CN115247575A - Spiral turbine blade cooling unit and cooling structure - Google Patents
Spiral turbine blade cooling unit and cooling structure Download PDFInfo
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- CN115247575A CN115247575A CN202210520824.6A CN202210520824A CN115247575A CN 115247575 A CN115247575 A CN 115247575A CN 202210520824 A CN202210520824 A CN 202210520824A CN 115247575 A CN115247575 A CN 115247575A
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- cooling structure
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- 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
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- 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
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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
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a spiral turbine blade cooling unit and a cooling structure, and belongs to the technical field of turbine blades of aero-engines. The cooling unit comprises a plurality of bent cooling channels which are spirally and alternately arranged. The spiral turbine blade cooling unit enables the direction of cold air to be continuously turned through the spiral staggered curved cooling channels, so that strong secondary circulation flow can be caused on the cross section, and the effect of enhancing internal heat exchange can be remarkably achieved. And the cold air flow cross-sectional area is approximately the same along the way, the phenomena of flow sudden expansion and throttling are avoided, the air flow deflection angle is small, mutual impact and mixing are avoided, and the flow resistance is smaller compared with the conventional tail edge full-slit structure or the conventional front edge convection heat exchange structure.
Description
Technical Field
The invention belongs to the technical field of turbine blades of aero-engines, and particularly relates to a spiral turbine blade cooling unit and a cooling structure.
Background
The trailing edge serves as one of the critical portions of the turbine blade that require cooling. Firstly, the structural integrity of the trailing edge is crucial to the aerodynamic performance and the life reliability of the turbine blade; secondly, the gas velocities of the pressure surface and the suction surface reach quite high values at the tail edge of the blade and are in a turbulent state, so that the convection intensity at the tail edge is very high. To ensure that the structural integrity of the trailing edge is not compromised by hot gas ablation during engine service, it must be efficiently cooled. For advanced aircraft engines currently in service, the amount of cold air used for trailing edge cooling has accounted for approximately 20-30% of the total cooling air usage for the high pressure turbine blades. Due to the small trailing edge geometry, it is often desirable to design a cooling structure that is both structurally strong and cooling efficient. The typical cooling structure of the turbine blade tail edge mainly comprises three structural forms of a full-split cooling structure, a discrete small hole cooling structure and a half-split cooling structure. The research results of the document "the development of the cooling structure of the air-cooled turbine blade of an aircraft engine" ("propulsion technology") show that the cooling capacity of the traditional trailing edge cooling structure gradually tends to be limited along with the continuous increase of the temperature of the combustion gas of the aircraft engine, and the ablation phenomenon of the turbine blade with high pressure frequently occurs in the area of the trailing edge.
The turbine blade leading edge is the region where the thermal load is most severe. Since the leading edge directly bears the impact of the incoming flow of high-temperature fuel gas, the heat transfer and the flow of the leading edge are extremely complicated due to various factors, and the leading edge is always the focus and the difficulty of attention of researchers. In order to improve the cooling effect, rough elements such as turbulence columns/ribs can be arranged on the inner side of the concave surface of a cooling cavity channel of the front edge of the turbine blade, so that a combined cooling mode of inner jet flow impact and the rough elements is formed. With the continuous increase of the front temperature of the turbine of the engine, a new and efficient front edge cooling mode needs to be continuously developed to solve the problem of cooling the front edge of the turbine blade.
Therefore, the development and design of the efficient cooling structure for the trailing edge and the leading edge of the turbine blade further improve the comprehensive cooling effect of the blade on the basis of not increasing the amount of cold air, and are very necessary and meaningful for the development of advanced high-performance aircraft engines.
Disclosure of Invention
In order to solve the above problems, an object of the present invention is to provide a spiral cooling structure disposed at the trailing edge or the leading edge of a turbine blade, so as to improve the overall cooling efficiency of the turbine blade and achieve the purpose of improving the temperature-bearing capability of the blade.
In order to achieve the above object, the present invention provides a helical turbine blade cooling unit, which comprises a plurality of curved cooling channels arranged in a helical staggered manner;
the bent cooling channel comprises an inlet straight section (3), a spiral turning channel (4) and an outlet straight section (5), wherein the inlet straight section (3), the spiral turning channel (4) and the outlet straight section (5) are sequentially connected along the airflow flowing direction to form a cold air channel; the tail end of the inlet straight section (3) is connected with the starting end of the spiral turning channel (4) through arc natural smooth transition; the tail end of the spiral turning channel (4) is naturally connected with the initial end of the outlet straight section (5) through an arc.
The spiral turbine blade cooling unit provided by the invention is also characterized in that the central line of the spiral turning channel (4) is a spiral line, the spiral diameter D of the spiral turning channel is 1.2-5.2mm, and the pitch p of the spiral turning channel is 2.1-3.6.
The helical turbine blade cooling unit of the present invention is further characterized by said inlet flat segment length L1 being from 0.6 x d to 3.0 x d; the length t = (p/2) = k of the spiral turning channel, wherein k is more than or equal to 2, and k is a natural number; the outlet flat segment length L2 is 0.5 x d-3.0 x d.
The helical turbine blade cooling unit provided by the invention is also characterized in that the number of the plurality of the curved cold air channels is n, and the initial azimuth angle difference of the adjacent curved cold air channels is 2 pi/n, wherein n is not less than 2.
The spiral turbine blade cooling unit provided by the invention is also characterized in that the cross sections of the inlet straight section (3), the spiral turning channel (4) and the outlet straight section (5) are the same in shape, and are rectangles with vertex angles subjected to fillet treatment, the long side H of each rectangle is 0.4-1.6mm, the width L of each rectangle is 0.25-1.05mm, and the radius R of each fillet is 0.2-0.5mm.
It is another object of the present invention to provide a helical turbine blade cooling structure including a cooling unit as defined in any one of the preceding claims.
The helical turbine blade cooling structure provided by the invention is also characterized in that the cooling structure is arranged at the leading edge or the trailing edge of the helical turbine blade.
The spiral turbine blade cooling structure provided by the invention is also characterized in that when the cooling structure is arranged at the leading edge, the center line of the cooling structure is consistent with the height direction of the turbine blade.
The spiral turbine blade cooling structure provided by the invention is also characterized in that when the cooling structure is arranged at the tail edge, the cooling structure comprises a plurality of cooling units arranged in an array, and the radial distance S3 between the adjacent cooling units is 2.5-4.0mm.
The distance S1 between the central line of the cooling structure and the central line of the bent cold air channel in the cooling unit is 0.45-1.3.
Advantageous effects
The spiral turbine blade cooling unit provided by the invention continuously turns the direction of cold air through the spiral staggered bent cooling channels, so that strong secondary circulation is caused on the cross section, and the effect of enhancing internal heat exchange can be remarkably achieved. And the cold air flow cross section area is approximately the same along the way, the phenomena of flow sudden expansion and throttling are avoided, the air flow deflection angle is small, mutual impact and mixing are avoided, and the flow resistance is smaller compared with a conventional tail edge full-split seam structure or a conventional front edge convection heat exchange structure.
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 three-dimensional isometric view of a helical turbine blade cooling structure provided by an embodiment of the present invention;
FIG. 2 is a schematic view of a centerline of a helical turbine blade cooling structure provided by an embodiment of the present invention;
FIG. 3 is a schematic cross-sectional view of a helical turbine blade cooling configuration provided by an embodiment of the present invention;
FIG. 4 is a front view of a helical turbine blade cooling configuration provided by an embodiment of the present invention;
FIG. 5 is a top view of a helical turbine blade cooling structure provided by an embodiment of the present invention;
FIG. 6 is a schematic view of a helical turbine blade cooling structure provided by an embodiment of the present invention applied to the trailing edge region of an aircraft engine turbine blade;
FIG. 7 is a three-dimensional schematic view of a leading edge helical cooling structure provided by an embodiment of the present invention;
FIG. 8 is a schematic view of a helical turbine blade cooling structure provided by an embodiment of the present invention applied to the leading edge region of a turbine blade of an aircraft engine;
FIG. 9 is a graph of the variation of the comprehensive heat exchange performance parameter eta of the spiral turbine blade cooling structure at the trailing edge of the blade provided by the embodiment of the invention along with the Reynolds number Re of the inlet;
FIG. 10 is a graph of the integrated heat exchange performance parameter η with the inlet Reynolds number Re for a helical turbine blade cooling configuration for a blade leading edge in accordance with an embodiment of the present invention.
Detailed Description
The present invention is further described in detail with reference to the drawings and examples, but it should be understood that these embodiments are not intended to limit the present invention, and those skilled in the art should understand that the functional, methodological, or structural equivalents of these embodiments or substitutions may be included in the scope of the present invention.
In the description of the embodiments of the present invention, it should be understood that the terms "central", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only used for convenience in describing and simplifying the description of the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.
The terms "mounted," "connected," and "coupled" are to be construed broadly and may include, for example, fixed connections, removable connections, or integral connections; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
As shown in fig. 1 to 5, the present embodiment provides a helical turbine blade cooling unit, which includes a plurality of curved cooling channels 1 and cooling channels 2 arranged in a helical staggered manner; the bent cooling channel comprises an inlet straight section 3, a spiral turning channel 4 and an outlet straight section 5, wherein the inlet straight section 3, the spiral turning channel 4 and the outlet straight section 5 are sequentially connected along the airflow flowing direction to form a cold air channel; the tail end of the inlet straight section 3 is connected with the starting end of the spiral turning channel 4 through arc natural smooth transition; the tail end of the spiral turning channel 4 is naturally connected with the starting end of the outlet straight section 5 through an arc.
The spiral turbine blade cooling unit provided by the embodiment continuously turns the direction of the cold air through the spiral staggered bent cooling channels, so that strong secondary circulation flow is caused on the cross section, and the effect of enhancing internal heat exchange can be remarkably achieved.
In some embodiments, the center line of the helical turn-around passage 4 is a helix with a helix diameter D of 1.2-5.2mm and a pitch p of 2.1 × D-3.6 × D.
In some embodiments, the inlet flat segment length L1 is 0.6 × d-3.0 × d; the length t = (p/2) × k of the spiral-shaped turning channel, wherein k is more than or equal to 2, and k is a natural number; the outlet flat section length L2 is 0.5 x d-3.0 x d.
In some embodiments, the number of the plurality of curved cold air channels is n, and the difference between the initial azimuth angles of the adjacent curved cold air channels is 2 pi/n, wherein n is not less than 2.
In some embodiments, the cross-sectional shapes of the inlet straight section 3, the spiral turning channel 4 and the outlet straight section 5 are the same, and are rectangles with rounded corners at vertex angles, the long side H of each rectangle is 0.4-1.6mm, the width L of each rectangle is 0.25-1.05mm, and the radius R of each circle is 0.2-0.5mm.
In the embodiment, the cold air flow cross-sectional area is approximately the same along the way, the flow sudden expansion and throttling phenomena cannot be generated, the air flow deflection angle is small, mutual impact and mixing are avoided, and the flow resistance is smaller compared with a conventional tail edge full-slit structure or a conventional front edge convection heat exchange structure.
In some embodiments, a helical turbine blade cooling structure is provided, the cooling structure comprising a cooling unit as defined in any one of the preceding claims.
As shown in fig. 8, in some embodiments, the cooling structure is provided at the leading edge 12 of the helical turbine blade 6.
The machining method of the spiral turbine blade cooling structure provided by the embodiment comprises the following steps:
step one, referring to fig. 1 to 8, drawing an auxiliary line MN in the vertical direction on the XOY plane along the Y-axis direction, and taking the auxiliary line MN as a center line of the spiral cooling structure; selecting a point Q on the MN; then, taking the point Q as a center, making a circle with the diameter of 4.0mm in a horizontal plane, and selecting points Q1, Q2, Q3, Q4 and Q5 on which the arc length is divided into five parts; respectively drawing five line segments with the length of 3.5mm along the vertical downward direction by taking the Q1, the Q2, the Q3, the Q4 and the Q5 as starting points; then respectively drawing five spiral lines with the spiral diameter of 4.0mm, the thread pitch of 8.5mm and the spiral length of 68.0mm in a vertical downward direction by taking the tail ends of the five line segments as starting points, wherein the difference of the starting azimuth angles of the two adjacent spiral lines is 36 degrees; and then respectively taking the tail ends of the five spiral lines as starting points, establishing five line segments which are parallel to the negative direction of the Y axis and are 5.5mm long, and finally obtaining the central lines of the five bent cooling channels of the spiral cooling unit.
And step two, taking the rectangle with the length of 1.0mm and the width of 0.65 as shown in fig. 3 as the cross section and with the vertex angle being fillet treatment as the cross section, respectively sweeping along the five central lines drawn in the step one to establish a three-dimensional entity, and then performing arc smoothing treatment between the straight section and the spiral section to finally form the blade leading edge spiral cooling structure, as shown in fig. 7.
And step three, keeping the center of the spiral cooling structure consistent with the height direction of the turbine blade, and then calculating the difference with the front edge area of the blade model to finally obtain the turbine blade with the spiral cooling structure, as shown in fig. 8.
The comparison research of the flow state and the heat exchange performance of internal cooling gas is carried out on the conventional blade leading edge cooling structure and the cooling structure provided by the embodiment through three-dimensional numerical simulation, and a comprehensive heat exchange performance parameter eta is defined to represent the heat exchange strength corresponding to unit pressure drop, and the comprehensive heat exchange performance parameter eta is specifically defined as follows:
in the formula, f 0 ＝0.507*Re -0.3 ，f＝Δp/(0.5*ρ*U 2 )。
Wherein the dimensionless Knudsen number is defined as follows:
in the formula, h is a heat exchange coefficient, D is a characteristic length, lambda is a heat conduction coefficient, re is an inlet Reynolds number, and Pr is a Plante number.
As shown in fig. 10, the enhanced heat exchange effective coefficient of the leading edge helical cooling unit 13 is always higher than that of the conventional cooling structure of the leading edge of the blade, and the comprehensive heat exchange performance of the leading edge helical cooling unit is 18.7% higher than that of the conventional cooling structure of the leading edge of the blade within the flow parameter range of the leading edge of the blade (Re = 5000-26000).
On the basis of not increasing the amount of cold air, the spiral turbine blade cooling structure provided by the embodiment is arranged in the front edge area of the blade, so that the cooling efficiency of the blade can be further improved by 4.7%, and the temperature bearing capacity of the turbine blade can be greatly improved.
As shown in fig. 6, in some embodiments, the cooling structure is provided at the trailing edge 7 of the helical turbine blade 6.
The machining method of the spiral turbine blade cooling structure provided by the embodiment comprises the following steps:
step one, referring to fig. 1-6, drawing two line segments which are parallel to the X axis, have a distance of 1.2mm and have lengths of 1.6mm on an XOY plane; then drawing two spiral lines with the spiral diameter of 1.2mm, the thread pitch of 3.0mm and the length of 7.5mm by taking the tail ends of the two line segments as starting points respectively, wherein the starting azimuth angles of the two spiral lines are different by 180 degrees; and then respectively establishing two line segments which are parallel to the X axis and have the length of 1.5mm by taking the tail ends of the two spiral lines as starting points to form a graph shown in figure 2.
And step two, taking the rectangular cross section with the length of 0.50mm and the width of 0.40 as shown in fig. 3 as the vertex angle and performing fillet treatment, respectively performing sweeping along the two curves drawn in the step one to establish a three-dimensional entity, and performing arc smoothing treatment between the straight section and the spiral section to finally form a spiral cooling structure unit, which is shown in fig. 4 and 5.
And step three, arraying the spiral cooling structure units according to the radial distance S3=2.2mm, and then calculating the difference with the tail edge area of the turbine blade model to finally obtain the turbine blade with the spiral cooling structure, as shown in fig. 6.
The comparison research of the flow state and the heat exchange performance of the internal cooling gas is carried out on the conventional blade leading edge cooling structure and the cooling structure provided by the embodiment through three-dimensional numerical simulation, and a comprehensive heat exchange performance parameter eta is defined to represent the heat exchange strength corresponding to unit pressure drop, and the comprehensive heat exchange performance parameter eta is specifically defined as follows:
in the formula, f 0 ＝0.507*Re -0.3 ，f＝Δp/(0.5*ρ*U 2 )。
Wherein the dimensionless Knudsen number is defined as follows:
in the formula, h is a heat exchange coefficient, D is a characteristic length, lambda is a heat conduction coefficient, re is an inlet Reynolds number, and Pr is a Plantt number.
As shown in FIG. 9, the effective coefficient of enhanced heat exchange of the helical cooling unit 7 at the trailing edge is always higher than that of the conventional cooling structure at the leading edge of the blade no matter in the case of low inlet Reynolds number or high inlet Reynolds number, the three-dimensional data simulation structure shows that the comprehensive heat exchange performance of the helical cooling unit at the trailing edge is 29.4% higher than that of the conventional cooling structure at the trailing edge of the blade within the flow parameter range (Re = 5000-26000).
On the basis of not increasing the cold air quantity, through arranging the heliciform turbine blade cooling structure that above-mentioned embodiment provided to blade trailing edge region, can further make blade cooling efficiency promote 8.3%, can improve turbine blade's temperature-bearing ability by a wide margin.
In some embodiments, the centerline of the cooling structure coincides with the direction of the height of the turbine blade when the cooling structure is disposed at the leading edge.
In some embodiments, when the cooling structure is arranged at the trailing edge, the cooling structure comprises a plurality of cooling units arranged in an array, and the radial distance S3 between adjacent cooling units is 2.5-4.0mm.
In some embodiments, the distance S1 between the center line of the cooling structure and the center line of the curved cold air channel in the cooling unit is 0.45 × d-1.3 × d.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, it is possible to make various improvements and modifications without departing from the technical principle of the present invention, and those improvements and modifications should be also considered as the protection scope of the present invention.
Claims (10)
1. A helical turbine blade cooling unit, characterized by: the cooling unit comprises a plurality of bent cooling channels which are spirally and alternately arranged;
the bent cooling channel comprises an inlet straight section (3), a spiral turning channel (4) and an outlet straight section (5), wherein the inlet straight section (3), the spiral turning channel (4) and the outlet straight section (5) are sequentially connected along the airflow flowing direction to form a cold air channel; the tail end of the inlet straight section (3) is connected with the starting end of the spiral turning channel (4) through arc natural smooth transition; the tail end of the spiral turning channel (4) is naturally connected with the starting end of the outlet straight section (5) through an arc.
2. The helical turbine blade cooling unit according to claim 1, wherein the centre line of the helical turning channel (4) is a helix with a helix diameter D of 1.2-5.2mm and a pitch p of 2.1 x D-3.6 x D.
3. The helical turbine blade cooling unit as claimed in claim 2 wherein said inlet flat segment length L1 is 0.6 x d-3.0 x d; the length t = (p/2) = k of the spiral turning channel, wherein k is more than or equal to 2, and k is a natural number; the outlet flat section length L2 is 0.5 x d-3.0 x d.
4. The helical turbine blade cooling unit as claimed in claim 1, wherein the number of said plurality of curved cooling air channels is n, and the difference in the initial azimuth angles of said adjacent curved cooling air channels is 2 pi/n, wherein n is not less than 2.
5. The helical turbine blade cooling unit as claimed in claim 1, wherein the cross-sectional shapes of the inlet straight section (3), the helical turning channel (4) and the outlet straight section (5) are the same, and are all rectangles with rounded corners, and the long side H of the rectangle is 0.4-1.6mm, the width L is 0.25-1.05mm, and the rounding radius R is 0.2-0.5mm.
6. A helical turbine blade cooling structure, characterized in that the cooling structure comprises a cooling unit according to any one of claims 1 to 5.
7. The helical turbine blade cooling structure as claimed in claim 6, wherein the cooling structure is provided at a leading edge or a trailing edge of the helical turbine blade.
8. The helical turbine blade cooling structure as claimed in claim 7, wherein a centerline of the cooling structure coincides with a direction of a height of the turbine blade when the cooling structure is disposed at the leading edge.
9. The helical turbine blade cooling structure as claimed in claim 7, wherein the cooling structure comprises a plurality of cooling units arranged in an array when the cooling structure is disposed at the trailing edge, and the radial distance S3 between adjacent cooling units is 2.5-4.0mm.
10. The helical turbine blade cooling structure of claim 6, wherein the distance S1 between the centerline of the cooling structure and the centerline of the curved cooling gas channel in the cooling unit is 0.45 x d-1.3 x d.
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