CN211008774U - Novel turbine blade rotational flow cooling structure - Google Patents
Novel turbine blade rotational flow cooling structure Download PDFInfo
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- CN211008774U CN211008774U CN201922198930.3U CN201922198930U CN211008774U CN 211008774 U CN211008774 U CN 211008774U CN 201922198930 U CN201922198930 U CN 201922198930U CN 211008774 U CN211008774 U CN 211008774U
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Abstract
The utility model discloses a novel turbine blade rotational flow cooling structure, which comprises a rotational flow cooling cavity, a jet hole and the like; the top of the rotational flow cooling cavity is of a plane structure, and the target surface is of a curved surface structure; the jet holes are arranged on one side of the top surface of the cyclone cooling cavity at equal intervals, the outflow grooves are arranged on the other side of the top surface of the cyclone cooling cavity opposite to the jet holes at equal intervals, and the outflow grooves and the jet holes are arranged in a staggered manner; the ball socket structures and the air film holes are arranged on the target surface of the cyclone cooling cavity; when the device works, a cooling working medium is injected from the jet hole to enter the rotational flow cooling cavity, flows along one side of a target surface where the jet hole is located, forms a transverse large-scale vortex under the action of the bent target surface, carries out strong heat exchange with the target surface, generates flow separation and reattachment when flowing through the ball socket structure, enhances the local heat transfer of the ball socket, obtains higher fluid turbulence energy under the suction action of the air film hole, eliminates the local heat transfer deterioration phenomenon, and discharges the cooling working medium after heat exchange through the outflow groove adjacent to the jet hole.
Description
Technical Field
The utility model belongs to the technical field of turbine blade cooling, in particular to novel turbine blade whirl cooling structure.
Background
As one of the core components of the gas turbine, the turbine is close to the downstream of the combustion chamber and is continuously flushed by high-temperature and high-pressure gas in the operation process, the working environment is extremely severe, and when the turbine is designed, besides the consideration of pneumatic factors, an efficient cooling technology is also needed to reduce the temperature of the turbine to be within a material allowable range so as to ensure the safe and stable operation of the gas turbine. The high temperature combustion gases output from the combustor directly impinge on the turbine blade leading edge as they enter the cascade channels, and therefore this region, particularly the first stage guide vane leading edge region, has an extremely high thermal load and is a significant concern in blade cooling design.
In order to improve the cooling performance of the leading edge of the turbine blade, an impingement cooling mode with the highest heat transfer enhancement effect is often adopted, a plurality of jet holes are formed in the surface of an inner liner plate of a leading edge area, cooling air supplied from a blade root impacts a curved target surface of the leading edge through the jet holes, strong heat and mass exchange is generated in the area near an impact point, and the cooling air absorbs heat from the target surface, so that the temperature of the inner surface and the outer surface of the leading edge is effectively reduced.
With the development of gas turbines, according to the intrinsic law of the brayton cycle, the increase in power and efficiency requires the turbine inlet temperature to rise continuously, which brings great challenges to the cooling design of the turbine components, especially the cooling design of the leading edge of the first stage guide vane of the turbine. Because the traditional impingement cooling can not deal with the rapid rise of the thermal load of the front edge of the blade under many conditions, related experts and designers propose a rotational flow cooling structure, namely, jet holes are arranged on one side area of the top surface, and a transverse large-scale vortex system is formed along an arc target surface after a cooling working medium enters a channel, so that the turbulent kinetic energy of the fluid is enhanced, and the cooling performance obviously superior to that of the traditional impingement structure is obtained.
However, the adoption of the rotational flow cooling structure can cause local heat transfer deterioration among the jet holes, aggravate the nonuniformity of the temperature distribution of the front edge of the blade, and meanwhile, the cross flow formed by the aggregation of the upstream rotational flow working medium can obviously weaken the enhanced heat transfer effect of the downstream jet flow, so that the potential cooling performance of the rotational flow structure cannot be fully exerted. Therefore, there is a need for a new turbine blade cyclone cooling structure that achieves better cyclone cooling performance by overcoming the above problems, thereby achieving efficient thermal protection of the leading edge of the turbine blade.
SUMMERY OF THE UTILITY MODEL
In order to solve the problems, the utility model provides a novel turbine blade rotational flow cooling structure, which eliminates the influence of the cross flow through a distributed outflow groove, avoids the rapid attenuation of the rotational flow heat transfer performance in the flow direction, improves the overall heat transfer level and reduces the pressure loss; the ball socket and the air film hole combined structure arranged on the target surface strengthens local heat transfer, obviously reduces the heat transfer deterioration area of the traditional rotational flow target surface, improves the heat transfer performance and simultaneously reduces the temperature difference of the target surface, thereby improving the overall cooling performance.
The utility model discloses a following technical scheme realizes:
a novel turbine blade rotational flow cooling structure comprises a rotational flow cooling cavity, a jet hole, a flow outlet groove, a ball socket structure and a gas film hole; the top of the rotational flow cooling cavity is of a plane structure, and the target surface is of a curved surface structure; the jet holes are arranged on one side of the top surface of the cyclone cooling cavity at equal intervals, the outflow grooves are arranged on the other side of the top surface of the cyclone cooling cavity opposite to the jet holes at equal intervals, and the outflow grooves and the jet holes are arranged in a staggered manner; the ball socket structures and the air film holes are arranged on the target surface of the cyclone cooling cavity;
when the device works, a cooling working medium is injected from the jet hole to enter the rotational flow cooling cavity, flows along one side of a target surface where the jet hole is located, forms a transverse large-scale vortex under the action of the bent target surface, carries out strong heat exchange with the target surface, generates flow separation and reattachment when flowing through the ball socket structure, enhances the local heat transfer of the ball socket, obtains higher fluid turbulence energy under the suction action of the air film hole, eliminates the local heat transfer deterioration phenomenon, and discharges the cooling working medium after heat exchange through the outflow groove adjacent to the jet hole.
The further improvement of the utility model lies in that the target surface shape of the rotational flow cooling cavity adopts a circular arc, an elliptic arc, a parabola or a hyperbola.
The utility model discloses further improvement lies in, the jet hole shape is rectangle, straight notch shape, circular and oval, and the jet hole arranges that the ratio S/w of interval and jet hole width is at 2 ~ 5 within ranges, and the ratio w/t of jet hole width and thickness is at 1 ~ 6 within ranges.
The utility model discloses further improvement lies in, the opposite side that the groove of effluenting arranged between adjacent jet hole, and its shape is rectangle, straight flute kou shape, circular and oval, and structural dimension and arrangement are the same with the jet hole.
The utility model discloses further improvement lies in, the ball socket structure arranges the target surface region between adjacent efflux hole, the degree of depth and the diameter ratio e/D of ball socket structure (4)dIn the range of 0.1-0.3, the target surface is uniformly arranged in the circumferential direction, and the number of the circumferential arrangement is 1-6.
The utility model discloses further improvement lies in, and the target surface region between adjacent jet hole is arranged to the air film hole, and its cross sectional shape is circular or oval, and the air film hole is arranged angle α and is changed at 0 ~ 180 within range, and the circumference in air film hole is arranged quantity and is 1 ~ 4.
The utility model discloses further improvement lies in, and the air film hole is arranged at ball and socket structure surface, or arranges the target surface region near ball and socket structure.
The utility model discloses at least, following profitable technological effect has:
the utility model provides a pair of turbine blade whirl cooling structure, it has introduced a plurality of distributed outflow grooves, and the cooling working medium that the jet orifice kicked into the passageway is discharged at these outflow grooves of accessible after accomplishing the heat transfer, can not form the cross flow of ubiquitous among the traditional whirl passageway and flow, consequently can eliminate the crossing flow and to the weakening effect of low reaches heat transfer for strike the whirl and can radially keep better intensive heat transfer effect, thereby show the whole heat transfer performance who improves the target surface.
Furthermore, the flexibly variable target surface shape can adapt to different blade leading edge molded lines, the height adaptation with the turbine blade leading edge structure is realized, the shapes and the structural sizes of the jet hole and the flow outlet groove can be selected according to the heat load on the leading edge when the turbine operates, and the adaptability and the cooling performance of the novel rotational flow structure are improved to the maximum extent;
furthermore, the ball socket structure has the excellent characteristics of high heat transfer and low flow resistance, only generates small resistance loss while enhancing heat transfer, can increase the heat transfer area, and can realize local flow heat transfer control by arranging the ball socket structure on the target surface of the rotational flow cooling cavity, thereby eliminating heat transfer deterioration areas and realizing more uniform temperature distribution while improving the heat transfer level;
furthermore, the pumping action of the gas film holes can enhance the turbulent kinetic energy of the fluid in the area nearby the gas film holes, destroy the flow boundary layer and promote the heat and mass exchange nearby the wall surface, in addition, the outflow of the gas film holes can also form a protective gas film on the outer surface of the blade, the heat exchange between high-temperature gas and the blade is weakened, and efficient internal and external coupling cooling is realized.
According to the above, the utility model discloses a novel turbine blade whirl cooling structure has been established, has eliminated the negative influence of crossing current to heat transfer in the traditional whirl passageway through the distributing type groove of effluenting for high heat transfer level can be kept at whole passageway, and the ball and socket structure and the arrangement of air film hole have realized local flow control simultaneously, can obtain more even temperature distribution when promoting heat transfer performance, thereby realize more excellent comprehensive cooling performance.
Drawings
FIG. 1 is a three-dimensional view of a turbine blade cyclonic cooling structure;
FIG. 2 is a schematic view of the arrangement of fluidic orifices and outflow channels on the top surface of a channel;
FIG. 3 is a schematic view of the orifice and the outflow groove shape, wherein FIG. 3(a) is a rectangular orifice/outflow groove, FIG. 3(b) is a straight notch-shaped orifice/outflow groove, FIG. 3(c) is a circular orifice/outflow groove, and FIG. 3(d) is an elliptical orifice/outflow groove;
FIG. 4 is a schematic view of a ball and socket structure and an arrangement of air film holes in a localized area of the target surface;
FIG. 5 is a cross-sectional schematic view of a ball and socket arrangement;
FIG. 6 is a schematic cross-sectional view of the structure and arrangement of the gas film holes.
Description of reference numerals:
1 is the whirl cooling chamber, 2 is the jet orifice, 3 is the play chute, 4 is the ball and socket structure, 5 is the air film hole, 231 is rectangle jet orifice/play chute, 232 is straight notch shape jet orifice/play chute, 233 is circular jet orifice/play chute, 234 is oval jet orifice/play chute.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
Referring to fig. 1 and 2, the utility model provides a pair of novel turbine blade whirl cooling structure, including whirl cooling chamber 1, a plurality of efflux hole 2, a plurality of groove 3, a plurality of ball socket structure 4 and a plurality of air film hole 5 of effluenting. The top of the cyclone cooling cavity 1 is of a plane structure, and the target surface is of a curved surface structure; the jet holes 2 are arranged on one side of the top surface of the cyclone cooling cavity 1 at equal intervals, the outflow grooves 3 are arranged on the other side of the top surface of the cyclone cooling cavity 1 opposite to the jet holes 2 at equal intervals, and the outflow grooves 3 and the jet holes 2 are arranged in a staggered manner; a plurality of ball and socket structures 4 and air film holes 5 are arranged on the target surface of the cyclone cooling cavity 1. The whole flow heat transfer process comprises the following steps: the cooling working medium is injected from the jet hole 2 to enter the rotational flow cooling cavity 1, flows along one side of a target surface where the jet hole 2 is located, forms a transverse large-scale vortex under the action of a bent target surface, carries out strong heat exchange with the target surface, generates flow separation and reattachment when flowing through the ball socket structure 4, enhances the local heat transfer of the ball socket, obtains higher fluid turbulence kinetic energy under the suction action of the air film hole 5, eliminates the local heat transfer deterioration phenomenon, and discharges the cooling working medium after heat exchange through the outflow groove 3 adjacent to the jet hole 2.
The target surface shape may take the form of a circular arc, elliptical arc, parabolic curve, hyperbolic curve, or other curve that approximates the configuration of the leading edge of the turbine blade.
Referring to fig. 2 and 3, the shape of the jet hole 2 may be rectangular, straight notch, circular, oval, etc., the S/w ratio of the arrangement pitch of the jet holes 2 to the width of the jet hole 2 is preferably in the range of 2 to 5, and the w/t ratio of the width to the thickness of the jet hole 2 is preferably in the range of 1 to 6. The outflow groove 3 is arranged on the other side of the area between the adjacent jet holes 2, the shape of the outflow groove can be rectangular, straight notch-shaped, circular, oval and the like, and the structural size and the arrangement mode of the outflow groove are the same as those of the jet holes 2. Correspondingly, the present invention has a rectangular jet hole/outflow groove 231, a straight notch-shaped jet hole/outflow groove 232, a circular jet hole/outflow groove 233, and an oval jet hole/outflow groove 234.
Referring to fig. 1, 4, 5 and 6, a ball and socket structure 4 is disposed in a target surface region between adjacent jet holes 2, the depth to diameter ratio e/D of the ball and socket structure 4dThe jet holes 5 are preferably arranged in the range of 0.1-0.3 and are uniformly arranged in the circumferential direction of the target surface, the circumferential arrangement number is preferably 1-6, the cross section of each air film hole 5 in the target surface area between the adjacent jet holes 2 can be circular or elliptical, the arrangement angle α of the air film holes 5 can be changed in the range of 0-180 degrees, the circumferential arrangement number of the air film holes 5 is preferably 1-4, and the air film holes 5 can be arranged on the surface of the ball socket structure 4 or in the target surface area near the ball socket.
Claims (7)
1. A novel turbine blade rotational flow cooling structure is characterized by comprising a rotational flow cooling cavity (1), a jet hole (2), an outflow groove (3), a ball socket structure (4) and an air film hole (5); wherein the content of the first and second substances,
the top of the cyclone cooling cavity (1) is of a plane structure, and the target surface is of a curved surface structure; the jet holes (2) are arranged on one side of the top surface of the cyclone cooling cavity (1) at equal intervals, the outflow grooves (3) are arranged on the other side of the top surface of the cyclone cooling cavity (1) opposite to the jet holes (2) at equal intervals, and the outflow grooves (3) and the jet holes (2) are arranged in a staggered manner; the ball socket structures (4) and the air film holes (5) are arranged on the target surface of the cyclone cooling cavity (1).
2. The novel turbine blade cyclone cooling structure according to claim 1, wherein the target surface shape of the cyclone cooling cavity (1) is a circular arc, an elliptical arc, a parabola or a hyperbola.
3. The novel turbine blade rotational flow cooling structure as claimed in claim 1, wherein the jet holes (2) are rectangular, straight notch, circular and oval in shape, the S/w ratio of the arrangement pitch of the jet holes (2) to the width of the jet holes is within the range of 2 to 5, and the w/t ratio of the width of the jet holes to the thickness is within the range of 1 to 6.
4. The new turbine blade cyclone cooling structure according to claim 3, characterized in that the outflow slots (3) are arranged on the other side of the area between the adjacent jet holes (2), and have the shape of rectangle, straight slot, circle and ellipse, and the structure size and arrangement are the same as the jet holes (2).
5. The new turbine blade cyclone cooling structure according to claim 1, characterized in that the ball and socket structure (4) is arranged in the target surface area between adjacent jet holes (2), the depth to diameter ratio e/D of the ball and socket structure (4)dIn the range of 0.1-0.3, the target surface is uniformly arranged in the circumferential direction, and the number of the circumferential arrangement is 1-6.
6. The novel turbine blade rotational flow cooling structure as claimed in claim 1, wherein the gas film holes (5) are arranged in the target surface area between the adjacent jet holes (2), the cross section of the gas film holes is circular or elliptical, the arrangement angle α of the gas film holes (5) is changed within the range of 0-180 degrees, and the circumferential arrangement number of the gas film holes (5) is 1-4.
7. The novel turbine blade cyclone cooling structure according to claim 1, characterized in that the film holes (5) are arranged on the surface of the ball-and-socket structure (4) or in the target surface area near the ball-and-socket structure (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922198930.3U CN211008774U (en) | 2019-12-10 | 2019-12-10 | Novel turbine blade rotational flow cooling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922198930.3U CN211008774U (en) | 2019-12-10 | 2019-12-10 | Novel turbine blade rotational flow cooling structure |
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| CN211008774U true CN211008774U (en) | 2020-07-14 |
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| CN201922198930.3U Active CN211008774U (en) | 2019-12-10 | 2019-12-10 | Novel turbine blade rotational flow cooling structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113266427A (en) * | 2021-04-28 | 2021-08-17 | 西安交通大学 | Inside compound cooling structure of turbine movable vane |
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2019
- 2019-12-10 CN CN201922198930.3U patent/CN211008774U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113266427A (en) * | 2021-04-28 | 2021-08-17 | 西安交通大学 | Inside compound cooling structure of turbine movable vane |
| CN113266427B (en) * | 2021-04-28 | 2022-07-12 | 西安交通大学 | Inside compound cooling structure of turbine movable vane |
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