CN115749970A - Dovetail-shaped air film hole, turbine blade containing dovetail-shaped air film hole and machining method of dovetail-shaped air film hole - Google Patents
Dovetail-shaped air film hole, turbine blade containing dovetail-shaped air film hole and machining method of dovetail-shaped air film hole Download PDFInfo
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- CN115749970A CN115749970A CN202211580867.XA CN202211580867A CN115749970A CN 115749970 A CN115749970 A CN 115749970A CN 202211580867 A CN202211580867 A CN 202211580867A CN 115749970 A CN115749970 A CN 115749970A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention relates to the technical field of turbine blades, in particular to a dovetail type air film hole, a turbine blade containing the dovetail type air film hole and a processing method of the turbine blade, wherein the structure of the dovetail type air film hole comprises a dovetail cone and a cylinder, the tail end of the dovetail cone comprises a first dovetail curve and a second dovetail curve which are sequentially connected end to end, and the invention provides a drawing method of the dovetail type air film hole; the dovetail-shaped air film hole provided by the invention can effectively improve the heat insulation effect, improve the cooling efficiency of the turbine blade, save the consumption of cold air and improve the efficiency and thrust-weight ratio of an engine.
Description
Technical Field
The invention relates to the technical field of turbine blades, in particular to a dovetail type air film hole, a turbine blade with the dovetail type air film hole and a processing method of the turbine blade.
Background
The turbine is a core component of a gas turbine engine and is a work-doing device working in a severe environment with high temperature, high pressure and complex load. With the improvement of performance requirements such as thrust-weight ratio and thermal conversion rate of an engine, the inlet temperature of a turbine is continuously increased and is far beyond the temperature use limit of materials of high-temperature turbine components, so that advanced and efficient cooling protection means and coating of a thermal barrier coating need to be adopted for the high-temperature turbine components, and the high-temperature turbine components can reliably operate in high-temperature gas with the melting point higher than the melting point of the high-temperature turbine components.
The cooling technology of the high-temperature components of the turbine at present comprises disturbance enhanced convection cooling, impingement cooling, film cooling, diffusion cooling and the like, wherein the film hole cooling is the most main and effective cooling mode. The film cooling effect is influenced by pneumatic parameters (such as blowing ratio, density ratio, main flow Reynolds number, main flow turbulence degree and the like), and is also greatly dependent on the hole type of the film hole. The cooling characteristics of the profiled bore are significantly improved relative to the round bore, especially at the large blow-out ratios common in practical engine operating conditions. In addition, due to the complex configuration of the special-shaped air film hole, the qualified processing of the special-shaped air film hole is difficult to realize by the existing processing technology, and particularly, the three-dimensional processing of a complex structure is realized on the hard high-temperature alloy, which puts high requirements on the processing technology.
Disclosure of Invention
The invention provides a dovetail type air film hole, a turbine blade containing the dovetail type air film hole and a processing method thereof aiming at the problems in the background technology, and the technical scheme of the invention is realized as follows:
in one aspect, the present disclosure provides a dovetail-shaped air film hole, which includes a dovetail-shaped cone and a cylinder; the length of the cylinder is L 3 (ii) a The cylinder is fixedly connected with the head end of the dovetail cone through one end of the cylinder; the distance between the head end and the tail end of the dovetail cone is L 1 (ii) a The orthographic projection of the tail end of the dovetail cone comprises a projection circle of a cylinder, and further comprises a first dovetail curve and a second dovetail curve which are sequentially connected end to end; the describedThe radius of the circumscribed circle of the first dovetail curve and the second dovetail curve is R 1 (ii) a The distance between the vertex of the projection circle and the vertex of the first dovetail curve is L 2 The distance between the vertex of the projection circle and the vertex of the second dovetail curve is L 2 (ii) a The diameter of the cylinder is phi 1 (ii) a The spreading angle of the dovetail cone is 2 beta, and the wide angle at the bottom of the tail end of the dovetail cone is delta; and satisfies the following conditions:
further, L 3 The length of (A) is 8-12 mm; l is a radical of an alcohol 1 Has a length of 8-12 mm and phi 1 The length of the angle beta is 0.2-0.6 mm, the angle delta is 3-7 degrees, and the angle beta is 15-25 degrees.
The invention also provides a drawing method of the dovetail type air film hole, which comprises the following steps:
s1: plotting a diameter of phi 1 The circle center is O, and the circle center is projected to a distance L along the axial direction 1 The projection plane of (2) forms a projection circle with a center of O 1 ；
S2: respectively drawing the length of the projection circle from the highest point of the over-projection circle to the horizontal left direction and the horizontal right direction to be L 2 The line segment of (2);
s3: each translating downwards at the end points of the two tangent lines
Distance to obtain O 2 (ii) a Then with O 2 Is used as the center of a circle,
the radius draws a circle;
s4: round O 1 The lowest point of the two-dimensional space is drawn into a line segment in the horizontal left and right directions, and the other end of the line segment is respectively connected with the other end of the line segmentTwo circles O 2 Near circle O of 1 One end of the two ends are connected through a circular arc;
s5: rub off the circle O 2 Obtaining the orthographic projection of the tail end of the dovetail cone by using the redundant lines;
s6: respectively leading out two bilaterally symmetrical line segments from the left end and the right end of the orthographic projection of the tail end of the dovetail cone in the z direction, wherein the z direction is perpendicular to the orthographic projection surface of the tail end of the dovetail cone, respectively connecting the other ends of the two line segments with the left end and the right end of a circle O, and sewing the connected curves into the dovetail cone through an artistic curved surface instruction;
s7: stretching L with the circle O as the object 3 Length, obtaining a cylinder;
s8: and combining the cylinder and the dovetail cone to obtain the dovetail air film hole structure.
On the other hand, the invention provides a turbine blade, which comprises the dovetail air film hole and a blade, wherein the dovetail air film hole is penetrated through the blade, the included angle between the central axis of the dovetail air film hole and the surface of the blade is alpha, and the thickness of the blade is H 2 The distance H from the part of the dovetail cone part, which is connected with the inclined hole, to the bottom of the blade 1 。
Further, H 1 The length of (A) is 0.5-1 mm; h 2 The length of the angle alpha is 1-2 mm, and the angle alpha is 30-55 degrees.
The invention provides a drawing method of the turbine blade, which comprises the following steps:
s1: the middle part of the dovetail-shaped air film hole is overlapped with the blade part, and the central axis of the dovetail-shaped air film hole and the blade are placed at an alpha angle;
s2: the difference set is obtained by using the blade and the dovetail type air film hole core, and the turbine blade with the dovetail type air film hole is provided.
The invention also provides a processing method of the turbine blade, which comprises the following steps:
s1: the method comprises the following steps of (1) cutting a model of a dovetail type air film hole by stretching the surface of the dovetail type air film hole to obtain a dovetail plane model, a dovetail inclined model and a corresponding processing laser deflection angle;
s2: according to the processing laser deflection angle obtained in the step S1, carrying out layered slicing on the dovetail plane model and the dovetail inclination model along the processing direction, and taking a two-dimensional wire frame model of the cross section edge of each layer to obtain a dovetail plane wire frame and a dovetail inclination wire frame;
s3: according to the two-dimensional wire frame model obtained in the step S2, carrying out laser scanning processing on the blade based on the dovetail plane wire frame to obtain a dovetail plane model-shaped hole, then offsetting the blade by a corresponding angle according to a processing laser deflection angle corresponding to the dovetail inclination model, positioning by using six degrees of freedom, and carrying out laser scanning processing on the blade based on the dovetail inclination wire frame to obtain a dovetail cone-shaped hole;
s4: according to the dovetail cone-shaped hole obtained in the step S3, laser rotary cutting processing is carried out on the center of the dovetail cone-shaped hole after positioning is carried out by utilizing six degrees of freedom, and the diameter phi is processed 1 And finally obtaining the dovetail-shaped air film hole on the blade.
Further, in step S1, the machining laser deflection angle is 0 ° for the dovetail plane model, and 90 ° - α for the dovetail slope model.
Further, in step S1, the interlayer distance of the layered slice is 0.05mm.
The dovetail air film hole, the turbine blade with the dovetail air film hole and the processing method thereof provided by the invention have the following beneficial effects:
(1) The dovetail air film hole cooling characteristic is remarkably improved relative to a round hole, especially under a common large blowing ratio in the working condition of an actual engine;
(2) The parametric modeling is carried out aiming at the dovetail type air film hole, and R in a formula can be changed 1 、Φ 1 The parameters of alpha, beta, delta and the like can change the parameters of the dovetail type air film hole model such as the aperture, the main inclination angle, the open angle, the wide angle and the like, thereby easily realizing the change of the shape of the air film hole model;
(3) The problem of shading in the process of laser processing the dovetail type air film hole is solved by cutting the dovetail type air film hole model and processing the variable processing laser deflection angle, so that the processing problem of the dovetail type air film hole is solved, and the dovetail type air film hole on the turbine blade is processed.
Drawings
FIGS. 1-2 are plan views of dovetail-shaped film apertures provided by embodiments of the present invention.
FIG. 3 is a schematic perspective view of a dovetail film hole provided in accordance with an embodiment of the present invention.
FIG. 4 is a perspective view of a dovetail film hole core provided in accordance with an embodiment of the present invention.
FIG. 5 is an illustration of the positional relationship of a dovetail film hole core and a blade provided in accordance with an embodiment of the present invention.
FIG. 6 is a diagram of a dovetail-shaped film hole blade provided by an embodiment of the invention.
FIG. 7 is a diagram of a dovetail film hole model provided in accordance with an embodiment of the present invention.
FIG. 8 is a sectional view of a dovetail gas film hole pattern provided in accordance with an embodiment of the present invention.
FIG. 9 is a layer-by-layer slice of a dovetail gas film hole model provided by an embodiment of the invention.
The reference numerals of the main elements in the figures are explained as follows:
101: a projection circle, 102: a tangent line of a dovetail curve, 103: a dovetail curve circumcircle, 104: a line segment, 105: a first dovetail curve, 106: a second dovetail curve, 107: a dovetail cone and cylinder junction circle, 108: a connecting straight line, 109: a dovetail cone, 110: a cylinder, 111: a dovetail air film hole, 201: a central axis of the dovetail air film hole, 202: a blade, 203: the dovetail air film hole, 301: the dovetail air film hole model 302: a dovetail air film hole surface, 303: a dovetail plane model, 304: a dovetail inclined model, 305: a dovetail plane wire frame, 306: a dovetail inclined wire frame.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the embodiments of the present invention, and it should be apparent that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. 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 invention.
Example 1
The embodiment provides a dovetail-shaped air film hole and a drawing method thereof.
Referring to FIG. 4, an embodiment of the present invention provides a dovetail-shaped film hole having a structure including a dovetail cone 109 and a cylinder 110; the cylinder 110 has a length L 3 =10mm; the cylinder 110 is fixedly connected with the head end of the dovetail cone 109 through one end; the distance between the head end and the tail end of the dovetail cone 109 is L 1 =10mm; the orthographic projection of the tail end of the dovetail cone 109 comprises a projection circle 101 of a cylinder 110, and further comprises a first dovetail curve 105 and a second dovetail curve 106 which are sequentially connected end to end; the first dovetail curve 105 and the second dovetail curve 106 have a circumscribed circle radius R 1 (ii) a The distance between the vertex of the projected circle 101 and the vertex of the first dovetail curve 105 is L 2 A distance between a vertex of the projected circle 101 and a vertex of the second dovetail curve 106 is L 2 (ii) a The diameter of the cylinder 110 is phi 1 =0.4mm; the opening angle of the dovetail cone 109 is 2 beta, and the wide angle at the bottom of the tail end of the dovetail cone 109 is delta; and satisfies the following conditions:
referring to fig. 1 to 4, a dovetail type film hole and a drawing method thereof provided by the embodiment of the invention include the following steps:
s1: plotting a diameter of phi 1 A circle 107 with a center of O =0.4mm, which is projected to a distance L along the axial direction 1 Forms a projection circle 101 with a center O 1 ；
S2: the maximum point of the over-projection circle 101 respectively draws the length L of the projection circle to the horizontal left direction and the horizontal right direction 2 A segment of tangent line 102;
s3: each translating downwards at the end points of the two tangent lines 102
Distance, obtaining O 2 (ii) a Followed by O 2 Is used as the center of a circle,
drawing a circle 103 for the radius;
s4: circle O 1 The lowest point of the circle is drawn into a line segment in the horizontal left and right directions, and the other end of the line segment is respectively connected with two circles O 2 Near circle O of 1 One end of the connecting rod is connected through a circular arc;
s5: rub off the circle O 2 Obtaining the orthographic projection of the tail end of the dovetail cone by using the redundant lines;
s6: respectively leading out two bilaterally symmetrical line segments from the left end and the right end of the orthographic projection of the tail end of the obtained dovetail cone 109 in the z direction, wherein the z direction is the direction vertical to the orthographic projection surface of the tail end of the dovetail cone, respectively connecting the other ends of the two line segments with the left end and the right end of a circle O, and stitching the connected curves into the dovetail cone 109 through an artistic curved surface instruction;
s7: drawing L with the circle O as the object 3 Length, resulting in cylinder 110;
s8: the cylinder 110 and the dovetail cone 109 are combined to obtain a dovetail film hole 111 structure.
Example 2
The present embodiment provides a turbine blade including the dovetail film hole according to the first embodiment, and a drawing method and a machining method thereof.
Referring to fig. 5 and 6, the turbine blade provided by the embodiment of the invention comprises a blade 202 and the dovetail-shaped film hole provided by the invention, wherein an included angle between a central axis 201 of the dovetail-shaped film hole and the surface of the blade 202 is 30 degrees, and the wall thickness H of the blade 202 is H 2 =1.5mm, and the distance H between the part of the dovetail cone body, which is connected with the inclined hole, and the bottom of the blade 1 =0.75mm; the dovetail film holes are subtracted from the blade 202 to obtain the dovetail film holes 203 on the blade 202.
The drawing method of the turbine blade provided by the embodiment comprises the following steps:
s1: the middle part of the dovetail-shaped air film hole is partially overlapped with the blade 202, and the central axis 201 of the dovetail-shaped air film hole is arranged at an angle of 30 degrees with the blade 202;
s2: the difference between the blade 202 and the dovetail film hole 111 cores is used to calculate the turbine blade 203 with the dovetail film hole 111.
Referring to fig. 7-9, the present invention may accomplish the machining of a dovetail film hole in a turbine blade by the following steps:
s1: by stretching the surface 302 of the dovetail-shaped air film hole, the model 301 of the dovetail-shaped air film hole is divided to obtain a dovetail plane model 303, a dovetail inclination model 304 and corresponding processing laser deflection angles thereof;
s2: slicing the dovetail plane model 303 and the dovetail inclination model 304 layer by layer along the processing direction according to the processing laser deflection angle obtained in the step S1, and taking a two-dimensional wire frame model of the cross section edge of each layer to obtain a dovetail plane wire frame 305 and a dovetail inclination wire frame 306;
s3: according to the two-dimensional wire frame model obtained in the step S2, laser scanning processing is carried out on the blade based on the dovetail plane wire frame 305 to obtain a hole in the shape of a dovetail plane model 303, then the blade is offset by a corresponding angle according to a processing laser deflection angle corresponding to the dovetail inclination model 304, and the blade is positioned by six degrees of freedom and then is subjected to laser scanning processing based on the dovetail inclination wire frame 306 to obtain a hole in the shape of a dovetail cone;
s4: according to the dovetail cone-shaped hole obtained in the step S3, laser rotary cutting processing is carried out on the center of the dovetail cone-shaped hole after positioning is carried out by utilizing six degrees of freedom, and the diameter phi is processed 1 An oblique hole of =0.4mm, and a dovetail-shaped film hole 203 in the blade 202 is finally obtained.
While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (9)
1. A dovetail type air film hole, which is characterized in thatCharacterized in that the structure of the dovetail air film hole comprises a dovetail cone and a cylinder; the length of the cylinder is L 3 (ii) a The cylinder is fixedly connected with the head end of the dovetail cone through one end of the cylinder; the distance between the head end and the tail end of the dovetail cone is L 1 (ii) a The orthographic projection of the tail end of the dovetail type cone comprises a projection circle of a cylinder, and further comprises a first dovetail curve and a second dovetail curve which are sequentially connected end to end; the radius of the circumscribed circle of the first dovetail curve and the second dovetail curve is R 1 (ii) a The distance between the vertex of the projection circle and the vertex of the first dovetail curve is L 2 The distance between the vertex of the projection circle and the vertex of the second dovetail curve is L 2 (ii) a The diameter of the cylinder is phi 1 (ii) a The spreading angle of the dovetail cone is 2 beta, and the wide angle at the bottom of the tail end of the dovetail cone is delta; and satisfies the following conditions:
2. the dovetail film hole of claim 1, wherein L is 3 The length of (A) is 8-12 mm; l is a radical of an alcohol 1 Has a length of 8-12 mm, phi 1 The length of the angle beta is 0.2-0.6 mm, the angle delta is 3-7 degrees, and the angle beta is 15-25 degrees.
3. The method for drawing a dovetail-shaped film hole according to claim 1, comprising the steps of:
s1: plotting a diameter of phi 1 The circle center is O, and the circle center is projected to a distance L along the axial direction 1 The projection plane of (2) forms a projection circle with a center of O 1 ；
S2: the highest point of the over-projection circle is divided into two directions of horizontal left and rightRespectively drawing the length of the projection circle as L 2 The line segment of (2);
s3: each translating downwards at the end points of the two tangent lines
Distance, obtaining O 2 (ii) a Followed by O 2 Is used as the center of a circle,
drawing a circle for the radius;
s4: circle O 1 The lowest point of the circle is drawn into a line segment in the horizontal left and right directions, and the other end of the line segment is respectively connected with two circles O 2 Near circle O of 1 One end of the two ends are connected through a circular arc;
s5: wipe off circle O 2 Obtaining the orthographic projection of the tail end of the dovetail cone by using the redundant lines;
s6: respectively leading out two bilaterally symmetrical line segments from the left end and the right end of the orthographic projection of the tail end of the dovetail cone in the z direction, respectively connecting the other ends of the two line segments with the left end and the right end of a circle O, and sewing the connected curves into the dovetail cone through an artistic curved surface instruction;
s7: drawing L with the circle O as the object 3 Length, obtaining a cylinder;
s8: and combining the cylinder and the dovetail cone to obtain the dovetail air film hole structure.
4. A turbine blade comprising the dovetail film hole of claim 1 and further comprising a blade, wherein the dovetail film hole intersects the blade, an included angle between a central axis of the dovetail film hole and a surface of the blade is α, and a thickness of the blade is H 2 The distance H from the joint part of the dovetail cone part and the inclined hole to the bottom of the blade 1 。
5. A turbine blade according to claim 4, characterised in that H 1 The length of (A) is 0.5-1 mm; h 2 Has a length of 1-2 mm and an alpha angle of 30-up to55°。
6. A method of mapping a turbine blade as claimed in claim 4, comprising the steps of:
s1: superposing the middle part of the dovetail air film hole with the blade part, and placing the central axis of the dovetail air film hole and the blade at an alpha angle;
s2: and solving a difference set by using the blade and the dovetail air film hole mold core to obtain the turbine blade with the dovetail air film hole.
7. A method of machining a turbine blade as claimed in claim 4, including the steps of:
s1: the method comprises the following steps of (1) cutting a model of a dovetail type air film hole by stretching the surface of the dovetail type air film hole to obtain a dovetail plane model, a dovetail inclined model and a corresponding processing laser deflection angle;
s2: according to the processing laser deflection angle obtained in the step S1, carrying out layered slicing on the dovetail plane model and the dovetail inclination model along the processing direction, and taking a two-dimensional wire frame model of the cross section edge of each layer to obtain a dovetail plane wire frame and a dovetail inclination wire frame;
s3: according to the two-dimensional wire frame model obtained in the step S2, carrying out laser scanning machining on the blade based on the dovetail plane wire frame to obtain a dovetail plane model-shaped hole, then offsetting the blade by a corresponding angle according to a machining laser deflection angle corresponding to the dovetail inclination model, positioning by utilizing six degrees of freedom, and carrying out laser scanning machining on the blade based on the dovetail inclination wire frame to obtain a dovetail cone-shaped hole;
s4: according to the dovetail cone-shaped hole obtained in the step S3, laser rotary cutting processing is carried out on the center of the dovetail cone-shaped hole after positioning is carried out by utilizing six degrees of freedom, and the diameter phi is processed 1 And finally obtaining the dovetail-shaped air film hole on the blade.
8. The method for machining a turbine blade as claimed in claim 7, wherein in step S1, the machining laser deflection angle corresponds to 0 ° for a dovetail plane model and 90 ° - α for a dovetail tilt model.
9. The method for machining a turbine blade as claimed in claim 7, wherein in step S1, the layer pitch of the sliced layers is 0.05mm.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211580867.XA CN115749970A (en) | 2022-12-09 | 2022-12-09 | Dovetail-shaped air film hole, turbine blade containing dovetail-shaped air film hole and machining method of dovetail-shaped air film hole |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211580867.XA CN115749970A (en) | 2022-12-09 | 2022-12-09 | Dovetail-shaped air film hole, turbine blade containing dovetail-shaped air film hole and machining method of dovetail-shaped air film hole |
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| CN115749970A true CN115749970A (en) | 2023-03-07 |
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| CN202211580867.XA Pending CN115749970A (en) | 2022-12-09 | 2022-12-09 | Dovetail-shaped air film hole, turbine blade containing dovetail-shaped air film hole and machining method of dovetail-shaped air film hole |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116174946A (en) * | 2023-04-20 | 2023-05-30 | 西北工业大学 | Femtosecond laser processing method for special-shaped air film hole with complex expansion port |
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2022
- 2022-12-09 CN CN202211580867.XA patent/CN115749970A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116174946A (en) * | 2023-04-20 | 2023-05-30 | 西北工业大学 | Femtosecond laser processing method for special-shaped air film hole with complex expansion port |
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