CN116122916A - Duck-foot-shaped turbine blade air film hole and turbine blade - Google Patents
Duck-foot-shaped turbine blade air film hole and turbine blade Download PDFInfo
- Publication number
- CN116122916A CN116122916A CN202310105376.8A CN202310105376A CN116122916A CN 116122916 A CN116122916 A CN 116122916A CN 202310105376 A CN202310105376 A CN 202310105376A CN 116122916 A CN116122916 A CN 116122916A
- Authority
- CN
- China
- Prior art keywords
- branch
- turbine blade
- duck
- foot
- groove
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a duck foot type turbine blade air film hole and a turbine blade, wherein the air film hole comprises: a cylindrical hole section, wherein one end of the cylindrical hole section is an upstream cold air inlet end, and the other end of the cylindrical hole section is a downstream cold air outlet end according to the cold air flowing direction; the expansion section is communicated with the downstream cold air outlet end of the cylindrical hole section; the expansion section is of a groove-shaped structure with an opening on the top surface, the groove body of the groove-shaped structure comprises a bulge which extends outwards in the flowing direction of cold air, and a first branch and a second branch which are respectively positioned at two sides of the bulge, wherein the first branch and the second branch are symmetrical structures positioned at two sides of the bulge, and the first branch, the bulge and the second branch are in arc transition, so that the appearance of the expansion section is duck-foot-shaped; the semi-groove is of a semi-cylindrical structure with an open top surface, one end of the semi-cylindrical structure is communicated with the expansion section, and the other end of the semi-cylindrical structure extends towards the upstream direction of cold air flow to form the semi-groove. The invention can effectively improve the covering effect of the cool air film of the turbine blade.
Description
Technical Field
The invention relates to the technical field of aeroengine turbine blade cooling, in particular to a duck-foot-shaped turbine blade air film hole and a turbine blade.
Background
In order to obtain higher thrust weight ratio and thermal efficiency, the modern aviation gas turbine engine continuously increases the turbine inlet temperature, the turbine inlet temperature at present is far higher than the melting point temperature of blade materials, a complex cooling technology is required to be adopted to keep the normal work of turbine blades, the turbine blade cooling technology is divided into external cooling and internal cooling, a series of air film holes are arranged on the surfaces of the turbine blades, cold air flows out of the air film holes and covers the surfaces of the blades, and the blades and the gas are isolated, so that the blade temperature is reduced, and therefore, the improvement of the air film covering effect of the air film holes is very important to the cooling design of the turbine blades.
Disclosure of Invention
In view of this, the embodiment of the application provides a duck-foot type turbine blade air film hole and turbine blade to reach the purpose that improves turbine blade air conditioning air film and cover the effect.
The embodiment of the application provides the following technical scheme: a duck foot turbine blade air film hole comprising:
a cylindrical hole section, wherein one end of the cylindrical hole section is an upstream cold air inlet end, and the other end of the cylindrical hole section is a downstream cold air outlet end according to the cold air flowing direction;
an expansion section communicated with the downstream cool air outlet end of the cylindrical hole section; the expansion section is of a groove-shaped structure with an opening on the top surface, the groove body of the groove-shaped structure comprises a protrusion extending outwards in the flowing direction of cold air, and a first branch and a second branch which are respectively positioned at two sides of the protrusion, the first branch and the second branch are symmetrical structures positioned at two sides of the protrusion, and the first branch, the protrusion and the second branch are in arc transition, so that the appearance of the expansion section is a duck-foot shape;
the semi-groove is of a semi-cylindrical structure with an open top surface, one end of the semi-cylindrical structure is communicated with the expansion section, and the other end of the semi-cylindrical structure extends towards the upstream direction of cold air flow to form the semi-groove; and the top surface of the half groove and the top surface of the expansion section are in the same plane;
wherein, the top surface that the top surface of half slot and the top surface of expansion section constitutes intersects with the axis of cylinder hole section.
According to one embodiment of the present application, the first and second branches are each tapered structures in the direction of cold gas flow.
According to one embodiment of the present application, the end face of the downstream cold air outlet end, where the cylindrical hole section is communicated with the expansion section, is an inclined surface.
According to one embodiment of the present application, the diameter of the cylindrical hole section is D; taking the intersection point of the axis of the cylindrical hole section and the top surface as the center, wherein the included angles between the central line of the half groove and the central lines of the first branch and the second branch are respectively alpha, the lengths of the first branch and the second branch are L5, and the lengths of the protrusions are L6;
wherein, alpha is 120-130 degrees, L5 is 1.5D-2.0D in length, and L6 is 0.8D-0.9D in length.
According to one embodiment of the application, the outer sides of the first branch and the second branch are of arc structures, the arc radius of each arc structure is r, and the distance between the circle centers of the arcs of the first branch and the second branch is L4;
wherein r is 0.1D-0.3D, and L4 is 2.5D-3.5D.
According to one embodiment of the present application, the height of the expansion section is L1, and L1 is 0.9D-1.1D.
According to one embodiment of the application, the depth of the half groove is L2, and the length of the half groove is L3; l2 is 0.4D-0.6D, and L3 is 2.5D-3.5D.
The application also provides a turbine blade, the turbine blade includes as above duck foot formula turbine blade air film hole.
According to the duck-foot-shaped turbine blade air film hole provided by the invention, when cold air flows out of the air film hole, part of fuel gas can enter the groove under the action of the upstream groove, as shown in fig. 6, the fuel gas entering the groove impacts the cold air, and the cold air is pressed upwards to enable the cold air to be closer to the wall surface. In addition, at the protruding position of the downstream of the duck-foot turbine blade air film hole, part of cold air can be attached to the wall surface, and the redundant cold air flows to the two sides through branches at the two sides, so that the air film coverage range is widened. Compared with the cylindrical air film hole, the air film efficiency of the duck-foot type turbine blade air film hole is improved by 200% as shown in fig. 7.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a gas film hole structure of a duck foot turbine blade of the invention;
FIG. 2 is a top view of a gas film hole of a duck foot turbine blade of the present invention;
FIG. 3 is a bottom view of a duck foot turbine blade air film hole of the present invention;
FIG. 4 is a cross-sectional view of a gas film hole of a duck foot turbine blade of the present invention;
FIG. 5 is a cross-sectional view taken along the A-A plane of FIG. 4;
FIG. 6 is a flow chart of a gas film hole of a duck foot turbine blade of the present invention;
FIG. 7 is a graph comparing the gas film efficiencies of the gas film holes of the duck foot turbine blade of the present invention;
wherein, 1-cylinder hole section, 2-half groove, 3-expansion section, 4-first branch, 5-arch, 6-second branch.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The technical solution of the present invention will be clearly and completely described below in detail with reference to the accompanying drawings in combination with the embodiments, and it is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1-7, an embodiment of the present invention provides a duck-foot turbine blade air film hole, including:
a cylindrical hole section 1, wherein one end of the cylindrical hole section 1 is an upstream cold air inlet end, and the other end is a downstream cold air outlet end according to the cold air flowing direction;
an expansion section 3, wherein the expansion section 3 is communicated with a downstream cool air outlet end of the cylindrical hole section 1; the expansion section 3 is of a groove-shaped structure with an opening top surface, the groove body of the groove-shaped structure comprises a protrusion 5 extending outwards in the cold air flowing direction, and a first branch 4 and a second branch 6 which are respectively positioned at two sides of the protrusion 5, the first branch 4 and the second branch 6 are of symmetrical structures positioned at two sides of the protrusion 5, and the first branch 4, the protrusion 5 and the second branch 6 are in arc transition, so that the appearance of the expansion section 3 is duck-foot-shaped;
a half tank 2, wherein the half tank 2 has a semi-cylindrical structure with an open top surface, one end of the semi-cylindrical structure is communicated with the expansion section 3, and the other end extends to the upstream direction of the cold air flow to form the half tank 2; and the top surface of the half groove 2 and the top surface of the expansion section 3 are coplanar; wherein the top surface of the half groove 2 and the top surface of the expansion section 3 intersect with the axis of the cylindrical hole section 1.
In a preferred embodiment, the first and second branches are each tapered structures in the direction of flow of the cold gas.
In another preferred embodiment, an end face of a downstream cool air outlet end of the cylindrical hole section communicating with the expansion section is an inclined face.
In this embodiment, the diameter of the cylindrical hole section 1 is D, at the top of the gas film hole of the duck-foot turbine blade, as shown in fig. 2, the gas film hole is typically duck-foot, taking the intersection point of the axis of the cylindrical hole section 1 and the top surface as the center, the included angle between the center line of the upstream half groove 2 and the center line of the first branch 4 (or the second branch 6) is α, the lengths of the first branch 4 and the second branch 6 are L5, and the length of the protrusion 5 is L6, where in this embodiment, α is preferably 120 ° to 130 °, the length of L5 is 1.5D-2.0D, and the length of L6 is preferably 0.8D-0.9D.
The outer sides of the first branch 4 and the second branch 6 of the gas film hole of the duck-foot turbine blade are of arc structures, the radius of the arc is r, the distance between circle centers of the arcs on two sides is L4, as shown in fig. 3, wherein in the embodiment, r is preferably 0.1D-0.3D, and L4 is preferably 2.5D-3.5D. As shown in figures 4 and 5, the height of the expansion section is L1, the depth of the groove is L2, the length of the groove is L3, L1 is preferably 0.9D-1.1D, L2 is preferably 0.4D-0.6D, and L3 is preferably 2.5D-3.5D.
In the present invention, when the cool air flows out from the air film hole, part of the fuel gas enters the groove due to the effect of the upstream half groove 2, as shown in fig. 6, the fuel gas entering the half groove 2 impacts the cool air, and the cool air is pressed up to the wall surface, so that the cool air is closer to the wall surface. The position of the bulge 5 at the downstream of the gas film hole of the duck web turbine blade can enable part of cold air to be attached to the wall surface, and the redundant cold air flows to two sides through branches at two sides, so that the gas film coverage range is widened. And, the expansion section 3 can effectively increase the width of the spread direction coverage of the cold air, thereby improving the coverage of the air film.
The gas film hole of the duck-foot turbine blade can comprise a plurality of gas film hole units, the gas film hole units can maximize the covering effect of the gas film hole, and different numbers of gas film hole units can be selected in the embodiment so as to meet different working conditions.
According to the embodiment of the invention, the duck-foot-shaped turbine blade air film hole and the traditional cylindrical air film hole are compared through numerical calculation, and compared with the cylindrical air film hole, the air film efficiency of the duck-foot-shaped turbine blade air film hole is improved by 200% as shown in fig. 7.
The application also provides a turbine blade, the turbine blade includes as above duck foot formula turbine blade air film hole.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in 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 (8)
1. The utility model provides a duck web formula turbine blade air film hole which characterized in that includes:
a cylindrical hole section, wherein one end of the cylindrical hole section is an upstream cold air inlet end, and the other end of the cylindrical hole section is a downstream cold air outlet end according to the cold air flowing direction;
an expansion section communicated with the downstream cool air outlet end of the cylindrical hole section; the expansion section is of a groove-shaped structure with an opening on the top surface, the groove body of the groove-shaped structure comprises a protrusion extending outwards in the flowing direction of cold air, and a first branch and a second branch which are respectively positioned at two sides of the protrusion, the first branch and the second branch are symmetrical structures positioned at two sides of the protrusion, and the first branch, the protrusion and the second branch are in arc transition, so that the appearance of the expansion section is a duck-foot shape;
the semi-groove is of a semi-cylindrical structure with an open top surface, one end of the semi-cylindrical structure is communicated with the expansion section, and the other end of the semi-cylindrical structure extends towards the upstream direction of cold air flow to form the semi-groove; and the top surface of the half groove and the top surface of the expansion section are in the same plane;
wherein, the top surface that the top surface of half slot and the top surface of expansion section constitutes intersects with the axis of cylinder hole section.
2. The duck-foot turbine blade air film hole as recited in claim 1, wherein the first and second branches are each tapered structures in the direction of flow of the cold air.
3. The duck foot turbine blade air film hole as recited in claim 1, wherein the end face of the downstream cool air outlet end of the cylindrical hole section communicating with the expansion section is an inclined face.
4. The duck foot turbine blade air film hole as recited in claim 1 wherein the diameter of the cylindrical hole section is D; taking the intersection point of the axis of the cylindrical hole section and the top surface as the center, wherein the included angles between the central line of the half groove and the central lines of the first branch and the second branch are respectively alpha, the lengths of the first branch and the second branch are L5, and the lengths of the protrusions are L6;
wherein, alpha is 120-130 degrees, L5 is 1.5D-2.0D in length, and L6 is 0.8D-0.9D in length.
5. The gas film hole of the duck foot turbine blade according to claim 4, wherein the outer sides of the first branch and the second branch are arc structures, the arc radius of the arc structures is r, and the interval between the circle centers of the arcs of the first branch and the second branch is L4;
wherein r is 0.1D-0.3D, and L4 is 2.5D-3.5D.
6. The duck foot turbine blade air film hole as recited in claim 4, wherein the height of the expansion section is L1, L1 is 0.9D-1.1D.
7. The duck foot turbine blade air film hole as recited in claim 4 wherein the half slot has a depth L2 and a length L3; l2 is 0.4D-0.6D, and L3 is 2.5D-3.5D.
8. A turbine blade comprising the duck-foot turbine blade film hole as claimed in any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310105376.8A CN116122916A (en) | 2023-02-07 | 2023-02-07 | Duck-foot-shaped turbine blade air film hole and turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310105376.8A CN116122916A (en) | 2023-02-07 | 2023-02-07 | Duck-foot-shaped turbine blade air film hole and turbine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116122916A true CN116122916A (en) | 2023-05-16 |
Family
ID=86307904
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310105376.8A Pending CN116122916A (en) | 2023-02-07 | 2023-02-07 | Duck-foot-shaped turbine blade air film hole and turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116122916A (en) |
-
2023
- 2023-02-07 CN CN202310105376.8A patent/CN116122916A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10711619B2 (en) | Turbine airfoil with turbulating feature on a cold wall | |
| CN1318735C (en) | Pulsing impact cooling blade for gas turbine engine | |
| CN107060892B (en) | A kind of turbine blade cooling unit of gas-liquid coupling | |
| CN112746870B (en) | Interrupted wave rib cooling structure | |
| CN112145234B (en) | Omega type gyration chamber plywood cooling structure | |
| CN112145235B (en) | Omega type gyration chamber plywood cooling structure | |
| CN112780356B (en) | Air film cooling structure with surface depression, turbine blade and turbine | |
| CN116122916A (en) | Duck-foot-shaped turbine blade air film hole and turbine blade | |
| CN113550794A (en) | Multi-cavity efficient cooling structure and cooling method for turbine rotor blade | |
| US10619487B2 (en) | Cooling assembly for a turbine assembly | |
| CN112282860A (en) | Turbine rotor blade platform cooling structure | |
| CN115013076B (en) | Gondola water faucet form turbine blade cooling unit and turbine blade | |
| CN114483201A (en) | Cooling hole suitable for gas turbine blade and gas turbine blade | |
| CN112145233B (en) | S-shaped rotary cavity laminate cooling structure | |
| CN113356932B (en) | Air film cooling composite hole structure for turbine blade and turbine blade | |
| CN113719323B (en) | Composite cooling structure for turbine blade of gas turbine | |
| CN115898693A (en) | Corrugated turbulent flow plane cooling device and application | |
| CN112922676B (en) | Internal back basin rotary cooling channel of turbine blade | |
| CN205445688U (en) | Gas turbine turbine does not have hat film cooling rotor blade | |
| US20130224019A1 (en) | Turbine cooling system and method | |
| CN210599117U (en) | Cooling structure for improving cooling effect of turbine | |
| CN113107608A (en) | A vortex screw hole cooling structure and turbine blade for turbine blade trailing edge | |
| CN115898554B (en) | Air film hole structure of turbine blade | |
| CN112145236B (en) | double-S-shaped rotary cavity layer plate cooling structure | |
| US10208606B2 (en) | Airfoil for turbomachine and airfoil cooling method |
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 |