CN113324262A - Coaxial staged gas fuel combustor head for low emission gas turbine - Google Patents
Coaxial staged gas fuel combustor head for low emission gas turbine Download PDFInfo
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- CN113324262A CN113324262A CN202110664719.5A CN202110664719A CN113324262A CN 113324262 A CN113324262 A CN 113324262A CN 202110664719 A CN202110664719 A CN 202110664719A CN 113324262 A CN113324262 A CN 113324262A
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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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
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
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Abstract
本发明属于燃气轮机燃烧室技术领域，具体涉及一种用于低排放燃气轮机的同轴分级气体燃料燃烧室头部。本发明中燃烧室头部末端与渐缩掺混段结合的一体化文氏管能有效的将火焰托举从而避免回火，无需布置吹扫空气或在高工况时无需打开值班级扩散燃料；中心值班级与第一级燃料管形成部分套管形式，减少了对来流空气的扰动，从而使各叶间流道气量分配均匀；第二级燃料管布置在第二级轮毂外侧，减小燃料管对第二级空气进气的影响；旋流空气与燃料分别在平直预混通道内预混后进入渐缩掺混通道加强掺混，从而燃料掺混更均匀，降低污染物排放。
The invention belongs to the technical field of gas turbine combustion chambers, and in particular relates to a coaxially graded gas fuel combustion chamber head for a low-emission gas turbine. In the present invention, the integrated venturi combined with the end of the combustion chamber head and the tapered blending section can effectively lift the flame to avoid flashback, and there is no need to arrange purge air or to open the duty stage to diffuse the fuel under high working conditions. ; The central duty stage and the first stage fuel pipe form part of the sleeve form, which reduces the disturbance of the incoming air, so that the air flow distribution between the blades is even; the second stage fuel pipe is arranged outside the second stage hub, reducing the The influence of the small fuel pipe on the air intake of the second stage; the swirling air and fuel are premixed in the straight premixing channel respectively and then enter the tapered mixing channel to strengthen the mixing, so that the fuel is mixed more uniformly and pollutant emissions are reduced .
Description
Technical Field
The invention belongs to the technical field of gas turbine combustors, and particularly relates to a coaxial staged gas fuel combustor head for a low-emission gas turbine.
Background
Gas turbine pollutant emission characteristics are primarily related to the combustion mode and combustion characteristics within the combustion chamber. The pollutants mainly comprise nitrogen oxides, carbon monoxide, unburned hydrocarbons and sulfur oxides, wherein the nitrogen oxides are one of the main sources of pollutants generated by combustion of the gas turbine. The formation mechanism of thermal nitrogen oxides plays a dominant role in the formation of NOx in the combustion chamber, and therefore reducing the temperature of the main combustion zone in the combustion chamber is an effective means for reducing nitrogen oxide emissions. The lean premixed combustion technology can effectively reduce the combustion temperature of the main combustion zone, and further reduce the emission of nitrogen oxides. Aiming at the lean premixed combustion technology, the coaxial graded lean premixed combustion technology proposed by domestic and foreign researchers can effectively control the combustion temperature in the combustion chamber, thereby reducing the generation of pollutants while ensuring the combustion stability.
In recent years, domestic patent applications for low pollution burners have been made. Patent 201710509255.1 discloses a gas turbine low pollution combustor list whirl head structure, and thereby central whirl air mixes with central natural gas, and outer wall non-whirl air mixes with outer wall natural gas and further mixes in natural gas-air mixing chamber, and its mode of solving the spontaneous combustion of head sets up the tangential air inlet aperture on the swirler outer wall. Patent 201910312864.X provides a coaxial staged swirl and blending integrated head for a gaseous fuel combustor. The three-stage mixing/cyclone integrated swirler comprises a three-stage mixing/cyclone integrated swirler, a fuel guide pipe, a fuel cavity and a fuel support plate, and the mode of preventing backfire is that a divergent purging channel is arranged in the first-stage mixing/cyclone integrated swirler. The patent 202010034769.0 discloses a center-graded lean premixed low-pollution combustion chamber, the duty grade is located at the center and consists of a film-forming air atomizing nozzle and a two-stage swirler, the center-graded zoning combustion technology is adopted, the problems of flame stability under a small working condition and pollution emission under a large working condition can be effectively solved, and the fuel used by the patent is fuel oil and cannot be applied to gas fuel.
Disclosure of Invention
It is an object of the present invention to provide a coaxial staged gas fuel combustor head for a low emission gas turbine engine.
The purpose of the invention is realized by the following technical scheme: comprises an on-duty fuel flow path 5, a first stage hub 14, a second stage hub 24, a first stage fuel conduit 61 and a second stage fuel conduit 71; the inner side space of the inner wall of the first-stage hub 14 consists of a first-stage straight premixing channel 1 and a first-stage tapered mixing channel 3, the front end of the first-stage tapered mixing channel 3 is communicated with the first-stage straight premixing channel 1, and the tail end of the first-stage tapered mixing channel 3 is provided with a first-stage venturi 31; the inner side space of the inner wall of the second-stage hub 24 consists of a second-stage straight premixing channel 2 and a second-stage tapered mixing channel 4, the front end of the second-stage tapered mixing channel 4 is communicated with the second-stage straight premixing channel 2, and the tail end of the second-stage tapered mixing channel 4 is provided with a second-stage venturi 41; the duty-stage fuel flow path comprises a duty-stage fuel conduit 51 and a central blunt body 52; the central blunt body 52 is arranged in the first-stage straight premixing channel 1, and a ring of first swirl blades 13 are arranged between the central blunt body 52 and the first-stage hub 14; a first-stage fuel cavity 62 is arranged between the inner wall and the outer wall of the first-stage hub 14, first-stage fuel jet holes 63 are uniformly distributed on the surface of the inner wall of the first-stage hub 14, and the first-stage fuel jet holes 63 are communicated with the first-stage fuel cavity 62; the second-stage hub 24 is integrally positioned on the outer side of the outer wall of the first-stage hub 14, a circle of second swirl blades 23 are arranged between the first-stage hub 14 and the second-stage hub 24, the second swirl blades 23 are all positioned in the second-stage straight premixing channel 2, a swirl blade fuel cavity 73 is arranged inside the second swirl blades 23, a second-stage fuel jet hole 74 is formed in the surface of each second swirl blade 23, and the second-stage fuel jet hole 74 is communicated with the second-stage tapered mixing channel 4; a second-stage fuel cavity 72 is arranged between the inner wall and the outer wall of the second-stage hub 24; the second stage fuel conduit 71 is integrally positioned outside the outer wall of the second stage hub 24, and the second stage fuel conduit 71 is communicated with the second stage fuel cavity 72 through a fuel conduit; the first stage fuel conduit 61 is arranged in front of the head end of the first stage hub 14, and the first stage fuel conduit 61 is communicated with the first stage fuel cavity 62 through a fuel branch; one end of the duty-level fuel conduit 51 is connected with the front end of the central blunt body 52, and the other end extends out of the bottom of the first-level fuel conduit 61; the central blunt body 52 is internally provided with an on-duty fuel cavity 53, an on-duty fuel jet hole 54 is formed along the slope surface and the end surface of the central blunt body 52, and the on-duty fuel jet hole 54 is communicated with the first-stage tapered mixing channel 3.
The present invention may further comprise:
the outlet end surface of the first-stage venturi 31 is flush with the throat part of the second-stage venturi 41.
The quantity of the on-duty fuel jet holes 54 formed in the slope surface and the end surface of the central blunt body 52 is the same as that of the first swirl vanes 13.
The first swirl vanes 13 and the second swirl vanes 23 are lossless straight vanes, the swirl angle of the vanes is 30-60 degrees, and the number of the vanes is 6-12.
The invention has the beneficial effects that:
the integrated venturi combined with the tapered mixing section at the tail end of the head of the combustion chamber can effectively lift the flame so as to avoid backfire, and purge air does not need to be arranged or class-wide diffusion fuel does not need to be opened under high working conditions; the center class and the first-stage fuel pipe form a partial sleeve form, so that disturbance to incoming flow air is reduced, and the air quantity distribution of flow passages among the blades is uniform; the second-stage fuel pipe is arranged outside the second-stage hub, so that the influence of the fuel pipe on the air intake of the second stage is reduced; the swirling air and the fuel are premixed in the straight premixing channel respectively and then enter the tapered mixing channel to be mixed, so that the fuel is mixed more uniformly, and the pollutant emission is reduced.
Drawings
Fig. 1 is a general schematic view (from the front) of the present invention.
Fig. 2 is a cross-sectional view of the present invention.
FIG. 3 is a schematic view of a swirl vane fuel chamber within a second swirl vane of the present invention.
Fig. 4 is a general schematic view of the present invention (from the back).
FIG. 5 is a schematic view of a combustion chamber of a model to which the present invention is applied.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
The invention designs a coaxial staged gas fuel combustion chamber head for a low-emission gas turbine, which consists of a fuel pipe, two stages of straight premixing sections, a stage of center class, fuel cavities of all stages, a reducing mixing section and an integrated venturi; the fuel and the air are premixed in the straight premixing section and then further mixed in the reducing mixing section, and a backflow area is formed under the action of the swirl vanes. The fuel is supplied by the duty fuel flow path and the first stage fuel flow path under the ignition working condition, the supply of the first stage fuel is gradually increased along with the rise of the working condition, the supply of the second stage fuel is opened, the supply of the duty fuel is gradually reduced until the duty fuel is closed, and the fuel supply of the first stage and the duty can stabilize the combustion flame and quickly ignite the second stage fuel. The tapered blending section and the integrated venturi can effectively avoid backfire. The burner is simple in structure, can realize stable combustion and has the characteristics of high combustion efficiency, low pollutant discharge and the like.
A coaxial staged gas fuel combustor head for a low emission gas turbine engine includes an on-duty stage fuel flow path 5, a first stage hub 14, a second stage hub 24, a first stage fuel conduit 61, a second stage fuel conduit 71;
the inner side space of the inner wall of the first-stage hub 14 consists of a first-stage straight premixing channel 1 and a first-stage tapered mixing channel 3, the front end of the first-stage tapered mixing channel 3 is communicated with the first-stage straight premixing channel 1, and the tail end of the first-stage tapered mixing channel 3 is provided with a first-stage venturi 31;
the inner side space of the inner wall of the second-stage hub 24 consists of a second-stage straight premixing channel 2 and a second-stage tapered mixing channel 4, the front end of the second-stage tapered mixing channel 4 is communicated with the second-stage straight premixing channel 2, and the tail end of the second-stage tapered mixing channel 4 is provided with a second-stage venturi 41;
the duty-stage fuel flow path comprises a duty-stage fuel conduit 51 and a central blunt body 52; the central blunt body 52 is arranged in the first-stage straight premixing channel 1, and a ring of first swirl blades 13 are arranged between the central blunt body 52 and the first-stage hub 14; a first-stage fuel cavity 62 is arranged between the inner wall and the outer wall of the first-stage hub 14, first-stage fuel jet holes 63 are uniformly distributed on the surface of the inner wall of the first-stage hub 14, and the first-stage fuel jet holes 63 are communicated with the first-stage fuel cavity 62;
the second-stage hub 24 is integrally positioned on the outer side of the outer wall of the first-stage hub 14, a circle of second swirl blades 23 are arranged between the first-stage hub 14 and the second-stage hub 24, the second swirl blades 23 are all positioned in the second-stage straight premixing channel 2, a swirl blade fuel cavity 73 is arranged inside the second swirl blades 23, a second-stage fuel jet hole 74 is formed in the surface of each second swirl blade 23, and the second-stage fuel jet hole 74 is communicated with the second-stage tapered mixing channel 4; a second-stage fuel cavity 72 is arranged between the inner wall and the outer wall of the second-stage hub 24;
the second stage fuel conduit 71 is integrally positioned outside the outer wall of the second stage hub 24, and the second stage fuel conduit 71 is communicated with the second stage fuel cavity 72 through a fuel conduit; the first stage fuel conduit 61 is arranged in front of the head end of the first stage hub 14, and the first stage fuel conduit 61 is communicated with the first stage fuel cavity 62 through a fuel branch; one end of the duty-level fuel conduit 51 is connected with the front end of the central blunt body 52, and the other end extends out of the bottom of the first-level fuel conduit 61; the central blunt body 52 is internally provided with an on-duty fuel cavity 53, an on-duty fuel jet hole 54 is formed along the slope surface and the end surface of the central blunt body 52, and the on-duty fuel jet hole 54 is communicated with the first-stage tapered mixing channel 3.
Wherein, the outlet end surface of the first-stage venturi 31 is flush with the throat part of the second-stage venturi 41.
The on-duty fuel jet holes 54 are formed along the slope surface and the end surface of the central blunt body 52, the aperture size is 1-2 mm, and the number of the blunt body slope surface jet holes and the end surface jet holes is the same as that of the first-stage blades.
The first-stage fuel jet holes 63 are uniformly distributed on the surface of the inner wall of the first-stage hub 14, and the aperture is 1-1.5 mm.
The second stage fuel jet holes 74 are formed in the surface of the second swirl vane 23, and the hole diameter is 0.8 mm-1.5 mm.
The first swirl vanes 13 and the second swirl vanes 23 are lossless straight vanes, the swirl angle of the vanes is 30-60 degrees, and the number of the vanes is 6-12.
The invention has the beneficial effects that:
the integrated venturi combined with the tapered mixing section at the tail end of the head of the combustion chamber can effectively lift the flame so as to avoid backfire, and purge air does not need to be arranged or class-wide diffusion fuel does not need to be opened under high working conditions; the center class and the first-stage fuel pipe form a partial sleeve form, so that disturbance to incoming flow air is reduced, and the air quantity distribution of flow passages among the blades is uniform; the second-stage fuel pipe is arranged outside the second-stage hub, so that the influence of the fuel pipe on the air intake of the second stage is reduced; the swirling air and the fuel are premixed in the straight premixing channel respectively and then enter the tapered mixing channel to be mixed, so that the fuel is mixed more uniformly, and the pollutant emission is reduced.
Example 1:
as shown in fig. 1-5, the present invention provides a coaxial staged gas fuel combustor head for a low emission gas turbine engine, comprising a first stage straight premix passage 1, a second stage straight premix passage 2, a first stage tapered blend passage 3, a second stage tapered blend passage 4, an on-duty stage fuel flow path 5, a first stage fuel flow path 6, and a second stage fuel flow path 7. The fuel flow of each stage can be independently controlled, so that the combustion temperature in the flame tube is controlled, and the pollution is reduced.
A first-stage fuel jet hole 63 and a first-stage air inlet 12 are formed in the first-stage straight premixing channel 1, one end of the first-stage tapered mixing channel 3 is communicated with the first-stage straight premixing channel 1, and a first-stage venturi 31 is arranged at the other end of the first-stage tapered mixing channel; a first-stage air flow path is formed by a first-stage air inlet 12, a first-stage straight premixing channel 1, a first-stage tapered mixing channel 3 and a first-stage venturi 31; the first stage straight section premix passage 1 is located between the center bluff body 52 and the first stage hub 14. A second-stage fuel jet hole 74 and a second-stage air inlet 22 are formed in the second-stage straight premixing channel 2, one end of the second-stage tapered mixing channel 4 is communicated with the second-stage straight premixing channel 2, and a second-stage venturi 41 is arranged at the other end of the second-stage tapered mixing channel; the end surface of the first-stage venturi 31 is flush with the throat part of the second-stage venturi 41; the second stage straight section premix passage 2 is located between the first stage hub 14 and the second stage hub 24; the second stage air inlet 22, the second stage straight premixing passage 2, the second stage tapered blending passage 4 and the second stage venturi 41 form a second stage air flow path. Wherein, the two-stage straight premixing channels 1 and 2 are provided with a first-stage swirl blade 13 and a second-stage swirl blade 23, the number of the first-stage swirl blade 13 and the number of the second-stage swirl blade 23 are 6 and 12 in sequence, and the thickness of the blades is 2mm and 3mm in sequence. The two stages all adopt lossless straight blades, the mounting angles of the swirl blades are both 40 degrees, and the two-stage premixing stage swirl numbers are respectively 0.6 and 0.7. The air forms rotational flow under the action of the rotational flow blades through the straight premixing channel, then the air is accelerated in the reducing mixing channel and is expanded through the venturi to form a backflow zone, and the venturi can effectively prevent tempering.
The class fuel conduit 51, the class fuel chamber 53 and the class fuel jet hole 54 constitute a class fuel flow path in the present example; the duty-level fuel guide pipe 51 is positioned in front of the central blunt body 52 and connected with the central blunt body 52, the duty-level fuel cavity 53 is positioned inside the central blunt body 52, the duty-level fuel jet hole is positioned at the tail end of the central blunt body 52, the circumferential hole diameter is 6, the end surface hole diameter is 1.5mm, and the arrangement mode can effectively form diffusion flame under the low working condition so as to enable the combustion to be stable.
The first stage fuel conduit 61, the first stage fuel cavity 62 and the first stage fuel jet orifice 63 constitute a first stage fuel flow path in this example; the fuel of the first-stage premixing stage enters a first-stage fuel cavity 62 from a fuel inlet through a fuel conduit 61 and is divided into four fuel conduit branches, and is ejected from a first-stage hub jet hole 63. The first-stage fuel guide pipe 61 is arranged in front of the first-stage hub 14 and coaxial with the duty-stage fuel guide pipe 51, the first-stage fuel cavity 62 is positioned in the first-stage hub 14, the first-stage hub jet holes 63 are uniformly distributed on the inner side of the first-stage hub 14, 5 holes are arranged in flow channels among blades, and the hole diameter is 1.5 mm. The first-stage hub jet hole 63 is arranged in a manner that fuel can be effectively prevented from gathering at the tail end of the central blunt body 52, so that a backfire phenomenon can be avoided.
In this example, the second stage fuel conduit 71, the second stage fuel cavity 72, the swirl vane fuel cavity 73, and the second stage fuel jet hole 74 form a second stage fuel flow path, the second stage fuel conduit 71 is located outside the second stage hub 24, the second stage fuel cavity 72 is located inside the second stage hub 24, the second stage swirl vane 23 fuel cavity is located inside the swirl vane, the second stage fuel jet hole is located on the swirler vane, the second stage fuel jet hole has a hole diameter of 1mm, 1.2mm, 1.5mm, so that the fuel can be mixed more uniformly to avoid local high temperature area in the combustion chamber.
The specific working process of the combustion chamber head fuel circuit is as follows:
the fuel is supplied by the duty fuel flow path and the first-stage fuel flow path under the ignition working condition, the supply of the first-stage fuel flow path is gradually increased along with the increase of the working condition, the second-stage fuel flow path is opened, the supply of the duty fuel flow path is gradually reduced until the duty fuel is closed, the fuel supply of the first stage and the duty can stabilize the combustion flame and quickly ignite the second-stage fuel, and therefore the generation of pollutants is reduced while the stable combustion is ensured.
The specific working process of the air circuit at the head part of the combustion chamber is as follows:
air is distributed from the two-stage air inlet to enter the two-stage straight premixing section and forms rotary flow under the action of the swirl vanes, then enters the tapered mixing channel for acceleration, and is expanded in the expansion section of the integrated venturi, so that a backflow zone can be formed in the flame tube while tempering is avoided.
As shown in FIG. 5, the present invention is applied to a model combustor, and when installed, a bolt hole 18 for fixing can be opened at the second stage tapered mixing passage 4 as shown in FIG. 2. The invention can be applied to an annular combustion chamber and a ring tube combustion chamber, and the size of the head of the rotary combustion chamber is adjusted according to the specific structure and the size of the gas turbine in practical application.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
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| CN113803743A (en) * | 2021-09-15 | 2021-12-17 | 中国联合重型燃气轮机技术有限公司 | Secondary combustion device and combustion chamber and gas turbine with same |
| CN114183772A (en) * | 2021-11-30 | 2022-03-15 | 哈尔滨工程大学 | A high-efficiency and low-emission combustor head with hydrogen premix |
| CN115264533A (en) * | 2022-07-24 | 2022-11-01 | 哈尔滨工程大学 | Natural gas coaxial staged combustion chamber adopting center ignition and combustion method |
| CN115264531A (en) * | 2022-06-30 | 2022-11-01 | 哈尔滨工程大学 | A split lobe swirl vane and swirler suitable for gas fuel |
| CN115597087A (en) * | 2022-08-12 | 2023-01-13 | 中国航发沈阳发动机研究所（Cn） | Hydrogen fuel combustion chamber head structure of expansion type jet hole |
| CN116293805A (en) * | 2023-04-03 | 2023-06-23 | 西北工业大学 | A multi-swirler inlet head structure of a hydrogen-doped gas turbine |
| CN116358000A (en) * | 2023-04-10 | 2023-06-30 | 西安热工研究院有限公司 | A double-swirl premix nozzle and a single-tube combustor structure in which fuel is injected from blades |
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Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4899538A (en) * | 1987-11-20 | 1990-02-13 | Sundstrand Corporation | Hot gas generator |
| US20020014078A1 (en) * | 2000-07-13 | 2002-02-07 | Shigemi Mandai | Fuel discharge member, a burner, a premixing nozzle of a combustor, a combustor, a gas turbine, and a jet engine |
| US6381964B1 (en) * | 2000-09-29 | 2002-05-07 | General Electric Company | Multiple annular combustion chamber swirler having atomizing pilot |
| FR2853129A1 (en) * | 2003-03-28 | 2004-10-01 | Salvarem | Decontamination of surfaces, e.g. radioactive decontamination, involves mixing acid aqueous cerium-IV solution and aqueous non-ionic surfactant solution in a foam generator and applying the foam to the surface |
| CN101158476A (en) * | 2006-10-05 | 2008-04-09 | 通用电气公司 | Method and apparatus for reducing gas turbine engine emissions |
| CN101220953A (en) * | 2007-01-10 | 2008-07-16 | 通用电气公司 | Fuel-flexible triple-counter-rotating swirler and method of use |
| CN101893242A (en) * | 2009-04-16 | 2010-11-24 | 通用电气公司 | Dual orifice pilot fuel injector |
| CN102032598A (en) * | 2010-12-08 | 2011-04-27 | 北京航空航天大学 | Circumferentially graded low-pollution combustion chamber with multiple middle spiral-flow flame stabilizing stages |
| EP2497922A2 (en) * | 2011-03-10 | 2012-09-12 | Delavan Inc. | Systems and methods for cooling a staged airblast fuel injector |
| CN103175223A (en) * | 2013-03-19 | 2013-06-26 | 哈尔滨工程大学 | Gas circuit axial grading type dual-fuel nozzle |
| CN103196159A (en) * | 2013-03-18 | 2013-07-10 | 哈尔滨工程大学 | Annular grading trapped vortex combustor |
| CN103939943A (en) * | 2014-03-05 | 2014-07-23 | 哈尔滨工程大学 | Double-swirl dual-fuel nozzle used for chemical regenerative cycle |
| CN105042638A (en) * | 2015-06-25 | 2015-11-11 | 中国科学院工程热物理研究所 | Two-oil-way three-air-way multi-rotational-flow air atomizing nozzle structure |
| CN106247405A (en) * | 2015-06-10 | 2016-12-21 | 通用电气公司 | Membranae praeformativa air blast (PAB) guide for low emission combustor |
| CN205939145U (en) * | 2016-08-26 | 2017-02-08 | 中能服能源科技股份有限公司 | Low NOx gas combustion ware structure |
| CN107543201A (en) * | 2017-07-25 | 2018-01-05 | 西北工业大学 | A kind of oil-poor directly injection and mixing low pollution combustor |
| CN108980891A (en) * | 2018-04-27 | 2018-12-11 | 北京航空航天大学 | A kind of center classification low emission combustor head with pneumatic water conservancy diversion and anti-backfire structure |
| CN110056906A (en) * | 2019-04-18 | 2019-07-26 | 哈尔滨工程大学 | For the coaxial classification eddy flow of gaseous fuel combustion room and the integrated head of blending |
| CN110822478A (en) * | 2019-11-08 | 2020-02-21 | 哈尔滨工程大学 | A variable geometry cyclone with adjustable swirl angle |
| US10679829B1 (en) * | 2011-09-07 | 2020-06-09 | Nano-Product Engineering, LLC | Reactors and methods for making diamond coatings |
-
2021
- 2021-06-16 CN CN202110664719.5A patent/CN113324262B/en active Active
Patent Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4899538A (en) * | 1987-11-20 | 1990-02-13 | Sundstrand Corporation | Hot gas generator |
| US20020014078A1 (en) * | 2000-07-13 | 2002-02-07 | Shigemi Mandai | Fuel discharge member, a burner, a premixing nozzle of a combustor, a combustor, a gas turbine, and a jet engine |
| US6381964B1 (en) * | 2000-09-29 | 2002-05-07 | General Electric Company | Multiple annular combustion chamber swirler having atomizing pilot |
| FR2853129A1 (en) * | 2003-03-28 | 2004-10-01 | Salvarem | Decontamination of surfaces, e.g. radioactive decontamination, involves mixing acid aqueous cerium-IV solution and aqueous non-ionic surfactant solution in a foam generator and applying the foam to the surface |
| CN101158476A (en) * | 2006-10-05 | 2008-04-09 | 通用电气公司 | Method and apparatus for reducing gas turbine engine emissions |
| CN101220953A (en) * | 2007-01-10 | 2008-07-16 | 通用电气公司 | Fuel-flexible triple-counter-rotating swirler and method of use |
| CN101893242A (en) * | 2009-04-16 | 2010-11-24 | 通用电气公司 | Dual orifice pilot fuel injector |
| CN102032598A (en) * | 2010-12-08 | 2011-04-27 | 北京航空航天大学 | Circumferentially graded low-pollution combustion chamber with multiple middle spiral-flow flame stabilizing stages |
| EP2497922A2 (en) * | 2011-03-10 | 2012-09-12 | Delavan Inc. | Systems and methods for cooling a staged airblast fuel injector |
| US10679829B1 (en) * | 2011-09-07 | 2020-06-09 | Nano-Product Engineering, LLC | Reactors and methods for making diamond coatings |
| CN103196159A (en) * | 2013-03-18 | 2013-07-10 | 哈尔滨工程大学 | Annular grading trapped vortex combustor |
| CN103175223A (en) * | 2013-03-19 | 2013-06-26 | 哈尔滨工程大学 | Gas circuit axial grading type dual-fuel nozzle |
| CN103939943A (en) * | 2014-03-05 | 2014-07-23 | 哈尔滨工程大学 | Double-swirl dual-fuel nozzle used for chemical regenerative cycle |
| CN106247405A (en) * | 2015-06-10 | 2016-12-21 | 通用电气公司 | Membranae praeformativa air blast (PAB) guide for low emission combustor |
| CN105042638A (en) * | 2015-06-25 | 2015-11-11 | 中国科学院工程热物理研究所 | Two-oil-way three-air-way multi-rotational-flow air atomizing nozzle structure |
| CN205939145U (en) * | 2016-08-26 | 2017-02-08 | 中能服能源科技股份有限公司 | Low NOx gas combustion ware structure |
| CN107543201A (en) * | 2017-07-25 | 2018-01-05 | 西北工业大学 | A kind of oil-poor directly injection and mixing low pollution combustor |
| CN108980891A (en) * | 2018-04-27 | 2018-12-11 | 北京航空航天大学 | A kind of center classification low emission combustor head with pneumatic water conservancy diversion and anti-backfire structure |
| CN110056906A (en) * | 2019-04-18 | 2019-07-26 | 哈尔滨工程大学 | For the coaxial classification eddy flow of gaseous fuel combustion room and the integrated head of blending |
| CN110822478A (en) * | 2019-11-08 | 2020-02-21 | 哈尔滨工程大学 | A variable geometry cyclone with adjustable swirl angle |
Non-Patent Citations (1)
| Title |
|---|
| 宋少鹏: "燃料分级与烟气再循环对天然气低氮燃烧特性影响机理", 《中国电机工程学报》 * |
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| CN114183772A (en) * | 2021-11-30 | 2022-03-15 | 哈尔滨工程大学 | A high-efficiency and low-emission combustor head with hydrogen premix |
| CN115264531A (en) * | 2022-06-30 | 2022-11-01 | 哈尔滨工程大学 | A split lobe swirl vane and swirler suitable for gas fuel |
| CN115264531B (en) * | 2022-06-30 | 2023-04-07 | 哈尔滨工程大学 | A split lobe swirl vane and swirler suitable for gas fuel |
| CN115264533A (en) * | 2022-07-24 | 2022-11-01 | 哈尔滨工程大学 | Natural gas coaxial staged combustion chamber adopting center ignition and combustion method |
| CN115597087A (en) * | 2022-08-12 | 2023-01-13 | 中国航发沈阳发动机研究所（Cn） | Hydrogen fuel combustion chamber head structure of expansion type jet hole |
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| CN116293805A (en) * | 2023-04-03 | 2023-06-23 | 西北工业大学 | A multi-swirler inlet head structure of a hydrogen-doped gas turbine |
| CN116358000A (en) * | 2023-04-10 | 2023-06-30 | 西安热工研究院有限公司 | A double-swirl premix nozzle and a single-tube combustor structure in which fuel is injected from blades |
| CN116428612A (en) * | 2023-04-12 | 2023-07-14 | 南京航空航天大学 | Cyclone capable of preventing backfire phenomenon |
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