CN210599117U - Cooling structure for improving cooling effect of turbine - Google Patents
Cooling structure for improving cooling effect of turbine Download PDFInfo
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- CN210599117U CN210599117U CN201921606271.6U CN201921606271U CN210599117U CN 210599117 U CN210599117 U CN 210599117U CN 201921606271 U CN201921606271 U CN 201921606271U CN 210599117 U CN210599117 U CN 210599117U
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Abstract
The utility model relates to a cooling structure for improving turbine cooling effect, including setting up the air film hole on turbine blade and turbine end wall, be provided with along the upstream of mainstream flow direction protruding with the class fin type that this air film hole is corresponding in air film hole export, the protruding one side of meeting mainstream incoming flow direction of class fin type is the windward side, one side that faces away from mainstream incoming flow direction is the backpressure face, windward side and backpressure face all are the arc surface, the protruding setting of class fin type is on turbine blade surface or turbine end wall, the bellied protruding height H of class fin type is 0.5D ~ 2D, and flow direction length L is 1D ~ 2D, and span width W is 1D ~ 2D, and with the distance S between the corresponding air film hole export 0.5D ~ 5D, wherein D is the span width in the air film hole that corresponds with the class fin type arch. The fin-like protrusion in the cooling structure has the advantages of simple structure, convenience in processing, lower process requirement and production cost and capability of improving the overall effect of air film cooling.
Description
Technical Field
The utility model relates to a turbine cooling field, concretely relates to a cooling structure for improving turbine cooling effect.
Background
The film cooling is a cooling technology widely applied to blades of turbines (aeroengines, gas turbines and the like), namely, high-pressure cold air is extracted from the middle or the last stage of a compressor and is transported to a cooling channel 7 in the turbine blade, as shown in fig. 1, the cold air carries away a part of heat in the blade through enhanced convection heat exchange, a part of cold air flows out from a film hole on the turbine blade 2 or the turbine end wall 1, and the cold air can be adhered to the surface of the turbine blade 2 under the flowing action to form a cold air layer with lower temperature, so that a good high-temperature isolation effect is achieved, and the blades are not ablated by high-temperature gas.
Since the 90 s of the 20 th century, the research on film holes began to turn from circular holes to various shaped holes and various flow-improving structures (e.g., arc-shaped or square-shaped spoilers), which in some degree weakened the penetration of cooling air into the main stream and improved the coverage of the cooling air outflow. The influence of an upstream turbulence structure at the outlet of the gas film hole on the flowing vortex structure is analyzed and researched, and the fact that secondary flow kidney-shaped vortex can be formed near the outlet of the gas film hole due to the effect of the turbulence structure of the main flow gas is found, so that the jet penetration of cold air is reduced, and the cooling efficiency of the gas film hole is influenced. Therefore, different shapes of the upstream structure of the air film hole are proposed and the flow characteristics of the upstream structure are analyzed in detail. The chinese patent application No. 201721095167.6 discloses a new structure for improving cooling effect, because the structure of the cowling is added at the outlet of the film hole, the cooling air flow is more difficult to penetrate the main flow gas after passing through, thereby improving the film cooling effect. The Chinese patent with application number 201510993385.0 discloses an upstream structure for improving the external cooling effect of a component, which improves the distribution and uniformity of the spread direction of the cold air outflow of a film hole and can effectively improve the cooling efficiency of the film by adding two strip-shaped boss structures at the upstream of the film hole outlet on the wall surface of an end wall. Although the improved structures can effectively improve the air film cooling efficiency, the improved structures have high processing difficulty and high cost and are not easy to adopt in practical turbines.
SUMMERY OF THE UTILITY MODEL
In view of the above shortcomings in the prior art, the to-be-solved technical problem of the present invention is to provide a cooling structure for improving the cooling effect of turbine air film, which has a simple structure and low process requirements and cost.
In order to achieve the above object, the utility model provides a cooling structure for improving turbine cooling effect, including setting up the air film hole on turbine blade and turbine endwall, be provided with the class fin type arch corresponding with this air film hole along mainstream flow direction' S upper reaches in the air film hole export, the one side that class fin type arch is facing mainstream incoming flow direction is the windward side, the one side that faces away from mainstream incoming flow direction is the backpressure face, windward side and backpressure face all are the arc surface, the class fin type arch sets up on turbine blade surface or turbine endwall wall, the bellied protruding height H of class fin type is 0.5D ~ 2D, and flow direction length L is 1D ~ 2D, and span width W is 1D ~ 2D, and with the distance between the corresponding air film hole export 0.5D ~ 5D, wherein D is the span width with the protruding air film hole that corresponds of class fin type.
Furthermore, the diameter R1 of the windward side of the fin-like protrusion is 2D-10D, and the diameter R2 of the back pressure side is 0.1R 1-0.5R 1.
Further, the fin-like protrusions are located just upstream of the corresponding film hole outlets.
Furthermore, the fin-like protrusions are symmetrical structures in the spanwise width, and the symmetrical center planes of the fin-like protrusions are parallel to the flow direction.
Further, the air film hole is a round hole.
Further, the air film holes arranged on the end wall of the turbine are cylindrical straight holes, and the inclination angle α between the air film holes and the main flow direction is 0-90 degrees.
Further, the fin-like protrusions arranged on the turbine end wall and the turbine end wall are integrated, and smooth transition is achieved between the fin-like protrusions and the turbine end wall.
Furthermore, the fin-like protrusions arranged on the turbine blade and the turbine blade are integrated, and smooth transition is achieved between the fin-like protrusions and the turbine blade.
Further, the film holes comprise a blade pressure surface film hole, a blade suction surface film hole and an end wall film hole.
As described above, the cooling structure of the present invention has the following advantageous effects:
through set up class fin-shaped protrusion at the upper reaches of gas film hole along mainstream flow direction, the protruding specification of a dimension of class fin-shaped is confirmed according to the span-wise width D of its gas film hole that corresponds, and class fin-shaped protrusion can strengthen the disturbance that flows to the air current that is close to turbine end wall or turbine blade surface, produces reverse suppression vortex at gas film hole export and low reaches to reach and weaken the mixing effect of gas film hole export air conditioning to mainstream air current, improve the refrigerated overall effect of gas film. The utility model provides a fin-like type among the cooling structure is protruding, simple structure, convenient processing, and technological requirement and manufacturing cost are lower.
Drawings
Fig. 1 is a schematic structural diagram of the air film hole of the present invention.
Fig. 2 is a schematic view of the structural arrangement of the fin-like protrusions of the present invention.
Fig. 3 is a schematic structural layout view of the fin-like protrusions of the present invention, which is a view viewed along the spanwise direction.
Fig. 4 is a schematic view of the structural arrangement of the fin-like protrusions of the present invention, which is a view viewed along the height direction.
Fig. 5 is a schematic structural arrangement diagram of the fin-like protrusion in the present invention, which is a view viewed along the flow direction.
Description of the element reference numerals
1 turbine end wall
2 turbine blade
3 internal cooling channels of blade
4 air film hole on pressure surface of blade
5 air film hole of suction surface of blade
6 end wall air film hole
7-type fin-shaped bulge
71 windward side
72 back pressure surface
Detailed Description
The following description is provided for illustrative purposes, and other advantages and features of the present invention will become apparent to those skilled in the art from the following detailed description.
It should be understood that the drawings of the present application are only used to match the contents disclosed in the specification, so as to be known and read by those skilled in the art, and not to limit the practical limitations of the present invention, so that the present application does not have any technical significance, and any modification of the structure, change of the ratio relationship, or adjustment of the size should still fall within the scope of the present application without affecting the function and the achievable purpose of the present application. Meanwhile, the terms such as "upper", "lower", "left", "right", "middle", and the like used in the present specification are for convenience of description, and are not intended to limit the scope of the present invention, and changes or adjustments of the relative relationship thereof may be considered as the scope of the present invention without substantial changes in the technical content.
Referring to fig. 1 to 5, the present invention provides a cooling structure for improving the cooling effect of a turbine, including film holes provided on turbine blades 2 and a turbine end wall 1, a fin-like bulge 7 corresponding to the air film hole is arranged on the upstream of the outlet of the air film hole along the main flow direction, one side of the fin-like bulge 7 facing the main flow incoming flow direction is a windward side 71, one side of the fin-like bulge 7 opposite to the main flow incoming flow direction is a back pressure side 72, both the windward side 71 and the back pressure side 72 are arc surfaces, the fin-like bulge 7 is arranged on the surface of the turbine blade 2 or the wall surface of the turbine end wall 1, the bulge height H of the fin-like bulge 7 is 0.5D-2D, the flow direction length L is 1D-2D, the span direction width W is 1D-2D, and the distance S between the air film hole and the corresponding air film hole outlet is 0.5D-5D, wherein D is the spanwise width of the air film hole corresponding to the fin-like protrusion 7. The fin-like protrusion 7 is a protrusion structure with a fin-shaped outline, and the surface of the fin-like protrusion is a curved surface and is in smooth transition.
Specifically, referring to fig. 1, the turbine blade 2 is provided with a blade internal cooling passage 3, the film holes provided in the turbine blade 2 include a blade pressure surface film hole 4 and a blade suction surface film hole 5, the outlets of which are located in the blade surface, and the film hole provided in the turbine end wall 1 is an end wall film hole 6, the outlet of which is located in the wall surface of the turbine end wall 1.
The utility model discloses an among the cooling structure, the air film hole that sets up on turbine blade 2 and turbine end wall 1 can be a plurality of, and its size and dimension also can be different, and the protruding 7 size specification of class fin type is confirmed according to its air film hole that corresponds, and the shape in air film hole can adopt multiple shape, preferably is the round hole. The fin-like projections 7 on the turbine endwall 1 will now be described by way of example.
Referring to fig. 2 to 5, fig. 2 to 5 show an arrangement of fin-like protrusions 7 disposed on a turbine end wall 1 and corresponding end wall film holes 6, and fig. 2 shows a schematic view of a main flow direction, i.e., a flow direction of a main flow gas, an X-axis is a spanwise direction, a Y-axis is a spanwise direction, and a Z-axis is a vertical height direction, in this embodiment, the end wall film holes 6 are preferably cylindrical holes having a diameter D, i.e., a spanwise width D of the end wall film holes 6, and corresponding fin-like protrusions 7 have a protrusion height H of 0.5D to 2D (i.e., a height protruding from a wall surface of the turbine end wall 1 in a Z-axis direction), a flow direction length L of 1D to 2D, a spanwise width W of 1D to 2D, and a distance S from an outlet of the end wall film holes 6 of 0.5D to 5D, see fig. 3 to 5.
As a preferable design, referring to fig. 2 to 5, in the present embodiment, the diameter R1 of the windward side 71 of the fin-like protrusion 7 is 2D to 10D, and the diameter R2 of the back pressure side 72 is 0.1R1 to 0.5R1, so that the fin-like protrusion 7 has a good effect and improves the air film cooling effect. Preferably, referring to fig. 4, the profile of the fin-like protrusion 7 in the normal flow cross-section is a circular arc, and its diameter R3 is as actually confirmed to ensure a smooth transition of the fin-like protrusion 7 from the front end to the rear end. In the present invention, the normal flow cross section of the fin-like protrusion 7 is a cross section perpendicular to the flow direction.
In the present invention, the fin-like protrusion 7 is preferably a symmetrical structure symmetrical in the span-wise width, and the symmetrical center plane is parallel to the main flow direction X. The fin-like protrusions 7 are preferably located right upstream of the corresponding air film hole outlets, the fin-like protrusions 7 are right opposite to the air film holes, namely the symmetrical center planes of the fin-like protrusions are overlapped with the axes of the air film holes, and therefore the fin-like protrusions 7 can achieve the best effect. The center plane of symmetry of the fin-like projection 7 may also deviate from the axis of the film hole, i.e. the position of the fin-like projection 7 may be suitably offset directly upstream of the film hole outlet.
Referring to fig. 3, the end wall air film hole 6 is provided in the wall surface of the turbine end wall 1, the fin-like projection 7 is provided upstream of the outlet of the end wall air film hole 6, the end wall air film hole 6 is a cylindrical hole inclined in the main flow direction (X direction), the inclination angle is α mm, the cylinder diameter is 0.8mm, and the fin-like structure has no spanwise (Y direction) inclination angle, the projection height H is 1.25D is 1mm, the flow direction length L is 1.5D is 1.2mm, the spanwise width W is 1.25D is 1mm, the distance S from the air film hole outlet is 1.25D is 1mm, the wind surface 71 diameter R1 of the fin-like projection 7 is 1.5D is 4mm, the back pressure surface R2 is 0.25R 35 mm, the fin-like projection is not easily penetrated into the main flow direction, the upstream air film hole 6 is more easily, the forward flow direction of the fin-like projection 6 is more smoothly changed, and the cooling effect of the fin-like projection is more remarkably reduced, and the entire upstream air film-like projection 6 is more easily generated in the cooling area.
The fin-like projections 7 provided on the surface of the turbine blade 2 corresponding to the film holes of the turbine blade 2 are in accordance with the above-described design principle of the fin-like projections 7 provided on the turbine end wall 1, and therefore will not be described in detail.
The utility model discloses in, protruding 7 of class fin type sets up on turbine blade 2 surface or with turbine end wall 1 wall as required, preferably, the protruding 7 of class fin type that sets up on turbine end wall 1 and turbine end wall 1 formula as an organic whole, and smooth-going transition between protruding 7 of class fin type and the turbine end wall 1, the protruding 7 of class fin type that sets up on turbine blade 2 and turbine blade 2 formula as an organic whole, and smooth-going transition between protruding 7 of class fin type and the turbine blade 2.
The cooling structure of the utility model, the fin-like protrusion 7 has simple structure and lower process requirement and production cost. Through setting up class fin type arch 7, can strengthen the disturbance that flows to the mainstream that presses close to turbine end wall 1 wall and turbine blade 2 surface, produce reverse suppression vortex in film hole export and low reaches to weaken film hole export air conditioning to the mixing effect of mainstream, and make cooling gas press close to the wall better under the effect of mainstream, thereby restrain the vortex simultaneously and can increase the effect that the gas film covered to the ascending velocity component of expansion direction, finally reach the total effect that improves the gas film cooling. Fin-like protrusions 7 can be arranged on the surfaces of more cylindrical air film hole structures in high-temperature components of aero-engines and gas turbines, so that air film cooling efficiency is effectively improved, and the working reliability and the service life of components such as turbine blades 2 and cylinder bodies are improved.
To sum up, the utility model effectively overcomes various defects in the prior art and has high industrial utilization value.
The above embodiments are merely illustrative of the principles and effects of the present invention, and are not to be construed as limiting the invention. Modifications and variations can be made to the above-described embodiments by those skilled in the art without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which may be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.
Claims (9)
1. A cooling structure for improving the cooling effect of a turbine, comprising film holes provided on turbine blades (2) and a turbine end wall (1), characterized in that: the fin-like bulges (7) corresponding to the air film holes are arranged on the upstream of the outlets of the air film holes along the main flow direction, the side, facing the main flow incoming flow direction, of each fin-like bulge (7) is a windward side (71), the side, facing away from the main flow incoming flow direction, of each fin-like bulge is a back pressure side (72), the windward sides (71) and the back pressure sides (72) are both arc surfaces, the fin-like bulges (7) are arranged on the surface of the turbine blade (2) or the wall surface of the turbine end wall (1), the bulge height H of each fin-like bulge (7) is 0.5D-2D, the flow direction length L is 1D-2D, the span direction width W is 1D-2D, the distance S between each fin-like bulge and the corresponding outlet of the air film hole is 0.5D-5D, and D is the span direction width of the air film hole corresponding to the fin-like bulge (7).
2. The cooling structure according to claim 1, wherein: the diameter R1 of the windward side (71) of the fin-like protrusion (7) is 2D-10D, and the diameter R2 of the back pressure side (72) is 0.1R 1-0.5R 1.
3. The cooling structure according to claim 1, wherein: the fin-like protrusions (7) are located right upstream of the corresponding gas film hole outlets.
4. The cooling structure according to claim 1, wherein: the fin-like protrusions (7) are symmetrical structures in the spanwise width, and the symmetrical center planes of the fin-like protrusions are parallel to the flow direction.
5. The cooling structure according to claim 1, wherein: the air film hole is a round hole.
6. The cooling structure according to claim 1, wherein the film holes provided in the turbine end wall (1) are cylindrical straight holes and have an inclination angle α of 0-90 ° with respect to the main flow direction.
7. The cooling structure according to claim 1, wherein: the fin-like protrusion (7) arranged on the turbine end wall (1) and the turbine end wall (1) are integrated, and smooth transition is realized between the fin-like protrusion (7) and the turbine end wall (1).
8. The cooling structure according to claim 1, wherein: the fin-like protrusion (7) arranged on the turbine blade (2) and the turbine blade (2) are integrated, and smooth transition is realized between the fin-like protrusion (7) and the turbine blade (2).
9. The cooling structure according to claim 1, wherein: the air film holes comprise a blade pressure surface air film hole (4), a blade suction surface air film hole (4) and an end wall air film hole (6).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921606271.6U CN210599117U (en) | 2019-09-25 | 2019-09-25 | Cooling structure for improving cooling effect of turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921606271.6U CN210599117U (en) | 2019-09-25 | 2019-09-25 | Cooling structure for improving cooling effect of turbine |
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| CN210599117U true CN210599117U (en) | 2020-05-22 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110529191A (en) * | 2019-09-25 | 2019-12-03 | 上海电气燃气轮机有限公司 | It is a kind of for improving the cooling structure of turbine cooling effect |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110529191A (en) * | 2019-09-25 | 2019-12-03 | 上海电气燃气轮机有限公司 | It is a kind of for improving the cooling structure of turbine cooling effect |
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