CN114320482A - Turbine blade, gas turbine and aircraft engine - Google Patents
Turbine blade, gas turbine and aircraft engine Download PDFInfo
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- CN114320482A CN114320482A CN202111447035.6A CN202111447035A CN114320482A CN 114320482 A CN114320482 A CN 114320482A CN 202111447035 A CN202111447035 A CN 202111447035A CN 114320482 A CN114320482 A CN 114320482A
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- 238000001816 cooling Methods 0.000 claims abstract description 25
- 238000010248 power generation Methods 0.000 claims description 4
- 230000002093 peripheral effect Effects 0.000 claims description 2
- 241001391944 Commicarpus scandens Species 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 8
- 239000000463 material Substances 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000012809 cooling fluid Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 210000002307 prostate Anatomy 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The invention discloses a turbine blade, a gas turbine and an aeroengine, wherein the turbine blade comprises a tail edge area and a plurality of column ribs, a plurality of impact holes are arranged on the windward side of the tail edge area, the tail edge area comprises a middle area and edge areas positioned at two sides of the middle area in the length direction, a plurality of column ribs are connected on the inner circumferential surface of the tail edge area, at least parts of a plurality of impact holes are opposite to the column ribs, cooling airflow flowing through the impact holes can impact the column ribs, the column ribs are arranged at intervals in the length direction of the tail edge area and are arranged in a plurality of rows in the width direction of the tail edge area, the plurality of rows of column ribs comprise the most front column ribs, and the most front column ribs are adjacent to the impact holes, and in the most front row rib column, the diameter of the column rib at the middle area is larger than that of the column rib at the edge area, and/or the spacing of the ribs in the central region is less than the spacing of the ribs in the edge region. The turbine blade has the advantages that the temperature distribution of the tail edge area is uniform, the integral strength of the blade is high, and the blade is not easy to break.
Description
Technical Field
The invention relates to the technical field of gas engine equipment, in particular to a turbine blade, a gas turbine and an aircraft engine.
Background
The turbine blade is a main work-applying element of the turbine, the working condition of the turbine blade is very severe, the turbine blade not only works in a high-temperature environment, but also is in a rotating state, and the safe and stable operation of the turbine blade is a prerequisite condition for the successful operation of a heavy-duty gas turbine. The trailing edge district is one of the primary area that one-level movable vane needs the cooling, through set up the vortex column rib in trailing edge district inside among the correlation technique to carry out the vortex to cooling fluid, reinforcing heat transfer coefficient reaches refrigerated purpose. However, the turbine blade in the related art has a phenomenon that the temperatures of all regions are not uniform in the trailing edge region, and the blade cracks or even breaks under a high-speed and strong-vibration working environment.
Disclosure of Invention
The invention aims to solve the technical problems that the temperature distribution of the tail edge area of the turbine blade is uniform, the overall strength of the blade is high, and the blade is not easy to break.
The embodiment of the invention also provides a gas turbine.
The embodiment of the invention also provides an aircraft engine.
A turbine blade according to an embodiment of the invention comprises: the wind power generation device comprises a tail edge area, a wind power generation system and a control system, wherein the windward side of the tail edge area is provided with a plurality of impact holes, and the tail edge area comprises a middle area and edge areas positioned on two sides of the middle area in the length direction; a plurality of column ribs connected to an inner peripheral surface of the trailing edge region, at least a portion of the plurality of impingement holes being opposed to the column ribs, the column ribs being impinged by the cooling airflow flowing through the impingement holes, the plurality of column ribs being arranged at intervals in a length direction of the trailing edge region and in a plurality of rows in a width direction of the trailing edge region, the plurality of rows including a leading-most column rib which is adjacent to the impingement holes, and in the leading-most column, a diameter of the column rib at the central region is larger than a diameter of the column rib at the edge region, and/or a pitch of the column ribs at the central region is smaller than a pitch of the column ribs at the edge region.
According to the turbine blade provided by the embodiment of the invention, in the most front row rib column, the diameter of the column rib in the middle area is larger than that of the column rib in the edge area, and/or the distance between the column ribs in the middle area is smaller than that of the column ribs in the edge area, so that the turbulence effect of the column ribs in the middle area can be improved, the heat exchange coefficient of the middle area is enhanced, the temperature distribution of the turbine blade is uniform, the thermal stress is reduced, and the overall strength of the blade is improved.
In some embodiments, a plurality of the impingement holes are arranged at intervals in a length direction of the trailing edge region, and the plurality of the impingement holes correspond one-to-one to the plurality of the column ribs of the most leading column rib.
In some embodiments, the cross-sectional area of the impingement holes at the middle region is greater than the cross-sectional area of the impingement holes at the edge region.
In some embodiments, the pitch of the impingement holes in the middle region is less than the pitch of the impingement holes in the edge region.
In some embodiments, a plurality of air outlet holes are arranged on the leeward side of the tail edge region, the air outlet holes are arranged at intervals in the length direction of the tail edge region, and the column rib is located between the impact hole and the air outlet hole in the width direction of the tail edge region.
In some embodiments, the plurality of columns of column ribs includes a last column rib adjacent to the air outlet holes, and the air outlet holes correspond one-to-one to the column ribs of the last column rib.
In some embodiments, the diameter of the rib post in the last column of rib posts is greater in the central region than in the edge region.
In some embodiments, the cross-sectional area of the exit apertures in the central region is greater than the cross-sectional area of the exit apertures in the edge region.
In some embodiments, a plurality of the column ribs of two adjacent columns of column ribs are staggered in the length direction of the trailing edge region.
A gas turbine according to an embodiment of the invention comprises a turbine blade according to any of the above.
According to the gas turbine provided by the embodiment of the invention, by adopting the turbine blade, the gas turbine has long service life and good performance.
An aircraft engine according to an embodiment of the invention comprises a turbine blade according to any of the above.
According to the aero-engine provided by the embodiment of the invention, by adopting the turbine blade, the aero-engine has the advantages of long service life and good performance.
Drawings
FIG. 1 is a schematic illustration of a turbine blade according to an embodiment of the invention.
Fig. 2 is an enlarged view of a portion a in fig. 1.
Reference numerals:
trailing edge region 1, column rib 11, impingement holes 12, exit holes 13, leading column rib 14, trailing column rib 15, and air supply channel 2.
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.
As shown in fig. 1 and 2, a turbine blade according to an embodiment of the invention comprises a trailing edge region 1 and a plurality of cylindrical ribs 11.
As shown in fig. 1, a plurality of impact holes 12 are provided on the windward side of the trailing edge region 1, and the trailing edge region 1 includes a middle region and edge regions on both sides of the middle region in the length direction thereof, a plurality of column ribs 11 are connected to the inner circumferential surface of the trailing edge region 1, and at least part of the plurality of impact holes 12 is opposed to the column ribs 11.
It should be noted that the trailing edge region 1 is arc-shaped, the impact holes 12 are located on the windward side of the trailing edge region 1, the column ribs 11 are connected to the concave surface and extend inward, the impact holes 12 are opposite to the column ribs 11 in the flow direction of the cooling airflow, and then the cooling airflow can impact the column ribs 11 after passing through the impact holes 12, that is, the column ribs 11 can disturb the cooling airflow, enhance the heat exchange coefficient, and achieve the cooling purpose.
Further, as shown in fig. 1 and 2, a plurality of rib columns 11 are arranged at intervals in the length direction of the trailing edge region 1 and in a plurality of rows in the width direction of the trailing edge region 1, the plurality of rows of rib columns include the most front row rib column 14, the most front row rib column 14 is adjacent to the impingement hole 12, and in the most front row rib column 14, the diameter of the column rib 11 located in the middle region is larger than that of the column rib 11 located in the edge region, and/or the pitch of the column ribs 11 located in the middle region is smaller than that of the column ribs 11 located in the edge region. It should be noted that the temperature of the gas side is usually lower in the edge area (blade root and blade tip area) than in the middle area, so that the metal temperature of the blade in the tail area 1 of the middle area is higher than that in the edge area, and the temperature unevenness occurs.
The inventor finds that in the related art, the column ribs are uniformly distributed in the trailing edge area, and the sizes and the intervals of the column ribs are the same, namely, the column rib turbulence can realize uniform cooling of all areas of the trailing edge area, and the arrangement mode of the column ribs has no pertinence, namely, effective cooling cannot be carried out aiming at overhigh temperature of the middle area.
And this application, the overall arrangement that sets up the most prostate rib post 14 does, and the diameter of the post rib 11 in the middle part region is greater than the diameter of the post rib 11 in the marginal zone, can increase the vortex face of the post rib 11 in the middle part region, improves the vortex effect, perhaps is less than the interval that is located the post rib 11 in the marginal zone through the interval that sets up the post rib 11 in the middle part region, and the post rib 11 in the middle part region is more intensive promptly, and the vortex effect is also better.
According to the turbine blade provided by the embodiment of the invention, in the most front row rib column, the diameter of the column rib in the middle area is larger than that of the column rib in the edge area, and/or the distance between the column ribs in the middle area is smaller than that of the column ribs in the edge area, so that the turbulence effect of the column ribs in the middle area can be improved, the heat exchange coefficient of the middle area is enhanced, the temperature distribution of the turbine blade is uniform, the thermal stress is reduced, and the overall strength of the blade is improved.
Further, as shown in fig. 2, the impingement holes 12 are arranged at intervals in the length direction of the trailing edge region 1, and a plurality of impingement holes 12 correspond one-to-one to a plurality of column ribs 11 of the leading column rib 14. Thus, the cooling airflow passing through the impingement holes 12 may maximally impinge on the foremost column rib 14 to enhance the flow disturbance effect. Preferably, the cross-sectional area of the impingement holes 12 in the middle region is larger than the cross-sectional area of the impingement holes 12 in the edge region to increase the flow rate of the cooling air through the impingement holes 12 in the middle region, further increasing the cooling effect of the cooling air on the middle region.
In some embodiments, as shown in FIG. 2, the spacing of the impingement holes 12 in the center region is less than the spacing of the impingement holes 12 in the edge region to increase the concentration of impingement holes 12 in the center region and increase the flow of cooling air.
In some embodiments, as shown in fig. 2, a plurality of air outlet holes 13 are provided on the leeward side of the trailing edge region 1, the plurality of air outlet holes 13 are arranged at intervals in the length direction of the trailing edge region 1, and the pillar rib 11 is located between the impingement holes 12 and the air outlet holes 13 in the width direction of the trailing edge region 1. It will be appreciated that the cooling air flows along the air supply passage 2 to the impingement holes 12 and flows into the inside of the trailing edge region 1 through the impingement holes 12, the column ribs 11 disturb the air flow inside the trailing edge region 1, and the cooling air flow is finally discharged from the air outlet holes 13.
Further, as shown in fig. 2, the plurality of columns of column ribs 11 includes a rearmost column rib 15, the rearmost column rib 15 is adjacent to the air outlet hole 13, and the plurality of air outlet holes 13 correspond one-to-one to the plurality of column ribs 11 of the rearmost column rib 15. Therefore, after the cooling air flows through the impact holes 12, the front row of column ribs 14 disturb the cooling air, the cooling air flows out of the air outlet holes 13, the rear row of column ribs 15 disturb the cooling air, and the middle area can be greatly cooled.
Further, as shown in fig. 2, in the rearmost column of rib columns 15, the diameter of the rib column 11 located in the central region is larger than the diameter of the rib column 11 located in the edge region.
Further, as shown in fig. 2, the sectional area of the air outlet hole 13 located at the central region is larger than that of the air hole located at the edge region. From this, venthole 13 can allow cooling air to pass through with great flow, guarantees that cooling air passes through the velocity of flow of trailing edge district 1, improves cooling air to the impact force of column rib 11, guarantees the vortex effect, reinforcing heat transfer coefficient.
In some embodiments, as shown in fig. 2, a plurality of column ribs 11 of two adjacent columns of column ribs 11 are staggered in the length direction of the trailing edge region 1. Therefore, the column rib 11 at the front side does not shield the column rib 11 at the rear side thereof, and the cooling air flow can sufficiently impact each column rib 11, ensuring the turbulent flow effect.
A gas turbine according to an embodiment of the invention comprises a turbine blade according to any of the above.
According to the gas turbine provided by the embodiment of the invention, by adopting the turbine blade, the gas turbine has long service life and good performance.
An aircraft engine according to an embodiment of the invention comprises a turbine blade according to any of the above.
According to the aero-engine provided by the embodiment of the invention, by adopting the turbine blade, the aero-engine has the advantages of long service life and good performance.
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 (11)
1. A turbine blade, comprising:
the wind power generation device comprises a tail edge area, a wind power generation system and a control system, wherein the windward side of the tail edge area is provided with a plurality of impact holes, and the tail edge area comprises a middle area and edge areas positioned on two sides of the middle area in the length direction;
a plurality of column ribs connected to an inner peripheral surface of the trailing edge region, at least a portion of the plurality of impingement holes being opposed to the column ribs, the column ribs being impinged by the cooling airflow flowing through the impingement holes, the plurality of column ribs being arranged at intervals in a length direction of the trailing edge region and in a plurality of rows in a width direction of the trailing edge region, the plurality of rows including a leading-most column rib which is adjacent to the impingement holes, and in the leading-most column, a diameter of the column rib at the central region is larger than a diameter of the column rib at the edge region, and/or a pitch of the column ribs at the central region is smaller than a pitch of the column ribs at the edge region.
2. The turbine blade of claim 2 wherein a plurality of said impingement holes are spaced apart along the length of said trailing edge region and correspond one-to-one with a plurality of said column ribs of said leading column rib.
3. The turbine blade of claim 1 wherein the cross-sectional area of the impingement holes at the mid region is greater than the cross-sectional area of the impingement holes at the edge region.
4. The turbine blade of claim 1 wherein the pitch of the impingement holes in the mid region is less than the pitch of the impingement holes in the edge region.
5. The turbine blade of claim 1 wherein said trailing edge region has a plurality of air exit holes on a leeward side thereof, said plurality of air exit holes being spaced apart along a length of said trailing edge region, and said post rib being located between said impingement holes and said air exit holes along a width of said trailing edge region.
6. The turbine blade of claim 5 wherein said plurality of columns of said post ribs includes a last column rib, said last column rib being adjacent said exit holes, and a plurality of said exit holes being in one-to-one correspondence with a plurality of said post ribs of said last column rib.
7. The turbine blade of claim 6 wherein in the last column of rib columns, the rib columns at the mid region have a diameter greater than the rib columns at the edge region.
8. The turbine blade of claim 5 wherein the cross-sectional area of the exit holes at the center region is greater than the cross-sectional area of the exit holes at the edge region.
9. The turbine blade of claim 2 wherein a plurality of said post ribs of two adjacent columns of post ribs are staggered along the length of said trailing edge region.
10. A gas turbine comprising a turbine blade according to any one of claims 1 to 9.
11. An aircraft engine, characterized in that it comprises a turbine blade according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111447035.6A CN114320482A (en) | 2021-11-30 | 2021-11-30 | Turbine blade, gas turbine and aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111447035.6A CN114320482A (en) | 2021-11-30 | 2021-11-30 | Turbine blade, gas turbine and aircraft engine |
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| Publication Number | Publication Date |
|---|---|
| CN114320482A true CN114320482A (en) | 2022-04-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111447035.6A Pending CN114320482A (en) | 2021-11-30 | 2021-11-30 | Turbine blade, gas turbine and aircraft engine |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104196574A (en) * | 2014-07-15 | 2014-12-10 | 西北工业大学 | Gas turbine cooling blade |
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2021
- 2021-11-30 CN CN202111447035.6A patent/CN114320482A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104196574A (en) * | 2014-07-15 | 2014-12-10 | 西北工业大学 | Gas turbine cooling blade |
Non-Patent Citations (2)
| Title |
|---|
| 刘作宏: "涡轮叶片柱肋冷却通道流动换热特性研究", 工程科技Ⅱ辑, no. 8, 31 August 2018 (2018-08-31), pages 86 * |
| 葛海潮: "双腔室模型中扰流柱对冲击冷却的影响", 工程科技Ⅱ辑, no. 9, 30 September 2015 (2015-09-30), pages 31 - 34 * |
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