CN108870445A - A kind of flame combustion chamber tube wall surface using the Y shape effusion wall type of cooling - Google Patents
A kind of flame combustion chamber tube wall surface using the Y shape effusion wall type of cooling Download PDFInfo
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- CN108870445A CN108870445A CN201810319996.0A CN201810319996A CN108870445A CN 108870445 A CN108870445 A CN 108870445A CN 201810319996 A CN201810319996 A CN 201810319996A CN 108870445 A CN108870445 A CN 108870445A
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- Prior art keywords
- cooling
- shape
- inner liner
- wall surface
- air film
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Abstract
The present invention provides a kind of flame combustion chamber tube wall surface using the Y shape effusion wall type of cooling, has in the flame tube wall plate and be uniformly distributed and perforative multiple Y shape inclined holes.The structure includes a primary inlet port and three points of air film holes, and air film hole is divided to be located in each branch of cooling access ramp.More combinations can be obtained by the inlet and outlet angle and inlet and outlet diameter, the arrangement mode in flame tube wall plate that change Y shape inclined hole.Compared to the form in other holes, the Y shape inclined hole pressure loss is low, saves cooling gas consumption, and air film is more evenly distributed, and turbulence intensity is low, uniform along burner inner liner axial and circumferential cooling effect, obtains the performance of the air film of better burner inner liner inner wall.Present invention improves the problems that burner inner liner near wall air-film thickness unevenness leads to wall cooling effect unevenness, keep burner inner liner wall surface Temperature Distribution more uniform, while reducing burner inner liner wall surface temperature gradient, so that wall surface thermal stress effectively reduces.
Description
Technical field
The invention belongs to gas-turbine unit fields, are related to a kind of efficiently cold using the burner inner liner wall surface of Y shape effusion wall
But mode.
Background technique
The demand for development combustion chamber of modern aeroengine has the characteristic of high temperature rise, under conditions of oil-gas ratio is fixed,
Participation burning gas consumption must be increased, under conditions of combustion chamber charge amount is certain, it means that cooling gas consumption constantly subtracts
Few, the requirement of high temperature rise and wall cooling to air conditioning quantity forms contradiction, therefore new and effective there is an urgent need to use on burner inner liner
Cooling technology.The basic type of cooling cooling currently used for combustion chamber flame drum has gaseous film control, convection current gaseous film control, impacts
Gaseous film control, diverging cooling and laminate cooling etc., basic cooling principle are all that cold air ring cavity inside and outside combustion chamber enters flame
Cylinder in, burner inner liner inner wall surface formed one layer of air film, air film be close to burner inner liner inner wall flowing, air film play cooling wall and
The effect of burner inner liner wall surface is washed away in isolation combustion gas.Cooling air can be effectively utilized in the air film of high-quality, and obtains high air film
Cooling efficiency, wherein the adherent effect of degree, that is, air film of air film close to two-dimensional flow is to characterize the main indicator of air film quality.
In terms of shaped film-hole, researcher has carried out a large amount of research, and result of study shows and traditional cylinder
Straight hole is compared, and Film Cooling can effectively be promoted by improving shaped film-hole.The flame tube wall of conventional film cooling structure
It is relatively more to consume cooling tolerance, it is serious along the waste of burner inner liner axial downstream cooling air, cause overall efficiency to reduce larger；Flame
Cooling air film near cylinder inner wall, which is constantly superimposed, to thicken, and causes to occupy the more combustion volume in combustion chamber；Along burner inner liner axial direction
Decline rapidly, leads to higher Calculating Wall Temperature of Flame Tube gradient, generates higher thermal stress.
Effusion wall burner inner liner cooling technology is a kind of efficient cooling technology of NEW TYPE OF COMPOSITE, for high-performance aeroengine
Development potential have great application value.There are many form, such as oblique straight hole, shrinkage hole, shrinkage expansions for the form of effusion wall
Hole etc..Y shape inclined hole is also a kind of effusion wall, and only its cooling air is flowed out from multiple cooling duct branches, and this pass compares
For other passes, the pressure loss is small, and cooling gas consumption is small, and air film distribution is more uniform.This Y shape effusion wall is navigating
It is studied during the turbine blade air film of empty engine is cooling, but does not carry out correlation also in terms of burner inner liner wall surface cooling technology
Research.
Summary of the invention
The technical problem to be solved by the present invention is to propose a kind of combustion chamber flame drum using the Y shape effusion wall type of cooling
Wall surface.Compared with prior art, the present invention is uniformly distributed and perforative multiple Y shape inclined holes are set using having on burner inner liner wall surface
Meter.Compared to the form of other cooling holes, the Y shape effusion wall pressure loss is low, saves cooling gas consumption, and air film distribution is more equal
Even, turbulence intensity is low, uniform along burner inner liner axial and circumferential cooling effect, obtains the property of the air film of better burner inner liner inner wall
Energy.This cooling hole, which improves burner inner liner near wall air-film thickness unevenness, leads to the problem of wall cooling effect unevenness, makes fire
Flame tube wall surface Temperature Distribution is more uniform, while reducing burner inner liner wall surface temperature gradient, so that wall surface thermal stress effectively reduces.
Technical solution
The purpose of the present invention is to provide a kind of flame combustion chamber tube wall surfaces using the Y shape effusion wall type of cooling.
Technical solution of the present invention is as follows：
A kind of flame combustion chamber tube wall surface using the Y shape effusion wall type of cooling, it is characterised in that：Have in flame tube wall plate
It is uniformly distributed and perforative multiple Y shape inclined holes.The Y shape inclined hole is made of a primary inlet port and three points of air film holes, divides gas
Fenestra is located in each branch of cooling access ramp.Primary inlet port and the Circularhole diameter for dividing air film hole to be formed on burner inner liner wall surface
Magnitude range be 0.5~2mm, and the diameter of primary inlet port is greater than and divides the diameter of air film hole, primary inlet port and each point of air film
The angle a of axis is 120~150 degree where hole.There is fork to arrange in the arrangement mode of the Y shape inclined hole of the adjacent row of burner inner liner axial direction
With in-line arrangement two ways, the range for arranging spacing is 1~10 times of aperture, and the Y shape inclined hole of same row has phase on burner inner liner
Same shape and pitch of holes, the holes of difference row can have different pitchs of holes, and the range of pitch of holes is the 1~10 of aperture
Times.Cooling air-flow enters burner inner liner wall cooling access ramp from primary inlet port, flows out from each point of air film hole, in burner inner liner inner wall
Gaseous film control is formed on face.
The invention has the advantages that：
The type of cooling of Y shape effusion wall is used on flame combustion chamber tube wall surface, different from other cooling holes, the Y shape is more
Inclined hole is made of a primary inlet port and three points of air film holes, divides air film hole to be located in each branch of cooling access ramp, Y shape is more
Inclined hole is uniformly distributed and is applied on burner inner liner wall surface.The inlet and outlet angle and inlet and outlet diameter for reasonably adjusting Y shape inclined hole, can
To obtain good Film Cooling.This is because it is low using Y shape effusion wall pressure loss, cooling gas consumption is saved,
Air film is more evenly distributed, and turbulence intensity is low, uniform along burner inner liner axial and circumferential cooling effect, while improving burner inner liner wall surface
Neighbouring air-film thickness unevenness leads to the problem of wall cooling effect unevenness, keeps burner inner liner wall surface Temperature Distribution more uniform, reduces
Calculating Wall Temperature of Flame Tube gradient, avoids excessively high thermal stress, avoids the failures such as the warpage for causing wall surface and crackle, improve flame
Cylinder service life.
Detailed description of the invention
Fig. 1：The Y shape effusion wall flame tube wall plate three-dimensional figure arranged in a manner of the row of pitching
Fig. 2：Flame tube wall plate cross-sectional view on burner inner liner axial direction
Fig. 3：Flame tube wall plate longitudinal section
Fig. 4：Primary inlet port distribution schematic diagram on flame drum outer wall
Fig. 5：Divide air film hole distribution schematic diagram on burner inner liner inner wall
Fig. 6：Gas-turbine combustion chamber basic structure
1- flame tube wall plate 2- primary inlet port 3- divides air film hole in figure
Specific embodiment
Now in conjunction with attached drawing, the invention will be further described：
Fig. 1 is the Y shape effusion wall flame tube wall plate three-dimensional figure arranged in a manner of the row of pitching, it can be seen that the layout of Y shape inclined hole
Mode, Fig. 2 and Fig. 3 are respectively flame tube wall plate cross-sectional view and longitudinal section on burner inner liner axial direction, for determining
The angle and Y shape inclined hole cooling duct shape of axis where primary inlet port and each point of air film hole, Fig. 4 and Fig. 5 are respectively flame
Primary inlet port and the distribution schematic diagram for dividing air film hole on cylinder inside and outside wall, for determining diameter, the row's spacing of each Y shape inclined hole
And pitch of holes.Fig. 6 is gas-turbine combustion chamber basic structure, and the air-flow come out from the diffuser of gas-turbine combustion chamber is divided into
Three strands, one intermediate air-flow, which enters inside burner inner liner, forms DIE Temperature up to the combustion gas of 2500K with fuel burning, and in addition
The temperature of two strands of air-flows is lower, this two strands of air-flows are entered inside burner inner liner by the Y shape inclined hole in flame tube wall plate, meets high temperature
Gas mixing reduces thermal stress, improves burner inner liner so that the gas flow temperature of burner inner liner near wall is reduced to reasonable level
Service life.
According to Fig. 1, have on flame tube wall plate (1) and be uniformly distributed and perforative multiple Y shape inclined holes, and Y shape
Effusion wall fork arrangement is set.The Y shape inclined hole is made of a primary inlet port (2) and three points of air film holes (3), divides air film hole
(3) be located in each branch of cooling access ramp, one of branch along burner inner liner axial direction or the flow direction of combustion gas,
Other two branch is along burner inner liner circumferential direction.It can make in this way, cooling gas is when passing through Y shape inclined hole, along flame
Cylinder axial direction, air film can more be bonded wall surface, and also more evenly, the flow regime of air film is also more stable for air-film thickness.In addition,
The air film formed between different Y shape inclined holes has the effect mutually compensated, the stream of the air-flow in each point of air film hole (3) exit
Dynamic state also can be more stable.Since the diameter of primary inlet port (2) is greater than the diameter for dividing air film hole (3), airflow pressure losses are low,
And cooling gas consumption is saved, turbulence intensity reduces, to obtain good Film Cooling.
Claims (5)
1. a kind of flame combustion chamber tube wall surface using the Y shape effusion wall type of cooling, it is characterised in that：Have in flame tube wall plate
It is uniformly distributed and perforative multiple Y shape inclined holes.
2. a kind of flame combustion chamber tube wall surface using the Y shape effusion wall type of cooling according to claim 1, feature exist
In：The Y shape effusion wall is made of a primary inlet port and three points of air film holes, divides air film hole positioned at each point of cooling access ramp
Zhi Shang.
3. a kind of flame combustion chamber tube wall surface using the Y shape effusion wall type of cooling according to claim 1 or 2, special
Sign is：The magnitude range of primary inlet port and the Circularhole diameter for dividing air film hole to be formed on burner inner liner wall surface is 0.5~2mm, and
The diameter of primary inlet port is greater than the diameter for dividing air film hole, and the angle a of axis is 120 where primary inlet port and each point of air film hole
~150 degree.
4. a kind of flame combustion chamber tube wall surface using the Y shape effusion wall type of cooling according to claim 1,2 or 3,
It is characterized in that：There are fork row and in-line arrangement two ways in the arrangement mode of the Y shape inclined hole of the adjacent row of burner inner liner axial direction, arranges spacing
Range be 1~10 times of aperture, the Y shape inclined hole of same row is of similar shape and pitch of holes on burner inner liner, difference row
Hole can have different pitchs of holes, the range of pitch of holes is 1~10 times of aperture.
5. a kind of flame combustion chamber tube wall surface using the Y shape effusion wall type of cooling according to claim 1,2,3 or 4,
It is characterized in that：Cooling air-flow enters burner inner liner wall cooling access ramp from primary inlet port, flows out from each point of air film hole, in fire
Gaseous film control is formed on flame cylinder inner wall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810319996.0A CN108870445A (en) | 2018-04-11 | 2018-04-11 | A kind of flame combustion chamber tube wall surface using the Y shape effusion wall type of cooling |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810319996.0A CN108870445A (en) | 2018-04-11 | 2018-04-11 | A kind of flame combustion chamber tube wall surface using the Y shape effusion wall type of cooling |
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| CN108870445A true CN108870445A (en) | 2018-11-23 |
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| CN201810319996.0A Pending CN108870445A (en) | 2018-04-11 | 2018-04-11 | A kind of flame combustion chamber tube wall surface using the Y shape effusion wall type of cooling |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109469512A (en) * | 2019-01-04 | 2019-03-15 | 西北工业大学 | A kind of chiasma type X air film hole cooling structure for turbo blade |
| CN110925791A (en) * | 2019-11-06 | 2020-03-27 | 西北工业大学 | Double-wall impact/Y-shaped multi-inclined-hole-wall composite cooling type combustion chamber flame tube wall surface structure |
| CN111911962A (en) * | 2020-08-18 | 2020-11-10 | 西北工业大学 | Novel flame tube wall surface cooling structure |
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|---|---|---|---|---|
| EP1001222A2 (en) * | 1998-11-13 | 2000-05-17 | General Electric Company | Multi-hole film cooled combustor liner |
| CN103437889A (en) * | 2013-08-06 | 2013-12-11 | 清华大学 | Branch gas film hole structure for cooling gas turbine engine |
| CN104791848A (en) * | 2014-11-25 | 2015-07-22 | 西北工业大学 | Combustion chamber flame cylinder wall face with blade grid channel multi-inclined-hole cooling manner adopted |
| CN104879171A (en) * | 2015-05-08 | 2015-09-02 | 西北工业大学 | Y-shaped air film hole structure used for turbine blade |
| CN107060894A (en) * | 2017-06-15 | 2017-08-18 | 中国科学院工程热物理研究所 | Fork type film hole structure |
| CN107683391A (en) * | 2015-06-03 | 2018-02-09 | 赛峰航空器发动机 | The annular wall of combustion chamber with optimization cooling |
-
2018
- 2018-04-11 CN CN201810319996.0A patent/CN108870445A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1001222A2 (en) * | 1998-11-13 | 2000-05-17 | General Electric Company | Multi-hole film cooled combustor liner |
| CN103437889A (en) * | 2013-08-06 | 2013-12-11 | 清华大学 | Branch gas film hole structure for cooling gas turbine engine |
| CN104791848A (en) * | 2014-11-25 | 2015-07-22 | 西北工业大学 | Combustion chamber flame cylinder wall face with blade grid channel multi-inclined-hole cooling manner adopted |
| CN104879171A (en) * | 2015-05-08 | 2015-09-02 | 西北工业大学 | Y-shaped air film hole structure used for turbine blade |
| CN107683391A (en) * | 2015-06-03 | 2018-02-09 | 赛峰航空器发动机 | The annular wall of combustion chamber with optimization cooling |
| CN107060894A (en) * | 2017-06-15 | 2017-08-18 | 中国科学院工程热物理研究所 | Fork type film hole structure |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109469512A (en) * | 2019-01-04 | 2019-03-15 | 西北工业大学 | A kind of chiasma type X air film hole cooling structure for turbo blade |
| CN110925791A (en) * | 2019-11-06 | 2020-03-27 | 西北工业大学 | Double-wall impact/Y-shaped multi-inclined-hole-wall composite cooling type combustion chamber flame tube wall surface structure |
| CN111911962A (en) * | 2020-08-18 | 2020-11-10 | 西北工业大学 | Novel flame tube wall surface cooling structure |
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Application publication date: 20181123 |
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