CN106287814A - 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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- CN106287814A CN106287814A CN201610861437.3A CN201610861437A CN106287814A CN 106287814 A CN106287814 A CN 106287814A CN 201610861437 A CN201610861437 A CN 201610861437A CN 106287814 A CN106287814 A CN 106287814A
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- inner liner
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- assembly
- cyclone
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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
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention discloses the ground gas turbine can burner of a kind of axial admission, including combustion chamber charge pipeline, casing, combustor exit section, casing upper end connects combuster admission line, and lower end connects combuster outlet section, and combustor exit section is provided with burner inner liner；Burner inner liner is connected with combustion chamber charge pipeline by Imported gas pipeline；Burner inner liner apical head is provided with natural gas combustion nozzle, and be enclosed within natural gas combustion nozzle one-level swirler assembly, second cyclone assembly；Natural gas combustion nozzle arranges multiple natural gas spray orifice；Being provided with primary holes on the upside of burner inner liner stage casing, the upper end of primary holes is provided with lighter mounting assembly；Burner inner liner is provided with blending hole on the downside of stage casing；The invention also discloses the internal structure of swirler assembly；The combustor of the present invention can be conducive to the Quick uniform of fuel and air to mix, and burner inner liner head forms stable recirculating zone, and improves the service life that combustor is overall.
Description
Technical field
The invention belongs to ground gas turbine field, be specifically related to the ground gas turbine single tube burning of a kind of axial admission
Room.
Background technology
Nearly ten years, use value and the application prospect of ground gas turbine is fully demonstrate,proved by scholar both domestic and external
Bright.And along with the increase day by day of energy resource consumption, distributed power source is the most gradually paid attention to.Distributed power supply need not far
Distance equipment for power transmission and distribution, it is possible to utilize the energy nearby, requires conveniently realize heat-electricity-refrigerate co-operation and possess energy according to user
Enough meet the power of application circumstances and the advantage of need for electricity.Ground gas turbine is that the chemical energy of fuel is changed into electricity
One of energy conversion device with high power density the most quickly, stably and easily of energy.Ground gas turbine is used
Fuel can be gaseous fuel or liquid fuel, wherein gaseous fuel is with natural gas for many, liquid fuel include diesel oil and
Heavy oil etc..The development of ground gas turbine technology and application are developed by aircraft engine technology and theory, ground combustion machine self
The development of technology, the development of related discipline technology and the excitation of the market demand.
The most domestic research to ground gas-turbine combustion chamber, the technology that Primary Reference is the most ripe, Qi Zhongsuo
The fuel majority used is gaseous fuel.Gaseous fuel is different from liquid and solid fuel, and combustion process comprises three phases:
(1) fuel mixes with air, the heating of (2) mixed gas is caught fire, (3) complete combustion chemistry and react.Gas-turbine combustion chamber is most
Employing diffusion type burns, and mixed fuel gas is that outer portion incendiary source is lighted, and for anti-anti-avulsion fire, stops working, except being
Outside the spouting velocity of gas and flame propagation velocity adapt, also should be taken that the strong incendiary source of composition, by self
The heat produced realizes the burning of continuous-stable.In order to improve the overall performance of ground gas turbine, its combustor typically uses
High-temperature alloy material, uses the mode of Multi-stage spiral to form recirculating zone and stablizes flame, is formed more in conjunction with primary holes and blending hole
Uniform outlet temperature field, uses rational type of cooling cooling flame tube wall surface, thus ensures the life-span of burner inner liner.For ground
Face gas turbine, uses backflow annular and the combustor of baffling form mostly, and size is come relative to aero-gas turbine combustor
Say longer, there is the advantages such as and outlet temperature insensitive to blower outlet flow field is the most uniform, and need not too consider burning
The labyrinth of room and weight.But reverse-flow can type combustor also exists, and burner inner liner film-cooled heat is big, turning additional pressure drops and
The shortcomings such as non-uniform flow.The especially ground gas turbine with natural gas as fuel, due to the methane of the natural gas of different regions
Equal size is not quite similar, and the parameter such as calorific value which results in fuel has certain change, and this just requires that its combustor should have
There is the fuel value adaptability of one fixed width.Above-mentioned spy should be taken into full account in the design process of ground gas turbine combustor
Point is designed, and plays its strong point, overcomes its weakness.Therefore, design a kind of can raising the service life that combustor is overall, same
Quick uniform between Shi Shixian natural gas and air draught blends, and burner inner liner head forms stable recirculating zone, favorably
It is always the technical barrier that those skilled in the art are to be solved in the combustor that flame combustion chamber is stable.
Summary of the invention
The present invention is directed to the problem that prior art exists, it is proposed that the ground gas turbine single tube burning of a kind of axial admission
Room, it is possible to be conducive to the Quick uniform mixing of fuel and air, and burner inner liner head utilizes cyclone to form stable backflow
District, beneficially flame combustion chamber are stable and improve the service life that combustor is overall.
The present invention is achieved in that the ground gas turbine can burner of a kind of axial admission, enters including combustor
Feed channel, casing, combustor exit section, it is characterised in that described casing upper end connects combuster admission line, described
Casing lower end connects combuster outlet section, and described combustor exit section is provided with burner inner liner；Described burner inner liner passes through
Imported gas pipeline is connected with combustion chamber charge pipeline；Described burner inner liner apical head is provided with natural gas combustion nozzle, and
The one-level swirler assembly that is enclosed within natural gas combustion nozzle, second cyclone assembly, and there is space；When burner inner liner expanded by heating
Time, natural gas combustion nozzle maintains static, and burner inner liner can move up certain axial distance, thus eliminates combustion chamber flame drum
Thermal stress；Multiple natural gas spray orifice is set on described natural gas combustion nozzle；On the upside of described burner inner liner stage casing, primary holes is installed,
The upper end of primary holes is provided with lighter mounting assembly；On the downside of described burner inner liner stage casing, blending hole is installed；Pass through natural gas
Burner and the setting of swirler assembly, it is possible to achieve the Quick uniform between natural gas and head cyclone swirling eddy blends,
Be conducive to the tissue of head burning；Head recirculating zone can effectively be blocked by the design of primary holes, and supplementary head oxygen
Participate in burning so that the natural gas of nozzle ejection burns completely；The setting of blending hole is so that air and main flow high-temperature fuel gas
Uniformly mixing, and form the temperature field meeting turbine inlet, reduce combustor exit high temperature hotspot, thus improve turbine life；
Burner inner liner circumferentially designs multiple blending hole, thus regulates combustor exit temperature distribution；One-level swirler assembly, two grades
The air that swirler assembly flows out starts the most outwards high speed rotating expansion, thus causes burner inner liner centre pressure to reduce,
Cause gas flow counterflow below to supplement, thus form stable recirculating zone at head of combustion chamber, carry for forming stable incendiary source
Supply aerodynamic conditions.
Further, described spray orifice with axially there is certain angle；Natural gas spurt on described natural gas combustion nozzle
Aperture is 0.3～3.5mm；Quantity is 6～20；The angle of the natural gas spray orifice injection on described burner is 30 °～150 °.
Further, described combustion chamber charge pipeline is by combustor suction flange and combustion chamber charge section flange and machine
Casket connects；Described combustor exit section is connected with casing by turbine inlet flange and combustor exit flange.
Further, described lighter mounting assembly can move on burner inner liner outer wall；It is heated in view of burner inner liner swollen
Swollen and component processing and alignment error, have lighter mounting assembly in the design of burner inner liner outer wall, and lighter mounting assembly is permissible
Circumferentially all there is certain mobile space in 360 ° of directions, thus facilitate the free wxpansion of being heated after lighter installation and burning.
Further, described burner inner liner head surface is provided with burner inner liner head gaseous film control aperture, segment table in burner inner liner
Face is provided with burner inner liner stage casing gaseous film control aperture, and flame drum tail surface is provided with burner inner liner contraction section gaseous film control aperture；
Burner inner liner wall devises all standing gaseous film control aperture and can improve the burner inner liner life-span.
Further, described coordinated by certain gap with Imported gas pipeline with burner inner liner head；Described
Imported gas pipeline and combustion chamber charge pipeline by being welded to connect or Flange joint；Ensure to seal, prevent combustor
Pressure-air in admission line spills.
Further, the junction of described combustor exit section and flame drum tail be sequentially provided with burner inner liner gripper shoe and
Turbine support plate；Whole Combustion chamber design, for be vertically placed in turbine inlet gripper shoe, is fixed by burner inner liner gripper shoe
Burner inner liner, wherein the burner inner liner gripper shoe of afterbody is main stressed member, and the gravity of whole burner inner liner is by burner inner liner gripper shoe
Pass to turbine support plate bear；It is fixed by certain gap between burner inner liner head and natural gas combustion nozzle, thus protects
Card burner inner liner freely upwards expands after being heated.
The invention also discloses the ground gas turbine can burner of a kind of axial admission, described one-level a cluster cyclone
Part, second cyclone assembly are the combination of biaxially cyclone, biradial cyclone combines or radial swirler combination of cutting sth. askew.
Further, described one-level cyclone and second cyclone can also merge into single-stage axial swirler.
Further, the one-level swirler assembly of described can burner, second cyclone assembly are separately installed with one
Level swirler blades, second cyclone blade；Described one-level swirler blades, second cyclone blade be prismatic blade formula or
Spirally, setting angle is 20 °～80 °, and lobe numbers is 6～30.
The present invention has the beneficial effects that with prior art:
(1) by cyclone, primary holes and the setting of blending hole structure so that two strands of swirling eddies of head enter shape after burner inner liner
Become the Quick uniform mixing of shear layer, beneficially fuel and air, and burner inner liner head forms stable recirculating zone, is conducive to
Flame combustion chamber is stable；
(2) by design natural gas combustion nozzle structure and gas spraying hole number, angle, thus natural gas and head cyclone are realized
Quick uniform between swirling eddy blends, beneficially the tissue of head burning；
(3) appropriate design primary holes and the size and number of blending hole.Jet Penetration Depth is regulated by the size changing primary holes,
Block combustion centre recirculating zone, shorten burning length.Regulate Jet Penetration Depth by changing blending hole size, and with main flow high temperature
Combustion gas uniformly mixes, and forms the temperature field meeting turbine inlet, reduces combustor exit high temperature hotspot, thus improves turbine life
(4) by the design of vertical placing burning room, possessed rational mechanical stress and thermal stress force mechanism, it is ensured that flame
The load of cylinder and the free wxpansion being heated, the gripper shoe that the gravity of the most whole burner inner liner is welded by flame drum tail is held
It is subject to；And the expanded by heating of entirety burner inner liner, upwards stretch, by moving freely between head burner and swirler assembly
Realization is heated free wxpansion.
(5) burner inner liner wall is designed with all standing cooling aperture, and the internal face at burner inner liner is formed about air film, cold
But burner inner liner wall, reduces flame tube wall surface temperature and thermograde, thus improves the service life that combustor is overall.
(6) it is designed to two-stage axial swirler, air-flow rotation direction phase by one-level axial swirler and two grades of axial swirlers
Instead, quickly mixing of stronger air-flow shear layer, beneficially fuel and air can be formed so that fuel gas and air fast
Speed uniformly mixing, mixed combustible gas body forms stable recirculating zone at the head of burner inner liner after high speed rotating, serves stable
The effect of flame, lights fuel gas by lighter and carries out stable burning；Or merge as single-stage axial swirler, guarantor
Card head recirculating zone structure and with under the blending permanence condition of natural gas, it is achieved can burner's head construction is simple, thus
Reduce processing cost.
Accompanying drawing explanation
Fig. 1 is the ground gas turbine can burner structural representation of a kind of axial admission of the present invention.
Fig. 2 is the ground gas turbine combustor rotation of the ground gas turbine can burner of a kind of axial admission of the present invention
Stream device structural representation.
Wherein, 1-combustion chamber charge pipeline, 2-natural gas admission line, 3-one-level swirler assembly, 4-second cyclone
Assembly, 5-natural gas combustion nozzle, 6-lighter installing hole assembly, 7-primary holes, 8-burner inner liner, 9-blending hole, 10-burner inner liner supports
Plate, 11-turbine inlet gripper shoe, 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 stage casing gaseous film control aperture, 18-burner inner liner head air film is cold
But aperture, 19-combustor suction flange, 20-combustion chamber charge section flange, 21-one-level swirler blades, 22-second cyclone
Blade, 23-natural gas spray orifice.
Detailed description of the invention
With embodiment, invention is further illustrated below in conjunction with the accompanying drawings.
As it is shown in figure 1, the ground gas turbine can burner of a kind of axial admission of the present invention includes combustion chamber inlet duct
Road 1, casing 16, casing 16 upper end described in combustor exit section 12 connects combuster admission line 1, described casing 16 times
End connects combuster outlet section 12, and the hollow end that three is surrounded is provided with burner inner liner 8, and described burner inner liner 8 is arranged on combustion
Burn outlet section 12 upper end, room；Described burner inner liner 8 is fixed with combustion chamber charge pipeline 1 by Imported gas pipeline 2；Institute
Burner inner liner 8 apical head stated is provided with natural gas combustion nozzle 5；One end of Imported gas pipeline 2 is connected with natural gas combustion nozzle 5
Connect；One-level swirler assembly 3, second cyclone assembly 4 are enclosed within natural gas combustion nozzle 5, and there is space；Described is natural
Arranging multiple natural gas spray orifice 23 on gas burner 5, 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
Suitable adjustment can be carried out according to required duty to the version being nozzle, thus reach the fuel of injection to the greatest extent
Mix homogeneously with air soon.Being provided with primary holes 7 on the upside of burner inner liner 8 stage casing, the upper end of primary holes 7 is provided with lighter installation group
Part 6；Burner inner liner 8 is provided with blending hole 9 on the downside of stage casing；Burner inner liner 8 head surface is provided with burner inner liner head gaseous film control aperture
18, in burner inner liner 8, section surface is provided with burner inner liner stage casing gaseous film control aperture 17, and burner inner liner 8 tail surface is provided with burner inner liner
Contraction section gaseous film control aperture 15.
From centrifugal compressor gases at high pressure through spiral case collect after, enter single tube from axial combustion chambers admission line 1
After combustor, it is divided into 4 partial flowpafh to enter combustion chamber flame drum, is to flow through one-level swirler assembly 3, second cyclone group respectively
The all standing gaseous film control aperture on primary holes 7, blending hole 9 and burner inner liner wall on part 4, burner inner liner, i.e. burner inner liner are received
Contracting section gaseous film control aperture 15, middle section surface are provided with burner inner liner stage casing gaseous film control aperture 17 and burner inner liner head air film is cold
But aperture 18 enters burner inner liner.Combustion chamber charge pipeline 1 is by combustor suction flange 19 and combustion chamber charge section flange 20
It is connected with casing 16；Combustor exit section 12 is connected with casing 16 by turbine inlet flange 13 and combustor exit flange 14
Connect, it is ensured that seal, prevent gas leakage；The Imported gas pipeline 2 of head is provided with screw thread, is conveniently connected with natural gas line,
Can ensure that sealing, prevent gas leakage, and Imported gas pipeline 2 is welded to connect with combustion chamber charge pipeline 1 or passes through flange
Connect, it is ensured that seal, prevent the pressure-air in combustion chamber charge pipeline from spilling；Owing to whole gas turbine master-plan is wanted
Asking, whole Combustion chamber design is for be vertically placed in turbine inlet gripper shoe 11, it is therefore desirable to consider that its mechanical stress and heat should
The bearing member design of power, mainly by the one-level swirler assembly 3 of head, second cyclone assembly 4 and the company of natural gas combustion nozzle 5
Connecing, and the burner inner liner gripper shoe 10 of burner inner liner 8 afterbody fixes, wherein the burner inner liner gripper shoe 10 of afterbody is main stress
Parts, the gravity of whole burner inner liner is passed to turbine support plate 11 by burner inner liner gripper shoe and bears；Ensure the load of burner inner liner
With the free wxpansion being heated；The gripper shoe that the gravity of whole burner inner liner is welded by flame drum tail is born；And entirety flame
By being free to move axially between the burner of head design and swirler assembly, the expanded by heating of cylinder, ensures that it is the most swollen
Swollen.
One-level swirler assembly 3, second cyclone assembly 4 are enclosed within natural gas combustion nozzle 5 and have certain void space,
When burner inner liner expanded by heating, natural gas combustion nozzle 5 maintains static, 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 alignment error, in burner inner liner
The leading portion in portion is designed with lighter mounting assembly 6, and lighter mounting assembly 6 can be able to move on burner inner liner 8 outer wall, and
All there is certain mobile space in 360 ° of directions of circumference, thus facilitate lighter to install.
The air of 10%～about 40% is entered from one-level swirler assembly 3, second cyclone assembly 4, with burner ejection
Natural gas is sufficiently mixed, and forms stable recirculating zone under two-stage vortex gas-flow effect, after on wall, lighter is lighted,
Form stable combustion flame；The air of 10%～about 40% enters main flow area from primary holes, is cut by the jet of primary holes
High temperature recirculation zone, broken end portion, thus control reflux area length, and supplementary fresh air, the natural gas making burner spray fires completely
Burn；The air of 10%～about 40% enters from blending hole, regulates Exit temperature distribution so that it is temperature field meets turbine design and wants
Ask, thus improve the life-span of turbine；The air that all standing gaseous film control aperture from burner inner liner enters, at burner inner liner internal face
Upper formation all standing air film, thus improve the burner inner liner life-span.
As in figure 2 it is shown, the primary structure of head of combustion chamber is two-stage cyclones structure, including one-level swirler assembly 3 He
Second cyclone assembly 4, one-level swirler assembly 3 and second cyclone assembly 4 can be biaxially cyclone combination, biradial
Cyclone combination or radial swirler combination of cutting sth. askew.One-level swirler assembly 3 is mainly designed as axial swirler, two grades of eddy flows
Device assembly 4 is designed to axial swirler, and its 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, it is ensured that natural gas mixes rapidly and uniformly with air.From one-level cyclone
The air that assembly 3, second cyclone assembly 4 flow out starts the most outwards high speed rotating expansion, thus causes burner inner liner central part
Position pressure reduces, and causes gas flow counterflow below to supplement, thus forms stable recirculating zone at head of combustion chamber, stable for being formed
Incendiary source provide aerodynamic conditions；Mixed gas burns rapidly after ignitor assembly 6 is lighted at head of combustion chamber, discharges heat,
Air-flow accelerates, and from combustion chamber flame drum outlet section 12 ejection at a high speed, promotes the turbine acting after combustor, is machine by thermal energy
Tool energy.
One-level swirler assembly 3 can be processed by one piece casting or machining mode, second cyclone assembly 4
Can be processed by modes such as overall machining, one piece casting or welding, the parts such as swirler blades can be by weldering
Connect wall inside and outside mode and cyclone to be attached, by being welded to connect between two-stage cyclones；One-level swirler assembly 3, two
Level swirler assembly 4 connects by being weldingly connected with combustion chamber flame drum 8；Burner inner liner wall flame cylinder contraction section gaseous film control of getting angry is little
Hole 15, middle section surface are provided with burner inner liner stage casing gaseous film control aperture 17 and burner inner liner head gaseous film control aperture 18 can lead to
Crossing laser boring or mechanical perforation techniques is processed, primary holes 7 and the bigger hole of blending hole 9 can be by machinings
Mode is processed；By primary holes reasonable in design and the size and number of blending hole, thus rational primary holes is organized to penetrate
Flow depth degree and air inflow, primary holes jet can block recirculating zone, makes combustion chemistry reaction occur mainly in recirculating zone.Tissue
Good rational blending hole Jet Penetration Depth and tolerance, form the temperature field meeting turbine inlet requirement, thus reduce high temperature hotspot.Fire
Flame cylinder gripper shoe 10 is connected with burner inner liner outlet section 12 by welding manner so that burner inner liner entirety load-bearing is sat by gripper shoe 10
In turbine inlet gripper shoe 11.
One-level cyclone 3 is axial swirler, eddy flow angle between 20 °～80 °, blade quantity between 6～30,
These are arranged all can make suitable adjustment, and air-flow rotation direction can be clockwise or counter-clockwise along airflow direction；Two grades of eddy flows
Device 4 is also configured as bladed axial swirler, and blade angle degree is between 20 °～80 ° and lobe numbers is between 6～30
All can make suitable adjustment.One-level swirler assembly 3, second cyclone assembly 4 air-flow oppositely oriented, can be formed relatively
Quickly mixing of strong air-flow shear layer, beneficially fuel and air, and two-stage cyclones blade can be prismatic blade formula or
Helical blade type；Get angry flame cylinder contraction section gaseous film control aperture 15, middle section surface of burner inner liner 8 burner inner liner wall above is provided with
Burner inner liner stage casing gaseous film control aperture 17 and burner inner liner head gaseous film control aperture 18 and the angle that flows between wall are at 15 °
～between 45 °, compound angle between 30 °～60 °, these arrange and carry out suitable adjustment according to practical situation, thus reach
Good cooling effect.
Under ensureing two-stage cyclones circulation area permanence condition, can also be one-level cyclone 3 and two grades of rotations in engineering
Single-stage axial swirler merged into by stream device 4, by designing the swirling number of single-stage cyclone, and mates with natural gas combustion nozzle,
Ensure that head of combustion chamber forms stable Combustion Flow Field, thus realize simple in construction, and reduce its processing cost.
The air capacity of head of combustion chamber, including one-level cyclone 3, second cyclone 4 air inflow and burner inner liner head
The cooling air volume of Cooling Holes 18 accounts for the 12%～about 40% of import total air, and head of combustion chamber is generally the combustion of inclined rich oil
Burn, thus ensure there is preferable combustion stability.
Claims (10)
1. a ground gas turbine can burner for axial admission, including combustion chamber charge pipeline (1), casing (16), combustion
Burn room outlet section (12), it is characterised in that described casing (16) upper end connects combuster admission line (1), described machine
Casket (16) lower end connects combuster outlet section (12), and described combustor exit section (12) is provided with burner inner liner (8)；Described
Burner inner liner (8) be connected with combustion chamber charge pipeline (1) by Imported gas pipeline (2)；Described Imported gas pipeline
(2) top is provided with natural gas combustion nozzle (5), and be enclosed within natural gas combustion nozzle (5) one-level swirler assembly (3), two grades
On swirler assembly (4), and one-level swirler assembly (3), second cyclone assembly (4) and Imported gas pipeline (2)
Natural gas combustion nozzle (5) is fixed by certain matched in clearance；On described natural gas combustion nozzle (5), multiple gas spraying is set
Hole (23)；Being provided with primary holes (7) on the upside of described burner inner liner (8) stage casing, the upper end of primary holes (7) is provided with lighter and installs
Assembly (6)；On the downside of described burner inner liner (8) stage casing, blending hole (9) is installed.
The ground gas turbine can burner of axial admission the most according to claim 1, it is characterised in that described sky
So gas spurt (23) and axial admission air-flow have certain angle；The described natural gas spray orifice on natural gas combustion nozzle (5)
(23) aperture is 0.3～3.5mm；Quantity is 6～20；The angle of described burner injection is 30 °～150 °.
The ground gas turbine can burner of axial admission the most according to claim 1, it is characterised in that described combustion
Burn room admission line (1) to be connected with casing (16) by combustor suction flange (19) and combustion chamber charge section flange (20)；
Described combustor exit section (12) is connected with casing (16) by turbine inlet flange (13) and combustor exit flange (14)
Connect.
The ground gas turbine can burner of axial admission the most according to claim 1, it is characterised in that described point
Firearm mounting assembly (6) can move on burner inner liner (8) outer wall.
The ground gas turbine can burner of axial admission the most according to claim 1, it is characterised in that described fire
Flame cylinder (8) head surface is provided with burner inner liner head gaseous film control aperture (18), and in burner inner liner (8), section surface is provided with burner inner liner
Stage casing gaseous film control aperture (17), burner inner liner (8) tail surface is provided with burner inner liner contraction section gaseous film control aperture (15).
The ground gas turbine can burner of axial admission the most according to claim 1, it is characterised in that described sky
So gas inlet pipeline (2) is right-angle structure, and described Imported gas pipeline (2) passes through to weld with combustion chamber charge pipeline (1)
Connect or Flange joint.
The ground gas turbine can burner of axial admission the most according to claim 1, it is characterised in that described combustion
The junction burning room outlet section (12) and burner inner liner (8) afterbody is sequentially provided with burner inner liner gripper shoe (10) and turbine support plate
, and can burner is vertically to place (11).
8. the ground gas turbine can burner of an axial admission as claimed in claim 1, it is characterised in that described
One-level swirler assembly (3), second cyclone assembly (4) combine for the combination of biaxially cyclone, biradial cyclone or cut sth. askew
Radial swirler combines.
The ground gas turbine can burner of axial admission the most according to claim 8, it is characterised in that described one
Level cyclone (3) and second cyclone (4) can also merge into single-stage axial swirler.
The ground gas turbine can burner of axial admission the most according to claim 8, it is characterised in that described
It is separately installed with one-level swirler blades (21), second cyclone on one-level swirler assembly (3), second cyclone assembly (4)
Blade (22)；Described one-level swirler blades (21), second cyclone blade (22) are prismatic blade formula or spiral, install
Angle is 20 °～80 °, and lobe numbers is 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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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| 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 |
| CN108758690A (en) * | 2018-05-31 | 2018-11-06 | 马鞍山松鹤信息科技有限公司 | Combustion chamber for 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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| CN105674330A (en) * | 2016-01-27 | 2016-06-15 | 南京航空航天大学 | Single-tube combustor device of ground combustion gas turbine |
| CN206176457U (en) * | 2016-09-29 | 2017-05-17 | 南京航空航天大学 | Ground gas turbine can burner of axial admission |
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| US2826039A (en) * | 1947-01-09 | 1958-03-11 | Power Jets Res & Dev Ltd | Gas inlet structure for combustion chambers |
| 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 |
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| 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 |
| CN104896512A (en) * | 2015-05-11 | 2015-09-09 | 北京航空航天大学 | Low-emission natural gas combustion chamber with wide stable working range |
| CN105674330A (en) * | 2016-01-27 | 2016-06-15 | 南京航空航天大学 | Single-tube combustor device of ground combustion gas turbine |
| CN206176457U (en) * | 2016-09-29 | 2017-05-17 | 南京航空航天大学 | Ground gas turbine can burner of axial admission |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| 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 |
| CN108758690A (en) * | 2018-05-31 | 2018-11-06 | 马鞍山松鹤信息科技有限公司 | Combustion chamber for 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 |
| CN116336503B (en) * | 2023-03-27 | 2024-05-10 | 中国航发贵阳发动机设计研究所 | Combustion chamber unit body structure |
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