CN112879103A - Array impact air film structure based on ellipsoidal protrusions - Google Patents
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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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Abstract
The invention relates to an array impact air film structure based on ellipsoidal protrusions, belonging to the technical field of cooling of turbine blades of an aero-engine; the device comprises an air inlet cavity, an impact plate, an impact target plate, a flow guide rib, an air film hole and an ellipsoidal bulge, wherein the air film hole and the ellipsoidal bulge are arranged on the impact target plate; the distance between the impact plate and the impact target plate is H, and a plurality of ellipsoidal protrusions are arranged on one side surface of the impact target plate facing the impact plate in a rectangular array mode, so that the cooling gas vertically irradiates the ellipsoidal protrusions through the impact holes and flows along the ellipsoidal surfaces of the ellipsoidal protrusions; the air film hole is positioned at the downstream of the ellipsoidal bulge on the impact target plate along the flow direction; the plurality of flow guide ribs are vertically arranged on the impact target plate and used for supporting the impact plate, an impact area between the impact plate and the impact target plate is divided into a plurality of heat exchange units in the spanwise direction, and each heat exchange unit comprises two rows of ellipsoidal protrusions. The ellipsoidal convex turbulence element has good heat exchange characteristic and can be used for cooling structures of various aeroengines and turbine blades of gas turbines.
Description
Technical Field
The invention belongs to the technical field of cooling of turbine blades of aero-engines, and particularly relates to an array impact air film structure based on ellipsoidal protrusions.
Background
In the design and development process of modern aeroengines, the thrust-weight ratio and the thermal efficiency of the engines can be improved by continuously increasing the front inlet temperature of the turbine. The inlet temperature before the turbine of the current aeroengine can reach more than 2000K at most, which far exceeds the temperature resistance limit of aeroengine materials. Therefore, how to ensure that the turbine blade works normally under the condition of the temperature far higher than the self-material bearing temperature becomes the key point of research of many experts.
Currently, there are two main ways to reduce the temperature of turbine blades: firstly, the temperature-resistant material which can be more effectively used for turbine blades of aero-engines is continuously developed and developed; and the second is to adopt a novel cooling technology including internal cooling and external cooling. In the internal cooling technology, the local heat exchange coefficient can be effectively improved by the impingement cooling. The cooling gas passes through the impingement holes and impinges on the inner wall surface of the blade at a high velocity, thereby effectively cooling the blade. Therefore, the impact target surface design has important influence on the impact heat exchange effect, and the impact heat exchange effect can be obviously improved by arranging different bulges or concave structures on the target surface, so that the performance of the aero-engine is further improved.
ChangshyWoei et al[1]The heat exchange characteristics of the impact concave surface of the array are researched, the eccentricity between the jet flow center and the pit center is 0, 1/4 and 1/2, the experimental Reynolds number is 5000 to 15000, and the interval between the impact porous plates is 0.5 to 11.
Although this research gives that the pit is located the efflux center, and the heat transfer effect is best, to pit shape research comparatively limited, and the pit structure gathers the dust easily, and difficult washing, this can influence impact heat transfer intensity to a certain extent, can produce certain influence to aeroengine performance.
In addition, the combination of an internal impact heat exchange structure and external cooling is considered, so that the comprehensive cooling performance can be effectively improved, and the method has important significance for prolonging the service life of the blades of the aero-engine.
The following are relevant documents retrieved:
[1]Chang S W,Liou H F.Heat transfer of impinging jet-array onto concave-and convex-dimpled surfaces with effusion[J].International Journal of Heat&Mass Transfer,2009,52(19-20):4484-4499.
disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the invention provides an array impact gas film structure based on the ellipsoidal protrusions.
The technical scheme of the invention is as follows: an array impact air film structure based on ellipsoidal protrusions comprises an air inlet cavity, an impact plate and an impact target plate, wherein cooling air enters the air inlet cavity and vertically shoots on the surface of the impact target plate through impact holes in the impact plate; the method is characterized in that: the air film hole and the ellipsoidal bulge are arranged on the impact target plate;
the distance between the impact plate and the impact target plate is an impact distance H, a plurality of ellipsoidal protrusions are arranged on one side surface of the impact target plate, which faces the impact plate, in a rectangular array mode, the curvature of each ellipsoidal protrusion is 0.25-2, and each ellipsoidal protrusion is located below each impact hole, so that cooling gas vertically irradiates each ellipsoidal protrusion through each impact hole, flows along the ellipsoidal surface of each ellipsoidal protrusion, and then flows out of each gas film hole on the impact target surface;
the impact target plate is provided with a plurality of air film holes, and the air film holes are positioned at the downstream of the ellipsoidal bumps on the impact target plate along the flow direction;
the flow guide ribs are vertically arranged on the impact target plate and used for supporting the impact plate, an impact area between the impact plate and the impact target plate is divided into a plurality of heat exchange units in the spanwise direction, and each heat exchange unit comprises two rows of ellipsoidal protrusions.
The further technical scheme of the invention is as follows: the range of the impact distance H is 0.8-1.2 mm.
The further technical scheme of the invention is as follows: the ellipsoidal convex is formed by rotating a plane ellipse around the major axis by 360 degrees, and a structure obtained by horizontally cutting 1/2 parts is arranged on the surface of the impact target plate as a convex, and the major axis of the ellipsoidal convex forms an included angle of 45 degrees with the flow direction.
The further technical scheme of the invention is as follows: the ratio of the length a of the major semi-axis of the ellipsoidal projection to the impact distance H is 1.8-2.2, and the ratio of the length b of the minor semi-axis to the impact distance H is 0.8-1.2.
The further technical scheme of the invention is as follows: the two rows of ellipsoidal protrusions in each heat exchange unit are arranged in a mirror image mode.
The further technical scheme of the invention is as follows: the ratio of the thickness of the impact plate to the impact distance H is 0.15-0.25, the ratio of the diameter D of the impact hole to the impact distance H is 0.7-1.0, the ratio of the spanwise spacing of the impact hole to the impact distance H is 4.0-5.0, and the ratio of the flow direction spacing of the impact hole to the impact distance H is 4.0-5.0.
The further technical scheme of the invention is as follows: the ratio of the diameter d of the air film hole to the impact distance H is 0.6-0.8, and the included angle between the axis of the air film hole and the horizontal plane is 30-60 degrees; the ratio of the span-wise distance of the air film holes to the impact distance H is 1.5-2.5, and the ratio of the flow direction distance of the air film holes to the impact distance H is 2.0-3.0.
The further technical scheme of the invention is as follows: the air film holes are divided into a plurality of rows along the flow direction, and the air film holes in two adjacent rows are arranged in a staggered mode.
The further technical scheme of the invention is as follows: the ratio of the thickness of the impact target plate to the impact distance H is 0.8-1.2; the ratio of the height of the flow guide ribs to the impact distance H is 0.8-1.2, and the ratio of the width of the flow guide ribs to the impact distance H is 0.8-1.2; the flow guide ribs are positioned opposite to the ellipsoidal protrusions.
The further technical scheme of the invention is as follows: the impact plate is parallel to the impact target plate.
Advantageous effects
The invention has the beneficial effects that: the invention provides an array impact heat exchange air film structure based on ellipsoidal protrusions, namely, an ellipsoidal protrusion structure is arranged on a target plate of a turbine blade impact heat exchange structure, and air film holes are formed in the impact target plate. The advantages of the invention are as follows:
1. compared with flat plate heat exchange, the array impact heat exchange air film structure based on the ellipsoidal protrusions can weaken the influence of cross flow generated after upstream impact on downstream impact heat exchange to a certain extent. For the flat plate structure, after the upstream cooling gas vertically impacts the target plate through the impact holes, cross flow is generated on the surface of the impact target plate and is mixed with the downstream jet flow to generate momentum exchange, so that the downstream cooling gas cannot vertically impact the surface of the target plate, and the impact heat exchange effect is weakened to a certain extent. The ellipsoidal bumps can weaken the influence of cross flow on heat exchange, enhance gas disturbance and local turbulence, and improve the cooling effect of cooling gas on the impact target plate.
2. Compared with flat plate heat exchange, the turbine blade array impact heat exchange structure based on the ellipsoidal protrusions can damage the boundary layer of the region except the impact stagnation point, improve local turbulence and improve the overall heat exchange effect of the target plate. For the flat plate structure, the cooling gas vertically impacts and cools the target plate, a thinner boundary layer is formed in an impact area and then flows to the rest surface of the target plate, and the thickness of the boundary layer is gradually increased, so that the heat exchange effect is weakened. The ellipsoidal bumps are arranged on the impact target plate, so that the boundary layer on the surface except the impact area can be damaged, the gas disturbance is enhanced, and the heat exchange effect is enhanced.
3. The ellipsoidal convex turbulence elements are arranged on the surface of the heat exchange target plate in an array mode, and the convex design can increase the heat exchange area on the surface of the target plate. After the jet flow impacts the ellipsoidal projection of the target surface, the cooling gas flows to other target surfaces along the ellipsoidal side surface with a certain curvature, and secondary impact is formed at the junction of the projection and the target surface, so that the heat exchange capacity of the impact structure is further improved.
4. Strike target plate surface and be provided with the water conservancy diversion rib, will strike the board and strike the impact region between the target plate and divide into a plurality of units along the span direction through a plurality of water conservancy diversion ribs, can improve the heat transfer homogeneity of target plate surface along the span direction, strengthened blade intensity simultaneously, extension blade life.
5. The impact target plate is provided with air film holes, and the combination of internal cooling and external cooling makes the comprehensive cooling performance obvious.
According to the array impact heat exchange air film structure based on the ellipsoidal protrusions, the ellipsoidal protrusion turbulence elements are arranged on the surface of the impact target plate, so that the structure has good heat exchange characteristics, and can be used for cooling structures of various turbine blades of aero-engines and gas turbines.
Based on the optimization of the array impact heat exchange air film structure based on the ellipsoidal protrusions to parameters, under the working condition of jet flow Reynolds numbers of 10000 and 20000, numerical simulation is carried out, and the parameter values are as follows: the impact aperture D is 0.9mm, the impact distance H is 0.9mm, the ratio of the thickness of the impact plate to the impact distance H is 0.22, the ratio of the diameter D of the impact hole to the impact distance H is 0.77, the ratio of the span-wise distance of the impact hole to the impact distance H is 5.0, the ratio of the flow direction distance of the impact hole to the impact distance H is 4.4, the included angle between the axis of the air film hole and the horizontal plane is 40 degrees, the ratio of the span-wise distance of the air film hole to the impact distance H is 2.3, the ratio of the flow direction distance of the air film hole to the impact distance H is 2.8, the ratio of the thickness of the impact target plate to the impact distance H is 1.1, the ratio of the height of the flow guide rib to the impact distance H is 1, and the ratio of the width of the flow guide rib to. The numerical simulation results are shown in fig. 7 and fig. 8, and the knoop number of the impact target surface of the array impact heat exchange gas film structure with the ellipsoidal protrusions is obviously higher than that of a planar target plate under the same reynolds number. Compared with a plane target plate, the average Nurseer number of the mapping area is improved by 18.39%, and the average Nurseer number of the wetting area is improved by 9.78%.
Drawings
FIG. 1 is a front view of an array impingement heat exchange air film structure unit based on ellipsoidal projections according to the present invention.
FIG. 2 is an isometric view of an array impingement heat exchange air film structural unit based on ellipsoidal bumps in accordance with the present invention.
FIG. 3 is a top view of an array impingement heat exchange air film structural unit based on ellipsoidal projections according to the present invention.
FIG. 4 is a bottom view of an array impact heat exchange air film structural unit based on ellipsoidal projections according to the present invention.
FIG. 5 is a cross-sectional view of an array impingement heat exchange gas membrane structure unit based on ellipsoidal projections according to the present invention.
FIG. 6 is a perspective view of an impact target plate of an array impact heat exchange air film structure unit based on ellipsoidal protrusions.
FIG. 7 is an average value of the Knudsen's number in the spanwise direction of an impact target plate and a planar target plate of an array impact heat exchange air film structural unit based on ellipsoidal protrusions when the jet flow Reynolds number is 10000.
FIG. 8 is an average value of the Knudsen's number of the impact target plate and the planar target plate of the array impact heat exchange air film structure unit based on the ellipsoidal protrusions when the jet flow Reynolds number is 20000.
Description of reference numerals: 1. the heat exchange unit comprises an impact target plate 2, an impact plate 3, a gas film hole 4, a heat exchange unit periodic surface 5, a flow guide rib 6, an impact hole 7 and an ellipsoidal bulge.
Detailed Description
The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
Referring to fig. 1 to 5, the impact heat exchange air film structure based on the array of the ellipsoidal protrusions of the present embodiment is applied to the impact air film structure of the turbine blade of the aero-engine, and is composed of an impact target plate 1, an impact plate 2, an air film hole 3, a flow guide rib 5, an impact hole 6, and ellipsoidal protrusions 7. The impact distance H, namely the distance between the impact plate and the impact target plate is 0.8-1.2 mm, the ratio of the thickness of the impact plate to the impact distance H is 0.15-0.25, the ratio of the diameter D of the impact hole to the impact distance H is 0.8-1.0, the ratio of the spanwise distance of the impact hole to the impact distance H is 4.0-5.0, the ratio of the flow direction distance of the impact hole to the impact distance H is 3.5-4.5, the ratio of the diameter D of the air film hole to the impact distance H is 0.5-0.9, and the included angle between the axis of the air film hole and the wall surface is 30-60 degrees. The ratio of the span-wise distance of the air film holes to the impact distance H is 1.5-2.5, and the ratio of the flow direction distance of the air film holes to the impact distance H is 2.0-3.0. The ratio of the thickness of the impact target plate to the impact distance H is 0.8-1.2, the ratio of the height of the flow guide rib to the impact distance H is 0.8-1.2, and the ratio of the width of the flow guide rib to the impact distance H is 0.8-1.2. The impact plate is parallel to the impact target plate.
The ellipsoidal vortex element rotates 360 degrees around the long axis by a plane ellipse, the 1/2 parts are horizontally cut out and are arranged on the surface of the impact target plate as bulges, the long axis and the positive direction form an included angle of 45 degrees with the flow direction, the ratio of the length a of the long half shaft to the impact distance H is 1.8-2.2, and the ratio of the length b of the short half shaft to the impact distance H is 0.8-1.2. The results show that the design of fig. 5 can improve the heat exchange capacity by 22.27% compared to the flat plate structure.
In this example, the cooling air passes through the impingement plate 2, is blown out from the impingement holes 6, is sprayed onto the ellipsoidal projections 7 on the surface of the impingement target plate 1, then flows along the sides of the ellipsoidal projections with a certain curvature radius to other areas of the target plate, and finally flows out from the film holes 3 to exchange heat with the outside of the turbine blades. The ellipsoidal convex structure damages the boundary layer on the impact target surface in the impact heat exchange process, the thickness of the boundary layer is reduced, meanwhile, after the cooling air and the ellipsoidal convex top are subjected to impact heat exchange, the ellipsoidal convex side surface flow direction with a certain curvature impacts the target surface to form secondary impact, the impact heat exchange strength of the blade is further enhanced, external cooling is realized through air film outflow, therefore, the internal impact heat exchange strength can be enhanced based on the ellipsoidal convex array impact heat exchange air film structure, and meanwhile, the good comprehensive cooling performance is realized by combining the external cooling measure of air film cooling.
Based on the array impact heat exchange air film structure based on the ellipsoidal protrusions, under the working condition of jet flow Reynolds numbers of 10000 and 20000, the parameter values are as follows: the impact aperture D is 0.9mm, the impact distance H is 0.9mm, the ratio of the thickness of the impact plate to the impact distance H is 0.22, the ratio of the diameter D of the impact hole to the impact distance H is 0.77, the ratio of the span-wise distance of the impact hole to the impact distance H is 5.0, the ratio of the flow direction distance of the impact hole to the impact distance H is 4.4, the included angle between the axis of the air film hole and the horizontal plane is 40 degrees, the ratio of the span-wise distance of the air film hole to the impact distance H is 2.3, the ratio of the flow direction distance of the air film hole to the impact distance H is 2.8, the ratio of the thickness of the impact target plate to the impact distance H is 1.1, the ratio of the height of the flow guide rib to the impact distance H is 1, and the ratio of the width of the flow guide rib to. The numerical simulation results are shown in fig. 7 and fig. 8, and the knoop number of the impact target surface of the array impact heat exchange gas film structure with the ellipsoidal protrusions is obviously higher than that of a planar target plate under the same reynolds number. Compared with a plane target plate, the average Nurseer number of the mapping area is improved by 18.39%, and the average Nurseer number of the wetting area is improved by 9.78%.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (10)
1. An array impact air film structure based on ellipsoidal protrusions comprises an air inlet cavity, an impact plate and an impact target plate, wherein cooling air enters the air inlet cavity and vertically shoots on the surface of the impact target plate through impact holes in the impact plate; the method is characterized in that: the air film hole and the ellipsoidal bulge are arranged on the impact target plate;
the distance between the impact plate and the impact target plate is an impact distance H, a plurality of ellipsoidal protrusions are arranged on one side surface of the impact target plate, which faces the impact plate, in a rectangular array mode, the curvature of each ellipsoidal protrusion is 0.25-2, and each ellipsoidal protrusion is located below each impact hole, so that cooling gas vertically irradiates each ellipsoidal protrusion through each impact hole, flows along the ellipsoidal surface of each ellipsoidal protrusion, and then flows out of each gas film hole on the impact target surface;
the impact target plate is provided with a plurality of air film holes, and the air film holes are positioned at the downstream of the ellipsoidal bumps on the impact target plate along the flow direction;
the flow guide ribs are vertically arranged on the impact target plate and used for supporting the impact plate, an impact area between the impact plate and the impact target plate is divided into a plurality of heat exchange units in the spanwise direction, and each heat exchange unit comprises two rows of ellipsoidal protrusions.
2. The structure of claim 1, wherein: the range of the impact distance H is 0.8-1.2 mm.
3. The structure of claim 1, wherein: the ellipsoidal convex is formed by rotating a plane ellipse around the major axis by 360 degrees, and a structure obtained by horizontally cutting 1/2 parts is arranged on the surface of the impact target plate as a convex, and the major axis of the ellipsoidal convex forms an included angle of 45 degrees with the flow direction.
4. The structure of claim 1, wherein: the ratio of the length a of the major semi-axis of the ellipsoidal projection to the impact distance H is 1.8-2.2, and the ratio of the length b of the minor semi-axis to the impact distance H is 0.8-1.2.
5. The structure of claim 1, wherein: the two rows of ellipsoidal protrusions in each heat exchange unit are arranged in a mirror image mode.
6. The structure of claim 1, wherein: the ratio of the thickness of the impact plate to the impact distance H is 0.15-0.25, the ratio of the diameter D of the impact hole to the impact distance H is 0.7-1.0, the ratio of the spanwise spacing of the impact hole to the impact distance H is 4.0-5.0, and the ratio of the flow direction spacing of the impact hole to the impact distance H is 4.0-5.0.
7. The structure of claim 1, wherein: the ratio of the diameter d of the air film hole to the impact distance H is 0.6-0.8, and the included angle between the axis of the air film hole and the horizontal plane is 30-60 degrees; the ratio of the span-wise distance of the air film holes to the impact distance H is 1.5-2.5, and the ratio of the flow direction distance of the air film holes to the impact distance H is 2.0-3.0.
8. The structure of claim 1, wherein: the air film holes are divided into a plurality of rows along the flow direction, and the air film holes in two adjacent rows are arranged in a staggered mode.
9. The structure of claim 1, wherein: the ratio of the thickness of the impact target plate to the impact distance H is 0.8-1.2; the ratio of the height of the flow guide ribs to the impact distance H is 0.8-1.2, and the ratio of the width of the flow guide ribs to the impact distance H is 0.8-1.2; the flow guide ribs are positioned opposite to the ellipsoidal protrusions.
10. The structure of claim 1, wherein: the impact plate is parallel to the impact target plate.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113251441A (en) * | 2021-06-28 | 2021-08-13 | 南京航空航天大学 | Novel many inclined hole board ellipsoid pendulum cooling structure for aeroengine |
| CN113374545A (en) * | 2021-06-27 | 2021-09-10 | 西北工业大学 | Impingement cooling structure based on array annular raised target plate |
| CN113374546A (en) * | 2021-06-27 | 2021-09-10 | 西北工业大学 | Array impact structure based on circular truncated cone and cylindrical bulge |
| CN114542194A (en) * | 2021-12-13 | 2022-05-27 | 西北工业大学 | Impact air film heat exchange structure based on conical protrusions |
| CN114658492A (en) * | 2021-12-13 | 2022-06-24 | 西北工业大学 | Impact air film heat exchange structure based on prismatic protrusions |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113374545A (en) * | 2021-06-27 | 2021-09-10 | 西北工业大学 | Impingement cooling structure based on array annular raised target plate |
| CN113374546A (en) * | 2021-06-27 | 2021-09-10 | 西北工业大学 | Array impact structure based on circular truncated cone and cylindrical bulge |
| CN113251441A (en) * | 2021-06-28 | 2021-08-13 | 南京航空航天大学 | Novel many inclined hole board ellipsoid pendulum cooling structure for aeroengine |
| CN113251441B (en) * | 2021-06-28 | 2022-03-25 | 南京航空航天大学 | Novel many inclined hole board ellipsoid pendulum cooling structure for aeroengine |
| CN114542194A (en) * | 2021-12-13 | 2022-05-27 | 西北工业大学 | Impact air film heat exchange structure based on conical protrusions |
| CN114658492A (en) * | 2021-12-13 | 2022-06-24 | 西北工业大学 | Impact air film heat exchange structure based on prismatic protrusions |
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