CN114278390A - Turbine stator blade, gas turbine and aircraft engine - Google Patents
Turbine stator blade, gas turbine and aircraft engine Download PDFInfo
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- CN114278390A CN114278390A CN202111438025.6A CN202111438025A CN114278390A CN 114278390 A CN114278390 A CN 114278390A CN 202111438025 A CN202111438025 A CN 202111438025A CN 114278390 A CN114278390 A CN 114278390A
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- 238000001816 cooling Methods 0.000 description 26
- 239000000112 cooling gas Substances 0.000 description 23
- 230000000694 effects Effects 0.000 description 14
- 239000007789 gas Substances 0.000 description 11
- 101100334009 Caenorhabditis elegans rib-2 gene Proteins 0.000 description 7
- 230000001965 increasing effect Effects 0.000 description 5
- 230000002708 enhancing effect Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000002035 prolonged effect Effects 0.000 description 3
- 238000005266 casting Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000013021 overheating Methods 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003110 molding sand Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The invention discloses a turbine stationary blade, a gas turbine and an aeroengine, wherein the turbine stationary blade comprises: the stator blade comprises a stator blade body, a middle wall, a plurality of first column ribs, a plurality of second column ribs and a plurality of third column ribs, wherein the stator blade body comprises a suction wall, a pressure wall and a cavity enclosed by the suction wall and the pressure wall, the cavity comprises a tail edge area, the tail edge area comprises a first tail edge area and a second tail edge area which are communicated with each other, the first tail edge area is adjacent to the tail end of the stator blade body along the extending direction of the stator blade body, and the second tail edge area is far away from the tail end of the stator blade body along the extending direction of the stator blade body; the first column ribs are arranged in the first tail edge area at intervals and uniformly; the middle wall is arranged in the second tail edge area; a plurality of second post rib intervals and establish at the second trailing edge district evenly, and a plurality of third post rib intervals and establish at the second trailing edge district evenly, and second post rib connects between suction wall and middle wall, and third post rib connects between pressure wall and middle wall. The turbine stator blade has the advantage of long service life.
Description
Technical Field
The invention relates to the technical field of power machinery, in particular to a turbine stator blade, a gas turbine and an aircraft engine.
Background
Since the turbine vane is one of important components in a gas turbine, the turbine vane generally operates at a high temperature, and thus, in order to ensure that the turbine vane is not damaged by the high temperature, a cooling structure is required to be provided in the turbine vane, thereby reducing the temperature of the turbine vane. In the related art, the trailing edge portion of the turbine stationary blade is cooled by providing the plurality of column ribs in the trailing edge region, and the middle chord portion of the turbine stationary blade is cooled by providing the impact bushing in the middle chord region, but the cooling structure cannot be provided in the position adjacent to the middle chord region in the trailing edge region, and the temperature of the region is further increased compared with other regions, so that the turbine stationary blade portion in the region is easily damaged by ablation, and the service life of the turbine stationary blade is reduced.
Disclosure of Invention
The present invention is based on the discovery and recognition by the inventors of the following facts and problems:
a related art turbine vane includes a body and a cavity defined by the body, the cavity including a leading edge region, a trailing edge region and a mid-chord region, the trailing edge region including a first trailing edge region and a second trailing edge region, wherein the second trailing edge region is located between the mid-chord region and the first trailing edge region. The leading edge region cools the leading edge part leading edge of the turbine stationary blade in an impingement cooling mode, the first trailing edge region carries out column rib cooling on the trailing edge part of the turbine stationary blade by being provided with a plurality of column ribs, and the middle chord region carries out column rib cooling on the trailing edge part of the turbine stationary blade by an impingement bushing. However, the length of the column rib is large when the column rib is arranged in the second trailing edge area, the difficulty of manufacturing the column rib in the turbine stationary blade is high, the column rib is not easy to achieve, the thickness of the impact bushing is larger than that of the second trailing edge area of the turbine stationary blade, and the impact bushing cannot be installed in the area.
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art. To this end, embodiments of the invention propose a turbine vane having the advantage of a long service life.
A turbine vane according to an embodiment of the present invention includes: the stator blade body comprises a suction wall, a pressure wall and a cavity enclosed by the suction wall and the pressure wall, the cavity comprises a tail edge area, the tail edge area comprises a first tail edge area and a second tail edge area which are communicated with each other, the first tail edge area is adjacent to the tail end of the stator blade body along the extending direction of the stator blade body, and the second tail edge area is far away from the tail end of the stator blade body along the extending direction of the stator blade body; a plurality of first column ribs spaced apart and uniformly disposed within the first trailing edge region, the first column ribs connected between the suction wall and the pressure wall; an intermediate wall disposed within the second trailing edge region; and a plurality of second column ribs and a plurality of third column ribs, a plurality of second column ribs are arranged at intervals and uniformly in the second trailing edge area, a plurality of third column ribs are arranged at intervals and uniformly in the second trailing edge area, the second column ribs are connected between the suction wall and the intermediate wall, and the third column ribs are connected between the pressure wall and the intermediate wall.
According to the turbine stationary blade provided by the embodiment of the invention, the second column ribs, the third column ribs and the middle wall are arranged in the second tail edge area, so that parts of the suction wall and the pressure wall corresponding to the second tail edge area can be cooled by a column rib cooling method, and the parts of the suction wall and the pressure wall corresponding to the second tail edge area are prevented from being damaged by overheating, so that the service life of the turbine stationary blade provided by the embodiment of the invention is prolonged.
Therefore, the turbine stator blade provided by the embodiment of the invention has the advantage of long service life.
In some embodiments, the plurality of second column ribs includes at least one first rib group including a plurality of second column ribs, the plurality of second column ribs in the first rib group being spaced apart in a width direction of the vane body, the plurality of third column ribs includes at least one second rib group including a plurality of third column ribs, the plurality of third column ribs in the second rib group being spaced apart in the width direction of the vane body.
In some embodiments, the first rib group is plural, a plurality of the first rib groups are spaced apart in the extending direction of the vane body, the second rib group is plural, and a plurality of the second rib groups are spaced apart in the extending direction of the vane body.
In some embodiments, a plurality of the second column ribs and a plurality of the third column ribs are symmetrically provided on both sides of the intermediate wall.
In some embodiments, a dimension of the intermediate wall in a width direction of the vane body is gradually reduced or constant in a direction adjacent to the trailing end of the vane body.
In some embodiments, the intermediate wall includes a first wall surface located on one side in a thickness direction of the intermediate wall and a second wall surface located on the other side in the thickness direction of the intermediate wall, the first wall surface having the same shape as an inner wall surface of the suction wall, and the second wall surface having the same shape as an inner wall surface of the pressure wall.
In some embodiments, the cavity includes a leading edge region, a mid-chord region, and the trailing edge region, the mid-chord region being located between the leading edge region and the trailing edge region.
In some embodiments, the tail end of the stator blade body is provided with a split slot, and the split slot is communicated with the first tail edge area and the outside.
A gas turbine according to an embodiment of the invention comprises a turbine vane according to any of the embodiments described above.
An aircraft engine according to an embodiment of the invention comprises a turbine vane as described in any of the embodiments above.
Drawings
FIG. 1 is a schematic structural view of a turbine vane of an embodiment of the present invention.
FIG. 2 is a schematic structural view of a turbine vane of an embodiment of the present invention.
Reference numerals:
a stationary blade body 1; a suction wall 11; a pressure wall 12; a cavity 13; a trailing edge region 131; a first trailing edge region 1311; a second trailing edge region 1312; a split seam 132; a mid-chord zone 133; a leading edge 134;
a first column rib 2; an intermediate wall 3; a second column rib 4; a third pillar rib 5; impacting the bushing 6.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. 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.
A turbine vane of an embodiment of the present invention is described below with reference to the accompanying drawings.
As shown in fig. 1 to 2, the turbine vane of the embodiment of the invention includes a vane body 1, a plurality of first column ribs 2, an intermediate wall 3, a plurality of second column ribs 4, and a plurality of third column ribs 5.
The vane body 1 includes a suction wall 11, a pressure wall 12, and a cavity 13 enclosed by the suction wall 11 and the pressure wall 12, the cavity 13 includes a trailing edge region 131, the trailing edge region 131 includes a first trailing edge region 1311 and a second trailing edge region 131 that are communicated with each other, the first trailing edge region 1311 is adjacent to a trailing end of the vane body 1 (such as a right end of the vane body 1 in fig. 1) in an extending direction of the vane body 1, the second trailing edge region 1312 is distant from the trailing end of the vane body 1 in the extending direction of the vane body 1, specifically, the first trailing edge region 1311 is located on a right side of the trailing edge region 131, and the second trailing edge region 1312 is located on a left side of the trailing edge region 131.
The plurality of first column ribs 2 are arranged in the first trailing edge area 1311 at intervals and uniformly, the first column ribs 2 are connected between the suction wall 11 and the pressure wall 12, and specifically, the plurality of first column ribs 2 are arranged in the first trailing edge area 1311 in an array manner.
It can be understood that the first trailing edge region 1311 includes first cold air passages formed between the circumferential surface of the adjacent first column rib 2, the lower surface of the suction wall 11 and the upper surface of the pressure wall 12, and the first cold air passages have a guiding effect on the cooling air passing through the first trailing edge region 1311, thereby enhancing the convection effect of the cooling air in the first trailing edge region 1311, and form turbulence at the trailing edge of the first column rib 2 after the cooling air passes through the first column rib 2, so that the cooling air can sufficiently exchange heat with the suction wall 11 and the pressure wall 12 in the first trailing edge region 1311, thereby enhancing the cooling effect of the cooling air on the suction wall 11 and the pressure wall 12.
In addition, the first column rib 2 is connected between the suction wall 11 and the pressure wall 12, and the heat absorbed by the suction wall 11 and the pressure wall 12 can be conducted to the first column rib 2, so that the heat dissipation area of the suction wall 11 and the pressure wall 12 is increased, that is, the contact area between the suction wall 11 and the pressure wall 12 and the cooling gas is increased by arranging the first column rib 2 between the suction wall 11 and the pressure wall 12, and thus the heat exchange effect between the cooling gas and the suction wall 11 and the pressure wall 12 is enhanced.
The intermediate wall 3 is provided in the second trailing edge region 1312, a plurality of second ribs 4 are provided at the second trailing edge region 1312 at intervals and uniformly, a plurality of third ribs 5 are provided at the second trailing edge region 1312 at intervals and uniformly, the second ribs 4 are connected between the suction wall 11 and the intermediate wall 3, and the third ribs 5 are connected between the pressure wall 12 and the intermediate wall 3.
Specifically, the second trailing edge region 1312 includes second and third cooling channels, a plurality of second ribs 4 are arranged in an array within the second trailing edge region 1312, and one end of each of the plurality of second ribs 4 is connected to the suction wall 11, and the other end of each of the plurality of second ribs 4 is connected to the intermediate wall 3, wherein the second cooling channel is formed between the circumferential surface of the adjacent second ribs 4, the lower surface of the suction wall 11, and the upper surface of the pressure wall 12. A plurality of third ribs 5 are arranged in an array within the second trailing edge region 1312, and one end of each of the plurality of third ribs 5 is connected to the pressure wall 12 and the other end of each of the plurality of second ribs 4 is connected to the intermediate wall 3, wherein third cooling passages are formed between the circumferential surfaces of the adjacent second ribs 4, the lower surface of the suction wall 11, and the upper surface of the pressure wall 12.
It will be understood that the second trailing edge region 1312 includes a second cold air channel and a third cold air channel, and the second cold air channel and the third cold air channel have a guiding effect on the cooling gas passing through the second trailing edge region 1312, so that the convection effect of the cooling gas in the second trailing edge region 1312 is enhanced, and the cooling gas forms a turbulent flow at the trailing edge of the second column rib 4 after passing through the second column rib 4, and forms a turbulent flow at the trailing edge of the third column rib 5 after passing through the third column rib 5, so that the flow mixing effect of the cooling gas in the second trailing edge region 1312 is enhanced, so that the cooling gas can sufficiently exchange heat with the suction wall 11 and the pressure wall 12 in the second trailing edge region 1312, and thus the cooling effect of the cooling gas on the suction wall 11 and the pressure wall 12 is enhanced.
In addition, the second column rib 4, the third column rib 5 and the intermediate wall 3 are connected between the suction wall 11 and the pressure wall 12, and heat absorbed by the suction wall 11 and the pressure wall 12 can be conducted to the second column rib 4, the third column rib 5 and the intermediate wall 3, thereby increasing the contact area of the suction wall 11 and the pressure wall 12 with the cooling gas, and thus enhancing the heat exchange effect of the cooling gas with the suction wall 11 and the pressure wall 12.
The turbine vane according to the embodiment of the present invention reduces the length of the column rib disposed in the second trailing edge region 1312 by disposing the intermediate wall 3 between the second column rib 4 and the third column rib 5 in the second trailing edge region 1312, so that the column rib in the second trailing edge region 1312 is easy to manufacture, and further, the suction wall 11 portion and the pressure wall 12 portion corresponding to the second trailing edge region 1312 can be cooled by a rib column cooling method, and thus, it is ensured that the local temperatures of the second trailing edge region 1312 portion corresponding to the suction wall 11 and the second trailing edge region 1312 portion corresponding to the pressure wall 12 are not too high to be damaged, and therefore, the service life of the turbine vane according to the embodiment of the present invention is prolonged.
In addition, in the turbine stationary blade according to the embodiment of the present invention, the plurality of second ribs 4, the plurality of third ribs 5, and the intermediate wall 3 are provided in the second trailing edge region 1312, so that the cross-sectional area of the flow passage through which the cooling gas passes is reduced, the pressure of the cooling gas entering the second trailing edge region 1312 is increased, and the amount of the cooling gas used is reduced while the cooling gas maintains the original flow velocity, and therefore, the turbine stationary blade according to the embodiment of the present invention has high cooling efficiency.
Therefore, the turbine stator blade provided by the embodiment of the invention has the advantages of long service life and high cooling efficiency.
In some embodiments, as shown in fig. 2, the plurality of second column ribs 4 includes at least one first rib group including a plurality of second column ribs 4, the plurality of second column ribs 4 in the first rib group are arranged at intervals in the width direction of the vane body 1 (the forward-backward direction in fig. 1), the plurality of third column ribs 5 includes at least one second rib group including a plurality of third column ribs 5, and the plurality of third column ribs 5 in the second rib group are arranged at intervals in the width direction of the vane body 1.
It will be appreciated that the cooling gas after passing through the second or third ribs 4, 5 forms turbulence at the trailing edge of the second or third ribs 4, 5, so that the cooling gas can exchange heat with the suction wall 11 and the pressure wall 12 sufficiently in this region, and a plurality of second and third ribs 4, 5 are provided in the width direction in the second trailing edge region 1312, thereby ensuring that any part of the suction wall 11 and the pressure wall 12 in the width direction can be cooled sufficiently, avoiding that the suction wall 11 and the pressure wall 12 are locally overheated and ablated, and thus improving the service life of the turbine vane of the embodiment of the present invention.
In some embodiments, as shown in fig. 1 and 2, the first rib group is plural, the plural first rib groups are arranged at intervals in the extending direction of the vane body 1 (the left-right direction in fig. 1), the second rib group is plural, and the plural second rib groups are arranged at intervals in the extending direction of the vane body 1.
It can be understood that the cooling gas after passing through the second or third column ribs 4 or 5 forms turbulence at the trailing edge of the second or third column ribs 4 or 5, so that the cooling gas can exchange heat with the suction wall 11 and the pressure wall 12 sufficiently in this region, and a plurality of second and third column ribs 4 and 5 are provided in the second trailing edge region 1312 in the extending direction of the vane body 1, thereby ensuring that any part of the suction wall 11 and the pressure wall 12 in the extending direction of the vane body 1 can be cooled sufficiently, avoiding that the part of the suction wall 11 and the pressure wall 12 in the extending direction of the vane body 1 is overheated locally to be ablated, and thus improving the service life of the turbine vane of the embodiment of the invention.
In addition, in the turbine vane according to the embodiment of the present invention, by providing the plurality of second and third column ribs 4 and 5 in the second trailing edge region 1312, the suction wall 11 and the pressure wall 12 are supported by the second and third column ribs 4 and 5, and thus the structure of the turbine vane according to the embodiment of the present invention is more stable.
In some embodiments, the second and third column ribs 4 and 5 are symmetrically disposed on both sides of the intermediate wall 3, that is, the second and third column ribs 4 and 5 correspond to each other in the up-down direction.
It can be understood that the plurality of second column ribs 4 and the plurality of third column ribs 5 are symmetrically provided on both sides of the intermediate wall 3, that is, the number of the second column ribs 4 connected to the suction wall 11 and the number of the third column ribs 5 connected to the pressure wall 12 are equal and the arrangement positions on the intermediate wall 3 are in one-to-one correspondence in the up-down direction, so that both the suction wall 11 and the pressure wall 12 can be uniformly and sufficiently cooled, and thus the cooling effect is improved.
In some embodiments, the dimension of the interwall 3 in the width direction of the vane body 1 is gradually reduced or constant in a direction adjacent to the trailing end of the vane body 1, that is, the outer contour of the cross section of the interwall 3 is substantially rectangular or trapezoidal.
That is, the outer contour of the cross section of the intermediate wall 3 should be located within the outer contour of the cross section of the pressure wall 12, and the intermediate wall 3 is located between at least a part of the suction wall 11 and at least a part of the pressure wall 12 in the vertical direction, so as to ensure that the intermediate wall 3 does not affect the turbine stator blade in the operating state of the turbine stator blade according to the embodiment of the present invention.
In some embodiments, the intermediate wall 3 includes a first wall surface located on one side (an upper side in fig. 1) in the thickness direction of the intermediate wall 3 and a second wall surface located on the other side (a lower side in fig. 1) in the thickness direction of the intermediate wall 3, the first wall surface having the same shape as the inner wall surface of the suction wall 11, and the second wall surface having the same shape as the inner wall surface of the pressure wall 12.
It can be understood that the shape of the first wall surface is the same as the shape of the inner wall surface of the suction wall 11, the distance between the first wall surface and the inner wall surface of the suction wall 11 in the vertical direction is not changed, the shape of the second wall surface is the same as the shape of the inner wall surface of the pressure wall 12, and the distance between the second wall surface and the inner wall surface of the pressure wall 11 in the vertical direction is not changed, that is, the sizes of the second cooling channel and the third cooling channel in the vertical direction are not changed, so that the convection effect of the cooling gas is ensured, the cooling gas after heat exchange can be smoothly discharged to the outside, and the cooling effect is improved.
In other embodiments, the first wall and the second wall of the intermediate wall are both flat or sloped.
It can be understood that the intermediate wall 3, the suction wall 11 and the pressure wall 12 are integrally formed by casting, and both the upper surface and the lower surface of the intermediate wall 3 are flat or inclined surfaces during casting, so that molding sand easily enters the gap between the intermediate wall 3 and the suction wall 11 and the gap between the intermediate wall 3 and the pressure wall 12, thereby reducing the difficulty in manufacturing the turbine stationary blade according to the embodiment of the present invention.
In some embodiments, as shown in fig. 1, the cavity 13 includes a leading edge region, a mid-chord region, and a trailing edge region 131, the mid-chord region being located between the leading edge region and the trailing edge region 131.
Specifically, the leading edge region 134 cools the leading edge portion leading edge of the turbine stator blade by means of impingement cooling, the first trailing edge region cools the first trailing edge region portion of the turbine stator blade by providing a plurality of first column ribs 2, the second trailing edge region cools the second trailing edge region portion of the turbine stator blade by providing intermediate walls 3, second column ribs 4, and third column ribs 5, and the mid-chord region cools the trailing edge portion of the turbine stator blade by means of impingement bushings.
Therefore, in the turbine vane according to the embodiment of the present invention, the second plurality of column ribs 4, the third plurality of column ribs 5, and the intermediate wall 3 are provided in the second trailing edge region 1312, and further, the portions of the suction wall 11 and the pressure wall 12 corresponding to the second trailing edge region 1312 can be cooled by the column rib cooling method, so that the portions of the suction wall 11 and the pressure wall 12 corresponding to the second trailing edge region 1312 are not damaged by overheating, and therefore, the service life of the turbine vane according to the embodiment of the present invention is prolonged.
In some embodiments, as shown in fig. 1, the trailing end of the vane body 1 is provided with a split 132, the split 132 communicating the first trailing edge region 1311 with the outside, specifically, the split 132 is formed between the right end suction wall 11 and the right end pressure wall 12.
It can be understood that the cleft 132 is arranged at the tail end of the stator blade body 1, so that the cooling gas can be discharged to the outside through the cleft 132, the convection effect of the cooling gas in the inner cavity is enhanced, the cooling gas after heat exchange is easily discharged, and the cooling effect on the stator blade body 1 is improved.
The gas turbine according to the embodiment of the present invention includes the turbine vane according to any one of the embodiments, and specifically, the gas turbine according to the embodiment of the present invention further includes a gas turbine, a compressor, and a combustor, wherein the gas turbine includes the turbine vane according to any one of the embodiments. The compressor continuously compresses external air, the compressed air is input into the combustion chamber, the compressed air and fuel are mixed and combusted in the combustion chamber to form high-temperature gas, and the high-temperature gas flows into the gas turbine to expand and do work, so that the turbine blades are pushed to rotate and output mechanical work.
An aircraft engine according to an embodiment of the invention comprises a turbine vane according to any of the embodiments described above.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the present disclosure, the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" and the like mean that a specific feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
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 to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (10)
1. A turbine vane, comprising:
the stator blade body comprises a suction wall, a pressure wall and a cavity enclosed by the suction wall and the pressure wall, the cavity comprises a tail edge area, the tail edge area comprises a first tail edge area and a second tail edge area which are communicated with each other, the first tail edge area is adjacent to the tail end of the stator blade body along the extending direction of the stator blade body, and the second tail edge area is far away from the tail end of the stator blade body along the extending direction of the stator blade body;
a plurality of first column ribs spaced apart and uniformly disposed within the first trailing edge region, the first column ribs connected between the suction wall and the pressure wall;
an intermediate wall disposed within the second trailing edge region; and
a plurality of second post ribs and a plurality of third post rib, it is a plurality of second post rib interval and evenly establish the second trailing edge district, it is a plurality of third post rib interval and evenly establish the second trailing edge district, the second post rib is connected the suction wall with between the interwall, the third post rib is connected the pressure wall with between the interwall.
2. The turbine vane of claim 1, wherein the plurality of second column ribs comprises at least one first rib group comprising a plurality of second column ribs, the plurality of second column ribs in the first rib group being spaced apart in a width direction of the vane body, the plurality of third column ribs comprises at least one second rib group comprising a plurality of third column ribs, the plurality of third column ribs in the second rib group being spaced apart in the width direction of the vane body.
3. The turbine vane of claim 2, wherein the first rib group is plural, a plurality of the first rib groups are arranged at intervals in an extending direction of the vane body, and the second rib group is plural, and a plurality of the second rib groups are arranged at intervals in the extending direction of the vane body.
4. The turbine vane of any one of claims 1 to 3 wherein a plurality of said second post ribs and a plurality of said third post ribs are symmetrically disposed on either side of said intermediate wall.
5. The turbine vane of any one of claims 1 to 3, wherein a dimension of the intermediate wall in a width direction of the vane body is gradually reduced or constant in a direction adjacent the trailing end of the vane body.
6. The turbine vane according to any one of claims 1 to 3, wherein the intermediate wall includes a first wall surface and a second wall surface, the first wall surface being located on one side in a thickness direction of the intermediate wall, the second wall surface being located on the other side in the thickness direction of the intermediate wall, the first wall surface having the same shape as that of an inner wall surface of the suction wall, and the second wall surface having the same shape as that of an inner wall surface of the pressure wall.
7. The turbine vane of any one of claims 1-3 wherein the cavity includes a leading edge region, a mid-chord region and the trailing edge region, the mid-chord region being located between the leading edge region and the trailing edge region.
8. The turbine vane of claim 7 wherein said trailing end of said vane body is provided with a split slot communicating said first trailing edge region with the ambient.
9. A gas turbine comprising a turbine vane according to any one of claims 1 to 8.
10. An aircraft engine comprising a turbine vane according to any of claims 1 to 8.
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| CN202111438025.6A CN114278390A (en) | 2021-11-30 | 2021-11-30 | Turbine stator blade, gas turbine and aircraft engine |
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| CN202111438025.6A CN114278390A (en) | 2021-11-30 | 2021-11-30 | Turbine stator blade, gas turbine and aircraft engine |
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| US20180045055A1 (en) * | 2016-08-12 | 2018-02-15 | General Electric Company | Impingement system for an airfoil |
| US20180195396A1 (en) * | 2017-01-10 | 2018-07-12 | Doosan Heavy Industries & Construction Co., Ltd. | Blade, cut-back of blade or vane and gas turbine having the same |
| CN113090335A (en) * | 2021-05-14 | 2021-07-09 | 中国航发湖南动力机械研究所 | Impact air-entraining film double-wall cooling structure for turbine rotor blade |
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- 2021-11-30 CN CN202111438025.6A patent/CN114278390A/en active Pending
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| US20020090294A1 (en) * | 2001-01-05 | 2002-07-11 | General Electric Company | Truncated rib turbine nozzle |
| US20180045055A1 (en) * | 2016-08-12 | 2018-02-15 | General Electric Company | Impingement system for an airfoil |
| US20180195396A1 (en) * | 2017-01-10 | 2018-07-12 | Doosan Heavy Industries & Construction Co., Ltd. | Blade, cut-back of blade or vane and gas turbine having the same |
| CN113090335A (en) * | 2021-05-14 | 2021-07-09 | 中国航发湖南动力机械研究所 | Impact air-entraining film double-wall cooling structure for turbine rotor blade |
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