CN108592084A - A kind of main combustion stage matches the low emission combustor head of blade injection structure using the pre- diaphragm plate of axial rotational flow - Google Patents
A kind of main combustion stage matches the low emission combustor head of blade injection structure using the pre- diaphragm plate of axial rotational flow Download PDFInfo
- Publication number
- CN108592084A CN108592084A CN201810472110.6A CN201810472110A CN108592084A CN 108592084 A CN108592084 A CN 108592084A CN 201810472110 A CN201810472110 A CN 201810472110A CN 108592084 A CN108592084 A CN 108592084A
- Authority
- CN
- China
- Prior art keywords
- main combustion
- combustion stage
- blade
- diaphragm plate
- rotational flow
- 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.)
- Granted
Links
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
Abstract
The invention discloses a kind of main combustion stages using the low emission combustor head of the pre- diaphragm plate matching blade injection structure of axial rotational flow.The head uses center grading design, is made of main combustion stage and pre-combustion grade two parts.Main combustion stage has the pre- membrane structure of axial rotational flow, and wherein main combustion stage cyclone main function is：So that air is generated eddy flow, and fuel oil is sprayed into air by the aperture in blade, fuel oil is atomized and blends in rotational flow air；The pre- film blade of axial rotational flow and the fuel injection hole face in swirler blades improve the atomizing effect of main combustion stage fuel oil, to reach higher low emission performance for carrying out pre- film atomization to fuel oil.Pre-combustion grade carries out stablizing flame using diffusion flame, and main combustion stage carries out fuel-oil atmozation premixed combustion using the structure in the present invention, and then improves the low emission performance of combustion chamber.
Description
Technical field
The present invention relates to the technical field of turbulent burner, more particularly to a kind of main combustion stage uses the pre- diaphragm plate of axial rotational flow
Low emission combustor head with blade injection structure.
Background technology
Aero-engine is referred to as the bright jewel of modern industry imperial crown, and design and manufacture level can most represent a state
The whole industrial level of family, aero-engine are divided into dual-use two kinds according to purposes.Military aero-engine pursuit is had an high regard for
Than using high temperature rise combustor, civilian engine chases efficiency and environmental protection uses low emission combustor.With Civil Aviation Industry
Development and the raising of environmental consciousness, the following disposal of pollutants to advanced gas-turbine combustion chamber propose more harsh requirement.
Center fractional combustion room is one of the main direction of development of low emission combustor now, and combustion chamber is using center point
The combustion method of grade, pre-combustion grade use diffusion combustion, have preferable point extinguishment characteristics；Main combustion stage is premixed combustion, is used
Cyclone reinforces the blending of fuel oil and air, can reduce the disposal of pollutants of big operating mode lower combustion chamber.
Oil stream amount in combustion chamber in main combustion stage is mainly sprayed from main combustion stage, and main combustion stage is premixed combustion, so
Main combustion stage intermediate fuel oil is atomized and influences the performance of burning with the quality of the blending of air and then influence the quality of emission performance.Therefore
And the number of the discharge capacity of main combustion stage determines the quality of entire combustion chamber emission performance.
In conclusion the present invention, which based on practical implementation, devises a kind of main combustion stage, uses the pre- diaphragm plate of axial rotational flow
The low emission combustor head of blade injection structure is matched, this head main combustion stage can make using the pre- diaphragm plate of matching swirl vane
Fuel oil is ejected on pre- diaphragm plate and is formed a film for the first time, preferably can be atomized and blend, and then further decrease the row of pollutant
It puts.
Invention content
The technical problem to be solved by the present invention is to：For the main combustion stage fuel-oil atmozation of center fractional combustion room and disposal of pollutants
Problem, it is proposed that a kind of main combustion stage matches the low emission combustor head of blade injection structure using the pre- diaphragm plate of axial rotational flow.Institute
That states head installs the pre- film blade of axial rotational flow additional at main combustion stage swirler blades, makes to spray from the fuel injection hole on blade
Fuel oil beat on pre- film blade and form oil film, oil film carries out broken atomization after leaving blade.The pre- diaphragm plate blade phase of axial rotational flow
For head compared with no pre- diaphragm plate blade, atomization and mixing effect are improved.By improve atomization and blending efficiency come
Reach higher premixing effect, and then reaches lower emission effect.
The technical solution adopted by the present invention is：A kind of main combustion stage is using the pre- diaphragm plate matching blade injection structure of axial rotational flow
Low emission combustor head, main combustion stage match blade injection structure using the pre- diaphragm plate of axial rotational flow；Head is using center classification
Structure is made of main combustion stage, pre-combustion grade, wherein the pre- diaphragm plate blade of main combustion stage swirl vane, main combustion stage axial rotational flow, main combustion stage set
Cylinder, main combustion stage inner ring pass sequentially through welding and form entire main combustion stage, and wherein main combustion stage swirl vane and main combustion stage axial rotational flow is pre-
Diaphragm plate blade is by being sleeved in main combustion stage inner ring and welding together after being welded to connect, then by main combustion stage sleeve and main combustion stage
Swirl vane top welds；Pre-combustion grade includes pre-combustion grade swirler blades, pre-combustion grade nozzle outer shroud, pre-combustion grade nozzle,
Middle pre-combustion grade nozzle outer shroud is connect by screw thread with pre-combustion grade nozzle, and then pre-combustion grade swirler blades are sleeved on outside pre-combustion grade nozzle
On ring, interstage section, by being welded to connect, is then threadedly connect with main combustion stage inner ring, shape with pre-combustion grade swirler blades
The low emission combustor head of blade injection structure is matched using the pre- diaphragm plate of axial rotational flow at main combustion stage.
Wherein, the pre- diaphragm plate blade of main combustion stage axial rotational flow is fired with the angle of main combustion stage swirl vane axis at -30 °~60 °
Oil impinges upon formation oil film on pre- film blade and is atomized at an angle after being sprayed by blade spray-hole, improve atomization effect
Rate.
Wherein, the pre- diaphragm plate blade of main combustion stage axial rotational flow and the radial angle of main combustion stage swirl vane are swirler blades diameter
To the 20%~80% of angle, then air line distance of the pre- film blade apart from fuel injection hole can be changed, and then change on blade
Oil film shape, and then optimize atomization.
Wherein, the ratio between the pre- diaphragm plate vane thickness of main combustion stage axial rotational flow and main combustion stage swirl vane thickness be 20%~
60%, the rigidity of pre- film blade can be changed in the thickness for changing pre- film blade, can pass through vibration when fuel oil impacts pre- film blade
Accelerate the broken of oil film, and then promotes atomization.
Wherein, the pre- diaphragm plate blade of the main combustion stage axial rotational flow can be long by adjusting the pre- diaphragm plate blade of main combustion stage axial rotational flow
Degree is 10%~80% with main combustion stage swirl vane length ratio, changes fuel oil in the stop on the pre- diaphragm plate blade of axial rotational flow
Between so change atomizing effect.
Wherein, the pre- diaphragm plate number of blade of main combustion stage axial rotational flow keeps quantity one with the fuel oil spray orifice on main combustion stage swirl vane
It causes, or arranges at interval according to the pre- film blade of an axial rotational flow is placed at interval of a channel.
Wherein, the shape of the pre- diaphragm plate blade of main combustion stage axial rotational flow can it is identical as main combustion stage swirl vane shape can also
To be streamlined, wherein thickness is the 20%~60% of main combustion stage swirl vane thickness.
Wherein, the pre- diaphragm plate blade used in the pre- diaphragm plate blade of the main combustion stage axial rotational flow can be by changing main combustion stage axis
Radial angle to the pre- diaphragm plate blade of eddy flow and main combustion stage swirl vane is the 20%~80% of swirler blades radial direction angle.
Wherein, the pre- diaphragm plate blade of the main combustion stage axial rotational flow can be according to the position of jet hole by changing blade height
The relative altitude of position and blade is coordinated with spray-hole, and then realizes the effect of preferable film forming atomization, and described is opposite
Height is centered on hole, blade length ratio is the 20%~80% of swirl vane height.
The operation principle of the present invention：The low emission combustor head using center classification frame mode design it is main,
Pre-combustion grade can effectively reduce combustion chamber disposal of pollutants.The main combustion stage on the head installs pre- diaphragm plate additional in main pre-combustion grade cyclone
Blade carries out pre- film to the oil column that main combustion stage swirl vane sprays and makes it easier to broken and atomization, and then in limited distance
Reach higher premixing effect, improve the efficiency of combustion of main combustion stage, to reduce the pollutant discharge amount of combustion chamber.
The present invention has the advantage that as follows compared with prior art：
(1) hydrocyclone structure that film forming blade is matched with cyclone is used, the combustion that swirler blades can be made to spray
Oil hits film forming blade and forms oil film, and carries out broken mist under the shear action of rotational flow air after oil film flows out pre- film blade
Change, while being blended with air, to reach more preferably premixing effect.
(2) head tissue in such a way that center is classified burns, and main combustion stage is for premixed combustion and in the effect of film forming blade
Lower premixing effect is more preferable, and burning is more abundant, can effectively reduce pollutant emission；Pre-combustion grade is diffusion combustion, and can guarantee head
Portion's point extinguishment characteristics.
(3) the configuration of the present invention is simple, process and assemble is convenient, and Er Qiezhu, pre-combustion grade can be carried out according to different swirling numbers
Combination.Flow field and flame structure can be adjusted by changing main pre-combustion grade swirling number, is suitable for different combustion apparatus.
Description of the drawings
Fig. 1 is that a kind of main combustion stage of the present invention matches the low emissions combustion of blade injection structure using the pre- diaphragm plate of axial rotational flow
Chamber-head portion structural schematic diagram；
Fig. 2 is the main combustion stage and interstage section assembling structure schematic diagram of the present invention；
Fig. 3 is that the main combustion stage cyclone of the present invention and the pre- diaphragm plate blade (scheme one) of axial rotational flow are assemblied in interstage section
Structural schematic diagram；
Fig. 4 is the main combustion stage cyclone of the present invention and the assembling structure left side of the pre- diaphragm plate blade (scheme one) of axial rotational flow etc.
Axis side schematic diagram；
Fig. 5 is main combustion stage cyclone fuel gallery and the fuel injection hole structural schematic diagram of the present invention；
Fig. 6 is the main combustion stage structural representation of the main combustion stage cyclone and the pre- diaphragm plate blade (scheme two) of axial rotational flow of the present invention
Figure；
Fig. 7 is the main combustion stage cyclone of the present invention and the assembling structure left side of the pre- diaphragm plate blade (scheme two) of axial rotational flow etc.
Axis side schematic diagram；
Fig. 8 is the main combustion stage cyclone of the present invention and the assembling structure right side of the pre- diaphragm plate blade (scheme two) of axial rotational flow etc.
Axis side schematic diagram；
Fig. 9 is the angle schematic diagram of the main combustion stage swirler blades and the pre- diaphragm plate blade of axial rotational flow of the present invention；
Figure 10 is the streamlined contour schematic diagram of the pre- film blade of axial rotational flow of the present invention.
In figure：01 is main combustion stage swirl vane, and 02 is the pre- diaphragm plate blade of main combustion stage axial rotational flow, and 03 is main combustion stage sleeve,
04 is main combustion stage channel, and 05 is main combustion stage inner ring, and 06 is interstage section, and 07 is pre-combustion grade swirler blades, and 08 is pre-combustion grade nozzle
Outer shroud, 09 is pre-combustion grade nozzle, and 10 be main combustion stage oil circuit tobacco pipe, and 11 be main combustion stage oil circuit ring cavity, and 12 be pre- diaphragm plate blade height,
13 be radial angle, and 14 be leaf angle, and 15 be pre- diaphragm plate vane thickness, and 16 be fuel gallery, and 17 be fuel injection hole.
Specific implementation mode
Below in conjunction with the accompanying drawings and the present invention is discussed in detail in specific implementation mode：
As shown in Figure 1, matching blade using the pre- diaphragm plate of axial rotational flow for a kind of main combustion stage described in the embodiment of the present invention
The low emission combustor head of injection structure uses the tissue burning of center hierarchical approaches, mainly by main combustion stage swirl vane
01, the pre- diaphragm plate blade 02 of main combustion stage axial rotational flow, main combustion stage sleeve 03, main combustion stage channel 04, main combustion stage inner ring 05, carry Wen
The interstage section 06 of pipe, pre-combustion grade swirler blades 07, pre-combustion grade nozzle outer shroud 08, pre-combustion grade nozzle 09, main combustion stage oil circuit tobacco pipe
10, main combustion stage oil circuit ring cavity 11.Interstage section 06 carries Venturi tube.Wherein main combustion stage swirl vane 01, main combustion stage axial rotational flow are pre-
Diaphragm plate blade 02, main combustion stage sleeve 03, main combustion stage channel 04, main combustion stage inner ring 05 are attached using welding manner, constitute master
Fire grade；Main combustion stage fuel oil is entered by main combustion stage oil circuit tobacco pipe 10, is sprayed from main combustion stage swirler blades, and fuel oil gets to pre- diaphragm plate
Oil film is formed on blade, is then blended with main combustion stage air, and uniform gas mixture is formed；Pre-combustion grade swirler blades
07 is connect with interstage section 06 using welding manner；With interstage section by the way of being threadedly coupled, formation has for main combustion stage, pre-combustion grade
Main combustion stage is using the center classification low emission combustor head of the pre- diaphragm plate matching blade injection structure of axial rotational flow, wherein pre-combustion grade
For diffusion flame, main combustion stage is premixed flame.
As shown in Fig. 2, entire main combustion stage is by main combustion stage swirl vane 01, the pre- diaphragm plate blade 02 of main combustion stage axial rotational flow, master
Grade sleeve 03, main combustion stage channel 04, main combustion stage inner ring 05 and interstage section 06 is fired to form.It can be by adjusting the height of pre- diaphragm plate blade
Degree, length, thickness and change film-formation result of the fuel oil on pre- film blade with the angles of swirler blades, so change with
The mixing effect of main combustion stage air realizes the complete blending of oil gas.
As shown in figure 3, main combustion stage swirl vane 01 is mounted on interstage section 06 with the pre- diaphragm plate blade 02 of main combustion stage axial rotational flow
On constitute main combustion stage fuel oil film forming mixing structure, as seen in Figure 3 fuel oil pre- diaphragm plate blade is ejected into from fuel hole
Upper formation oil film.Wherein pre- diaphragm plate leaf position is changed with respect to swirl vane, pre- diaphragm plate blade shape changes (length, height
Degree, thickness).
As shown in figure 4, the assembly knot of main combustion stage swirl vane 01 and pre- 02 structure one of diaphragm plate blade of main combustion stage axial rotational flow
Isometric side schematic diagram on the left of structure, it is shown that relative position and connection type between main combustion stage cyclone and pre- diaphragm plate blade.
As shown in figure 5, the 17 partial enlargement knot of fuel gallery 16 and fuel injection hole on 01 blade of main combustion stage swirl vane
Then composition, fuel oil get to main combustion stage from the outflow of fuel gallery 16 on main combustion stage swirl vane 01 by the ejection of fuel injection hole 17
Oil film is formed on the pre- diaphragm plate blade of axial rotational flow 02, and then forms the gas mixture that very high atomizing effect forms high quality.
As shown in fig. 6, pre- 02 structure two of diaphragm plate blade of main combustion stage axial rotational flow, is stretched using as shown in the figure by top down
Exhibition, each pre- diaphragm plate blade are structure as a whole with cyclic adapting piece, and pre- diaphragm plate structure is fixed by oblique fluting；The structure exists
While carrying out pre- film to fuel oil, reduces the influence to Swirling Flow as far as possible, do not change original flow field structure.
As shown in fig. 7, main combustion stage swirl vane 01 and the assembly of pre- 02 structure two of diaphragm plate blade of main combustion stage axial rotational flow connect
Schematic diagram is connect, can be changed with respect to swirl vane by changing pre- diaphragm plate leaf position, pre- diaphragm plate blade shape changes (length
Degree, height, streamline shape etc.) change film-formation result, and then improve the atomization of fuel oil and the mixing effect with air.
As shown in figure 8, the assembly knot of main combustion stage swirl vane 01 and pre- 02 structure two of diaphragm plate blade of main combustion stage axial rotational flow
Isometric side schematic diagram on the right side of structure.Show the structure and installation site and pre- diaphragm plate blade height 12 and pre- of pre- diaphragm plate blade
Diaphragm plate vane thickness 15 is adjustable.
As shown in figure 9, the radial angle 13 of main combustion stage axial rotational flow pre- diaphragm plate blade 02 and main combustion stage swirl vane 01, with
And the relative size relationship of swirler blades angle 14, it can be imitated by changing the size of radial angle 13 to adjust the pre- film of fuel oil
Fruit.
As shown in Figure 10, the shape of the pre- diaphragm plate blade of main combustion stage axial rotational flow 02 is streamlined, and wherein thickness is eddy flow
The 20%~60% of device vane thickness.
Claims (9)
1. a kind of main combustion stage is existed using the low emission combustor head of the pre- diaphragm plate matching blade injection structure of axial rotational flow, feature
In：Main combustion stage matches blade injection structure using the pre- diaphragm plate of axial rotational flow；Head use center classification structure, by main combustion stage,
Pre-combustion grade is constituted, wherein the pre- diaphragm plate blade (02) of main combustion stage swirl vane (01), main combustion stage axial rotational flow, main combustion stage sleeve
(03), main combustion stage inner ring (05) passes sequentially through welding and forms entire main combustion stage, wherein main combustion stage swirl vane (01) and main combustion stage
Then the pre- diaphragm plate blade (02) of axial rotational flow will by being sleeved in main combustion stage inner ring (05) and welding together after being welded to connect
Main combustion stage sleeve (03) is welded with main combustion stage swirl vane (01) top；Pre-combustion grade includes pre-combustion grade swirler blades
(07), pre-combustion grade nozzle outer shroud (08), pre-combustion grade nozzle (09), wherein pre-combustion grade nozzle outer shroud (08) pass through screw thread and pre-combustion grade
Nozzle (09) connects, and then pre-combustion grade swirler blades (07) are sleeved on pre-combustion grade nozzle outer shroud (08), interstage section (06) with it is pre-
Grade swirler blades (07) are fired by being welded to connect, and are then threadedly connect with main combustion stage inner ring (05), are formed main combustion
Grade matches the low emission combustor head of blade injection structure using the pre- diaphragm plate of axial rotational flow.
2. a kind of main combustion stage according to claim 1 is using the low emission of the pre- diaphragm plate matching blade injection structure of axial rotational flow
Head of combustion chamber, it is characterised in that：The pre- diaphragm plate blade (02) of main combustion stage axial rotational flow and main combustion stage swirl vane (01) axis
At -30 °~60 °, fuel oil impinges upon after being sprayed by blade spray-hole and forms oil film on pre- film blade angle at an angle
It is atomized, improves nebulization efficiency.
3. a kind of main combustion stage according to claim 1 is using the low emission of the pre- diaphragm plate matching blade injection structure of axial rotational flow
Head of combustion chamber, it is characterised in that：The radial direction of main combustion stage axial rotational flow pre- diaphragm plate blade (02) and main combustion stage swirl vane (01)
Angle is the 20%~80% of swirler blades radial direction angle, then can be changed straight line of the pre- film blade apart from fuel injection hole away from
From, and then change the oil film shape on blade, and then optimize atomization.
4. a kind of main combustion stage according to claim 1 is using the low emission of the pre- diaphragm plate matching blade injection structure of axial rotational flow
Head of combustion chamber, it is characterised in that：Pre- diaphragm plate blade (02) thickness of main combustion stage axial rotational flow is thick with main combustion stage swirl vane (01)
The ratio between degree is 20%~60%, and the rigidity of pre- film blade can be changed in the thickness for changing pre- film blade, impacts pre- film blade in fuel oil
When can accelerate the broken of oil film by vibration, and then promote atomization.
5. a kind of main combustion stage according to claim 1 is using the low emission of the pre- diaphragm plate matching blade injection structure of axial rotational flow
Head of combustion chamber, it is characterised in that：The pre- diaphragm plate blade (02) of main combustion stage axial rotational flow can axially revolve by adjusting main combustion stage
It is 10%~80% to flow pre- diaphragm plate blade (02) length with main combustion stage swirl vane (01) length ratio, changes fuel oil in axial rotation
It flows the residence time on pre- diaphragm plate blade and then changes atomizing effect.
6. a kind of main combustion stage according to claim 1 is using the low emission of the pre- diaphragm plate matching blade injection structure of axial rotational flow
Head of combustion chamber, it is characterised in that：The pre- diaphragm plate number of blade of main combustion stage axial rotational flow and the fuel oil spray orifice on main combustion stage swirl vane
It keeps quantity consistent, or arranges at interval according to the pre- film blade of an axial rotational flow is placed at interval of a channel.
7. a kind of main combustion stage according to claim 1 is using the low emission of the pre- diaphragm plate matching blade injection structure of axis eddy flow
Head of combustion chamber, it is characterised in that：The shape of the pre- diaphragm plate blade (02) of main combustion stage axial rotational flow can be with main combustion stage swirl vane
(01) shape is identical or streamlined, and wherein thickness is the 20%~60% of main combustion stage swirl vane (01) thickness.
8. a kind of main combustion stage according to claim 1 is using the low emission of the pre- diaphragm plate matching blade injection structure of axial rotational flow
Head of combustion chamber, it is characterised in that：The pre- diaphragm plate blade used in the pre- diaphragm plate blade (02) of main combustion stage axial rotational flow can lead to
It is swirler blades to cross the pre- diaphragm plate blade (02) of change main combustion stage axial rotational flow and the radial angle of main combustion stage swirl vane (01)
The 20%~80% of radial angle.
9. a kind of main combustion stage according to claim 1 is using the low emission of the pre- diaphragm plate matching blade injection structure of axial rotational flow
Head of combustion chamber, it is characterised in that：The pre- diaphragm plate blade (02) of the main combustion stage axial rotational flow can be logical according to the position of jet hole
The relative altitude for crossing change blade height position and blade is coordinated with spray-hole, and then realizes the effect of preferable film forming atomization
Fruit, the relative altitude are centered on hole, and blade length ratio is the 20%~80% of swirl vane height.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810472110.6A CN108592084B (en) | 2018-05-17 | 2018-05-17 | Low-emission combustion chamber head part adopting axial rotational flow prefilming plate matched blade injection structure for main combustion stage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810472110.6A CN108592084B (en) | 2018-05-17 | 2018-05-17 | Low-emission combustion chamber head part adopting axial rotational flow prefilming plate matched blade injection structure for main combustion stage |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108592084A true CN108592084A (en) | 2018-09-28 |
| CN108592084B CN108592084B (en) | 2020-04-24 |
Family
ID=63631704
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810472110.6A Active CN108592084B (en) | 2018-05-17 | 2018-05-17 | Low-emission combustion chamber head part adopting axial rotational flow prefilming plate matched blade injection structure for main combustion stage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108592084B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109539311A (en) * | 2018-11-13 | 2019-03-29 | 西北工业大学 | A kind of axial swirler structure with oil injection structure blade |
| CN109737386A (en) * | 2018-12-11 | 2019-05-10 | 北京航空航天大学 | Double-cyclone low emission combustor |
| CN111520750A (en) * | 2020-03-25 | 2020-08-11 | 西北工业大学 | Novel combustion chamber head oil injection structure |
| CN113280367A (en) * | 2021-05-31 | 2021-08-20 | 中国航空发动机研究院 | Staged combustion chamber head with swirl pre-membrane plate structure |
| CN115388428A (en) * | 2022-07-29 | 2022-11-25 | 北京航空航天大学 | Main combustion stage swirler capable of improving radial temperature distribution, combustion chamber nozzle and combustion chamber |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103335333A (en) * | 2013-06-21 | 2013-10-02 | 北京航空航天大学 | Single-oil passage pre-diaphragm type staggered plate primary combustion stage premixing and pre-vaporizing low-pollution combustor |
| CN103343985A (en) * | 2013-06-21 | 2013-10-09 | 北京航空航天大学 | Double-pre-film pneumatic nebulization low pollution combustor head structure |
| WO2015024139A1 (en) * | 2013-08-19 | 2015-02-26 | Wang Kangmei | Centrifugal conical-spray fuel spray nozzle |
| CN104456627A (en) * | 2014-10-27 | 2015-03-25 | 北京航空航天大学 | Lean oil premixing and pre-evaporating combustion chamber head structure with cyclone/pre-film plate integrated primary combustion stage |
| CN105180215A (en) * | 2015-10-16 | 2015-12-23 | 北京航空航天大学 | Low-pollution combustion chamber with main combustion stage adopting single-layer pre-film radial two-grade reverse rotational flow |
| CN103697500B (en) * | 2013-12-24 | 2016-04-20 | 北京航空航天大学 | The premixed preevaporated low contamination combustion chamber of a kind of pair of pre-membrane type main combustion stage of oil circuit four eddy flow |
-
2018
- 2018-05-17 CN CN201810472110.6A patent/CN108592084B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103335333A (en) * | 2013-06-21 | 2013-10-02 | 北京航空航天大学 | Single-oil passage pre-diaphragm type staggered plate primary combustion stage premixing and pre-vaporizing low-pollution combustor |
| CN103343985A (en) * | 2013-06-21 | 2013-10-09 | 北京航空航天大学 | Double-pre-film pneumatic nebulization low pollution combustor head structure |
| CN103343985B (en) * | 2013-06-21 | 2015-07-08 | 北京航空航天大学 | Double-pre-film pneumatic nebulization low pollution combustor head structure |
| WO2015024139A1 (en) * | 2013-08-19 | 2015-02-26 | Wang Kangmei | Centrifugal conical-spray fuel spray nozzle |
| CN103697500B (en) * | 2013-12-24 | 2016-04-20 | 北京航空航天大学 | The premixed preevaporated low contamination combustion chamber of a kind of pair of pre-membrane type main combustion stage of oil circuit four eddy flow |
| CN104456627A (en) * | 2014-10-27 | 2015-03-25 | 北京航空航天大学 | Lean oil premixing and pre-evaporating combustion chamber head structure with cyclone/pre-film plate integrated primary combustion stage |
| CN105180215A (en) * | 2015-10-16 | 2015-12-23 | 北京航空航天大学 | Low-pollution combustion chamber with main combustion stage adopting single-layer pre-film radial two-grade reverse rotational flow |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109539311A (en) * | 2018-11-13 | 2019-03-29 | 西北工业大学 | A kind of axial swirler structure with oil injection structure blade |
| CN109737386A (en) * | 2018-12-11 | 2019-05-10 | 北京航空航天大学 | Double-cyclone low emission combustor |
| CN111520750A (en) * | 2020-03-25 | 2020-08-11 | 西北工业大学 | Novel combustion chamber head oil injection structure |
| CN113280367A (en) * | 2021-05-31 | 2021-08-20 | 中国航空发动机研究院 | Staged combustion chamber head with swirl pre-membrane plate structure |
| CN113280367B (en) * | 2021-05-31 | 2022-08-02 | 中国航空发动机研究院 | Staged combustion chamber head with swirl pre-membrane plate structure |
| CN115388428A (en) * | 2022-07-29 | 2022-11-25 | 北京航空航天大学 | Main combustion stage swirler capable of improving radial temperature distribution, combustion chamber nozzle and combustion chamber |
| CN115388428B (en) * | 2022-07-29 | 2023-06-16 | 北京航空航天大学 | Main combustion stage swirler, combustor nozzle and combustor with improved radial temperature distribution |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108592084B (en) | 2020-04-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108592084A (en) | A kind of main combustion stage matches the low emission combustor head of blade injection structure using the pre- diaphragm plate of axial rotational flow | |
| CN107559881B (en) | A kind of main combustion stage uses the low pollution combustor head construction of angular injection nozzle | |
| CN106500130B (en) | A kind of three-level layered portion lean premixed combustor of main combustion stage fuel-firing preheating prevapourising | |
| CN206281000U (en) | Pre-combustion grade uses the low emission combustor of double-deck axial swirler | |
| CN105953265B (en) | A kind of combined burning room | |
| CN107543201B (en) | One kind is oil-poor directly to spray and mixes low pollution combustor | |
| CN101435585B (en) | Gas turbine combined type fuel evaporating and atomizing combustion apparatus | |
| CN105041539B (en) | A kind of Multi-stage spiral combination type air atomizing fuel nozzle device and its control method | |
| CN106594799B (en) | A kind of low emission combustor axially sprayed using blade inlet edge | |
| CN106091013B (en) | A kind of high temperature rise combustor structure of three-level stratified combustion | |
| CN108916912A (en) | A kind of pre-combustion grade uses the low emission combustor head of cooling anti-carbon deposition structure | |
| CN102889617B (en) | Premixing and pre-evaporation combustor for main combustion stage using radial film formation | |
| CN108253455A (en) | A kind of premix and pre-evaporation minimum discharge head of combustion chamber and its combustion chamber | |
| CN108561897A (en) | A kind of partly-premixed prevapourising minimum discharge combustion chamber for strengthening air-fuel mixture | |
| CN109654533A (en) | A kind of trailing edge blowing formula stabilizer adapting to incoming flow distortion | |
| CN108916911B (en) | A kind of pre-combustion grade uses the center classification low emission combustor head of pre- diaphragm plate structure | |
| CN204961141U (en) | Air atomizing fuel spray nozzle device | |
| CN103047683A (en) | Partial premixing and pre-evaporation combustion chamber with three-level oil passages | |
| CN107143880A (en) | A kind of direct injector head of oil-poor multiple spot for low-pollution burning chamber of gas turbine | |
| CN107763666A (en) | A kind of head of combustion chamber oil gas mixing machine and the engine with the structure | |
| CN109595593A (en) | A kind of swirl combustion chamber head of air inlet section-variable | |
| CN108844098A (en) | A kind of head of combustion chamber based on volute structure | |
| CN108151069B (en) | Main combustion zone radial flow combustion chamber and oil-gas mixing method | |
| CN106996579B (en) | A kind of oil-poor direct jetstream whirl nozzle mould of low-pollution burning chamber of gas turbine | |
| CN103791518A (en) | Combustion chamber fuel injecting and mixing device and aero-engine |
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 |