CN107796017A - A kind of combustion chamber and gas turbine - Google Patents
A kind of combustion chamber and gas turbine Download PDFInfo
- Publication number
- CN107796017A CN107796017A CN201711183853.3A CN201711183853A CN107796017A CN 107796017 A CN107796017 A CN 107796017A CN 201711183853 A CN201711183853 A CN 201711183853A CN 107796017 A CN107796017 A CN 107796017A
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- China
- Prior art keywords
- combustion chamber
- cyclone
- turbine
- charging aperture
- fuel
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The present invention relates to gas turbine technology field, discloses a kind of combustion chamber and gas turbine, to simplify the design cycle of the gas-turbine combustion chamber of different capacity and difficulty, so as to accelerate the product development progress of the miniature gas turbine combustion chamber of different capacity.The combustion chamber includes head charging aperture component, cyclone group, burner inner liner and turbine casing, wherein, the turbine casing is coated on the outside of head charging aperture component, cyclone and the burner inner liner sequentially coaxially connected in a manner of gap coordinates, and the side that the turbine casing corresponds to the head charging aperture component has air intake, the head charging aperture component has multiple fuel mouths of pipe being distributed along its sectional uniform.
Description
Technical field
The present invention relates to gas turbine technology field, more particularly to a kind of combustion chamber and gas turbine.
Background technology
Gas turbine is rotated at a high speed using the gas continuously flowed as working medium impeller, is to have by the energy conversion of fuel
Diligent internal combustion type dynamic power machine, it is typical new and high technology intensive product.As high-tech carrier, gas turbine represents
The level of aggregation of how theoretical subject and multiple-project field development, be that national high-tech is horizontal and the important symbol of scientific and technological strength it
One, there is very prominent strategic position.Three big parts of miniature gas turbine are combustion chamber, compressor and turbine, combustion chamber
Performance can directly affect the overall performance of miniature gas turbine.Miniature gas turbine is according to being actually needed different output works
Rate, such as 10KW, 30KW, 50KW, 65KW, 100KW, 300KW etc..Its each part of the miniature gas turbine of different output power needs
Redesign and match.Time-consuming for the design of the miniature gas turbine combustion chamber of existing different capacity, it is also necessary to many experiments
To adjust, product development progress is influenceed.
The content of the invention
The invention provides a kind of combustion chamber and gas turbine, to simplify the design of the gas-turbine combustion chamber of different capacity
Flow and difficulty, so as to accelerate the product development progress of the miniature gas turbine combustion chamber of different capacity.
To reach above-mentioned purpose, the present invention provides following technical scheme：
A kind of combustion chamber, including head charging aperture component, cyclone group, burner inner liner and turbine casing, wherein, the turbine
Casing is coated on the outside of head charging aperture component, cyclone and the burner inner liner sequentially coaxially connected in a manner of gap coordinates,
And the side that the turbine casing corresponds to the head charging aperture component has air intake, the head charging aperture component has
Multiple fuel mouths of pipe being distributed along its sectional uniform.
Preferably, the head charging aperture component has three fuel mouths of pipe.
Preferably, the combustion chamber also includes multiple blending holes, and the multiple blending hole spacer ring is around being arranged at the fire
Flame cylinder side wall.
Preferably, there is primary holes on the stage casing barrel of the burner inner liner.
Preferably, the burner inner liner barrel has the Cooling Holes around array arrangement.
Preferably, the aperture of the Cooling Holes is 0.8~1.2mm, and the primary holes aperture is more than the Cooling Holes hole
Footpath.
Preferably, the cyclone group includes multiple cyclones of connection corresponding with each fuel mouth of pipe.
Preferably, each cyclone is in open column shape, and each cyclone include cyclone inner ring, cyclone outer ring and
Swirler blades, be inserted with the cyclone inner ring corresponding to the fuel mouth of pipe.
Preferably, the fuel mouth of pipe end being inserted in the cyclone inner ring has 6~15 fuel jet orifices, and described
The aperture of fuel jet orifice is 1.2~4mm.
Gas-turbine combustion chamber provided in an embodiment of the present invention, its head charging aperture component have multiple fuel mouths of pipe,
The head charging aperture that existing small-power combustion chamber can be selected during the gas-turbine combustion chamber for designing different capacity is combined, this
The Combustion chamber design that inventive embodiments provide is more efficient and convenient, can be as preliminary Combustion chamber design scheme, so as to simplify not
With the design cycle and difficulty of the gas-turbine combustion chamber of power, the production of the miniature gas turbine combustion chamber of different capacity is accelerated
Product development progress.Turbine casing sets air intake, the air inlet streams in the side of corresponding head charging aperture component simultaneously
Direction is consistent with the direction that fuel enters combustion chamber to enable to air and high-temperature flue gas during burning to mix evenly, so as to improve
The uniformity coefficient of combustor exit gas flow temperature and the capacity usage ratio of combustion chamber.
A kind of gas turbine, including compressor, turbine and combustion chamber as described above.
Gas turbine provided in an embodiment of the present invention includes above-mentioned combustion chamber, can also reach the combustion gas of simplified different capacity
The design cycle and difficulty of turbine combustion room, so as to accelerate the product development progress of the miniature gas turbine combustion chamber of different capacity
Purpose.
Brief description of the drawings
Fig. 1 is the structural representation of gas-turbine combustion chamber provided in an embodiment of the present invention；
Fig. 2 is the axle sectional view of gas-turbine combustion chamber provided in an embodiment of the present invention；
Fig. 3 is the head charging aperture component sectional view of gas-turbine combustion chamber provided in an embodiment of the present invention；
Fig. 4 is the fuel mouth of pipe and cyclone combination diagram of gas-turbine combustion chamber provided in an embodiment of the present invention.
Reference：
1- heads charging aperture component
2- swirler assemblies
3- burner inner liners
4- turbine casings
5- air intakes
The 11- fuel mouths of pipe
111- fuel jet orifices
21- cyclones
211- cyclone inner rings
212- cyclones outer ring
213- swirler blades
31- blending holes
32- primary holes
33- Cooling Holes
Embodiment
To simplify the design cycle and difficulty of the gas-turbine combustion chamber of different capacity, so as to accelerate the miniature of different capacity
The product development progress of gas-turbine combustion chamber.To make the object, technical solutions and advantages of the present invention clearer, lift below real
Example is applied to be described in further detail the present invention.
The combustion chamber provided with reference to figure 1, Fig. 2 and Fig. 3, an embodiment of the present invention, including head charging aperture component 1, rotation
Device group 2, burner inner liner 3 and turbine casing 4 are flowed, wherein, turbine casing 4 is coated on what is sequentially coaxially connected in a manner of gap coordinates
The outside of head charging aperture component 1, cyclone 2 and burner inner liner 3, and the side of the corresponding head charging aperture component 1 of the turbine casing 4
With air intake 5, head charging aperture component 1 has multiple fuel mouths of pipe 11 being distributed along its sectional uniform.
Gas-turbine combustion chamber provided in an embodiment of the present invention, its head charging aperture component have multiple fuel mouths of pipe,
The head charging aperture that existing small-power combustion chamber can be selected during the gas-turbine combustion chamber for designing different capacity is combined, this
The Combustion chamber design that inventive embodiments provide is more efficient and convenient, can be as preliminary Combustion chamber design scheme, so as to simplify not
With the design cycle and difficulty of the gas-turbine combustion chamber of power, the production of the miniature gas turbine combustion chamber of different capacity is accelerated
Product development progress.Turbine casing sets air intake, the air inlet streams in the side of corresponding head charging aperture component simultaneously
Direction is consistent with the direction that fuel enters combustion chamber to enable to air and high-temperature flue gas during burning to mix evenly, so as to improve
The uniformity coefficient of combustor exit gas flow temperature and the capacity usage ratio of combustion chamber.
The fuel mouth of pipe quantity of the incorrect portion's charging aperture component of the embodiment of the present invention carries out concrete restriction, in actual applications
It can be accepted or rejected according to required combustion chamber power, but pass through inventor's lot of experiment validation, when head charging aperture component has three
During the individual fuel mouth of pipe, the output power range that combustion chamber can be formed is larger, and now causes air and high-temperature flue gas mixing more
Uniformly, so as to further improve the uniformity coefficient of combustor exit gas flow temperature and the capacity usage ratio of combustion chamber.
With reference to figure 1 and Fig. 2, in an alternative embodiment of the invention, there are multiple blending holes 31 on the barrel of burner inner liner 3, burn
The spacer ring of multiple blending holes 31 of room is around being arranged at the side wall of burner inner liner 3.The aperture of blending hole 31 is preferably 8mm~20mm.Flame
For cylinder sidewall spacers around multiple blending holes are set, the multiple blending holes being arranged such enable to dilution air more equably to enter
Enter into burner inner liner so that air and high-temperature flue gas are mixed evenly, so as to improve the uniform journey of combustor exit gas flow temperature
Degree and the capacity usage ratio of combustion chamber.
In still another embodiment of the process, as depicted in figs. 1 and 2, there is master on the stage casing barrel of the burner inner liner 3 of combustion chamber
Fire hole 32.Primary holes can improve the efficiency of combustion in burner inner liner and balance the pressure inside and outside burner inner liner, so as to improve combustion chamber
Service behaviour and service life.The barrel of burner inner liner 3 also has the Cooling Holes 33 around array arrangement.Cooling Holes can balance flame
Pressure inside and outside cylinder, and balance burner inner liner internal-external temperature difference and prevented cause thermal damage, so as to further improve combustion chamber operational performance and
Service life.Cooling effect is best between Cooling Holes aperture is in 0.8mm~1.5mm, can be reduced while stable burn
The damage of combustion chamber, so as to improve combustion chamber service life.Aperture is too small can not to effectively form gaseous film control, it is impossible to reach guarantor
Protect the purpose of cyclone and burner inner liner；Aperture too it is big then can extinguishing partial combustion processes, so as to reduce the final work in combustion chamber
Efficiency.Gaseous film control general principle is：Cooling air-flow, the cooling of this stock are introduced from the hole on the wall of hot environment to high temperature main flow
Air-flow high temperature main flow pressure and frictional force effect under downstream bend, be attached on wall certain area, formed temperature compared with
Low cold air film isolates wall with high-temperature fuel gas, and takes away part high-temperature fuel gas, is protected so as to play good cooling to wall
Shield acts on.
With reference to figure 3 and Fig. 4, the cyclone group 2 in the embodiment of the present invention includes connection corresponding with each fuel mouth of pipe 11
Multiple cyclones 21.Further, each cyclone 21 is in open column shape, and each cyclone 21 includes cyclone inner ring
211st, cyclone outer ring 212 and swirler blades 212, be inserted with cyclone inner ring 211 corresponding to the fuel mouth of pipe 11.Wherein,
The quantity of swirler blades is 6~14 in each cyclone.Cyclone group is set in combustion chamber, and air-flow is passing through cyclone
Low speed recirculating zone can be formed in combustion chamber during group, can so make gas velocity consistent with flame propagation velocity, so as to ensure
The stabilization of burning, the formation of recirculating zone can also ensure the safety of burning.In the embodiment of the present invention preferably using the fuel mouth of pipe and
The one-to-one setting structure of cyclone, it can preferably ensure stability and security during combustion chambers burn.Further
, the end of the fuel mouth of pipe 11 being inserted in cyclone inner ring 211 has 6~15 fuel jet orifices 111, and the fuel jet orifice
111 aperture is 1.2~4mm.Fuel jet orifice can be in the dispersion fuel mouth of pipe fuel form tiny fuel fog, so as to carry
Efficiency of combustion and combustion stability in high combustion chamber.
The embodiment of the present invention additionally provides a kind of gas turbine, including compressor, turbine and combustion chamber as described above.
Gas turbine provided in an embodiment of the present invention includes above-mentioned combustion chamber, can also reach the combustion gas of simplified different capacity
The design cycle and difficulty of turbine combustion room, so as to accelerate the product development progress of the miniature gas turbine combustion chamber of different capacity
Purpose.
Obviously, those skilled in the art can carry out various changes and modification without departing from this hair to the embodiment of the present invention
Bright spirit and scope.So, if these modifications and variations of the present invention belong to the claims in the present invention and its equivalent technologies
Within the scope of, then the present invention is also intended to comprising including these changes and modification.
Claims (10)
- A kind of 1. combustion chamber, it is characterised in that including head charging aperture component, cyclone group, burner inner liner and turbine casing, its In, the turbine casing is coated on head charging aperture component, cyclone and the fire sequentially coaxially connected in a manner of gap coordinates The outside of flame cylinder, and the side that the turbine casing corresponds to the head charging aperture component has air intake, the head is entered Material mouth component has multiple fuel mouths of pipe being distributed along its sectional uniform.
- 2. combustion chamber according to claim 1, it is characterised in that the head charging aperture component has three cartridges Mouthful.
- 3. combustion chamber according to claim 2, it is characterised in that also including multiple blending holes, between the multiple blending hole Spacer ring is around being arranged at the burner inner liner side wall.
- 4. combustion chamber according to claim 1, it is characterised in that there is primary holes on the stage casing barrel of the burner inner liner.
- 5. combustion chamber according to claim 4, it is characterised in that the burner inner liner barrel has around the cold of array arrangement But hole.
- 6. combustion chamber according to claim 5, it is characterised in that the aperture of the Cooling Holes is 0.8~1.2mm, and institute State primary holes aperture and be more than the Cooling Holes aperture.
- 7. combustion chamber according to claim 1, it is characterised in that the cyclone group includes corresponding with each fuel mouth of pipe Multiple cyclones of connection.
- 8. combustion chamber according to claim 7, it is characterised in that each cyclone is in open column shape, and each eddy flow Device includes cyclone inner ring, cyclone outer ring and swirler blades, and the corresponding fuel mouth of pipe is inserted with the cyclone inner ring.
- 9. combustion chamber according to claim 8, it is characterised in that the fuel mouth of pipe end being inserted in the cyclone inner ring End has 6~15 fuel jet orifices, and the aperture of the fuel jet orifice is 1.2~4mm.
- 10. a kind of gas turbine, it is characterised in that including compressor, turbine and according to any one of claims 1 to 9 Combustion chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711183853.3A CN107796017A (en) | 2017-11-23 | 2017-11-23 | A kind of combustion chamber and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711183853.3A CN107796017A (en) | 2017-11-23 | 2017-11-23 | A kind of combustion chamber and gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107796017A true CN107796017A (en) | 2018-03-13 |
Family
ID=61536420
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711183853.3A Withdrawn CN107796017A (en) | 2017-11-23 | 2017-11-23 | A kind of combustion chamber and gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107796017A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110925798A (en) * | 2019-11-06 | 2020-03-27 | 西北工业大学 | Combustion chamber with spiral-flow type flame tube |
| CN112963864A (en) * | 2021-03-26 | 2021-06-15 | 西北工业大学 | Strong-mixing type main combustion hole of combustion chamber of gas turbine |
| CN115095885A (en) * | 2022-06-06 | 2022-09-23 | 中国船舶集团有限公司系统工程研究院 | Combined multi-point LDI oblique-feeding combustion chamber |
| CN111237087B (en) * | 2020-01-19 | 2024-03-22 | 西北工业大学 | Micro-pore plate active and passive composite cooling structure for aerospace power and cooling method |
-
2017
- 2017-11-23 CN CN201711183853.3A patent/CN107796017A/en not_active Withdrawn
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110925798A (en) * | 2019-11-06 | 2020-03-27 | 西北工业大学 | Combustion chamber with spiral-flow type flame tube |
| CN111237087B (en) * | 2020-01-19 | 2024-03-22 | 西北工业大学 | Micro-pore plate active and passive composite cooling structure for aerospace power and cooling method |
| CN112963864A (en) * | 2021-03-26 | 2021-06-15 | 西北工业大学 | Strong-mixing type main combustion hole of combustion chamber of gas turbine |
| CN112963864B (en) * | 2021-03-26 | 2022-07-12 | 西北工业大学 | Strong-mixing type main combustion hole of combustion chamber of gas turbine |
| CN115095885A (en) * | 2022-06-06 | 2022-09-23 | 中国船舶集团有限公司系统工程研究院 | Combined multi-point LDI oblique-feeding combustion chamber |
| CN115095885B (en) * | 2022-06-06 | 2024-02-09 | 中国船舶集团有限公司系统工程研究院 | Combined multi-point LDI inclined combustion chamber |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information | ||
| CB02 | Change of applicant information |
Address after: 201306 101 new office building, A, 7 new industrial park, Shanghai, Pudong New Area, 600 new Yuan South Road, Pudong New Area. Applicant after: New Austrian energy power technology (Shanghai) Co., Ltd. Address before: 201406 228 yongyang Road, Yang Wang Industrial Park, South Bridge Town, Fengxian District, Shanghai Applicant before: Shanghai wisdom energy equipment Co., Ltd. |
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| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20180313 |