CN108561899B - A kind of microchannel cooling means for aero-engine low pollution combustor head - Google Patents
A kind of microchannel cooling means for aero-engine low pollution combustor head Download PDFInfo
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- CN108561899B CN108561899B CN201810381403.3A CN201810381403A CN108561899B CN 108561899 B CN108561899 B CN 108561899B CN 201810381403 A CN201810381403 A CN 201810381403A CN 108561899 B CN108561899 B CN 108561899B
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- cooling
- head
- microchannel
- aero
- combustion chamber
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Classifications
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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
-
- 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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/52—Toroidal combustion chambers
Abstract
A kind of microchannel cooling means for aero-engine low pollution combustor head, is related to aero-engine.Small cooling microchannel is opened up inside the classification expansion step for aero-engine low pollution combustor premix head, and head of combustion chamber structure is cooled down using coolant；In cooling procedure, coolant first flows through the cooling head of combustion chamber of microchannel structure, then sprays into head of combustion chamber premix grade and blended with air, and participate in the burning of combustion chamber；Coolant flows to the total runner of entrance from cooling oil path, then it scatter and flows through each microchannel of annular distribution, the wall surface of circle classification expansion step whole to head of combustion chamber cools down, then it is aggregated into the total runner of main combustion stage fuel oil to summarize spray orifice with the fuel oil of main combustion stage oil circuit again and spray into main mixer, the blending of last and air participates in burning.
Description
Technical field
The present invention relates to aero-engines, more particularly, to a kind of for the micro- of aero-engine low pollution combustor head
Channel cooling means.
Background technique
The research and development of low pollution combustor are the key that reduce aero-engine disposal of pollutants, because of the pollution of aero-engine
Object is mainly derived from combustion chamber.With the enhancing of people's environmental consciousness and becoming increasingly conspicuous for energy problem, control combustion tail gas row
Put the cardinal principle for having become Aeroengine Design.
In order to reduce the Air Pollutant Emissions such as aeroengine combustor buring nitrogen oxide in tail gas, oxycarbide, state at present
Inside and outside design low pollution combustor mainly uses the concept of fractional combustion, and such as bicyclic premixed swirl TAPS technology, combustion lean are pre-
Mixed prevapourising LPP technology, the oil-poor technology RQL of rich oil-extinguishing-etc., are divided into several combustion zones for combustion chamber, are fired by controlling each area
The oil-gas ratio of oil and air, makes disposal of pollutants of the combustion chamber under each operating condition be in reduced levels.But combustion with reduced pollutants
The normal work of room is but faced with the cooling insufficient problem in head.The main air of low pollution combustor is used for head fuel/sky
The blending of gas, few air can be used for head construction cooling, and head only leans on simple cross-ventilation heat exchange that can obtain
Cooling effect is extremely limited, easily burns head components and is difficult to meet the cooling need on aero-engine low pollution combustor head
It asks.And with the development of aero-engine high thrust ratio, High Mach number, aeroengine combustor buring chamber-head portion high temperature problem is more prominent
Out.
In order to guarantee the working life on aero-engine low pollution combustor head, in addition to the wall surface spray in its key structure
It applies outside heat insulating coat, also to carry out other necessary coolings, more preferably to solve the problems, such as the cooling of low pollution combustor head construction,
Guarantee the normal work of combustion chamber.
Summary of the invention
The purpose of the present invention is to provide a kind of microchannel cooling sides for aero-engine low pollution combustor head
Method.
The present invention the following steps are included:
1) small cooling is opened up inside the classification expansion step for aero-engine low pollution combustor premix head
Microchannel, and head of combustion chamber structure is cooled down using coolant；
In step 1), aero-engine cold conditions aviation kerosine is can be used as coolant in the coolant.
2) in cooling procedure, coolant first flows through the cooling head of combustion chamber of microchannel structure, then sprays into head of combustion chamber
Premix grade is blended with air, and participates in the burning of combustion chamber；
3) coolant flows to the total runner of entrance from cooling oil path, then scatter and flows through each microchannel of annular distribution,
It is whole to head of combustion chamber circle classification expansion step wall surface cool down, be then aggregated into the total runner of main combustion stage fuel oil again with main combustion
The fuel oil of grade oil circuit, which summarizes, sprays into main mixer through spray orifice, and the blending of last and air participates in burning.
In step 3), the cooling oil path is to provide coolant for the cooling of head of combustion chamber structure.The entrance is total
The shape of runner and the total runner of main combustion stage fuel oil is annular in shape, the total runner of entrance and the total runner of main combustion stage fuel oil and cooling microchannel
Two joining distal ends summarize for coolant disengaging；The cooling microchannel is embedded in the inside of classification expansion step, and every micro-
The hydraulic equivalent diameter in channel is less than or equal to 1mm, and the cross-sectional shape of cooling microchannel is rectangle or other shapes.Every micro-
Channel is opened up along the classification expansion step wall profile adjacent with pre-combustion grade and main combustion stage, and whole a plurality of rings of micro-tunnels is around head
Portion is annularly distributed；The total runner of access port on the both ends of each microchannel, under connect the total runner of main combustion stage fuel oil, overall structure connection
Flowing cavity.
The spray orifice can be used annular multiple spot spray orifice, and spray orifice is along the total runner of main combustion stage fuel oil towards main mixer side
The circle aperture that opens up of wall surface ring-type, 0.8~2mm of aperture, the centre distance of adjacent two o'clock aperture is no more than 5mm, the side in hole
To facing main cyclone device.
On the one hand cooling procedure can cool down classification expansion step wall surface, prevent head construction from damaging because of high temperature,
On the other hand so that cold conditions aviation kerosine itself heat absorption is improved temperature, promote fuel vaporization, blending, improve the efficiency of combustion of fuel.
Small cooling microchannel is opened up inside the classification expansion step on combustion chamber premix head, and uses aero-engine
Cold conditions aviation kerosine efficiently cools down head of combustion chamber structure as coolant.Primary structure of the invention has: cooling oil
Road, the total runner of entrance, cooling microchannel, main combustion stage oil circuit, the total runner of main combustion stage fuel oil and annular multiple spot spray orifice.Cooling procedure
In, cold conditions aviation kerosine first flows through the cooling head of combustion chamber of microchannel structure, then sprays into head premix grade and blended with air,
Finally participate in the burning of combustion chamber.
With it is existing for the microchannel cooling means on aero-engine low pollution combustor head compared with, the present invention is directed to
Traditional low pollution combustor head construction has the advantage that
1) one aspect of the present invention increases the specific surface area of coolant and wall surface heat convection using microchannel structure, mentions significantly
The heat transfer effect of high coolant plays efficiently cooling effect to combustion chamber wall surface；On the other hand it is fired using gas turbine cold conditions
Oil is used as coolant, first absorbs heat and burns again, promotes the evaporation mixing of fuel oil, improves efficiency of combustion.
2) mode for embedding cooling microchannel cools down head of combustion chamber structure, increases coolant and combustion chamber wall surface
Heat convection specific surface area, efficiently promotes cooling effect, protects low pollution combustor head construction not ablated, avoids low dirt
Contaminate the cooling insufficient problem of head of combustion chamber.
3) coolant of the gas turbine cold conditions fuel as cooling system is used, fuel is in cooling head of combustion chamber structural walls
It absorbs heat and heats up during face, promote its evaporation mixing, the head construction of high temperature rise can be cooled down and make full use of combustion chamber
Heat improves efficiency of combustion.
4) by the way of the present invention is cooling using wall surface microchannel, the specific surface area of cooling heat transferring is increased, to head of combustion chamber
Structure carries out temperature with high efficiency, prevents it from bringing damage due to wall superheat.Simultaneously using fuel as coolant, fuel is first inhaled
Heat is burnt again, is recycled to combustion chamber heat, is helped to improve efficiency of combustion, to promote the energy benefit of total system
With rate.
5) present invention has great importance to the research and development of the advanced aero engine combustion chamber of high temperature rise, low pollution.
Detailed description of the invention
Fig. 1 is the structure axial sectional view of the embodiment of the present invention.
Fig. 2 is the cross-sectional view in the direction A-A in Fig. 1.
Fig. 3 is to use aero-engine low pollution combustor head construction figure of the invention.
In figs. 1 to 3, each label are as follows: 1 is cooling oil path, and 2 be the total runner of entrance, and 3 be cooling microchannel, and 4 be main combustion stage
The total runner of fuel oil, 5 be main combustion stage oil circuit, and 6 be annular multiple spot spray orifice, and 7 be classification expansion step, and 8 be main mixer, and 9 be pre-burning
Grade oil circuit, 10 be double cyclone, and 11 be pre-burning nozzle, and 12 be Venturi tube, and 13 be main combustion cyclone.
Specific embodiment
Following embodiment will the present invention is further illustrated in conjunction with attached drawing.
Referring to Fig. 1~3, the embodiment of the present invention includes following steps:
1) small cooling is opened up inside the classification expansion step 7 for aero-engine low pollution combustor premix head
Microchannel, and head of combustion chamber structure is cooled down using coolant；The coolant uses the aviation of aero-engine cold conditions
Kerosene is as coolant.
2) in cooling procedure, coolant first flows through the cooling head of combustion chamber of microchannel structure, then sprays into head of combustion chamber
Premix grade is blended with air, and participates in the burning of combustion chamber；
3) coolant flows to the total runner 2 of entrance from cooling oil path 1, then scatter flow through annular distribution each item it is micro- logical
The wall surface in road, circle classification expansion step 7 whole to head of combustion chamber cools down, and is then aggregated into the total runner 4 of main combustion stage fuel oil again
Summarize with the fuel oil of main combustion stage oil circuit 5 through spray orifice 6 and spray into main mixer 8, the blending of last and air participates in burning.The cooling
Oil circuit 1 is to provide coolant for the cooling of head of combustion chamber structure.The total runner 2 of the entrance and the total runner 4 of main combustion stage fuel oil
Shape is annular in shape, two joining distal ends of the total runner 2 of entrance and main combustion stage fuel oil total runner 4 and cooling microchannel 3, for cooling down
Agent disengaging summarizes；The cooling microchannel 3 is embedded in the inside of classification expansion step 7, the hydraulic equivalent diameter of every microchannel
Less than or equal to 1mm, the cross-sectional shape of cooling microchannel 3 is rectangle or other shapes.It is expanded along classification every microchannel
The wall profile adjacent with pre-combustion grade and main combustion stage of step 7 opens up, and whole a plurality of rings of micro-tunnels is annularly distributed around head；Respectively
The total runner 2 of access port on the both ends of microchannel, under connect the total runner 4 of main combustion stage fuel oil, be integrally formed the flowing cavity of connection.
Using annular multiple spot spray orifice, spray orifice 6 is along the total runner 4 of main combustion stage fuel oil towards main mixer 8 one for the spray orifice 6
The circle aperture that the wall surface ring-type of side opens up, the centre distance of 0.8~2mm of aperture, adjacent two o'clock aperture are no more than 5mm, hole
Direction faces main combustion cyclone 13.
On the one hand cooling procedure can cool down classification expansion 7 wall surface of step, prevent head construction from damaging because of high temperature,
On the other hand so that cold conditions aviation kerosine itself heat absorption is improved temperature, promote fuel vaporization, blending, improve the efficiency of combustion of fuel.
Small cooling microchannel is opened up inside the classification expansion step 7 on combustion chamber premix head, and uses aeroplane engine
Machine cold conditions aviation kerosine efficiently cools down head of combustion chamber structure as coolant.Primary structure of the invention has: cooling
The total runner 2 of oil circuit 1, entrance, cooling microchannel 3, main combustion stage oil circuit 5, the total runner 4 of main combustion stage fuel oil and annular multiple spot spray orifice 6.It is cold
But during, cold conditions aviation kerosine first flows through the cooling head of combustion chamber of microchannel structure, then spray into head premix grade and air into
Row blending, finally participates in the burning of combustion chamber.
The embodiment of the present invention efficiently cools down head of combustion chamber wall surface using the cooling means of embedded microchannel structure,
Guarantee the normal work of combustion chamber.
The aero-engine low pollution combustor head construction is mainly by the pre-combustion grade of center diffusion combustion and one
The main combustion stage composition of coaxial premixed combustion, two-stage are expanded step 7 by the classification of certain altitude and are separated.Pre-combustion grade is mainly by pre-burning
Grade oil circuit 9, double cyclone 10, pre-burning nozzle 11 and Venturi tube 12 form, start and when low operating condition by diffusion combustion point
Stable flame is obtained at grade expansion step 7, and lights the premixed combustion of main combustion stage when gas turbine goes to operating condition appropriate.
Main combustion stage is mainly by main combustion stage oil circuit 5, the total runner 4 of main combustion stage fuel oil, annular multiple spot spray orifice 6, main mixer 8 and main combustion cyclone
13 compositions carry out fuel oil and air to carry out premixed combustion again after blending in advance, to obtain the disposal of pollutants of reduced levels.
But when the head of combustion chamber works long hours, cooling appropriate were it not for, flame stabilization expands step 7 in classification
Head of combustion chamber high temperature nearby is easily caused, maximum temperature easily burns components up to 2000K or so.The present invention expands in classification
Zhang Taijie 7 embeds microchannel structure, cools down to it,
Primary structure of the invention has: the total runner 2 of cooling oil path 1, entrance, cooling microchannel 3, main combustion stage oil circuit 5, main combustion
The total runner 4 of grade fuel oil and annular multiple spot spray orifice 6.Six cavitys are sequentially communicated, and make coolant in the process for passing in and out the cooling structure
In in " summarize-disperse-summarize " fluxus formae.
The present invention is to pass through cooling oil path while head of combustion chamber pre-combustion grade and main combustion stage carry out normal fuel injection burning
Fuel feeding enters microchannel structure and carries out head cooling.For the present invention using aero-engine cold conditions fuel as coolant, coolant is first
The total runner 2 of entrance is flowed into from cooling oil path 1, then flows into each elongated cooling microchannel 3 of item from the total dispersion of runner 2 of entrance, is then converged
Total total runner 4 of main combustion stage fuel oil for arriving the other end, the fuel oil come in main combustion stage oil circuit 5 summarize, and spray finally by annular multiple spot
Hole 6 is injected main mixer 8 and is blended with air, and indoor main combustion stage burning of burning is participated in.
During coolant flows inside classification expansion step 7 along microchannel, forced with microchannel wall surface
Heat convection cools down the head construction of the high temperature rise of work heating.Fluid boundary layer thickness is small in microchannel, diffusion resistance
Power is small, and microchannel increases the specific surface area of coolant and combustion chamber wall surface heat convection, and integrated microchannel enhances pair
The coefficient of heat transfer is flowed, efficiently cooling effect is played to wall surface, can be described as a kind of advanced type of cooling in combustion chamber.
Meanwhile aircraft engine fuel first cools down head construction as coolant, then participates in main combustion stage burning.Fuel stream
During head of combustion chamber microchannel, combustion chamber waste heat is recycled, due to itself heat absorption heating, injects main mixer 8
With can promote itself evaporation when air pre-mixing, improve the efficiency of combustion of combustion chamber, improve the utilization rate of integral energy.
The present invention is cooling approach with micro channel systems, to high temperature rise using aero-engine cold conditions fuel as coolant
Head of combustion chamber structure is efficiently cooled down, and is prevented head construction and is damaged because of overheat, and is carried out to combustion chamber waste heat
It recycles, promotes fuel vaporization, blending, improve the utilization rate of efficiency of combustion and integral energy, be high temperature rise, combustion with reduced pollutants
The thermal protection of room puts forward a new idea.
Claims (7)
1. a kind of microchannel cooling means for aero-engine low pollution combustor head, it is characterised in that including following step
It is rapid:
1) to open up small cooling inside the classification expansion step for aero-engine low pollution combustor premix head micro- logical
Road, and head of combustion chamber structure is cooled down using coolant；
2) in cooling procedure, coolant first flows through the cooling head of combustion chamber of cooling microchannel structure, then sprays into head of combustion chamber
Premix grade is blended with air, and participates in the burning of combustion chamber；
3) coolant flows to the total runner of entrance from cooling oil path, then scatter and flows through the cooling microchannel of each item of annular distribution,
It is whole to head of combustion chamber circle classification expansion step wall surface cool down, be then aggregated into the total runner of main combustion stage fuel oil again with main combustion
The fuel oil of grade oil circuit, which summarizes, sprays into main mixer through spray orifice, and the blending of last and air participates in burning.
2. a kind of microchannel cooling means for aero-engine low pollution combustor head as described in claim 1, special
Sign is that in step 1), the coolant is using aero-engine cold conditions aviation kerosine as coolant.
3. a kind of microchannel cooling means for aero-engine low pollution combustor head as described in claim 1, special
Sign is that in step 3), the cooling oil path is to provide coolant for the cooling of head of combustion chamber structure.
4. a kind of microchannel cooling means for aero-engine low pollution combustor head as described in claim 1, special
Sign is that in step 3), the shape of the total runner of the entrance and the total runner of main combustion stage fuel oil is annular in shape, the total runner of entrance and master
Two joining distal ends for firing the total runner of grade fuel oil and cooling microchannel summarize for coolant disengaging.
5. a kind of microchannel cooling means for aero-engine low pollution combustor head as described in claim 1, special
Sign is that in step 3), the cooling microchannel is embedded in the inside of classification expansion step, the waterpower of every cooling microchannel
Equivalent diameter is less than or equal to 1mm, and the cross-sectional shape of cooling microchannel is rectangle or other shapes.
6. a kind of microchannel cooling means for aero-engine low pollution combustor head as described in claim 1, special
Sign is that in step 3), the step wall profile adjacent with pre-combustion grade and main combustion stage is expanded along classification in every cooling microchannel
It opens up, whole a plurality of cooling rings of micro-tunnels is annularly distributed around head；Access port always flows on the both ends of the cooling microchannel of each item
Road, under connect the total runner of main combustion stage fuel oil, be integrally formed the flowing cavity of connection.
7. a kind of microchannel cooling means for aero-engine low pollution combustor head as described in claim 1, special
Sign is that in step 3), for the spray orifice using annular multiple spot spray orifice, spray orifice is mixed towards master along the total runner of main combustion stage fuel oil
The circle aperture that the wall surface ring-type of clutch side opens up, the centre distance of 0.8~2mm of aperture, adjacent two o'clock aperture are no more than
5mm, the direction in hole face main combustion cyclone.
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| CN201810381403.3A CN108561899B (en) | 2018-04-25 | 2018-04-25 | A kind of microchannel cooling means for aero-engine low pollution combustor head |
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| CN201810381403.3A CN108561899B (en) | 2018-04-25 | 2018-04-25 | A kind of microchannel cooling means for aero-engine low pollution combustor head |
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| CN108561899A CN108561899A (en) | 2018-09-21 |
| CN108561899B true CN108561899B (en) | 2019-07-09 |
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| CN112780411A (en) * | 2019-11-06 | 2021-05-11 | 中国航发商用航空发动机有限责任公司 | Gas turbine water vapor hybrid power system, water vapor generation assembly, aircraft and power supply method |
| CN113932253B (en) * | 2020-06-29 | 2022-10-18 | 中国航发商用航空发动机有限责任公司 | Combustion chamber head, combustion chamber, gas turbine engine, and combustion control method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102562176A (en) * | 2010-12-22 | 2012-07-11 | 通用电气公司 | Cooling channel systems for high-temperature components covered by coatings, and related processes |
| CN104165379A (en) * | 2014-09-01 | 2014-11-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Combustor head structure with cooling device |
| CN106322436A (en) * | 2016-11-11 | 2017-01-11 | 厦门大学 | Micro-channel regenerative cooling micro-combustor |
| EP3199871A1 (en) * | 2016-01-28 | 2017-08-02 | Rolls-Royce North American Technologies, Inc. | Heat exchanger integrated with fuel nozzle |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10584876B2 (en) * | 2016-03-25 | 2020-03-10 | General Electric Company | Micro-channel cooling of integrated combustor nozzle of a segmented annular combustion system |
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2018
- 2018-04-25 CN CN201810381403.3A patent/CN108561899B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102562176A (en) * | 2010-12-22 | 2012-07-11 | 通用电气公司 | Cooling channel systems for high-temperature components covered by coatings, and related processes |
| CN104165379A (en) * | 2014-09-01 | 2014-11-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Combustor head structure with cooling device |
| EP3199871A1 (en) * | 2016-01-28 | 2017-08-02 | Rolls-Royce North American Technologies, Inc. | Heat exchanger integrated with fuel nozzle |
| CN106322436A (en) * | 2016-11-11 | 2017-01-11 | 厦门大学 | Micro-channel regenerative cooling micro-combustor |
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