CN107062306A - A kind of combustion chamber and gas turbine - Google Patents
A kind of combustion chamber and gas turbine Download PDFInfo
- Publication number
- CN107062306A CN107062306A CN201710322498.7A CN201710322498A CN107062306A CN 107062306 A CN107062306 A CN 107062306A CN 201710322498 A CN201710322498 A CN 201710322498A CN 107062306 A CN107062306 A CN 107062306A
- Authority
- CN
- China
- Prior art keywords
- combustion chamber
- cyclone
- inner liner
- burner inner
- air inlet
- Prior art date
- 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.)
- Pending
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 67
- 238000002156 mixing Methods 0.000 claims abstract description 25
- 238000007599 discharging Methods 0.000 claims abstract description 6
- 239000000446 fuel Substances 0.000 claims description 7
- 125000006850 spacer group Chemical group 0.000 claims description 4
- 239000007789 gas Substances 0.000 abstract description 30
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 abstract description 13
- 239000003546 flue gas Substances 0.000 abstract description 13
- 238000000034 method Methods 0.000 abstract description 6
- 238000005516 engineering process Methods 0.000 abstract description 5
- 238000010790 dilution Methods 0.000 description 5
- 239000012895 dilution Substances 0.000 description 5
- 238000001816 cooling Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 239000002671 adjuvant Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 2
- 230000003134 recirculating effect Effects 0.000 description 2
- 230000002776 aggregation Effects 0.000 description 1
- 238000004220 aggregation Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000003685 thermal hair damage Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
-
- 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
- F23R3/58—Cyclone or vortex type combustion chambers
Landscapes
- 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, disclose a kind of combustion chamber and gas turbine, to improve the intake method of combustion chamber so that air and high-temperature flue gas are mixed evenly, so as to improve the uniformity coefficient of combustor exit gas flow temperature and the capacity usage ratio of combustion chamber.The combustion chamber includes cartridge, burner inner liner, cyclone group and turbine casing, wherein, the discharging opening of the cartridge is connected with the entrance of the burner inner liner, and the connectivity part of the cartridge and the burner inner liner is provided with cyclone group, the turbine casing gap, which coordinates, to be coated on the outside of the cartridge and burner inner liner, there are multiple blending holes, the turbine casing side wall is at least provided with an air inlet duct, and the multiple blending hole correspondence air inlet duct is set on the burner inner liner barrel.
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 by working medium impeller of the gas continuously flowed, is to have by the energy conversion of fuel
Diligent internal combustion type dynamic power machine, is typical new and high technology intensive product.As high-tech carrier, gas turbine is represented
How theoretical subject and the level of aggregation of multiple-project field development, be national high-tech level and scientific and technological strength important symbol it
One, with 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.Whether the Temperature Distribution of combustor exit uniformly also has to turbine
Material impact, local high temperature has destruction to turbine.Other combustor total pressure loss accounts for the loss of miniature gas turbine always
Greatly, combustor total pressure loss is small, then the loss of miniature gas turbine always is small so that miniature gas turbine overall efficiency
It is higher.
The combustion chamber charge of existing gas turbine is axial admission, and the momentum of the combustion chamber dilution air of axial admission is not
Foot, the mixing of air and high-temperature flue gas is not uniform enough so that combustor exit gas flow temperature is uneven, and combustion chamber self-energy is damaged
Lose high.
The content of the invention
The invention provides a kind of combustion chamber and gas turbine, to improve the intake method of combustion chamber so that air and height
Warm flue gas is mixed evenly, so as to improve the uniformity coefficient of combustor exit gas flow temperature and the capacity usage ratio of combustion chamber.
To reach above-mentioned purpose, the present invention provides following technical scheme：
A kind of combustion chamber, including cartridge, burner inner liner, cyclone group and turbine casing, wherein, the discharging of the cartridge
Mouth is connected with the entrance of the burner inner liner, and the connectivity part of the cartridge and the burner inner liner is provided with cyclone group, described
Turbine casing gap, which coordinates, to be coated on the outside of the cartridge and burner inner liner, has multiple blending holes on the burner inner liner barrel,
The turbine casing side wall is at least provided with an air inlet duct, and the multiple blending hole correspondence air inlet duct is set.
It is preferred that, the air inlet duct is two and is relatively arranged on the turbine casing side wall.
It is preferred that, the multiple blending hole spacer ring is around being arranged at burner inner liner side wall.
It is preferred that, the setting area of the multiple blending hole is located between the first setting position and the second setting position, and
First setting position and the second setting position are projected boundary of the air inlet duct on the burner inner liner.
It is preferred that, there is primary holes on the stage casing barrel of the burner inner liner.
It is preferred that, the burner inner liner barrel has the Cooling Holes around array arrangement.
Optionally, the fuel pipe end is provided with atomizer.
It is preferred that, the cyclone group includes one-level cyclone and second cyclone, the one-level cyclone and two grades of rotations
It is in open column shape to flow device, and the external diameter of the one-level cyclone is more than the external diameter of the second cyclone, and the one-level eddy flow
Device and second cyclone are coaxial and stepped in the axial direction shift to install.
It is preferred that, every grade of cyclone includes cyclone air inlet, cyclone bottom plate and swirler blades.
Combustion chamber provided in an embodiment of the present invention, the discharging opening of cartridge is connected with the entrance of burner inner liner, and cartridge and
The connectivity part of burner inner liner is provided with cyclone group, into turbine casing combustion adjuvant at cyclone group with cartridge provide combustion
Material reaction, and then go through burning generation high-temperature flue gas in burner inner liner.There are multiple blending holes, turbine machine on burner inner liner barrel
Casket side wall is at least provided with an air inlet duct, and multiple blending holes correspondence air inlet duct is set, and the dilution air in air inlet duct is laterally mixed
Enter the high-temperature flue gas in burner inner liner so that air and high-temperature flue gas are mixed evenly, so as to improve combustor exit gas flow temperature
Uniformity coefficient and combustion chamber capacity usage ratio.
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 improve the intake method of combustion chamber,
So that air and high-temperature flue gas mixing are evenly, so as to improve the uniformity coefficient of combustor exit gas flow temperature and the energy of combustion chamber
Measure utilization rate.
Brief description of the drawings
The structural representation for the combustion chamber that Fig. 1 provides for one embodiment of the invention；
The oblique sectional view for the burning that Fig. 2 provides for one embodiment of the invention；
The structural representation for the combustion chamber that Fig. 3 provides for another embodiment of the present invention；
The partial structural diagram for the combustion chamber that Fig. 4 provides for another embodiment of the present invention.
Reference：
1- cartridges
2- burner inner liners
21- blending holes
The setting positions of 211- first
The setting positions of 212- second
22- primary holes
23- Cooling Holes
3- cyclone groups
31- one-level cyclones
311- one-level cyclone bottom plates
312- one-level swirler blades
313- one-level cyclone air inlets
32- second cyclones
321- second cyclone bottom plates
322- second cyclone blades
323- second cyclone air inlets
4- turbine casings
41- air inlet ducts
Embodiment
To improve the intake method of combustion chamber so that air and high-temperature flue gas mixing evenly, go out so as to improve combustion chamber
The uniformity coefficient and the capacity usage ratio of combustion chamber of mouth gas flow temperature, the embodiments of the invention provide a kind of combustion chamber and combustion gas wheel
Machine.To make the object, technical solutions and advantages of the present invention clearer, the present invention is made further specifically by the following examples
It is bright.
The combustion chamber provided with reference to Fig. 1 and Fig. 2, an embodiment of the present invention, including cartridge 1, burner inner liner 2, cyclone
Group 3 and turbine casing 4, wherein, the discharging opening of cartridge 1 is connected with the entrance of burner inner liner 2, and the company of cartridge 1 and burner inner liner 2
Logical place is provided with cyclone group 3, and the gap of turbine casing 4, which coordinates, to be coated on cartridge 1 and the outside of burner inner liner 2, the barrel of burner inner liner 2
With multiple blending holes 21, the side wall of turbine casing 4 is at least provided with an air inlet duct 41, and the correspondence air inlet duct 41 of multiple blending holes 21
Set.
Combustion chamber provided in an embodiment of the present invention, the discharging opening of cartridge is connected with the entrance of burner inner liner, and cartridge and
The connectivity part of burner inner liner is provided with cyclone group, into turbine casing combustion adjuvant at cyclone group with cartridge provide combustion
Material reaction, and then go through burning generation high-temperature flue gas in burner inner liner.There are multiple blending holes, turbine machine on burner inner liner barrel
Casket side wall is at least provided with an air inlet duct, and multiple blending holes correspondence air inlet duct is set, and the dilution air in air inlet duct is laterally mixed
Enter the high-temperature flue gas in burner inner liner so that air and high-temperature flue gas are mixed evenly, so as to improve combustor exit gas flow temperature
Uniformity coefficient and combustion chamber capacity usage ratio.
With reference to Fig. 3, in an alternative embodiment of the invention, the air inlet duct 41 of combustion chamber is two and is relatively arranged on turbine machine
The side wall of casket 4.Turbine casing side wall is relatively set with two air inlet ducts, the interference between charge air flow can be reduced, so as to be formed
Stable dilution air stream, further improves the uniformity coefficient of combustor exit gas flow temperature and the capacity usage ratio of combustion chamber.
Further, as shown in figure 3, the spacer ring of multiple blending holes 21 of combustion chamber is around being arranged at the side wall of burner inner liner 2.Flame
Cylinder sidewall spacers are around multiple blending holes are set, and 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.
It is preferred that, as shown in figure 3, the setting area of multiple blending holes 21 is located at the first setting position 211 and the second setting
Between position 212, and the setting position 212 of the first setting position 211 and second is projection side of the air inlet duct 41 on burner inner liner 2
Boundary.
In still another embodiment of the process, as shown in figure 4, having primary holes on the stage casing barrel of the burner inner liner 2 of combustion chamber
22.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 operational
Performance and used life.The barrel of burner inner liner 2 also has the Cooling Holes 23 around array arrangement.Cooling Holes can be balanced in burner inner liner
Outer pressure, and balance burner inner liner internal-external temperature difference and prevented cause thermal damage, so as to further improve combustion chamber operational performance and use
Life-span.
With reference to Fig. 4, cyclone group 3 includes one-level cyclone 31 and second cyclone 32 in the preferred embodiment of the present invention, should
One-level cyclone 31 and second cyclone 32 are in open column shape, and the external diameter of one-level cyclone 31 is more than the outer of second cyclone 32
Footpath, and one-level cyclone 31 and second cyclone 32 are coaxial and stepped in the axial direction shift to install.Every grade of cyclone
Including cyclone air inlet, cyclone bottom plate and swirler blades.In corresponding diagram 4, i.e., one-level cyclone 31 includes one-level eddy flow
Device bottom plate 311, one-level swirler blades 312 and one-level cyclone air inlet 313, second cyclone 32 include second cyclone bottom
Plate 321, second cyclone blade 322 and second cyclone air inlet 323.Cyclone group is set in combustion chamber, and air-flow is logical
Low speed recirculating zone can be formed when crossing cyclone group in combustion chamber, 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.It is preferred to use two in the embodiment of the present invention
Level cyclone group, can preferably ensure the stability and security during combustion chambers burn.
In another preferred embodiment of the invention, the fuel pipe end of combustion chamber is provided with atomizer.Atomizer
Fuel that can be in dispersion fuel pipe forms tiny fuel fog, so as to improve the efficiency of combustion in combustion chamber.The present invention is not
The parameters such as model, material to atomizer are defined, and can voluntarily be selected according to the concrete condition of tool 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 improve the intake method of combustion chamber,
So that air and high-temperature flue gas mixing are evenly, so as to improve the uniformity coefficient of combustor exit gas flow temperature and the energy of combustion chamber
Measure utilization rate.
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)
1. a kind of combustion chamber, it is characterised in that including cartridge, burner inner liner, cyclone group and turbine casing, wherein, the combustion
The discharging opening of expects pipe is connected with the entrance of the burner inner liner, and the connectivity part of the cartridge and the burner inner liner is provided with eddy flow
Device group, the turbine casing gap, which coordinates, to be coated on the outside of the cartridge and burner inner liner, is had on the burner inner liner barrel many
Individual blending hole, the turbine casing side wall is at least provided with an air inlet duct, and the multiple blending hole correspondence air inlet duct is set
Put.
2. combustion chamber according to claim 1, it is characterised in that the air inlet duct is two and is relatively arranged on the wheel
Machine casing side wall.
3. combustion chamber according to claim 2, it is characterised in that the multiple blending hole spacer ring is around being arranged at the fire
Flame cylinder side wall.
4. combustion chamber according to claim 3, it is characterised in that the setting area of the multiple blending hole is set positioned at first
Positioning is put between the second setting position, and first setting position and the second setting position are the air inlet duct in the fire
Projected boundary on flame cylinder.
5. 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.
6. combustion chamber according to claim 5, it is characterised in that the burner inner liner barrel has around the cold of array arrangement
But hole.
7. combustion chamber according to claim 1, it is characterised in that the fuel pipe end is provided with atomizer.
8. combustion chamber according to claim 1, it is characterised in that the cyclone group includes one-level cyclone and two grades of rotations
Device is flowed, the one-level cyclone and second cyclone are in open column shape, and the external diameter of the one-level cyclone is more than described two grades
The external diameter of cyclone, and the one-level cyclone and second cyclone are coaxial and stepped in the axial direction shift to install.
9. combustion chamber according to claim 8, it is characterised in that every grade of cyclone includes cyclone air inlet, cyclone
Bottom plate and swirler blades.
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 |
|---|---|---|---|
| CN201710322498.7A CN107062306A (en) | 2017-05-09 | 2017-05-09 | A kind of combustion chamber and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710322498.7A CN107062306A (en) | 2017-05-09 | 2017-05-09 | A kind of combustion chamber and gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107062306A true CN107062306A (en) | 2017-08-18 |
Family
ID=59596668
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710322498.7A Pending CN107062306A (en) | 2017-05-09 | 2017-05-09 | A kind of combustion chamber and gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107062306A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107517793A (en) * | 2017-09-29 | 2017-12-29 | 青海大学 | Artificial snowfall operation device |
| 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 |
| CN109140500A (en) * | 2018-08-03 | 2019-01-04 | 新奥能源动力科技（上海）有限公司 | A kind of nozzle of combustion chamber, combustion chamber and miniature gas turbine |
| CN109404970A (en) * | 2018-12-04 | 2019-03-01 | 新奥能源动力科技（上海）有限公司 | Burner inner liner and gas turbine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101949551A (en) * | 2010-09-09 | 2011-01-19 | 北京航空航天大学 | Premix and pre-evaporation combustion chamber |
| CN204313312U (en) * | 2014-11-11 | 2015-05-06 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of term durability gas turbine flame barrel |
| 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 |
| CN106287814A (en) * | 2016-09-29 | 2017-01-04 | 南京航空航天大学 | A kind of ground gas turbine can burner of axial admission |
| CN206861592U (en) * | 2017-05-09 | 2018-01-09 | 上海泛智能源装备有限公司 | A kind of combustion chamber and gas turbine |
-
2017
- 2017-05-09 CN CN201710322498.7A patent/CN107062306A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101949551A (en) * | 2010-09-09 | 2011-01-19 | 北京航空航天大学 | Premix and pre-evaporation combustion chamber |
| CN204313312U (en) * | 2014-11-11 | 2015-05-06 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of term durability gas turbine flame barrel |
| 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 |
| CN106287814A (en) * | 2016-09-29 | 2017-01-04 | 南京航空航天大学 | A kind of ground gas turbine can burner of axial admission |
| CN206861592U (en) * | 2017-05-09 | 2018-01-09 | 上海泛智能源装备有限公司 | A kind of combustion chamber and gas turbine |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107517793A (en) * | 2017-09-29 | 2017-12-29 | 青海大学 | Artificial snowfall operation device |
| 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 |
| CN109140500A (en) * | 2018-08-03 | 2019-01-04 | 新奥能源动力科技（上海）有限公司 | A kind of nozzle of combustion chamber, combustion chamber and miniature gas turbine |
| CN109404970A (en) * | 2018-12-04 | 2019-03-01 | 新奥能源动力科技（上海）有限公司 | Burner inner liner and gas turbine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107062306A (en) | A kind of combustion chamber and gas turbine | |
| CN103534531B (en) | Combustor for gas turbine engine and gas turbine | |
| US5373695A (en) | Gas turbine combustion chamber with scavenged Helmholtz resonators | |
| CN207648852U (en) | A kind of combustion chamber and gas turbine | |
| CN206861592U (en) | A kind of combustion chamber and gas turbine | |
| CN102444476B (en) | Wave-shaped diffuser of gas turbine | |
| CN107796017A (en) | A kind of combustion chamber and gas turbine | |
| CN107062307A (en) | A kind of gas-turbine combustion chamber | |
| CN107036128B (en) | Combustion chamber of gas turbine | |
| CN110056906A (en) | For the coaxial classification eddy flow of gaseous fuel combustion room and the integrated head of blending | |
| CN207006235U (en) | A kind of pre-mixing apparatus of gas turbine and combustion chamber | |
| CN107763667A (en) | A kind of staged combustion device of fuel oil cooling flame tube wall surface | |
| CN114992672B (en) | Micro-premixing type combustion chamber of gas turbine | |
| JP2012201887A (en) | Top-combustion hot-blast furnace | |
| CN107327872A (en) | A kind of oblique spray ring stream toroidal combustion chamber | |
| CN107076418A (en) | Bypass type heat shield element | |
| CN206861593U (en) | A kind of gas-turbine combustion chamber | |
| CN110440290B (en) | Micro-mixing nozzle for gas turbine | |
| CN104612833A (en) | Gas turbine combustor | |
| CN202360225U (en) | Wave-type diffuser of combustion gas turbine | |
| US9010083B2 (en) | Apparatus for mixing fuel in a gas turbine | |
| CN107575865A (en) | A kind of Swirl tube flame burner of low-heat loss | |
| CN206861595U (en) | A kind of gas-turbine combustion chamber | |
| CN204593453U (en) | Gas-turbine combustion chamber | |
| CN217715047U (en) | Micro-premixing combustion chamber of gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: ENN 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 FANZHI ENERGY EQUIPMENT CO.,LTD. |
|
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170818 |