipeline (1) by Imported gas pipeline (2)；The Imported gas pipeline
(2) top is equipped with natural gas combustion nozzle (5), and covers level-one swirler assembly (3) on natural gas combustion nozzle (5), second level
Swirler assembly (4), and on level-one swirler assembly (3), second cyclone component (4) and Imported gas pipeline (2)
Natural gas combustion nozzle (5) is fixed by certain clearance fit；Multiple gas sprayings are set on the natural gas combustion nozzle (5)
Hole (23)；It is equipped with primary holes (7) on the upside of described burner inner liner (8) middle section, the upper end of primary holes (7) is provided with igniter installation
Component (6)；Blending hole (9) are installed on the downside of described burner inner liner (8) middle section.
2. the ground gas turbine can burner of axial admission according to claim 1, which is characterized in that the day
Right gas spurt (23) and axial admission air-flow have certain angle；Natural gas spray orifice on the natural gas combustion nozzle (5)
(23) aperture is 0.3~3.5mm；Quantity is 6~20；The angle of the burner injection is 30 °~150 °.
3. the ground gas turbine can burner of axial admission according to claim 1, which is characterized in that the combustion
Room admission line (1) is burnt to connect by combustion chamber suction flange (19) and combustion chamber charge section flange (20) with casing (16)；
The combustor exit section (12) is connected by turbine inlet flange (13) and combustor exit flange (14) and casing (16)
It connects.
4. the ground gas turbine can burner of axial admission according to claim 1, which is characterized in that the point
Firearm mounting assembly (6) can move on burner inner liner (8) outer wall.
5. the ground gas turbine can burner of axial admission according to claim 1, which is characterized in that the fire
Flame cylinder (8) head surface is equipped with flame tube head gaseous film control aperture (18), and section surface is equipped with burner inner liner in burner inner liner (8)
Middle section gaseous film control aperture (17), burner inner liner (8) tail surface are equipped with burner inner liner contraction section gaseous film control aperture (15).
6. the ground gas turbine can burner of axial admission according to claim 1, which is characterized in that the day
Right gas inlet pipe road (2) is right-angle structure, and the Imported gas pipeline (2) and combustion chamber charge pipeline (1) pass through welding
Connection or flanged joint.
7. the ground gas turbine can burner of axial admission according to claim 1, which is characterized in that the combustion
The junction for burning room outlet section (12) and burner inner liner (8) tail portion is successively arranged burner inner liner support plate (10) and turbine support plate
(11), and can burner is vertical places.
8. the ground gas turbine can burner of axial admission according to claim 1, which is characterized in that described one
Grade swirler assembly (3), second cyclone component (4) are biaxially cyclone combination, the combination of biradial cyclone or beveling diameter
It is combined to cyclone.
9. the ground gas turbine can burner of axial admission according to claim 8, which is characterized in that described one
Grade swirler assembly (3) and second cyclone component (4) can also merge into single-stage axial swirler.
10. the ground gas turbine can burner of axial admission according to claim 8, which is characterized in that described
Level-one swirler blades (21), second cyclone are separately installed on level-one swirler assembly (3), second cyclone component (4)
Blade (22)；The level-one swirler blades (21), second cyclone blade (22) are prismatic blade formula or spiral, installation
Angle is 20 °~80 °, and lobe numbers are 6~30.
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| CN201610861437.3A CN106287814B (en) | 2016-09-29 | 2016-09-29 | A kind of ground gas turbine can burner of axial admission |
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| CN201610861437.3A CN106287814B (en) | 2016-09-29 | 2016-09-29 | A kind of ground gas turbine can burner of axial admission |
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| 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 |
| CN108758690B (en) * | 2018-05-31 | 2020-08-21 | 广州珠江天然气发电有限公司 | Combustion chamber for a gas turbine |
| TWI710697B (en) * | 2019-10-31 | 2020-11-21 | 國家中山科學研究院 | Micro turbine combustor structure |
| CN116336503A (en) * | 2023-03-27 | 2023-06-27 | 中国航发贵阳发动机设计研究所 | Combustion chamber unit body structure |
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| CN102095208A (en) * | 2009-12-14 | 2011-06-15 | 北京理工大学 | Adjustable miniature single pipe combustion chamber |
| CN203203033U (en) * | 2013-04-11 | 2013-09-18 | 中钢集团鞍山热能研究院有限公司 | Premix natural gas burner |
| CN203309935U (en) * | 2013-05-10 | 2013-11-27 | 哈尔滨东安发动机（集团）有限公司 | Single-liner type combustion gas turbine combustion chamber |
| CN204534569U (en) * | 2014-12-15 | 2015-08-05 | 中国燃气涡轮研究院 | A kind of take ethanol as can burner's gas generator of fuel |
| CN104896512B (en) * | 2015-05-11 | 2017-02-01 | 北京航空航天大学 | Low-emission natural gas combustion chamber with wide stable working range |
| CN105674330B (en) * | 2016-01-27 | 2018-07-17 | 南京航空航天大学 | A kind of ground gas turbine can burner device |
| CN206176457U (en) * | 2016-09-29 | 2017-05-17 | 南京航空航天大学 | Ground gas turbine can burner of axial admission |
-
2016
- 2016-09-29 CN CN201610861437.3A patent/CN106287814B/en not_active Expired - Fee Related
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| CN106287814A (en) | 2017-01-04 |
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