CN110081466A - A kind of burner inner liner wall structure cooling using microchannel - Google Patents
A kind of burner inner liner wall structure cooling using microchannel Download PDFInfo
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- CN110081466A CN110081466A CN201910333588.5A CN201910333588A CN110081466A CN 110081466 A CN110081466 A CN 110081466A CN 201910333588 A CN201910333588 A CN 201910333588A CN 110081466 A CN110081466 A CN 110081466A
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- rib
- wall face
- microchannel
- inner liner
- longitudinal rib
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
The present invention provides a kind of burner inner liner wall structure cooling using microchannel, and a large amount of cross ribs and longitudinal rib are arranged between burner inner liner cold wall face and hot wall face.Cooling air-flow a part is by entering longitudinal rib microchannel on the outside of cold wall face, realize heat convection, finally from the aperture outflow on hot wall face and in hot wall face realization gaseous film control, another part cooling air-flow is entered the airflow channel between cross rib and longitudinal rib by the aperture on cold wall face, blast of cold air is along airflow channel lateral flow, another stock is moved by cold wall towards hot wall surface current by the flow-disturbing hole on cross rib, is finally gone out from hot wall surface current, realizes gaseous film control.Flame tube wall heat exchange area has been significantly greatly increased in the invention, and cooling performance has very big promotion, can meet the cooling requirement in the following high temperature rise aeroengine combustor buring locular wall face.
Description
Technical field
The invention belongs to gas-turbine unit fields, and in particular to a kind of burner inner liner wall surface knot cooling using microchannel
Structure.
Background technique
The demand for development combustion chamber of modern aeroengine has the characteristic of high temperature rise, and the following advanced aero engine can be into
One step improves turbine inlet temperature, in the case where oil-gas ratio is fixed, it is necessary to increase and participate in burning gas consumption, to reduce cooling
Gas consumption.Combustion chamber flame drum wall heat load increases severely, and cooling gas consumption but declines, in order to guarantee service life of burner inner liner and reliable
Property, it is very urgent to develop efficient cooling technology.
Early stage type uses single-layer flame tube wall surface cooling structure, such as using F404, F110 as the gaseous film control of representative, with
GE90 is that the full diverging gaseous film control of representative is also referred to as the veneer structure etc. of quasi- Sweat coolling.In order to improve cooling efficiency,
Start in aero-engine using Compound cooling technology, the types of cooling knot such as cooling, diverging cooling and gaseous film control by convection current
It closes and uses, although cooling efficiency increases, cooling air-flow cannot be fine with wall surface before forming air film in these methods
Heat exchange, it is not high to the utilization rate of cooling air-flow.How to allow cooling air-flow sufficiently to exchange heat before forming air film with wall surface reduces wall
Face temperature is the key that promote cooling efficiency.
The country, which further defines the research of this respect, strengthens heat convection in structures such as single cross rib, turbulence columns,
It there is no the burner inner liner wall surface cooling technology using microchannel.Microchannel refers to that characteristic size is less than the channel of 1.0mm, and microchannel is changed
Heat has the characteristics that exchange capability of heat is strong, structure size is small, light-weight, is widely used in the heat transmission of high energy current density.This
Invention proposes a kind of burner inner liner wall structure cooling using microchannel, increases heat convection using the arrangement of a large amount of microchannels
Area, allowing cooling air-flow sufficiently to exchange heat before forming air film with wall surface reduces wall surface temperature, improves the utilization rate of cooling air-flow.
Summary of the invention
It is and existing the technical problem to be solved by the present invention is to propose a kind of burner inner liner wall structure cooling using microchannel
The advantages of some technologies are compared, this programme is on the basis of traditional flame cylinder double wall cooling structure, in cold wall face and hot wall face
Between arrange a large amount of orthogonal rib structures, the airflow channel that a large amount of characteristic sizes are less than 1.0mm is formed between adjacent rib, laterally
It is provided with flow-disturbing hole on rib, a large amount of microchannels are also arranged in longitudinal rib, cooling air-flow flows in above-mentioned channel, hole, greatly increases
The heat exchange area for having added cooling air-flow Yu burner inner liner wall surface, is utmostly utilized cooling air-flow, improves burner inner liner surface
High-temperature capability and service life.
Technical solution
The purpose of the present invention is to provide a kind of burner inner liner wall structures cooling using microchannel.
Technical solution of the present invention is as follows:
A kind of burner inner liner wall structure cooling using microchannel, size and arrangement, cross including cross rib and longitudinal rib
To the size and arrangement, the size and arrangement of longitudinal rib microchannel in the flow-disturbing hole of rib, the size of cold wall face airflow hole and arrangement with
And the size and arrangement of hot wall face air film hole.
The size and arrangement of the cross rib and longitudinal rib, it is characterised in that: cross rib and longitudinal rib square crossing cloth
It sets, the rib thickness of cross rib and longitudinal rib is 0.2~0.5mm, and rib spacing is 0.5~1.0mm, the arrangement of cross rib and longitudinal rib
Number is depending on combustion chamber dimensions.
The size and arrangement in the flow-disturbing hole of the cross rib, it is characterised in that: on the cross rib between two longitudinal ribs
It is disposed with row's flow-disturbing hole, the diameter in hole is 0.3~0.5mm, and pitch of holes is 0.6~1.0mm, the angle in flow-disturbing hole and horizontal direction
Degree flow-disturbing hole on 30 °~60 °, adjacent transverse rib is opposite with the angle of horizontal direction.
The size and arrangement of the longitudinal rib microchannel, it is characterised in that: cold wall face, longitudinal direction are run through in longitudinal rib microchannel
Rib and hot wall face, diameter are 0.2~0.3mm, and the angle of part of the longitudinal rib microchannel in hot wall face and horizontal direction is by 90 °
Gradually decrease to 60 ° to 30 °.
The size and arrangement of the cold wall face airflow hole, it is characterised in that: cold wall face airflow hole is vertical with horizontal direction,
Diameter is 0.3~0.5mm, and pitch of holes is 0.6~1.0mm, connection cold wall face outside and the gas between cross rib and longitudinal rib
Circulation road.
The size and arrangement of the hot wall face air film hole, it is characterised in that: hot wall face air film bore dia be 0.3~
0.5mm, pitch of holes are 0.6~1.0mm, connection hot wall face outside and the airflow channel between cross rib and longitudinal rib, hot wall
Face air film hole and the angle of horizontal direction gradually decrease to 60 ° to 30 ° by 90 °.
The invention has the following advantages:
A kind of burner inner liner wall structure cooling using microchannel of program design the advantage is that a large amount of by arranging
Rib structure and in rib interior design airflow channel reaches and possesses the hole that a large amount of characteristic sizes are less than 1.0mm on the cooling structure
Gap, channel are flowed for cooling air-flow, and the heat exchange area of cooling air-flow Yu burner inner liner wall surface is significantly greatly increased, makes full use of cooling air
Stream, improves the high-temperature capability and service life on burner inner liner surface.
Detailed description of the invention
A kind of Fig. 1: burner inner liner wall structure overall schematic cooling using microchannel
Fig. 2: longitudinal rib schematic diagram of internal structure
Fig. 3: cross rib schematic diagram of internal structure
In figure: 1- cold wall face, 2- longitudinal rib, 3- cross rib, 4- hot wall face, 5- longitudinal rib microchannel, 6- cold wall face air-flow
Hole, 7- flow-disturbing hole, 8- hot wall face air film hole
Specific embodiment
Now in conjunction with attached drawing, the invention will be further described:
In conjunction with Fig. 1, Fig. 2, Fig. 3, the present invention provides a kind of burner inner liner wall structures cooling using microchannel.Fig. 1 is
A kind of burner inner liner wall structure overall schematic cooling using microchannel, Fig. 2 are longitudinal rib schematic diagram of internal structure, and Fig. 3 is
Cross rib schematic diagram of internal structure.
Cooling air-flow a part enters longitudinal rib microchannel 5, cold wall face 1, longitudinal rib 2, hot wall face 4 is flowed through, finally from heat
Outflow and to carrying out gaseous film control on the inside of hot wall face 4 on the inside of wall surface 4.Another part cooling air-flow is entered by cold wall face airflow hole 6
Airflow channel between cross rib 3 and longitudinal rib 2, one cooling air-flow exchange heat along airflow channel lateral flow, another stock
It is flowed by the flow-disturbing hole 7 on cross rib 3 from cold wall face 6 to hot wall face 4, is finally flowed out from hot wall face air film hole 8, realized to heat
The gaseous film control of 4 inside of wall surface, as shown in figure 3, the angle in flow-disturbing hole 7 and horizontal direction on adjacent cross rib 3 is on the contrary, increase
The big turbulivity of cooling air-flow, and then increase heat exchange amount.In the invention, cooling air-flow flows through before carrying out gaseous film control
The a large amount of characteristic sizes arranged in structure are less than the microchannel of 1.0mm, substantially increase cooling air-flow and burner inner liner wall surface
Cooling air-flow utmostly is utilized, it can be achieved that further decreasing aero-engine cooling tolerance in heat exchange area, and obtains more preferable
Cooling effect, improve burner inner liner surface heat resistance and service life, be conducive to combustion chamber realize high temperature rise.
Claims (6)
1. a kind of burner inner liner wall structure cooling using microchannel, size and arrangement, transverse direction including cross rib and longitudinal rib
The size in the flow-disturbing hole of rib and arrangement, the size and arrangement of longitudinal rib microchannel, the size and arrangement of cold wall face airflow hole and
The size and arrangement of hot wall face air film hole.
2. a kind of burner inner liner wall structure cooling using microchannel according to claim 1, it is characterised in that: cross rib
It is arranged with longitudinal rib square crossing, the rib thickness of cross rib and longitudinal rib is 0.2~0.5mm, and rib spacing is 0.5~1.0mm, laterally
The arrangement number of rib and longitudinal rib is depending on combustion chamber dimensions.
3. a kind of burner inner liner wall structure cooling using microchannel according to claim 1 or 2, it is characterised in that: two
It is disposed with single flow-disturbing hole on cross rib between a longitudinal rib, the diameter in hole is 0.3~0.5mm, pitch of holes is 0.6~
The angle phase in the angle of 1.0mm, flow-disturbing hole and horizontal direction flow-disturbing hole and horizontal direction on 30 °~60 °, adjacent transverse rib
Instead.
4. a kind of burner inner liner wall structure cooling using microchannel according to claim 1,2 or 3, it is characterised in that:
Cold wall face, longitudinal rib and hot wall face are run through in longitudinal rib microchannel, and diameter is 0.2~0.3mm, and longitudinal rib microchannel is in hot wall face
Part and the angle of horizontal direction gradually decrease to 60 ° to 30 ° by 90 °.
5. a kind of burner inner liner wall structure cooling using microchannel according to claim 1,2,3 or 4, feature exist
In: cold wall face airflow hole is vertical with horizontal direction, and diameter is 0.3~0.5mm, and pitch of holes is 0.6~1.0mm, is connected to cold wall
Face outside and the airflow channel between cross rib and longitudinal rib.
6. according to claim 1, a kind of burner inner liner wall structure cooling using microchannel, feature described in 2,3,4 or 5 exist
Be 0.3~0.5mm in: hot wall face air film bore dia, pitch of holes is 0.6~1.0mm, on the inside of connection hot wall face with cross rib and
The angle of airflow channel between longitudinal rib, hot wall face air film hole and horizontal direction gradually decreases to 60 ° to 30 ° by 90 °.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2019100491398 | 2019-01-18 | ||
| CN201910049139 | 2019-01-18 |
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| Publication Number | Publication Date |
|---|---|
| CN110081466A true CN110081466A (en) | 2019-08-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910333588.5A Pending CN110081466A (en) | 2019-01-18 | 2019-04-24 | A kind of burner inner liner wall structure cooling using microchannel |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111207412A (en) * | 2020-01-17 | 2020-05-29 | 西北工业大学 | Combustor flame tube adopting floating tile |
| CN112228903A (en) * | 2020-09-18 | 2021-01-15 | 西北工业大学 | Three-channel type combustion chamber flame tube wall surface structure with longitudinal vortex generator |
| CN113137627A (en) * | 2021-03-29 | 2021-07-20 | 华东师范大学 | Machining and positioning method for aero-engine flame tube cooling air film hole |
| CN113217949A (en) * | 2021-05-20 | 2021-08-06 | 西安航天动力研究所 | Combustion chamber diverging and cooling structure and ramjet combustion chamber |
| CN114370336A (en) * | 2022-01-07 | 2022-04-19 | 中国人民解放军国防科技大学 | Rankine cycle-thermoelectric drive coupling waste heat recovery energy management system |
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| CN105276620A (en) * | 2015-06-26 | 2016-01-27 | 中航空天发动机研究院有限公司 | Composite cooling structure for wall of combustion chamber flame tube of aero-engine |
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2019
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| US5605046A (en) * | 1995-10-26 | 1997-02-25 | Liang; George P. | Cooled liner apparatus |
| JP2002155758A (en) * | 2000-11-22 | 2002-05-31 | Mitsubishi Heavy Ind Ltd | Cooling structure and combustor using the same |
| CN101245745A (en) * | 2008-01-17 | 2008-08-20 | 清华大学 | Laminated board sweat cooling structure by strong endothermic reaction |
| 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 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111207412A (en) * | 2020-01-17 | 2020-05-29 | 西北工业大学 | Combustor flame tube adopting floating tile |
| CN112228903A (en) * | 2020-09-18 | 2021-01-15 | 西北工业大学 | Three-channel type combustion chamber flame tube wall surface structure with longitudinal vortex generator |
| CN113137627A (en) * | 2021-03-29 | 2021-07-20 | 华东师范大学 | Machining and positioning method for aero-engine flame tube cooling air film hole |
| CN113137627B (en) * | 2021-03-29 | 2022-07-08 | 星控激光科技(上海)有限公司 | Machining and positioning method for cooling air film hole of flame tube of aircraft engine |
| CN113217949A (en) * | 2021-05-20 | 2021-08-06 | 西安航天动力研究所 | Combustion chamber diverging and cooling structure and ramjet combustion chamber |
| CN114370336A (en) * | 2022-01-07 | 2022-04-19 | 中国人民解放军国防科技大学 | Rankine cycle-thermoelectric drive coupling waste heat recovery energy management system |
| CN114370336B (en) * | 2022-01-07 | 2023-08-18 | 中国人民解放军国防科技大学 | Rankine cycle-thermoelectric drive coupling waste heat recovery energy management system |
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Application publication date: 20190802 |
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