CN112197296A - Flame tube wall plate - Google Patents
Flame tube wall plate Download PDFInfo
- Publication number
- CN112197296A CN112197296A CN202010995839.9A CN202010995839A CN112197296A CN 112197296 A CN112197296 A CN 112197296A CN 202010995839 A CN202010995839 A CN 202010995839A CN 112197296 A CN112197296 A CN 112197296A
- Authority
- CN
- China
- Prior art keywords
- cascade channel
- flame tube
- channel holes
- inlet
- cascade
- 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.)
- Pending
Links
Images
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
- F23R3/002—Wall structures
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
The application belongs to the aeroengine field, in particular to flame tube wallboard. The method comprises the following steps: the flame tube wall plate (1) is provided with a plurality of cascade channel holes (2), wherein the diameters of the cascade channel holes (2) from an inlet to an outlet are gradually reduced; the included angle between the tangent line from the inlet to the outlet of the cascade channel hole (2) and the axis of the flame tube wall plate (1) is gradually reduced; the projection of the center line of the cascade channel hole (2) from the inlet to the outlet along the normal direction has a blending angle with the axis of the flame tube wall plate (1). The utility model provides a flame tube wallboard compares with current flame tube wallboard cooling hole, and the flame tube wallboard cooling effect of cascade passageway pass is better, and cooling efficiency is high, and loss of pressure is little, and the air film is attached better with the wall, distributes more evenly, and it is even along flame tube axial cooling effect, can also be better simultaneously reduce local thermal stress to avoid the bending deformation of flame tube wall production under high temperature state.
Description
Technical Field
The application belongs to the aeroengine field, in particular to flame tube wallboard.
Background
The development of modern aeroengines requires that a combustion chamber has the characteristic of high temperature rise, the gas consumption for combustion must be increased under the condition of fixed oil-gas ratio, and under the condition of certain gas input of the combustion chamber, the gas consumption for cooling is continuously reduced, and the requirements of high temperature rise and wall surface cooling on the gas consumption are contradictory, so that an efficient cooling technology is urgently needed to be adopted on a flame tube.
The basic cooling principle of the existing cooling method for the flame tube of the combustion chamber is that air with lower temperature enters the flame tube from inner and outer annular cavities of the combustion chamber through various types of holes or seams to form a layer of air film on the surface of the inner wall of the flame tube, the air film flows tightly attached to the inner wall surface of the flame tube, and the air film plays a role in cooling the wall surface and isolating gas from scouring the wall plate of the flame tube. High-quality film cooling can effectively utilize cooling gas and obtain high film cooling efficiency, but the cooling effect of the existing cooling mode is not ideal, and the cooling efficiency is low.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a liner panel to address at least one problem of the prior art.
The technical scheme of the application is as follows:
a liner panel, comprising: the flame tube wall plate is provided with a plurality of cascade channel holes, wherein,
the aperture of the cascade channel hole is gradually reduced from the inlet to the outlet;
the included angle between the tangent line of the cascade channel hole from the inlet to the outlet and the axis of the flame tube wall plate is gradually reduced;
the projection of the cascade channel holes from the center line of the inlet to the outlet along the normal direction has a blending angle with the axis of the flame tube wall plate.
Optionally, the inlet diameter of the cascade channel hole is 3mm, and the outlet diameter of the cascade channel hole is 0.5 mm.
Optionally, the blend angle ranges from 0 to 90 degrees.
Optionally, the cascade channel holes are arranged in parallel in a plurality of rows along the circumferential direction of the flame tube wall plate, and the variation range of the row spacing is 1-10 times of the inlet aperture of the cascade channel hole.
Optionally, in each row of the cascade channel holes, an included angle between a tangent of an inlet of a plurality of the cascade channel holes arranged in the airflow direction and an axis of the flame tube wall plate gradually increases, and an included angle between a tangent of an outlet of the cascade channel hole and the axis of the flame tube wall plate gradually decreases.
Optionally, in each row of the cascade channel holes, the distance between two adjacent cascade channel holes arranged in the airflow direction gradually increases, and the variation range of the hole distance is 1-10 times of the inlet aperture of the cascade channel hole.
Optionally, the plurality of cascade channel holes have the same shape and hole spacing at the same axial position of the liner wall.
Optionally, the plurality of cascade channel holes have different shapes and hole spacings at the same axial position of the liner panel.
Optionally, the arrangement of the cascade channel holes in two adjacent rows is staggered.
Optionally, the arrangement of the cascade channel holes in two adjacent rows is an aligned arrangement.
The invention has at least the following beneficial technical effects:
the utility model provides a flame tube wallboard, cooling efficiency is high, and loss of pressure is low, and the gas film distributes more evenly, and is even along flame tube axial cooling effect, the local thermal stress that reduces that can be better to avoid can bending deformation under high temperature state.
Drawings
FIG. 1 is an assembled view of a liner panel according to an embodiment of the present application;
FIG. 2 is a schematic view of a liner panel according to an embodiment of the present application;
FIG. 3 is a view of a cascade channel hole layout of a liner panel according to an embodiment of the present application;
FIG. 4 is a view A-A of FIG. 3;
FIG. 5 is a view of a cascade channel hole layout of another embodiment of a liner panel of the present application;
fig. 6 is a view B-B of fig. 5.
Wherein:
1-flame tube wall plate; 2-cascade channel holes.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 6.
The application provides a flame tube wallboard, has seted up a plurality of cascade passway holes 2 on this flame tube wallboard 1.
As shown in figure 1, the air flow discharged from the diffuser of the gas turbine combustor is divided into three flows, one flow enters the interior of the flame tube to be combusted with fuel oil to form fuel gas with the core temperature of 2500K, and the other two flows have lower temperature, and the two flows enter the interior of the flame tube through the cascade channel holes 2 on the wall plate 1 of the flame tube and are mixed when meeting high-temperature fuel gas, so that the temperature of the air flow near the wall plate 1 of the flame tube is reduced to a reasonable level, the thermal stress is reduced, and the service life of the flame tube is prolonged.
Specifically, in the flame tube wall plate, the cascade channel holes 2 are cascade channel-shaped holes formed through the flame tube wall plate 1, a plurality of the cascade channel holes are formed in the flame tube wall plate 1, inlets of the cascade channel holes 2 are located on the outer wall surface of the flame tube wall plate 1, outlets of the cascade channel holes 2 are located on the inner wall surface of the flame tube wall plate 1, and the aperture of each cascade channel hole 2 from the inlet to the outlet is gradually reduced; the included angle between the tangent line of the cascade channel hole 2 from the inlet to the outlet and the axis of the flame tube wall plate 1 is gradually reduced; the projection of the cascade channel holes 2 from the inlet to the outlet along the normal direction has a blending angle with the axis of the flame tube wall plate 1.
In one embodiment of the present application, the diameter of the circular hole formed by the inlet of the cascade channel hole 2 on the outer wall surface of the liner panel 1 is 3mm, the diameter of the circular hole formed by the outlet on the inner wall surface of the liner panel 1 is 0.5mm, and the diameter of the cascade channel hole 2 from the inlet to the outlet is uniformly reduced. In this example, the blending angle ranges from 0 to 90 degrees.
In one embodiment of the present application, as shown in fig. 2 to 4, the cascade channel holes 2 are arranged in parallel in a plurality of rows along the circumferential direction of the liner wall 1, and the row pitch P varies in a range of 1 to 10 times the inlet aperture of the cascade channel holes 2.
Referring to fig. 4, in the present embodiment, in each row of cascade channel holes 2, the included angle between the tangent of the inlet of the plurality of cascade channel holes 2 arranged in the airflow direction and the axis of the flame tube wall plate 1 gradually increases, and the included angle between the tangent of the outlet and the axis of the flame tube wall plate 1 gradually decreases, that is, the change rate of the included angle between the tangent of the plurality of cascade channel holes 2 arranged in the airflow direction from the inlet to the outlet and the axis of the flame tube wall plate 1 gradually increases. Preferably, in the present embodiment, the inlet tangent of the last cascade channel hole 2 in the airflow direction forms an angle of 90 degrees with the axis of the flame tube wall plate 1, and the inlet tangent forms an angle of 0 degree with the axis of the flame tube wall plate 1.
In this embodiment, in each row of cascade channel holes 2, the distance between two adjacent cascade channel holes 2 arranged in the airflow direction gradually increases, and the variation range of the hole distance S is 1 to 10 times of the inlet aperture of the cascade channel hole 2. The plurality of cascade channel holes 2 can have the same or different shapes and hole spacings at the same axial position of the liner panel 1.
Further, in this embodiment, the arrangement of the cascade channel holes 2 in two adjacent rows is staggered.
In another embodiment of the present application, as shown in fig. 5 to 6, the cascade channel holes 2 are arranged in parallel in a plurality of rows along the circumferential direction of the liner wall 1, and the row pitch P varies from 1 to 10 times the inlet aperture diameter of the cascade channel holes 2. In this embodiment, the arrangement of the cascade channel holes 2 in two adjacent rows is alignment.
The utility model provides a flame tube wallboard, cascade via hole 2 on flame tube wallboard 1 is the many inclined holes, does not mix, along the flow direction of flame tube axial direction or gas, the import angle of cascade via hole 2 is bigger and bigger, and the exit angle is littleer and smaller, can make cooling gas pass cascade via hole the time like this, along flame tube axial direction, the wall can be laminated more to the gas film, and the thickness of gas film is also thinner, and the flow state of gas film is also more stable. The cooling efficiency of the cascade channel holes 2 is higher and the pressure loss is low compared with straight inclined holes with the same inlet and outlet diameters. The flow state of the airflow at the outlet of the cascade channel hole 2 is more stable, the speed is higher, the heat exchange coefficient is high, the temperature of the wall surface of the flame tube can be better controlled at a reasonable level, the length of the hole is shorter under the same outlet angle, the energy loss of the airflow is small, and the structural rigidity of the wall surface is higher.
The utility model provides a flame tube wallboard compares with current flame tube wallboard cooling hole, and the flame tube wallboard cooling effect of cascade passageway pass is better, and cooling efficiency is high, and loss of pressure is little, and the air film is attached better with the wall, distributes more evenly, and it is even along flame tube axial cooling effect, can also be better simultaneously reduce local thermal stress to avoid the bending deformation of flame tube wall production under high temperature state.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A liner panel, comprising: a plurality of cascade channel holes (2) are arranged on the flame tube wall plate (1), wherein,
the aperture of the cascade channel hole (2) is gradually reduced from the inlet to the outlet;
the included angle between the tangent line from the inlet to the outlet of the cascade channel hole (2) and the axis of the flame tube wall plate (1) is gradually reduced;
the projection of the center line of the cascade channel hole (2) from the inlet to the outlet along the normal direction has a blending angle with the axis of the flame tube wall plate (1).
2. The liner panel according to claim 1, wherein the cascade channel holes (2) have an inlet diameter of 3mm and the cascade channel holes (2) have an outlet diameter of 0.5 mm.
3. The liner panel according to claim 1, wherein the blend angle is in the range of 0-90 degrees.
4. The liner wall according to claim 1, wherein the cascade channel holes (2) are arranged in parallel in a plurality of rows along the circumference of the liner wall (1), and the row pitch varies in the range of 1-10 times the inlet aperture of the cascade channel holes (2).
5. The liner wall according to claim 4, wherein in each row of the cascade channel holes (2), the included angle between the tangent of the inlet of the cascade channel holes (2) arranged along the airflow direction and the axis of the liner wall (1) is gradually increased, and the included angle between the tangent of the outlet of the cascade channel holes and the axis of the liner wall (1) is gradually decreased.
6. The flame tube wall plate according to claim 4, characterized in that in each row of the cascade channel holes (2), the distance between two adjacent cascade channel holes (2) arranged along the airflow direction is gradually increased, and the hole distance is 1-10 times of the inlet hole diameter of the cascade channel holes (2).
7. The liner panel according to claim 4, wherein the cascade channel holes (2) have the same shape and hole spacing at the same axial position of the liner panel (1).
8. The liner panel according to claim 4, wherein a plurality of the cascade channel holes (2) have different shapes and hole spacings at the same axial position of the liner panel (1).
9. The liner panel according to any one of claims 7 or 8, wherein the arrangement of the cascade channel holes (2) in two adjacent rows is staggered.
10. The liner panel according to any one of claims 7 or 8, wherein the arrangement of the cascade channel holes (2) in two adjacent rows is aligned.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010995839.9A CN112197296A (en) | 2020-09-21 | 2020-09-21 | Flame tube wall plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010995839.9A CN112197296A (en) | 2020-09-21 | 2020-09-21 | Flame tube wall plate |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112197296A true CN112197296A (en) | 2021-01-08 |
Family
ID=74015781
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010995839.9A Pending CN112197296A (en) | 2020-09-21 | 2020-09-21 | Flame tube wall plate |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112197296A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115493163A (en) * | 2022-09-06 | 2022-12-20 | 清华大学 | Combustor flame tube and efficient cooling method for combustor flame tube |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000130758A (en) * | 1998-07-16 | 2000-05-12 | General Electric Co <Ge> | Transition multi-hole combustor liner |
| 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 |
| WO2016204534A1 (en) * | 2015-06-16 | 2016-12-22 | 두산중공업 주식회사 | Combustion duct assembly for gas turbine |
| CN109990309A (en) * | 2019-03-05 | 2019-07-09 | 南京航空航天大学 | A kind of compound cooling structure of combustion chamber wall surface and turboshaft engine reverse flow type combustor |
| CN111520760A (en) * | 2020-04-10 | 2020-08-11 | 西北工业大学 | Combustion chamber flame tube wall surface structure adopting impact/gas film double-wall composite cooling mode |
-
2020
- 2020-09-21 CN CN202010995839.9A patent/CN112197296A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000130758A (en) * | 1998-07-16 | 2000-05-12 | General Electric Co <Ge> | Transition multi-hole combustor liner |
| 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 |
| WO2016204534A1 (en) * | 2015-06-16 | 2016-12-22 | 두산중공업 주식회사 | Combustion duct assembly for gas turbine |
| CN109990309A (en) * | 2019-03-05 | 2019-07-09 | 南京航空航天大学 | A kind of compound cooling structure of combustion chamber wall surface and turboshaft engine reverse flow type combustor |
| CN111520760A (en) * | 2020-04-10 | 2020-08-11 | 西北工业大学 | Combustion chamber flame tube wall surface structure adopting impact/gas film double-wall composite cooling mode |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115493163A (en) * | 2022-09-06 | 2022-12-20 | 清华大学 | Combustor flame tube and efficient cooling method for combustor flame tube |
| CN115493163B (en) * | 2022-09-06 | 2024-02-20 | 清华大学 | Combustion chamber flame tube and high-efficiency cooling method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104791848A (en) | Combustion chamber flame cylinder wall face with blade grid channel multi-inclined-hole cooling manner adopted | |
| CN109990309B (en) | Composite cooling structure of combustion chamber wall surface and turboshaft engine backflow combustion chamber | |
| JPH1082527A (en) | Gas turbine combustor | |
| CN202203987U (en) | Backflow combustion chamber flame tube cooling structure of shaft turbine | |
| US6553766B2 (en) | Cooling structure of a combustor tail tube | |
| CN102203509A (en) | Burner inserts for a gas turbine combustion chamber and gas turbine | |
| CN112050255B (en) | Flame tube adopting clearance rotational flow cooling | |
| CN105276620A (en) | Composite cooling structure for wall of combustion chamber flame tube of aero-engine | |
| CN113188154B (en) | Flame tube with cooling structure | |
| CN202203988U (en) | Backflow combustion chamber of shaft turbine | |
| CN111520760A (en) | Combustion chamber flame tube wall surface structure adopting impact/gas film double-wall composite cooling mode | |
| CN110081466A (en) | A kind of burner inner liner wall structure cooling using microchannel | |
| CN203464332U (en) | Transition section of combustion chamber of combustion gas turbine | |
| CN104807042A (en) | Combustion chamber | |
| CN112197296A (en) | Flame tube wall plate | |
| CN202419699U (en) | Multi-inclined-hole flame tube wall plate, flame tube and gas turbine combustion chamber | |
| CN202209695U (en) | Turboshaft engine backflow combustion chamber with novel flame tube cooling structure | |
| CN104612833A (en) | Gas turbine combustor | |
| CN108870445A (en) | A kind of flame combustion chamber tube wall surface using the Y shape effusion wall type of cooling | |
| CN112815357A (en) | Flame tube structure of combustion chamber and combustion chamber | |
| EP2107314A1 (en) | Combustor for a gas turbine | |
| CN111648866A (en) | Impact air film-divergent hole composite cooling structure | |
| JP2013127355A (en) | System of integrating baffle for enhanced cooling of cmc liner | |
| CN112082176B (en) | Combustion chamber of miniature turbojet engine | |
| CN212869853U (en) | Combustion chamber structure of micro turbojet 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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210108 |
|
| RJ01 | Rejection of invention patent application after publication |