CN111623991B - Igniter position adjusting mechanism for gas turbine combustion chamber test - Google Patents
Igniter position adjusting mechanism for gas turbine combustion chamber test Download PDFInfo
- Publication number
- CN111623991B CN111623991B CN202010531242.9A CN202010531242A CN111623991B CN 111623991 B CN111623991 B CN 111623991B CN 202010531242 A CN202010531242 A CN 202010531242A CN 111623991 B CN111623991 B CN 111623991B
- Authority
- CN
- China
- Prior art keywords
- igniter
- axial
- gas turbine
- combustion chamber
- mounting seat
- 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.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Spark Plugs (AREA)
- Testing Of Engines (AREA)
Abstract
The invention is suitable for the technical field of combustion chamber test equipment, and particularly relates to an igniter position adjusting mechanism for a combustion chamber test of a gas turbine. The igniter position adjusting mechanism for the gas turbine combustion chamber test changes the traditional test mode of fixing the igniter position in the gas turbine combustion chamber test, the igniter mounting seat is pushed by the first axial adjusting screw rod to drive the igniter to move axially, so that the accurate adjustment in the axial direction is completed, the igniter is driven by the screw thread to move up and down relative to the igniter mounting seat, so that the accurate adjustment in the radial direction is completed, the adjustment of the axial position and the radial position of the igniter is realized in the gas turbine combustion chamber test, the ignition position is optimized, the ignition success rate is improved, and the ignition performance of the combustion chamber is enhanced.
Description
Technical Field
The invention belongs to the technical field of combustion chamber test equipment, and particularly relates to an igniter position adjusting mechanism for a combustion chamber test of a gas turbine.
Background
In a gas turbine combustion chamber, the ignition performance directly affects the operational safety and reliability of the entire gas turbine. The ignition position directly influences the ignition success rate, and is an important parameter influencing the ignition performance, so that the pneumatic layout and the structural design of the whole combustion chamber are influenced. With the increasing awareness of environmental protection, the emission standards established require that the industrial gas turbine must reduce the emission of nitrogen oxides (NOx), carbon monoxide (CO), and Unburned Hydrocarbons (UHC), and thus lean-burn premixing technology is widely used in the combustion chamber of the gas turbine. For lean-burn premixing technology, generally, the average gas flow velocity in the main combustion zone is high, the difficulty of successful ignition is high, the position of the recirculation zone reattachment zone in the main combustion zone is difficult to determine, and it is extremely challenging to correctly place the igniter to obtain optimal and efficient ignition performance.
Currently, the position of the igniter is generally determined through past experience or simulation of a flow field in the combustion chamber based on a CFD tool, for a newly designed combustion chamber, the past experience may have a certain deviation, and the CFD result is difficult to simulate a non-chemical equilibrium transient process of ignition, so that whether the igniter is placed at a position easy to ignite has great uncertainty, and the risk of ignition failure is increased.
The conventional test operation is to estimate the ignition point position, and to provide a small hole of a single igniter at the relevant position on the flame tube, and to test the ignition points one by one. This mode of operation requires stopping the test when switching ignition point positions, pulling the igniter out from one ignition point and then inserting another ignition point. The operation mode not only increases the test duration, but also has complicated operation steps, and frequent disassembly and assembly of the igniter increases the damage risk of the igniter.
Disclosure of Invention
The embodiment of the invention aims to provide an igniter position adjusting mechanism for a gas turbine combustion chamber test, and aims to solve the problems that an igniter needs to be frequently disassembled and assembled in the existing ignition position test, the steps are complex, and the igniter is easily damaged.
The embodiment of the invention is realized in such a way that the igniter position adjusting mechanism for the gas turbine combustion chamber test comprises an igniter, the igniter position adjusting mechanism for the gas turbine combustion chamber test further comprises an igniter assembly base, a first axial adjusting screw rod, an igniter position locking screw rod, a sealing cover and an igniter mounting seat, the igniter assembly base is fixed on the outer diameter of a flame tube, a guide groove is arranged at the upper end of the igniter assembly base along the axial direction of the flame tube, the igniter mounting seat is arranged in the guide groove in a sliding manner, the sealing cover is detachably connected to one side, away from the flame tube, of the igniter assembly base, the first axial adjusting screw rod arranged parallel to the axial direction of the flame tube is connected with the sealing cover in a matching manner, one end of the first axial adjusting screw rod is abutted against the igniter mounting seat, and the igniter position locking screw rod arranged perpendicular to the igniter mounting seat is connected to the upper end of the sealing cover in a matching manner, and the lower end is abutted against the upper end of the igniter mounting seat, and the igniter is connected on the igniter mounting seat in a matching way.
Preferably, a sealing ring is arranged between the sealing cover and the igniter assembly base.
Preferably, the igniter assembly base is welded to the outer diameter of the flame tube.
Preferably, one end of the first axial adjusting screw, which is far away from the igniter mounting seat, is connected with a first axial sealing nut in a matching manner, and one end of the sealing cover, which is close to the first axial sealing nut, is provided with a first axial sealing seat.
Preferably, the one end cooperation that the dead screw rod of some firearm position kept away from some firearm mount pad is connected with radial seal nut, and the one end that the sealed lid is close to radial seal nut is provided with radial seal seat.
Preferably, the outer diameter of the igniter is provided with threads, and the igniter is connected with the igniter mounting seat through the threads.
Preferably, one end, far away from the first axial adjusting screw, of the sealing cover is provided with a second axial adjusting screw, one end, far away from the igniter mounting seat, of the second axial adjusting screw is connected with a second axial sealing nut in a matched mode, and one end, close to the second axial sealing nut, of the sealing cover is provided with a second axial sealing seat.
According to the igniter position adjusting mechanism for the gas turbine combustion chamber test, the traditional test mode of fixing the igniter position in the gas turbine combustion chamber test is changed, the igniter mounting seat is pushed by the first axial adjusting screw rod to drive the igniter to move axially, so that accurate adjustment in the axial direction is completed, the igniter is driven by threads to move up and down relative to the igniter mounting seat, so that accurate adjustment in the radial direction is completed, adjustment of the axial position and the radial position of the igniter in the gas turbine combustion chamber test is realized, the ignition position is optimized, the ignition success rate is improved, and the ignition performance of the combustion chamber is enhanced.
Drawings
FIG. 1 is a schematic structural diagram of an igniter position adjustment mechanism for a gas turbine combustor test according to an embodiment of the present invention;
FIG. 2 is a schematic view illustrating an axial position adjustment process of an igniter position adjustment mechanism for a gas turbine combustor test according to an embodiment of the present invention;
FIG. 3 is a schematic view illustrating an axial position adjustment process of an igniter position adjustment mechanism for a gas turbine combustor test according to an embodiment of the present invention;
FIG. 4 is a schematic view illustrating an axial position adjustment process of an igniter position adjustment mechanism for a gas turbine combustor test according to an embodiment of the present invention;
FIG. 5 is a schematic view illustrating an axial position adjustment process of an igniter position adjustment mechanism for a gas turbine combustor test according to an embodiment of the present invention;
FIG. 6 is a schematic view illustrating an axial position adjustment process of an igniter position adjustment mechanism for a gas turbine combustor test according to an embodiment of the present invention;
FIG. 7 is a schematic view illustrating a radial position adjustment process of an igniter position adjustment mechanism for a gas turbine combustor test according to an embodiment of the present invention;
FIG. 8 is a schematic view illustrating a radial position adjustment process of an igniter position adjustment mechanism for a gas turbine combustor test according to an embodiment of the present invention;
FIG. 9 is a schematic view illustrating a radial position adjustment process of an igniter position adjustment mechanism for a gas turbine combustor test according to an embodiment of the present invention;
FIG. 10 is a schematic structural diagram of another embodiment of an igniter position adjustment mechanism for a gas turbine combustor test, according to the present invention.
In the drawings: 1. a flame tube; 2. an igniter; 3. an igniter mounting seat; 4. a sealing cover; 5. a first axial adjustment screw; 6. a first axial seal nut; 7. a first axial seal seat; 8. an igniter assembly base; 9. the screw rod is locked at the position of the igniter; 10. a radial seal nut; 11. a radial seal seat; 15. a second axial adjusting screw; 16. a second axial seal nut; 17. a second axial seal seat.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Specific implementations of the present invention are described in detail below with reference to specific embodiments.
As shown in fig. 1, a schematic structural diagram of an igniter position adjusting mechanism for a gas turbine combustion chamber test provided by an embodiment of the present invention includes an igniter 2, the igniter position adjusting mechanism for a gas turbine combustion chamber test further includes an igniter assembly base 8, a first axial adjusting screw 5, an igniter position locking screw 9, a sealing cover 4 and an igniter mounting base 3, the igniter assembly base 8 is fixed on an outer diameter of a flame tube 1, a guide groove is axially formed at an upper end of the igniter assembly base 8 along the flame tube 1, the igniter mounting base 3 is slidably disposed in the guide groove, the sealing cover 4 is detachably connected to a side of the igniter assembly base 8 away from the flame tube 1, the first axial adjusting screw 5 disposed parallel to the axis of the flame tube 1 is connected to the sealing cover 4 in a matching manner, and one end of the first axial adjusting screw abuts against the igniter mounting base 3, the igniter position locking screw 9 disposed perpendicular to the igniter mounting base 3 is connected to an upper end of the sealing cover 4 in a matching manner, the lower end of the igniter is abutted against the upper end of the igniter mounting seat 3, and the igniter 2 is connected to the igniter mounting seat 3 in a matching way.
In the embodiment of the invention, by changing the traditional test mode of fixing the igniter position in the gas turbine combustion chamber test, the igniter mounting seat 3 is pushed by the first axial adjusting screw rod 5 to drive the igniter 2 to move axially, so that the accurate adjustment in the axial direction is completed, and the igniter 2 is driven by the screw thread to move up and down relative to the igniter mounting seat 3, so that the accurate adjustment in the radial direction is completed, so that the adjustment of the axial position and the radial position of the igniter 2 is realized in the gas turbine combustion chamber test, the ignition position is optimized, the ignition success rate is improved, and the ignition performance of the combustion chamber is enhanced.
As shown in fig. 1, a sealing ring is provided between the sealing cap 4 and the igniter assembly base 8 as a preferred embodiment of the present invention.
In the embodiment of the invention, the sealing performance of the invention is enhanced and the safety is improved by arranging the sealing ring.
As shown in FIG. 1, the igniter assembly base 8 is welded to the outer diameter of the flame tube 1 as a preferred embodiment of the invention.
In the embodiment of the invention, the igniter assembly base 8 is fixed on the flame tube 1 in a welding mode, so that the connection stability is ensured, and the problem of looseness caused by multiple use is avoided.
As shown in fig. 1, as a preferred embodiment of the present invention, a first axial sealing nut 6 is fittingly connected to an end of the first axial adjusting screw 5 away from the igniter mounting seat 3, and a first axial sealing seat 7 is disposed at an end of the sealing cover 4 close to the first axial sealing nut 6.
As shown in fig. 1, as a preferred embodiment of the present invention, a radial sealing nut 10 is fittingly connected to an end of the igniter position locking screw 9 away from the igniter mounting seat 3, and a radial sealing seat 11 is provided at an end of the sealing cap 4 close to the radial sealing nut 10.
In the embodiment of the invention, during the experiment, the first axial sealing nut 6 is abutted against the first axial sealing seat 7, and the radial sealing nut 10 is abutted against the radial sealing seat 11, so that the integral sealing is completed, and the air tightness is ensured.
As shown in fig. 1, as a preferred embodiment of the present invention, the igniter 2 is provided with a screw thread at its outer diameter, and the igniter 2 is coupled to the igniter mounting seat 3 by the screw thread.
As shown in fig. 10, as a preferred embodiment of the present invention, a second axial adjusting screw 15 is disposed at an end of the sealing cover 4 away from the first axial adjusting screw 5, a second axial sealing nut 16 is fittingly connected to an end of the second axial adjusting screw 15 away from the igniter mounting seat 3, and a second axial sealing seat 17 is disposed at an end of the sealing cover 4 close to the second axial sealing nut 16.
In the embodiment of the invention, the first axial adjusting screw 5 and the second axial adjusting screw 15 are respectively arranged at the two ends of the sealing cover 4 far away from the igniter mounting seat 3, so that the axial position of the igniter mounting seat 3 can be adjusted in two directions.
As shown in fig. 2, 3, 4, 5 and 6, the axial adjustment process of the igniter 2 is to rotate the rod of the first axial adjustment screw 5 to push the igniter mounting seat 3 to move in the guide groove along the axial direction, thereby adjusting the axial position of the igniter 2 in the flame tube 1 within a wide range, and when the igniter 2 stays at a certain axial position to prepare for ignition of the combustion chamber, the screw 9 is locked by rotating the igniter position to apply pressure to the igniter mounting seat 3 in the radial direction, thereby fixing the igniter mounting seat 3 and the igniter 2. Through the operation, the position of the igniter 2 is continuously adjusted in the combustion chamber test process, and the optimal axial position of the igniter 2 is found to obtain the optimal combustion chamber ignition performance. And the real-time position of the igniter 2 is recorded by measuring the distance between the end surface of the first axial adjusting screw 5 and the end surface of the sealing cover 4. After the optimal axial position of some firearm 2 has been obtained, can split sealed lid 4 and some firearm subassembly base 8, adjust first axial adjusting screw 5, adjust some firearm 2 to the optimal axial position after, connect sealed lid 4 and some firearm subassembly base 8 again. Subsequently, the igniter 2 is turned to position the deadlocking screw to fix the position of the igniter mount 3 and the igniter 2. When other tests of the combustion chamber are to be carried out, such as a high-temperature high-pressure test, the first axial seal nut 6 and the first axial seal seat 7 are sealed in the axial direction, and the radial seal nut 10 and the radial seal seat 11 are connected together to seal in the radial direction.
As shown in fig. 7, 8 and 9, when adjusting, it is usually necessary that the ignition end face of the igniter 2 is flush with the inner wall of the flame tube 1, but due to the aerodynamic and thermal design of the combustion chamber, the ignition performance of the igniter 2 on the end face may be poor, and at this time, it is necessary to extend the end face of the igniter 2 into the flame tube 1, which means that the optimal ignition position of the igniter needs to be found in the radial direction. When the axial position of the igniter 2 is adjusted, the radial position of the igniter 2 on the igniter mounting seat 3 can be adjusted through threads, so that the adjustment of the radial position of the igniter 2 on the flame tube 1 is realized.
The invention provides an igniter position adjusting mechanism for a gas turbine combustion chamber test, and aims to solve the problems that an igniter needs to be frequently disassembled and assembled in the existing ignition position test, the steps are complex, and the igniter is easily damaged. And the axial position of the igniter 2 can be accurately adjusted at a plurality of positions in the test process, so that the function of searching the optimal axial position and the optimal radial position of the igniter 2 in the test process is realized, the ignition success rate is improved, and the ignition performance is improved.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (6)
1. The utility model provides a gas turbine combustion chamber is experimental with some firearm position control mechanism, including some firearm (2), a serial communication port, some firearm position control mechanism is experimental with some firearm still includes some firearm subassembly base (8), first axial adjusting screw (5), some firearm position lock screw (9), sealed lid (4) and some firearm mount pad (3), some firearm subassembly base (8) are fixed on the external diameter of flame tube (1), some firearm subassembly base (8) upper end is provided with the guide way along flame tube (1) axial, some firearm mount pad (3) slide to be set up in the guide way, sealed lid (4) can be dismantled to be connected in one side that flame tube (1) was kept away from in some firearm subassembly base (8), first axial adjusting screw (5) that is on a parallel with flame tube (1) axis sets up is connected with sealed lid (4) cooperation, one end of the igniter is abutted against the igniter mounting seat (3), an igniter position locking screw (9) which is arranged perpendicular to the igniter mounting seat (3) is connected to the upper end of the sealing cover (4) in a matching way, the lower end of the igniter position locking screw is abutted against the upper end of the igniter mounting seat (3), and the igniter (2) is connected to the igniter mounting seat (3) in a matching way; one end, far away from the igniter mounting seat (3), of the igniter position locking screw (9) is connected with a radial sealing nut (10) in a matching mode, and one end, close to the radial sealing nut (10), of the sealing cover (4) is provided with a radial sealing seat (11).
2. The igniter position adjusting mechanism for gas turbine combustor test as claimed in claim 1 wherein a sealing ring is provided between the sealing cover (4) and the igniter assembly base (8).
3. The igniter position adjusting mechanism for gas turbine combustor test as claimed in claim 1 wherein said igniter assembly base (8) is welded on the outer diameter of the flame tube (1).
4. The igniter position adjusting mechanism for the gas turbine combustion chamber test is characterized in that a first axial sealing nut (6) is connected to one end, far away from the igniter mounting seat (3), of the first axial adjusting screw (5), and a first axial sealing seat (7) is arranged at one end, close to the first axial sealing nut (6), of the sealing cover (4).
5. The igniter position adjusting mechanism for the gas turbine combustion chamber test as claimed in claim 1, wherein the igniter (2) is provided with a screw thread at an outer diameter, and the igniter (2) is connected with the igniter mounting seat (3) through the screw thread.
6. The igniter position adjusting mechanism for the gas turbine combustion chamber test is characterized in that a second axial adjusting screw (15) is arranged at one end, away from the first axial adjusting screw (5), of the sealing cover (4), a second axial sealing nut (16) is connected to one end, away from the igniter mounting seat (3), of the second axial adjusting screw (15) in a matched mode, and a second axial sealing seat (17) is arranged at one end, close to the second axial sealing nut (16), of the sealing cover (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010531242.9A CN111623991B (en) | 2020-06-11 | 2020-06-11 | Igniter position adjusting mechanism for gas turbine combustion chamber test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010531242.9A CN111623991B (en) | 2020-06-11 | 2020-06-11 | Igniter position adjusting mechanism for gas turbine combustion chamber test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111623991A CN111623991A (en) | 2020-09-04 |
| CN111623991B true CN111623991B (en) | 2022-05-10 |
Family
ID=72272256
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010531242.9A Active CN111623991B (en) | 2020-06-11 | 2020-06-11 | Igniter position adjusting mechanism for gas turbine combustion chamber test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111623991B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115614776A (en) * | 2021-07-13 | 2023-01-17 | 中国航发商用航空发动机有限责任公司 | Combustion chamber test device |
| CN114484498A (en) * | 2022-01-25 | 2022-05-13 | 中国航发贵阳发动机设计研究所 | Fan-shaped combustion chamber structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203615366U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Combustion chamber |
| CN204984608U (en) * | 2015-09-16 | 2016-01-20 | 中国航空工业集团公司沈阳发动机设计研究所 | Ignition electric nozzle mounting structure |
| CN106285956A (en) * | 2016-10-09 | 2017-01-04 | 中科合肥微小型燃气轮机研究院有限责任公司 | A kind of combination type scalable igniter |
| CN109083745A (en) * | 2018-09-26 | 2018-12-25 | 新奥能源动力科技（上海）有限公司 | A kind of igniter mounting device and miniature gas turbine |
| CN210242385U (en) * | 2019-07-16 | 2020-04-03 | 南京贤云机电科技有限公司 | Gas ignition device with high safety and stability performance |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6920762B2 (en) * | 2003-01-14 | 2005-07-26 | General Electric Company | Mounting assembly for igniter in a gas turbine engine combustor having a ceramic matrix composite liner |
| US8171719B2 (en) * | 2008-03-21 | 2012-05-08 | Siemens Energy, Inc. | Igniter assembly for a gas turbine |
-
2020
- 2020-06-11 CN CN202010531242.9A patent/CN111623991B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203615366U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Combustion chamber |
| CN204984608U (en) * | 2015-09-16 | 2016-01-20 | 中国航空工业集团公司沈阳发动机设计研究所 | Ignition electric nozzle mounting structure |
| CN106285956A (en) * | 2016-10-09 | 2017-01-04 | 中科合肥微小型燃气轮机研究院有限责任公司 | A kind of combination type scalable igniter |
| CN109083745A (en) * | 2018-09-26 | 2018-12-25 | 新奥能源动力科技（上海）有限公司 | A kind of igniter mounting device and miniature gas turbine |
| CN210242385U (en) * | 2019-07-16 | 2020-04-03 | 南京贤云机电科技有限公司 | Gas ignition device with high safety and stability performance |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111623991A (en) | 2020-09-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8407892B2 (en) | Methods relating to integrating late lean injection into combustion turbine engines | |
| US8919137B2 (en) | Assemblies and apparatus related to integrating late lean injection into combustion turbine engines | |
| CN111623991B (en) | Igniter position adjusting mechanism for gas turbine combustion chamber test | |
| EP2554906A2 (en) | Assemblies and apparatus related to integrating late lean injection into combustion turbine engines | |
| US7284378B2 (en) | Methods and apparatus for low emission gas turbine energy generation | |
| EP3816516A1 (en) | Low pollution combustor and combustion control method therefor | |
| CN103635750B (en) | Rational late lean injection | |
| US20150159877A1 (en) | Late lean injection manifold mixing system | |
| US20100180599A1 (en) | Insertable Pre-Drilled Swirl Vane for Premixing Fuel Nozzle | |
| CN113983494B (en) | Diffusion ratio intelligent adjustable gas turbine main combustion chamber multi-channel diffuser | |
| US20120111019A1 (en) | System and method for combustion dynamics control by acoustic control/cancellation of fuel flow fluctuation at fuel injection location | |
| US20160281989A1 (en) | Systems and methods for creating a seal about a liquid fuel injector in a gas turbine engine | |
| CN112362352B (en) | Axial compresses tightly turns into radial sealed tower swirler flow test device | |
| CN117386543A (en) | One-way valve jet structure and equivalent ratio active jet system thereof | |
| KR20180101395A (en) | Duct fuel injection | |
| CN205237887U (en) | A frock clamp for atomizing of aeroengine swirler is experimental | |
| CN107044638B (en) | Gas-liquid dual-purpose burner | |
| CN215863524U (en) | Oil inlet structure of fuel nozzle and fuel nozzle comprising same | |
| CN220852206U (en) | Coal injection pipe convenient to equipment | |
| CN105397680B (en) | Tool clamp for aircraft engine cyclone atomization test | |
| CN116106020B (en) | Fixing frame for measuring frequency of combustion chamber of gas turbine | |
| JPH0343534B2 (en) | ||
| CN220931232U (en) | Be applicable to industry energy-conserving radiant heating combustor | |
| CN204648320U (en) | A kind of supporting construction improving gas-turbine combustion chamber cover cap stability | |
| CN109140493B (en) | A method of reducing the GE combustion engine firing optimization of combustion pulsation and exhaust emission |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: No. 357, Shiqiao Road, Xiacheng District, Hangzhou, Zhejiang 310000 Patentee after: Hangzhou Steam Turbine Holding Co.,Ltd. Address before: No. 357, Shiqiao Road, Xiacheng District, Hangzhou, Zhejiang 310000 Patentee before: HANGZHOU TURBINE POWER GROUP CO.,LTD. |