CN115898554A - Film hole structure of turbine blade - Google Patents
Film hole structure of turbine blade Download PDFInfo
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- CN115898554A CN115898554A CN202310218502.0A CN202310218502A CN115898554A CN 115898554 A CN115898554 A CN 115898554A CN 202310218502 A CN202310218502 A CN 202310218502A CN 115898554 A CN115898554 A CN 115898554A
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Abstract
The invention discloses an air film hole structure of a turbine blade, belongs to the technical field of turbine blades, and solves the technical problems that in the prior art, the air film coverage rate of air film holes in the turbine blade is low, and the cooling effect of the turbine blade is reduced. The air film hole structure comprises a cylindrical section, a protruding section, a contraction section, an expansion section and an outlet face which are sequentially arranged in an integrated mode in the airflow direction, so that the air film hole structure is suitable for external cooling of the turbine blades and improves the cold air covering effect of the turbine blades.
Description
Technical Field
The invention belongs to the technical field of turbine blades, and particularly relates to an air film hole structure of a turbine blade.
Background
Modern aviation gas turbine engine is in order to obtain higher thrust-weight ratio and thermal efficiency, constantly improve turbine inlet temperature, turbine inlet temperature has far exceeded the melting point temperature of blade material at present, need adopt complicated cooling technology to keep the normal work of turbine blade, turbine blade cooling technology divides external cooling and internal cooling, external cooling is a series of gas film holes of arranging on turbine blade surface, cold air flows out from the gas film hole, cover on the blade surface, keep apart blade and gas, thereby reduce the blade temperature, all adopt the structural design of arc hole among the prior art, reduce the gas film covering effect in gas film hole, cause the efficiency reduction of external cooling turbine dish or rotor or blade etc..
Disclosure of Invention
In view of this, the present invention provides an air film hole structure of a turbine blade, which solves the technical problems of the prior art that the air film coverage rate of the air film hole on the blade is low, and the cooling coverage effect of the blade is reduced.
The utility model provides a turbine blade's air film pore structure, be provided with a plurality ofly on turbine blade's axial direction air film pore structure, air film pore structure includes cylinder section, protruding section, shrink section, expansion section and the export face that sets gradually with the mode of integral type in the direction that flows along the air current, wherein:
the cylindrical section is arranged in a uniform cross-section structure;
the convex section is arranged in a structure that the convex section firstly protrudes towards one side far away from the axis of the air film hole structure in an arc shape and then is concave towards one side of the axis of the air film hole structure in an arc shape in the direction from the tail end of the cylindrical section to the outlet surface;
the contraction section extends from the arc concave structure of the bulge section to one side of the axis of the air film hole structure and extends in the form of an arc surface in the direction from the tail end of the bulge section to the outlet surface;
the expansion section is arranged in a structure that the tail end of the contraction section extends to one side far away from the axis of the air film hole structure and extends in an arc shape in the direction from the tail end of the contraction section to the outlet face, and extends to form an intersection line with the outlet face;
the profile of the outlet face comprises a first arc, a second arc, a third arc and a fourth arc, one end of the first arc is connected with one end of the third arc, the other end of the third arc is connected with one end of the second arc, the other end of the first arc is connected with one end of the fourth arc, the other end of the fourth arc is connected with the other end of the second arc, the first arc, the second arc, the third arc and the fourth arc form a continuous or closed geometric shape, and the radian of the second arc is greater than the radian of the first arc;
the end face of the cylindrical section inlet is used as a first plane, the first plane is perpendicular to the axis of the air film hole structure, the outlet face is an inclined face, and the included angle between the outlet face and the first plane is an acute angle.
Preferably, the included angle alpha between the arc-shaped concave structure and the axis of the air film hole structure is 25-35 degrees.
Preferably, the diameter of the cylindrical section is D, the maximum length of the outlet face in the axial direction of the film hole structure is a first length L1, and the maximum length of the projection of the outlet face on the first plane along the axial direction of the film hole structure is a second length L2, wherein the first length L1 is in the range of 0.55D-0.65D, and the second length L2 is in the range of 2D-2.5D.
Preferably, the length of the arc-shaped protrusion perpendicular to the axis of the air film hole structure is a third length L3, and the third length L3 ranges from 1.1D to 1.3D.
The invention has the beneficial effects that:
according to the structure arrangement of the air film holes on the blades, when cold air flows out of the air film holes, the air flow is pressed to the downstream wall surface under the action of the inclination angle of the convex section, and the expansion section expands along two sides, so that the air flow is dispersed along the spreading direction, the air flow is tightly pressed on the wall surface and is dispersed along the two sides, the covering range of the air film is greatly improved due to the wall-attached flow, and the cooling efficiency of components such as the cooling blades in an external cooling mode is improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings needed to be used in the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present disclosure, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a perspective view of a turbine blade film hole configuration of the present invention from a first perspective;
FIG. 2 is a perspective view of a second perspective of the turbine blade film hole configuration of the present invention;
FIG. 3 is a front view of the outlet face from a third perspective;
FIG. 4 is a front view of the outlet face from a fourth perspective;
FIG. 5 isbase:Sub>A cross-sectional view taken along A-A of FIG. 4;
FIG. 6 is a sectional view taken along line B-B of FIG. 5;
FIG. 7 is a graph comparing the gas film efficiency of the gas film pore structure of the present invention;
FIG. 8 is a schematic illustration of a turbine blade configured with film holes;
FIG. 9 is a schematic view of the exit face provided with a third arc and a fourth arc;
wherein, 1 is a cylindrical section; 2-a convex section; 3-a contraction section; 4-an expansion section; 5-an outlet face; 6-gas film pore structure; 7-a first straight line; 11-a first plane; 20-turbine blades; 50-first point; 51-a first arc; 52-second arc; 53-third arc; 54-fourth arc; 60-third point; 70-a fourth point; 80-fifth point; 90-sixth point; 100-second point.
Detailed Description
The embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.
The embodiments of the present disclosure are described below with specific examples, and other advantages and effects of the present disclosure will be readily apparent to those skilled in the art from the disclosure of the present disclosure. It is to be understood that the described embodiments are merely illustrative of some, and not restrictive, of the embodiments of the disclosure. The disclosure may be embodied or carried out in various other specific embodiments, and various modifications and changes may be made in the details within the description without departing from the spirit of the disclosure. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
As shown in fig. 1 to 9, the film hole structures 6 are provided in the axial direction of the turbine blades 20, and as shown in fig. 8, the film hole structures 6 according to the present invention are provided in adjacent turbine blades 20 of the casing. The air film hole structure 6 comprises a cylindrical section 1, a convex section 2, a contraction section 3, an expansion section 4 and an outlet face 5 which are sequentially arranged in an integrated manner in the direction of air flow, preferably, as shown in fig. 2, the cylindrical section 1, the convex section 2, the contraction section 3 and the expansion section 4 are symmetrically arranged with the axis of the air film hole structure 6, wherein:
the cylindrical section 1 is arranged in a uniform cross-sectional structure.
Protruding section 2 is at 1 end of cylinder section to the direction of export face 5, protruding section 2 with earlier to keeping away from the protruding structure setting of the arc concave yield to 6 axis one side arc of gas film hole structure one side again towards the gas film hole structure 6 axis one side arc.
The contracting section 3 extends from the arc-shaped concave structure of the convex section 2 to the axial line side of the air film hole structure 6 and extends in an arc shape in the direction from the tail end of the convex section 2 to the outlet face 5, and preferably, the contracting section 3 extends from the tail end of the arc-shaped concave structure to the axial line side of the air film hole structure 6 and extends in an arc shape;
the expanding section 4 is arranged in the direction from the tail end of the contracting section 3 to the outlet face 5, and the expanding section 4 is arranged in a structure which is far away from one side of the axis of the air film hole structure 6 and extends in an arc surface shape from the tail end of the contracting section 3 and extends to form a cross line with the outlet face 5.
As shown in fig. 9, the profile of the outlet face 5 includes a first arc 51, a second arc 52, a third arc 53 and a fourth arc 54, one end of the first arc 51 is connected with one end of the third arc 53, the other end of the third arc 53 is connected with one end of the second arc 52, the other end of the first arc 51 is connected with one end of the fourth arc 54, the other end of the fourth arc 54 is connected with the other end of the second arc 52, the first arc 51, the second arc 52, the third arc 53 and the fourth arc 54 form a continuous or closed geometric shape, and the arc of the second arc 52 is greater than the arc of the first arc 51. The point where third arc 53 intersects first arc 51 is a third point 60, the point where third arc 53 intersects second arc 52 is a fourth point 70, the point where fourth arc 54 intersects first arc 51 is a fifth point 80, and the point where fourth arc 54 intersects second arc 52 is a sixth point 90. Preferably, third arc 53 and fourth arc 54, each connect first arc 51 and second arc 52 in a radiused transition. The end face of the inlet of the cylindrical section 1 serves as a first plane 11, a virtual first straight line 7 is formed in the outlet face 5, the outlet face 5 is symmetrical through the first straight line 7, a first arc line 51 is symmetrical through the first straight line 7, the symmetry center is the point where the distance from the first arc line 51 to the first plane 11 is the largest in the axis direction of the film hole structure 6, a second arc line 52 is symmetrical through the first straight line 7, the symmetry center is the point where the distance from the second arc line 52 to the first plane 11 is the largest in the axis direction of the film hole structure 6, and the connecting line of the symmetry center points of the first arc line 51 and the second arc line 52 serves as the first straight line 7.
The first plane 11 is perpendicular to the axis of the film hole structure 6, the outlet face 5 is an inclined plane, and the angle between the outlet face 5 and the first plane 11 is an acute angle in the range of 20 ° to 55 °, preferably 45 °.
When the cold air flows out of the film hole structure 6, the air flow is pressed to the wall surface of the turbine blade 20 under the action of the inclination angle of the convex section 2, as shown in fig. 1, the cold air expands along the axial direction of the turbine blade 20 at the expansion section 4, as shown in fig. 8, the air flow is dispersed, so that the air flow is tightly pressed on the wall surface of the turbine blade 20 to flow along the wall surface, and the coverage of the film is greatly improved. It should be noted that the number of film hole structures 6 on turbine blade 20 is not limited, and may be configured to match the blade type or engine type.
As a specific embodiment provided by the scheme, as shown in FIG. 5, the included angle alpha formed between the structure of the arc-shaped recess and the axis of the air film hole structure 6 is in the range of 25-35 degrees, so as to improve the closing force of the air flow towards the wall surface of the turbine blade.
As a specific embodiment provided in the present disclosure, the diameter of the cylindrical section 1 is D. As shown in fig. 3, the maximum length of the outlet face 5 in the axial direction of the film hole structure 6 is a first length L1, and the first length L1 is in the range of 0.55D to 0.65D. As shown in FIG. 4, the maximum length of the projection of the outlet face 5 on the first plane 11 along the axial direction of the film hole structure 6 is a second length L2, and the second length L2 ranges from 2D to 2.5D.
Further, as shown in fig. 6, the length of the arc-shaped protrusion perpendicular to the axis of the air film hole structure 6 is taken as a third length L3, and the third length L3 ranges from 1.1D to 1.3D. The two points with the minimum distance from the outer contour of the contraction section 3 to the axis of the air film hole structure 6 are respectively a first point 50 and a second point 100, the distance between the first point 50 and the second point 100 is a fourth length L4, and the range of the fourth length L4 is 0.7D-0.9D.
Through calculation and comparison of the gas film hole structure 6 and the cylindrical gas film hole (the traditional gas film hole), compared with the cylindrical gas film hole, the gas film hole structure 6 has the advantages that the overall gas film efficiency of the gas film hole structure 6 is improved by more than 2 times, and as can be seen from fig. 7, the gas film coverage rate of the line change rate corresponding to the gas film hole structure 6 is higher than that of the line corresponding to the cylindrical gas film hole at each length position.
The above is only a specific embodiment of the present disclosure, but the scope of the present disclosure 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 disclosure should be covered within the scope of the present disclosure. Therefore, the protection scope of the present disclosure shall be subject to the protection scope of the claims.
Claims (4)
1. The utility model provides a turbine blade's air film pore structure which characterized in that is provided with a plurality of in turbine blade's axial direction air film pore structure, air film pore structure includes cylinder section, protruding section, shrink section, expansion section and the export face that sets gradually with the mode of integral type in the direction that flows along the air current, wherein:
the cylindrical section is arranged in a uniform cross-section structure;
the convex section is arranged in a structure that the convex section firstly protrudes towards one side far away from the axis of the air film hole structure in an arc shape and then is concave towards one side of the axis of the air film hole structure in an arc shape in the direction from the tail end of the cylindrical section to the outlet surface;
the contracting section extends from the arc concave structure of the convex section to one side of the axis of the air film hole structure and extends in the form of an arc surface in the direction from the tail end of the convex section to the outlet surface;
the expansion section is arranged in a structure that the tail end of the contraction section extends to one side far away from the axis of the air film hole structure and extends in an arc shape in the direction from the tail end of the contraction section to the outlet face, and extends to form an intersection line with the outlet face;
the profile of the outlet face comprises a first arc, a second arc, a third arc and a fourth arc, one end of the first arc is connected with one end of the third arc, the other end of the third arc is connected with one end of the second arc, the other end of the first arc is connected with one end of the fourth arc, the other end of the fourth arc is connected with the other end of the second arc, the first arc, the second arc, the third arc and the fourth arc form a continuous or closed geometric shape, and the radian of the second arc is greater than that of the first arc;
the end face of the cylindrical section inlet is used as a first plane, the first plane is perpendicular to the axis of the air film hole structure, the outlet face is an inclined face, and the included angle between the outlet face and the first plane is an acute angle.
2. The film hole structure of a turbine blade of claim 1, wherein said arcuate recessed structure includes an angle α in the range of 25 ° to 35 ° with respect to the axis of the film hole structure.
3. The film hole structure of the turbine blade of claim 1, wherein the diameter of the cylindrical section is D, the maximum length of the outlet face in the axial direction of the film hole structure is a first length L1, the maximum length of the projection of the outlet face on the first plane in the axial direction of the film hole structure is a second length L2, wherein the first length L1 is in the range of 0.55D-0.65D, and the second length L2 is in the range of 2D-2.5D.
4. The film hole structure of a turbine blade of claim 3, wherein a length of said arc-shaped protrusion perpendicular to an axis of the film hole structure is a third length L3, said third length L3 being in a range of 1.1D-1.3D.
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| CN202310218502.0A CN115898554B (en) | 2023-03-09 | 2023-03-09 | Air film hole structure of turbine blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310218502.0A CN115898554B (en) | 2023-03-09 | 2023-03-09 | Air film hole structure of turbine blade |
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| CN115898554A true CN115898554A (en) | 2023-04-04 |
| CN115898554B CN115898554B (en) | 2023-06-30 |
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