CN115898554B - Air film hole structure of turbine blade - Google Patents
Air film hole structure of turbine blade Download PDFInfo
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- CN115898554B CN115898554B CN202310218502.0A CN202310218502A CN115898554B CN 115898554 B CN115898554 B CN 115898554B CN 202310218502 A CN202310218502 A CN 202310218502A CN 115898554 B CN115898554 B CN 115898554B
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Abstract
The invention discloses a gas 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 gas film coverage rate of gas film holes on the blade is low, and the cooling effect of the blade is reduced. The air film hole structure comprises a cylindrical section, a convex section, a shrinkage section, an expansion section and an outlet surface which are sequentially arranged in an integrated manner in the air flow direction, so that the air film hole structure is suitable for external cooling of turbine blades, and the air conditioning covering effect of the turbine blades is improved.
Description
Technical Field
The invention belongs to the technical field of turbine blades, and particularly relates to a gas film hole structure of a turbine blade.
Background
In order to obtain higher thrust-weight ratio and thermal efficiency, the modern aviation gas turbine engine continuously improves 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 needed to keep the normal work of turbine blades, the turbine blade cooling technology is divided into external cooling and internal cooling, the external cooling is a series of air film holes arranged on the surface of the turbine blades, cold air flows out of the air film holes and covers the surfaces of the blades, and the blades are isolated from the gas, so that the temperature of the blades is reduced, the structural design of arc-shaped holes is adopted in the prior art, the air film covering effect of the air film holes is reduced, and the efficiency of externally cooling the turbine disc, the rotor or the blades is reduced.
Disclosure of Invention
In view of the above, the invention provides a gas film hole structure of a turbine blade, which solves the technical problems of lower gas film coverage rate of gas film holes on the blade and reduced cooling coverage effect of the blade in the prior art.
The utility model provides a turbine blade's air film hole structure is provided with a plurality of in turbine blade's axial direction air film hole structure, air film hole structure includes cylinder section, protruding section, shrink section, expansion section and the exit face that sets gradually with the mode of integral type in the direction along the air current flow, wherein:
the cylindrical sections are arranged in a constant cross-section structure;
the convex section is arranged in a structure of protruding towards one side far away from the axis of the air film hole structure in an arc shape and then recessing 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 shrinkage section extends from the arc-shaped concave structure of the bulge section to one side of the axis of the air film hole structure in the direction from the tail end of the bulge section to the outlet surface, and extends in a cambered surface mode;
the expansion section is arranged from the tail end of the contraction section to one side far away from the axis of the air film hole structure and extends in a cambered surface shape in the direction from the tail end of the contraction section to the outlet surface, and extends to form an intersection line with the outlet surface;
the outline of the outlet face comprises a first arc line, a second arc line, a third arc line and a fourth arc line, one end of the first arc line is connected with one end of the third arc line, the other end of the third arc line is connected with one end of the second arc line, the other end of the first arc line is connected with one end of the fourth arc line, the other end of the fourth arc line is connected with the other end of the second arc line, the first arc line, the second arc line, the third arc line and the fourth arc line form a continuous or closed geometric shape, and the radian of the second arc line is larger than that of the first arc line;
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 plane, 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 surface in the axial direction of the air film hole structure is a first length L1, the maximum length of the projection of the outlet surface on the first plane along the axial direction of the air film hole structure is a second length L2, wherein the range of the first length L1 is 0.55D-0.65D, and the range of the second length L2 is 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 range of the third length L3 is 1.1D-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, under the action of the inclination angle of the protruding section, air flow is pressed to the downstream wall surface, and the expansion section expands along the two sides, so that the air flow is dispersed along the expanding direction, the air flow is tightly pressed on the wall surface and dispersed along the two sides, the coverage range of the air film is greatly improved by the wall-attached flow, and the cooling efficiency of the external cooling mode cooling blades and other parts is improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, 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 disclosure, and other drawings may be obtained according to these drawings without inventive effort to a person of ordinary skill in the art.
FIG. 1 is a perspective view of a first view of a turbine blade film hole structure of the present invention;
FIG. 2 is a perspective view of a second view of the turbine blade film hole structure 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 is a cross-sectional view taken along the direction A-A in FIG. 4;
FIG. 6 is a cross-sectional view taken along the direction B-B in FIG. 5;
FIG. 7 is a graph showing the comparison of air film efficiency of the air film hole structure of the present invention;
FIG. 8 is a schematic view of a turbine blade with a film hole structure;
FIG. 9 is a schematic view of an exit face provided with a third arc and a fourth arc;
wherein, 1-a cylindrical section; 2-a convex section; 3-shrink section; 4-expansion section; 5-an outlet face; 6-a gas film hole structure; 7-a first straight line; 11-a first plane; 20-turbine blades; 50-first point; 51-a first arc; 52-a second arc; 53-third arc; 54-fourth arc; 60-third point; 70-fourth point; 80-fifth point; 90-sixth point; 100-second point.
Detailed Description
Embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present disclosure will become readily apparent to those skilled in the art from the following disclosure, which describes embodiments of the present disclosure by way of specific examples. It will be apparent that the described embodiments are merely some, but not all embodiments of the present disclosure. The disclosure may be embodied or practiced in other different specific embodiments, and details within the subject specification may be modified or changed from various points of view and applications without departing from the spirit of the disclosure. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art without inventive effort, based on the embodiments in this disclosure are intended to be within the scope of this disclosure.
It is noted that various aspects of the embodiments are described below within the scope of the following 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 present disclosure, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, 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. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
In the gas film hole structure of the turbine blade provided by the application, as shown in fig. 1 to 9, a plurality of gas film hole structures 6 are arranged in the axial direction of the turbine blade 20, and as shown in fig. 8, adjacent turbine blades 20 on a casing are all provided with the gas film hole structure 6. The gas film hole structure 6 includes cylindrical section 1, protruding section 2, shrink section 3, expansion section 4 and the export face 5 that set gradually in an integral type mode along the direction of air current flow, and preferably, as shown in fig. 2, cylindrical section 1, protruding section 2, shrink section 3, expansion section 4 set up with the axis symmetry of gas film hole structure 6, wherein:
the cylindrical section 1 is arranged in a constant cross-section configuration.
The protruding section 2 is arranged in a structure that the protruding section 2 protrudes towards one side far away from the axis of the air film hole structure 6 in an arc shape and then is recessed towards one side of the axis of the air film hole structure 6 in an arc shape in the direction from the tail end of the cylindrical section 1 to the outlet face 5.
The shrinkage section 3 extends from the arc-shaped concave structure of the convex section 2 to one side of the axis of the air film hole structure 6 in the direction from the tail end of the convex section 2 to the outlet surface 5, and preferably extends from the tail end of the arc-shaped concave structure to one side of the axis of the air film hole structure 6 in the form of an arc surface;
the expansion section 4 is arranged in a direction from the tail end of the contraction section 3 to the outlet face 5, and the expansion section 4 is arranged in a structure that the tail end of the contraction section 3 is far away from the axis side of the air film hole structure 6 and extends in a cambered surface shape, and extends to form an intersection line with the outlet face 5.
As shown in fig. 9, the profile of the outlet face 5 includes a first arc line 51, a second arc line 52, a third arc line 53 and a fourth arc line 54, one end of the first arc line 51 is connected with one end of the third arc line 53, the other end of the third arc line 53 is connected with one end of the second arc line 52, the other end of the first arc line 51 is connected with one end of the fourth arc line 54, the other end of the fourth arc line 54 is connected with the other end of the second arc line 52, the first arc line 51, the second arc line 52, the third arc line 53 and the fourth arc line 54 form a continuous or closed geometric shape, and the radian of the second arc line 52 is greater than that of the first arc line 51. The point at which third arc 53 intersects first arc 51 is third point 60, the point at which third arc 53 intersects second arc 52 is fourth point 70, the point at which fourth arc 54 intersects first arc 51 is fifth point 80, and the point at which fourth arc 54 intersects second arc 52 is sixth point 90. Preferably, third arc 53 and fourth arc 54 each connect first arc 51 and second arc 52 in a rounded manner. The end face of the inlet of the cylindrical section 1 is used as a first plane 11, a virtual first straight line 7 is formed in the outlet face 5, the outlet face 5 is symmetrical with the first straight line 7, the first arc line 51 is symmetrical with the first straight line 7, the symmetrical center is a point with the largest distance from the first arc line 51 to the first plane 11 in the axis direction of the air film hole structure 6, the second arc line 52 is symmetrical with the first straight line 7, the symmetrical center is a point with the largest distance from the second arc line 52 to the first plane 11 in the axis direction of the air film hole structure 6, and the connecting line of the symmetrical center points of the first arc line 51 and the second arc line 52 is used as the first straight line 7.
The first plane 11 is perpendicular to the axis of the air film hole structure 6, the outlet face 5 is an inclined plane, and the included angle between the outlet face 5 and the first plane 11 is an acute angle, and the included angle is 20-55 degrees, preferably 45 degrees.
When the cool air flows out of the air 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 bulge section 2, as shown in fig. 1, the cool air expands in the axial direction of the turbine blade 20 in 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 adhere to the wall surface for flowing, and the coverage of the air film is greatly improved. It should be noted that the number of the film hole structures 6 on the turbine blade 20 is not limited, and is set according to the type of the blade or the type matching of the engine.
As the specific embodiment provided by the scheme, as shown in fig. 5, an included angle alpha formed by the arc-shaped concave structure and the axis of the air film hole structure 6 ranges from 25 degrees to 35 degrees, so that the close force of air flow to the wall surface of the turbine blade is improved.
As an embodiment provided herein, the diameter of the cylindrical section 1 is D. As shown in fig. 3, the maximum length of the outlet surface 5 in the axial direction of the air film hole structure 6 is a first length L1, and the first length L1 ranges from 0.55D to 0.65D. As shown in fig. 4, the maximum length of the projection of the outlet surface 5 on the first plane 11 along the axial direction of the air 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 distance from the outer contour of the contraction section 3 to the axis of the air film hole structure 6 is the smallest at the first point 50 and the second point 100, the distance between the first point 50 and the second point 100 is the fourth length L4, and the range of the fourth length L4 is 0.7D-0.9D.
Compared with the cylindrical gas film hole (traditional 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 compared with that of the cylindrical gas film hole through calculation, and as can be seen in fig. 7, the gas film coverage rate of the line change rate corresponding to the gas film hole structure 6 is larger than that of the line change rate corresponding to the cylindrical gas film hole at each length position.
The above is merely a specific embodiment of the disclosure, but the protection scope of the disclosure is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the disclosure are intended to be covered in the protection scope of the 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 hole structure, its characterized in that is provided with a plurality of on turbine blade's axial direction air film hole structure, air film hole structure includes cylinder section, protruding section, shrink section, expansion section and the exit face that set gradually with the mode of an organic whole in the direction along the air current flow, wherein:
the cylindrical sections are arranged in a constant cross-section structure;
the convex section is arranged in a structure of protruding towards one side far away from the axis of the air film hole structure in an arc shape and then recessing 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 shrinkage section extends from the arc-shaped concave structure of the bulge section to one side of the axis of the air film hole structure in the direction from the tail end of the bulge section to the outlet surface, and extends in a cambered surface mode;
the expansion section is arranged from the tail end of the contraction section to one side far away from the axis of the air film hole structure and extends in a cambered surface shape in the direction from the tail end of the contraction section to the outlet surface, and extends to form an intersection line with the outlet surface;
the outline of the outlet face comprises a first arc line, a second arc line, a third arc line and a fourth arc line, one end of the first arc line is connected with one end of the third arc line, the other end of the third arc line is connected with one end of the second arc line, the other end of the first arc line is connected with one end of the fourth arc line, the other end of the fourth arc line is connected with the other end of the second arc line, the first arc line, the second arc line, the third arc line and the fourth arc line form a continuous or closed geometric shape, and the radian of the second arc line is larger than that of the first arc line;
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 plane, and the included angle between the outlet face and the first plane is an acute angle.
2. The gas film hole structure of a turbine blade according to claim 1, wherein the arc-shaped recessed structure forms an angle α with the axis of the gas film hole structure in the range of 25 ° -35 °.
3. The gas film hole structure of a turbine blade according to claim 1, wherein the diameter of the cylindrical section is D, the maximum length of the outlet face in the direction of the axis of the gas film hole structure is a first length L1, and the maximum length of the projection of the outlet face on the first plane in the direction of the axis of the gas film hole structure is a second length L2, wherein the first length L1 ranges from 0.55D to 0.65D, and the second length L2 ranges from 2D to 2.5D.
4. A gas film hole structure for a turbine blade according to claim 3, wherein the length of the arc-shaped protrusion perpendicular to the axis of the gas film hole structure is a third length L3, and the third length L3 ranges from 1.1D to 1.3D.
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| Application Number | Priority Date | Filing Date | Title |
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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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| CN202310218502.0A CN115898554B (en) | 2023-03-09 | 2023-03-09 | Air film hole structure of turbine blade |
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| CN115898554A CN115898554A (en) | 2023-04-04 |
| CN115898554B true CN115898554B (en) | 2023-06-30 |
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