An impulse turbine stator suitable for use in a gas turbine having up and down air inlets, a turbine and a gas turbine

Abstract

The application discloses a turbine vane, a turbine and a gas turbine suitable for upper and lower air inlet of the gas turbine. The turbine vane comprises a vane body, the vane body is provided with a first cooling cavity and a second cooling cavity which are spaced in the height direction of the vane body, the vane body is provided with a first air inlet and a second air inlet, the first air inlet is communicated with the first cooling cavity, and the second air inlet is communicated with the second cooling cavity. The turbine vane has the advantages of high reliability.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of gas turbine technology, in particular to an impingement type turbine vane suitable for upper and lower air inlet of a gas turbine, a turbine and a gas turbine. BACKGROUND

[0002] The gas turbine or the aero-engine usually adopts the single-sided air inlet mode of the upper end wall or the lower end wall or the mode of simultaneous air inlet of the upper and lower end walls, and the cooling gas is introduced into the internal cooling structure to reduce the temperature of the static blade base and prevent the static blade metal base from deforming or ablation under high temperature.

[0003] In the related art, the internal cooling structure usually adopts the bushing impingement cooling mode to cool the static blade. When the single-sided air inlet mode is adopted, for the case that there are film holes on the surface of the static blade, part of the cooling gas will flow out through the film holes during the flow of the cooling gas in the upper and lower directions (the height direction of the static blade), resulting in that the cooling gas at the inlet is relatively more and the cooling gas at the tail end is relatively less. When the upper and lower air inlet mode is adopted, the cooling gas entering through the upper and lower inlets will disturb each other, and the same problem of more cooling gas on one side and less cooling gas on the other side in the upper and lower directions will be caused. In summary, whether the single-sided air inlet mode or the double-sided air inlet mode is adopted, the problem of uneven distribution of the cooling gas will be caused, resulting in uneven temperature distribution on the surface of the static blade and the problem of stress concentration, and the reliability of the static blade is poor. SUMMARY

[0004] The present application aims to at least solve one of the technical problems in the related art to some extent.

[0005] To this end, an embodiment of the present application provides an impingement type turbine vane suitable for upper and lower air inlet of a gas turbine with high reliability.

[0006] An embodiment of the present application also provides a turbine with high reliability.

[0007] An embodiment of the present application also provides a gas turbine with high reliability.

[0008] The turbine vane of the embodiment of the present application comprises a blade body, the blade body has a first cooling cavity and a second cooling cavity which are arranged at intervals in the height direction of the blade body, the blade body has a first air inlet and a second air inlet, the first air inlet is in communication with the first cooling cavity, and the second air inlet is in communication with the second cooling cavity.

[0009] The impingement type turbine vane suitable for upper and lower air inlet of a gas turbine of the embodiment of the present application has the advantage of high reliability.

[0010] In some embodiments, the turbine vane of the present application further comprises a first partition plate arranged in the first cooling cavity and extending along the height direction of the vane body, the first partition plate separates the first cooling cavity into a first chamber and a second chamber arranged along the chord direction of the vane body, the first inlet port is in a plurality, a part of the plurality of first inlet ports is a first inlet port, the first inlet port is in communication with the first chamber, another part of the plurality of inlet ports is a second inlet port, the second inlet port is in communication with the second chamber;

[0011] the second partition plate is arranged in the second cooling cavity and extends along the height direction of the vane body, the second partition plate separates the second cooling cavity into a third chamber and a fourth chamber arranged along the chord direction of the vane body, the second inlet port is in a plurality, a part of the plurality of second inlet ports is a third inlet port, the third inlet port is in communication with the third chamber, another part of the plurality of second inlet ports is a fourth inlet port, the fourth inlet port is in communication with the fourth chamber.

[0012] In some embodiments, the turbine vane of the present application further comprises:

[0013] a first partition plate arranged in the second inlet port to block a part of the second inlet port, a third partition plate arranged in the second chamber and extending along the height direction of the vane body, one end of the third partition plate in the height direction of the vane body is connected with the first partition plate, the other end of the third partition plate is spaced apart from the cavity wall of the first cooling chamber to form a first communication port, the first partition plate, the third partition plate and the vane body define a first passage, the first partition plate, the third partition plate and the vane body define a second passage, the first passage and the second passage are in communication through the first communication port; and / or,

[0014] a second partition plate arranged in the fourth inlet port to block a part of the fourth inlet port, a fourth partition plate arranged in the fourth chamber and extending along the height direction of the vane body, one end of the fourth partition plate in the height direction of the vane body is connected with the second partition plate, the other end of the fourth partition plate is spaced apart from the cavity wall of the second cooling chamber to form a second communication port, the second partition plate, the fourth partition plate and the vane body define a third passage, the second partition plate, the fourth partition plate and the vane body define a fourth passage, the third passage and the fourth passage are in communication through the second communication port.

[0015] In some embodiments, the turbine vane of the present application further comprises:

[0016] a plurality of fifth partitions disposed in the second passage and extending along a chordal direction of the blade body, the plurality of fifth partitions being spaced apart along a height direction of the blade body, the plurality of fifth partitions defining a first serpentine passage in the second passage; and / or

[0017] a plurality of sixth partitions disposed in the fourth passage and extending along a chordal direction of the blade body, the plurality of sixth partitions being spaced apart along a height direction of the blade body, the plurality of sixth partitions defining a second serpentine passage in the fourth passage.

[0018] In some embodiments, the blade body has a leading edge and a trailing edge opposite to each other in a chordal direction of the blade body;

[0019] the first chamber is disposed more proximate to the leading edge relative to the second chamber in the chordal direction of the blade body, and / or

[0020] the third chamber is disposed more proximate to the leading edge relative to the fourth chamber in the chordal direction of the blade body.

[0021] In some embodiments, the first partition and the second partition are disposed in alignment in the chordal direction of the blade body.

[0022] In some embodiments, the first partition and the second partition are in an integral structure.

[0023] In some embodiments, a dimension of the first cooling chamber in the height direction of the blade body is equal to a dimension of the second cooling chamber in the height direction of the blade body.

[0024] In some embodiments, the blade body has a cooling chamber, the turbine vane further comprising a middle partition extending along a chordal direction of the blade body, the middle partition being disposed in the cooling chamber, the middle partition separating the cooling chamber into the first cooling chamber and the second cooling chamber.

[0025] In some embodiments, the blade body comprises a blade body having a cavity and a bushing disposed in the cavity, an annular chamber being defined between the bushing and the blade body, the bushing defining the cooling chamber, the first inlet and the second inlet being disposed on the bushing, the bushing having a plurality of first jet holes, the first cooling chamber and the annular chamber being in communication through a portion of the first jet holes, the second cooling chamber and the annular chamber being in communication through another portion of the first jet holes.

[0026] In some embodiments, the vane body has a leading edge and a trailing edge opposite in chordwise direction of the vane body, and the vane body is provided with a trailing edge split slot, the trailing edge split slot being in communication with the annular chamber so that the cooling gas in the annular chamber is discharged through the trailing edge split slot.

[0027] In some embodiments, the turbine vane further comprises a seventh partition plate arranged in the cavity, the seventh partition plate extending along the height direction of the vane body to divide the cavity into a mounting cavity and a trailing edge cooling cavity, the mounting cavity being arranged more adjacent to the leading edge in the chordwise direction of the vane body relative to the trailing edge cooling cavity, the bushing being arranged in the mounting cavity, the trailing edge split slot being in communication with the trailing edge cooling cavity, and the seventh partition plate being provided with a second jet hole extending along the chordwise direction of the vane body.

[0028] In some embodiments, the turbine vane further comprises an eighth partition plate arranged in the trailing edge cooling cavity, the eighth partition plate extending along the height direction of the vane body to divide the trailing edge cooling cavity into a first cooling part and a second cooling part, the first cooling part being arranged more adjacent to the leading edge in the chordwise direction of the vane body relative to the second cooling part, the trailing edge split slot being in communication with the second cooling part, and the eighth partition plate being provided with a third jet hole extending along the chordwise direction of the vane body.

[0029] In some embodiments, the second cooling part is provided with a plurality of heat dissipation columns.

[0030] The turbine according to the embodiments of the present application comprises the impact type turbine vane for up and down air intake of the gas turbine according to any one of the above embodiments.

[0031] The turbine according to the embodiments of the present application has the advantage of high reliability.

[0032] The gas turbine according to the embodiments of the present application comprises the turbine according to any one of the above embodiments.

[0033] The gas turbine according to the embodiments of the present application has the advantage of high reliability. BRIEF DESCRIPTION OF DRAWINGS

[0034] Figure 1 is a schematic view of the internal structure of the turbine vane according to the embodiments of the present application.

[0035] Figure 2 is Figure 1 is an enlarged view of A in FIG.

[0036] Figure 3 is a semi-sectional view of the impact type turbine vane for up and down air intake of the gas turbine according to the embodiments of the present application from a first perspective.

[0037] Figure 4This is a half-sectional view from a second perspective of an impact-type transparent blade suitable for upper and lower air intake of a gas turbine, according to an embodiment of the present invention.

[0038] Figure 5 This is a top view of the blade body of an impact-type transparent blade suitable for the upper and lower air intakes of a gas turbine, according to an embodiment of the present invention.

[0039] Figure label:

[0040] Translucent leaves 100;

[0041] 10 blades;

[0042] Blade body 1; cavity 101; mounting cavity 1011; trailing edge cooling cavity 1012; first cooling section 10121; second cooling section 10122; leading edge 102; trailing edge 103; trailing edge slit 104;

[0043] Bushing 2; First cooling chamber 201; First cavity 2011; Second cavity 2012; Second cooling chamber 202; Third cavity 2021; Fourth cavity 2022; First air inlet 203; First inlet 2031; Second inlet 2032; Second air inlet 204; Third inlet 2041; Fourth inlet 2042; First jet orifice 205;

[0044] Annular chamber 3;

[0045] First partition 401; Second partition 402; Third partition 403; Fourth partition 404; Fifth partition 405; Sixth partition 406; Middle partition 407;

[0046] First sealing plate 501; Second sealing plate 502;

[0047] Channel 1: 601; Channel 2: 602; Channel 3: 603; Channel 4: 604;

[0048] Seventh partition 701; Second jet hole 7011; Eighth partition 702; Third jet hole 7021;

[0049] Heat dissipation column 8;

[0050] Upper end wall 901; lower end wall 902.

[0051] First connection port 1001; Second connection port 1002. Detailed Implementation

[0052] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0053] The technical solutions of the present application will be described in detail below with reference to the drawings.

[0054] As shown in Figures 1 to 5 The turbine vane 100 of the embodiment of the present application includes a vane body 10 having a first cooling cavity 201 and a second cooling cavity 202 arranged in the height direction of the vane body 10, and the vane body 10 has a first air inlet 203 and a second air inlet 204, the first air inlet 203 being in communication with the first cooling cavity 201, and the second air inlet 204 being in communication with the second cooling cavity 202.

[0055] It can be understood that the vane body 10 has a first air outlet hole in communication with the first cooling cavity 201 and a second air outlet hole in communication with the second cooling cavity. The cooling gas entering the first cooling cavity 201 through the first air inlet 203 can flow out through the first air outlet hole, and the cooling gas entering the second cooling cavity 202 through the second air inlet 204 can flow out through the second air outlet hole.

[0056] In operation, the turbine vane 100 of the embodiment of the present application, the cooling gas enters the first cooling cavity 201 through the first air inlet 203 and is discharged through the first air outlet hole, and the cooling gas enters the second cooling cavity 202 through the second air inlet 204 and is discharged through the second air outlet hole, thereby achieving cooling of the vane body 10.

[0057] The turbine vane 100 of the embodiment of the present application has multiple cooling cavities including the first cooling cavity 201 and the second cooling cavity 202 arranged in the height direction of the vane body 10.

[0058] On the one hand, compared with the related art in which only one cooling cavity is arranged on the vane body and only one air inlet is arranged on one side of the vane body in the height direction of the vane body, the turbine vane 100 of the embodiment of the present application has the first cooling cavity 201 and the second cooling cavity 202, both of which have a smaller size in the height direction of the vane body 10, thereby shortening the flow path of the cooling gas in the first cooling cavity 201 and the second cooling cavity 202. During the flow of the cooling gas in the height direction of the vane body, even if part of the cooling gas flows out through the air film hole on the vane body 10, the difference in the amount of cooling gas at the inlet (the first air inlet 203 or the second air inlet 204) and the end (the end of the first cooling cavity 201 away from the first air inlet 203 or the end of the second cooling cavity 202 away from the second air inlet 204) can be reduced, thereby improving the uniformity of the distribution of the cooling gas in the vane body 10.

[0059] Compared with the prior art in which only one cooling cavity is arranged on the blade body and the air inlet is arranged on both sides of the blade body in the height direction of the blade body, the flow paths of the cooling gas in the first cooling cavity 201 and the cooling gas in the second cooling cavity 202 are independent of each other, the disturbance between the cooling gas in the first cooling cavity 201 and the cooling gas in the second cooling cavity 202 can be avoided, and the uniformity of the distribution of the cooling gas in the blade body 10 is improved.

[0060] In conclusion, the turbine vane 100 in the embodiment of the present application has good uniformity of the distribution of the cooling gas in the blade body 10, the problem of uneven distribution of the surface temperature of the turbine vane 100 can be alleviated, the problem of stress concentration of the turbine vane 100 can be further alleviated, and the reliability of the turbine vane 100 is improved.

[0061] In addition, it can be understood by those skilled in the art that, in the prior art, the surface of part of the turbine vane 100 is not provided with the film hole, when the unilateral air inlet is used, the turbine vane 100 can avoid the problem of uneven distribution of the cooling gas caused by the outflow of the cooling gas through the film hole, but the cooling gas is prone to accumulate at the end far from the inlet, and the problem of uneven distribution of the cooling gas still exists. The part of the turbine vane 100 with a higher temperature is located in the middle part of the turbine vane 100 in the height direction. Although the turbine vane 100 in the embodiment of the present application also has the problem of accumulation of the cooling gas at the end of the cooling cavity (the end of the first cooling cavity 201 far from the first air inlet 203 or the end of the second cooling cavity 202 far from the second air inlet 204), the accumulation position of the cooling gas is in the middle part of the turbine vane 100, and the middle part of the turbine vane 100 can be effectively cooled by the cooling gas accumulated in the middle part of the turbine vane 100. The problem of uneven distribution of the surface temperature of the turbine vane 100 can be alleviated, the problem of stress concentration of the turbine vane 100 can be further alleviated, and the reliability of the turbine vane 100 is improved.

[0062] Therefore, the impact turbine vane 100 suitable for the up-and-down air inlet of the gas turbine has the advantages of high reliability and the like.

[0063] In some embodiments, the blade body 10 has a cooling chamber, and the turbine vane 100 further comprises a middle partition plate 407, the middle partition plate 407 extends along the chord direction of the blade body 10, the middle partition plate 407 is arranged in the cooling chamber, and the middle partition plate 407 divides the cooling chamber into the first cooling cavity 201 and the second cooling cavity 202.

[0064] In order to make the technical scheme of the present application easier to be understood, the chord direction of the blade body 10 is consistent with the left-right direction, and the height direction of the blade body 10 is consistent with the up-down direction, which are taken as examples to further describe the technical scheme of the present application, wherein the left-right direction and the up-down direction are as shown in Figure 1、 Figure 3 and Figure 4 as shown.

[0065] As shown in Figure 3 and Figure 4 , a middle partition plate 407 extending along the left-right direction is arranged in the cooling chamber of the blade body 10 to divide the cooling chamber into a first cooling chamber 201 and a second cooling chamber 202. By arranging the middle partition plate 407 in the cooling chamber to divide the cooling chamber into the first cooling chamber 201 and the second cooling chamber 202, the machining and manufacturing of the blade body 10 are facilitated.

[0066] In some embodiments, the blade body 10 of the turbine vane 100 of the present embodiment comprises a blade body 1 and a bushing 2. The blade body 1 has a cavity 101, the bushing 2 is arranged in the cavity 101, an annular chamber 3 is defined between the bushing 2 and the blade body 1, the bushing 2 defines a cooling chamber, the first inlet 203 and the second inlet 204 are arranged on the bushing 2, the bushing 2 has a plurality of first jet holes 205, the first cooling chamber 201 and the annular chamber 3 are communicated through a part of the first jet holes 205, and the second cooling chamber 202 and the annular chamber 3 are communicated through another part of the first jet holes 205.

[0067] As shown in Figures 3 to 5 , the plurality of first jet holes 205 are uniformly arranged on the surface of the bushing 2, a part of the plurality of first jet holes 205 are communicated with the first cooling chamber 201, and another part of the plurality of first jet holes 205 are communicated with the second cooling chamber 202. The first jet holes communicated with the first cooling chamber 201 are taken as a first jet hole group, and the second jet holes communicated with the second cooling chamber 202 are taken as a second jet hole group. When the turbine vane 100 of the present embodiment works, the cooling gas in the first cooling chamber 201 entered through the first inlet 203 can enter the annular cavity 101 through the first jet hole group to impact cool and cool the blade body 1. The cooling gas in the second chamber 2012 entered through the second inlet 204 can enter the annular cavity 101 through the second jet hole group to impact cool and cool the blade body 1.

[0068] Therefore, the turbine vane 100 of the present embodiment improves the cooling effect of the turbine vane 100 by arranging the blade body 10 to comprise the blade body 1 and the bushing 2, defining the annular chamber 3 between the bushing 2 and the blade body 1, and arranging the plurality of first jet holes 205 on the bushing 2, so as to further improve the reliability of the turbine vane 100.

[0069] In some embodiments, the turbine vane 100 of the present application further comprises a first partition plate 401 and a second partition plate 402. The first partition plate 401 is arranged in the first cooling cavity 201 and extends along the height direction of the blade body 10, and the first partition plate 401 divides the first cooling cavity 201 into a first chamber 2011 and a second chamber 2012 arranged along the chord direction of the blade body 10. The first inlet 203 is in a plurality, and a part of the plurality of first inlets 203 is a first inlet 2031, and the first inlet 2031 is communicated with the first chamber 2011, and another part of the plurality of inlets is a second inlet 2032, and the second inlet 2032 is communicated with the second chamber 2012.

[0070] As shown in Figure 3 and Figure 4 , the first cooling cavity 201 is arranged above the second cooling cavity 202, the first partition plate 401 extends along the up-down direction, and the first partition plate 401 divides the first cooling cavity 201 into a first chamber 2011 and a second chamber 2012 arranged along the left-right direction.

[0071] In the working process of the turbine vane 100 of the present application, a part of the cooling gas enters the first chamber 2011 through the first inlet 2031 to cool the blade body 10, and a part of the cooling gas enters the second chamber 2012 through the second inlet 2032 to cool the blade body 10. The turbine vane 100 of the present application divides the first cooling cavity 201 into a first chamber 2011 and a second chamber 2012 by arranging a first partition plate 401 in the first cooling cavity 201, and respectively introduces cooling gas into the first chamber 2011 and the second chamber 2012 to cool the blade body 10, which is beneficial to the uniformity of the distribution of the cooling gas in the chord direction of the blade body 10, thereby further improving the uniformity of the distribution of the cooling gas in the blade body 10, and further improving the reliability of the turbine vane 100.

[0072] In some embodiments, the turbine vane 100 of the present application further comprises a second partition plate 402. The second partition plate 402 is arranged in the second cooling cavity 202 and extends along the height direction of the blade body 10, and the second partition plate 402 divides the second cooling cavity 202 into a third chamber 2021 and a fourth chamber 2022 arranged along the chord direction of the blade body 10. The second inlet 204 is in a plurality, and a part of the plurality of second inlets 204 is a third inlet 2041, and the third inlet 2041 is communicated with the third chamber 2021, and another part of the plurality of second inlets 204 is a fourth inlet 2042, and the fourth inlet 2042 is communicated with the fourth chamber 2022.

[0073] As shown in Figure 3 and Figure 4As shown, the second partition plate 402 extends in the up-down direction, and the second partition plate 402 divides the second cooling cavity 202 into a third cavity 2021 and a fourth cavity 2022 arranged in the left-right direction.

[0074] In operation, a part of the cooling gas enters the third cavity 2021 through the third inlet 2041 to cool the blade body 10, and another part of the cooling gas enters the fourth cavity 2022 through the fourth inlet 2042 to cool the blade body 10. The turbine vane 100 of the embodiment of the present application divides the second cooling cavity 202 into the third cavity 2021 and the fourth cavity 2022 along the chord direction of the blade body 10 by arranging the second partition plate 402 in the second cooling cavity 202, and respectively supplies cooling gas to the third cavity 2021 and the fourth cavity 2022 to cool the blade body 10, which further facilitates the uniformity of the distribution of the cooling gas in the chord direction of the blade body 10, thereby further improving the uniformity of the distribution of the cooling gas in the blade body 10 and further improving the reliability of the turbine vane 100.

[0075] In some embodiments, the turbine vane 100 of the embodiment of the present application further comprises a first sealing plate 501 arranged at the second inlet 2032 to block part of the second inlet 2032, and a third partition plate 403 arranged in the second cavity 2012 and extending in the height direction of the blade body 10. One end of the third partition plate 403 in the height direction of the blade body 10 is connected to the first sealing plate 501, and the other end of the third partition plate 403 is arranged apart from the cavity wall of the first cooling cavity 201 to form a first communication port 1001. The first partition plate 401, the third partition plate 403 and the blade body 10 define a first passage 601, and the first sealing plate 501, the third partition plate 403 and the blade body 10 define a second passage 602, and the first passage 601 and the second passage 602 are communicated through the first communication port 1001.

[0076] For example, as shown in Figure 3 and Figure 4 The first sealing plate 501 extends in the left-right direction, and the third partition plate 403 extends in the up-down direction. The third partition plate 403 is located on the left side of the first sealing plate 501, the left end of the first sealing plate 501 is connected to the upper end of the third partition plate 403, and the right end of the first sealing plate 501 is connected to the cavity wall of the first cavity 2011. The lower end of the third partition plate 403 is arranged apart from the middle partition plate 407 to form the first communication port 1001, and the first passage 601 is located on the left side of the second passage 602.

[0077] In use, the transparent flat vane 100 of this embodiment of the invention allows cooling gas to enter the first channel 601 through the second inlet 2032. The cooling gas in the first channel 601 flows downward and enters the second channel 602 through the first connecting port 1001. The cooling gas then flows upward in the second channel 602.

[0078] Therefore, the transparent flat vane 100 of this embodiment divides the second chamber 2012 into a first channel 601 and a second channel 602. This ensures that after the cooling gas enters the first channel 601, it is first cooled near the central partition 407. At this time, the amount of cooling gas is relatively large, and the temperature rise of the cooling gas is relatively small. This allows for better cooling of the central part of the cooling blade body 10 where the temperature is relatively high. Then, it flows upward through the second channel 602 to cool other parts. In addition, it is beneficial to increase the residence time of the cooling gas in the second chamber 2012, which helps to improve the utilization rate of the cooling gas and reduce the waste of cooling gas.

[0079] In some embodiments, the transparent cooling blade 100 of the present invention further includes a second sealing plate 502 and a fourth partition plate 404. The second sealing plate 502 is disposed at the fourth inlet 2042 to block part of the fourth inlet 2042. The fourth partition plate 404 is disposed in the fourth chamber 2022 and extends along the height direction of the blade body 10. One end of the fourth partition plate 404 in the height direction of the blade body 10 is connected to the second sealing plate 502. The other end of the fourth partition plate 404 is spaced apart from the cavity wall of the second cooling chamber 202 to form a second communication port 1002. A third channel 603 is defined between the second partition plate 402, the fourth partition plate 404 and the blade body 10. The third channel 603 and the fourth channel 604 are connected through the second communication port 1002.

[0080] For example, such as Figure 3 and Figure 4 As shown, the second sealing plate 502 extends in the left-right direction, and the fourth partition 404 extends in the up-down direction. The fourth partition 404 is located to the left of the second sealing plate 502. The left end of the second sealing plate 502 is connected to the lower end of the fourth partition 404, and the right end of the second sealing plate 502 is connected to the cavity wall of the first chamber 2011. The upper end of the fourth partition 404 and the middle partition 407 are spaced apart to form a second communication port 1002, and the third channel 603 is located to the left of the fourth channel 604.

[0081] In use, the transparent flat vane 100 of this embodiment of the invention allows cooling gas to enter the third channel 603 through the fourth inlet 2042. The cooling gas in the third channel 603 flows upward and enters the fourth channel 604 through the second connecting port 1002. The cooling gas then flows downward in the fourth channel 604.

[0082] Thus, the turbine vane 100 of the embodiment of the present application divides the fourth chamber 2022 into the third passage 603 and the fourth passage 604, which can ensure that the cooling gas entering the third passage 603 first cools the middle part near the middle partition plate 407, at this time, the amount of cooling gas is large, the temperature rise of the cooling gas is small, and the middle part of the cooling blade body 10 can be better cooled, and then the cooling gas moves downward through the fourth passage 604 to cool other positions. In addition, it is also beneficial to increase the residence time of the cooling gas in the fourth chamber 2022, which is beneficial to improve the use efficiency of the cooling gas and reduce the waste of the cooling gas.

[0083] In some embodiments, the turbine vane 100 of the embodiment of the present application further comprises a plurality of fifth partition plates 405, the fifth partition plates 405 are arranged in the second passage 602 and extend along the chord direction of the blade body 10, and the plurality of fifth partition plates 405 are arranged in the height direction of the blade body 10. The plurality of fifth partition plates 405 define a first serpentine passage in the second passage 602.

[0084] For example, as shown in Figure 3 and Figure 4 , the fifth partition plate 405 has two, and the two fifth partition plates 405 are arranged in the up-down direction to define a first serpentine passage in the second passage 602. By defining a first serpentine passage in the second passage 602, it is beneficial to increase the flow path of the cooling gas in the second passage 602, which is beneficial to further increase the residence time of the cooling gas in the second chamber 2012, which is beneficial to further improve the utilization rate of the cooling gas and reduce the waste of the cooling gas.

[0085] In some embodiments, the turbine vane 100 of the embodiment of the present application further comprises a plurality of sixth partition plates 406, the sixth partition plates 406 are arranged in the fourth passage 604 and extend along the chord direction of the blade body 10, and the plurality of sixth partition plates 406 are arranged in the height direction of the blade body 10. The plurality of sixth partition plates 406 define a second serpentine passage in the fourth passage 604.

[0086] For example, as shown in Figure 3 and Figure 4 , the sixth partition plate 406 has two, and the two sixth partition plates 406 are arranged in the up-down direction to define a second serpentine passage in the fourth passage 604. By defining a second serpentine passage in the fourth passage 604, it is beneficial to increase the flow path of the cooling gas in the fourth passage 604, which is beneficial to further increase the residence time of the cooling gas in the fourth chamber 2022, which is beneficial to further improve the utilization rate of the cooling gas and reduce the waste of the cooling gas.

[0087] In some embodiments, the blade body 10 of the transparent flat blade 100 of the present invention has a leading edge 102 and a trailing edge 103 opposite each other in the chordal direction, and a first chamber 2011 is disposed closer to the leading edge 102 in the chordal direction of the blade body 10 relative to a second chamber 2012.

[0088] For example, such as Figure 4 As shown, the first chamber 2011 is located to the left of the second chamber 2012. It is understood that during operation, the temperature at the mid-chord position of the blade body 10 (located between the leading edge 102 and the trailing edge 103) is higher than the temperature at the leading edge 102 and the trailing edge 103. By placing the first chamber 2011 to the left of the second chamber 2012, the second chamber 2012, which has multiple channels, is located at the mid-chord position of the blade body 10. This further improves the cooling effect on the blade body 10, enhances the uniformity of temperature distribution on the blade body, and improves the reliability of the turbine blade 100.

[0089] In some embodiments, the third chamber 2021 is disposed closer to the leading edge 102 in the chordal direction of the blade body 10 than the fourth chamber 2022.

[0090] For example, such as Figure 4 As shown, the third chamber 2021 is located to the left of the fourth chamber 2022. By placing the third chamber 2021 to the left of the fourth chamber 2022, the fourth chamber 2022, which has multiple channels, is located at the mid-chord position of the blade body 10. This is beneficial to further improve the cooling effect on the blade body 10, further improve the temperature distribution uniformity of the blade body, and further improve the reliability of the transparent flat blade 100.

[0091] In some embodiments, the first partition 401 and the second partition 402 are aligned chordally on the blade body 10.

[0092] like Figure 4 As shown, the first partition 401 and the second partition 402 are arranged in the left-right direction. By aligning the first partition 401 and the second partition 402 in the left-right direction, the internal volumes of the first chamber 2011 and the third chamber 2021 are the same, and the internal volumes of the second chamber 2012 and the fourth chamber 2022 are equal. This allows the cooling gas entering the first chamber 2011 and the third chamber 2021 to produce the same impact cooling effect on the blade body 1, and the cooling gas entering the second chamber 2012 and the fourth chamber 2022 to produce the same impact cooling effect on the blade body 1. This is beneficial for maintaining a consistent impact cooling effect of the cooling gas in different chambers on the blade body 1, and for ensuring a uniform surface temperature distribution of the transparent flat blade 100 of the present invention.

[0093] Optionally, the first partition 401 and the second partition 402 are an integral structure.

[0094] The transparent flat blade 100 of this embodiment of the invention has an integrated structure of the first partition 401 and the second partition 402, which is beneficial to the processing and manufacturing of the blade body 10.

[0095] Optionally, the dimension of the first cooling chamber 201 in the height direction of the blade body 10 is equal to the dimension of the second cooling chamber 202 in the height direction of the blade body 10.

[0096] like Figure 5 As shown, the dimension of the first cooling chamber 201 in the height direction of the blade body 10 is equal to the dimension of the second cooling chamber 202 in the height direction of the blade body 10. That is, the middle partition 407 is arranged in the middle position of the blade body 1 in the vertical direction, which is beneficial for the cooling gas accumulated at the bottom of the first cooling chamber 201 and the second cooling chamber 202 to cool the middle position of the blade body 10, which is beneficial to further improve the cooling effect of the transparent flat blade 100 of the present invention and further improve the reliability of the transparent flat blade 100.

[0097] In some embodiments, the blade body 1 is provided with a trailing edge slit 104, which communicates with the annular chamber 3 so that the cooling gas in the annular chamber 3 can be discharged through the trailing edge slit 104.

[0098] like Figure 2 As shown, the cooling gas entering the annular cavity 101 flows out through the trailing edge slit 104. The cooling gas flowing out through the trailing edge slit 104 can cover the outer surface of the trailing edge 103 to form a gas film, effectively avoiding direct contact between the trailing edge 103 and the high-temperature mainstream, thereby preventing the temperature of the trailing edge 103 from becoming too high. This is beneficial to improving the power and efficiency of the gas turbine with the embodiment of the present invention and maintaining its safe and stable operation.

[0099] Optionally, the trailing edge slit 104 forms a first vent and a second vent to discharge cooling gas entering the cooling chamber through the first inlet 203 and the second inlet 204.

[0100] In some embodiments, the transparent flat blade 100 of the present invention further includes a seventh partition 701, which is disposed in the cavity 101. The seventh partition 701 extends along the height direction of the blade body 10 to divide the cavity 101 into a mounting cavity 1011 and a trailing edge cooling cavity 1012. The mounting cavity 1011 is disposed in the chordal direction of the blade body 10, which is closer to the leading edge 102 than the trailing edge cooling cavity 1012. The bushing 2 is disposed in the mounting cavity 1011. The trailing edge slit 104 communicates with the trailing edge cooling cavity 1012. The seventh partition 701 is provided with a second jet hole 7011 extending along the chordal direction of the blade body 10.

[0101] like Figure 5 and Figure 2 As shown, the seventh partition 701 extends in the vertical direction, dividing the cavity 101 into an installation cavity 1011 and a trailing edge cooling cavity 1012 arranged at intervals in the left and right directions. The installation cavity 1011 is located on the left side of the trailing edge cooling cavity 1012. The cooling gas in the annular cavity 101 enters the trailing edge cooling cavity 1012 through the second jet hole 7011 to impact and cool the trailing edge 103, which is beneficial to improving the cooling effect at the trailing edge 103.

[0102] In some embodiments, the transparent flat blade 100 of the present invention further includes an eighth partition 702, which is disposed in the trailing edge cooling cavity 1012. The eighth partition 702 extends along the height direction of the blade body 10 to divide the trailing edge cooling cavity 1012 into a first cooling portion 10121 and a second cooling portion 10122. The first cooling portion 10121 is disposed in the chordal direction of the blade body 10 closer to the leading edge 102 than the second cooling portion 10122. The trailing edge slit 104 communicates with the second trailing edge cooling cavity 1012. The eighth partition 702 is provided with a third jet hole 7021 extending along the chordal direction of the blade body 10.

[0103] like Figure 5 and ​ As shown, the eighth partition 702 extends vertically, dividing the trailing edge cooling chamber 1012 into a first cooling section 10121 and a second cooling section 10122 arranged at intervals in the left-right direction. The first cooling section 10121 is located to the left of the first cooling section 10121. The cooling gas in the annular cavity 101 enters the first cooling section 10121 through the second jet hole 7011 to impact and cool the trailing edge 103, and then enters the second cooling section 10122 through the third jet hole 7021 to perform secondary impact cooling on the trailing edge 103. This is beneficial for further improving the power and efficiency of the gas turbine with the transparent flat blade 100 of the present invention and maintaining its safe and stable operation.

[0104] Optionally, the second trailing edge cooling cavity 1012 is provided with a plurality of heat dissipation columns 8, and the plurality of heat dissipation columns are evenly spaced along the vertical direction.

[0105] Because the cooling gas entering the second cooling section 10122 from the third jet hole 7021 has a relatively high velocity, the cooling gas entering the second cooling section 10122 passes through the heat dissipation column 8 in a convective manner, reducing the closed vortex near the trailing edge 103, thereby reducing the pressure loss of the cooling gas and ensuring that this part of the cooling gas can flow out through the trailing edge slit 104 to achieve cooling of the trailing edge 103.

[0106] Optionally, the turbine vane 100 of the embodiment of the present application further comprises an upper end wall 901 and a lower end wall 902 which are arranged in the up-down direction and are spaced apart, the upper end wall 901 is located on the upper side of the lower end wall 902, the upper end wall 901 is connected to the upper end of the vane body 1, and the lower end wall is connected to the lower end of the vane body 1.

[0107] The turbine of the embodiment of the present application comprises the turbine vane 100 described in any one of the above embodiments.

[0108] The turbine of the embodiment of the present application has the advantages of high operation reliability.

[0109] The gas turbine of the embodiment of the present application comprises the turbine described in any one of the above embodiments.

[0110] The gas turbine of the embodiment of the present application has the advantages of high operation reliability.

[0111] In the description of the present application, it should be understood that the orientations or positional relationships indicated by the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements indicated must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0112] In addition, the terms "first", "second", "third", etc. are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features defined with "first", "second", etc. can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "a plurality of" is at least two, for example, two, three, etc., unless otherwise specifically limited.

[0113] In the present application, unless otherwise specifically defined and limited, the terms "mounting", "connecting", "connecting", "fixing" and the like should be understood in a broad sense, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected or in communication with each other; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the internal communication or interaction relationship of two elements, unless otherwise specifically limited. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0114] In the present application, unless specifically stated and limited otherwise, a first feature "on" or "under" a second feature can be directly in contact with the second feature, or indirectly in contact with the second feature through an intermediate medium. Also, a first feature "over", "above" and "on top of" a second feature can be directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature "under", "below" and "underneath" a second feature can be directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0115] In the present application, the terms "one embodiment", "some embodiments", "an example", "a specific example", or "some examples" mean that a particular feature, structure, material or characteristic is included in at least one embodiment or example of the present application. Exemplary representations of the above terms in the present specification are not necessarily directed to the same embodiment or example. Also, the described specific features, structures, materials or characteristics can be combined in any suitable manner in any one or more embodiments or examples. In addition, different embodiments or examples described in the present specification and features of different embodiments or examples can be combined and combined by those skilled in the art without contradiction.

[0116] Although the above embodiments have been shown and described, it is to be understood that the above embodiments are exemplary, and are not to be construed as limiting the present application, and changes, modifications, replacements and variations of the above embodiments made by those skilled in the art are within the scope of the present application.

Claims

1. An impact-type transparent blade suitable for top and bottom air intakes of a gas turbine, characterized in that, include: The blade body has a first cooling chamber and a second cooling chamber spaced apart in its height direction. The blade body also has a first air inlet and a second air inlet, wherein the first air inlet is connected to the first cooling chamber and the second air inlet is connected to the second cooling chamber. The first partition is disposed in the first cooling cavity and extends along the height direction of the blade body. The first partition divides the first cooling cavity into a first chamber and a second chamber arranged along the chord direction of the blade body. There are multiple first air inlets. A portion of the multiple first air inlets is a first inlet, which communicates with the first chamber. Another portion of the multiple air inlets is a second inlet, which communicates with the second chamber. The second partition is disposed in the second cooling chamber and extends along the height direction of the blade body. The second partition divides the second cooling chamber into a third chamber and a fourth chamber arranged along the chord direction of the blade body. There are multiple second air inlets. A portion of the multiple second air inlets is a third inlet, which communicates with the third chamber. Another portion of the multiple second air inlets is a fourth inlet, which communicates with the fourth chamber. A first sealing plate and a third partition plate are provided. The first sealing plate is located at the second inlet to block part of the second inlet. The third partition plate is located in the second chamber and extends along the height direction of the blade body. One end of the third partition plate in the height direction of the blade body is connected to the first sealing plate. The other end of the third partition plate is spaced apart from the cavity wall of the first cooling chamber to form a first communication port. A first channel is defined between the first partition plate, the third partition plate and the blade body. A second channel is defined between the first sealing plate, the third partition plate and the blade body. The first channel and the second channel are connected through the first communication port. A second sealing plate and a fourth partition plate are provided. The second sealing plate is disposed at the fourth inlet to block part of the fourth inlet. The fourth partition plate is disposed in the fourth chamber and extends along the height direction of the blade body. One end of the fourth partition plate in the height direction of the blade body is connected to the second sealing plate. The other end of the fourth partition plate is spaced apart from the cavity wall of the second cooling chamber to form a second communication port. A third channel is defined between the second partition plate, the fourth partition plate, and the blade body. The third channel and the fourth channel are connected through the second communication port.

2. The impact-type transparent blade suitable for upper and lower air intakes of a gas turbine according to claim 1, characterized in that, Also includes: Multiple fifth partitions are disposed in the second channel and extend along the chord of the blade body. The multiple fifth partitions are arranged at intervals along the height direction of the blade body. The multiple fifth partitions define the second channel into a first serpentine channel. And / or, Multiple sixth partitions are disposed within the fourth channel and extend along the chord of the blade body. The multiple sixth partitions are spaced apart along the height direction of the blade body, and the multiple sixth partitions define the fourth channel into a second serpentine channel.

3. The impact-type transparent blade suitable for upper and lower air intakes of a gas turbine according to claim 2, characterized in that, The blade body has a leading edge and a trailing edge opposite each other in its chordal direction; The first chamber is disposed closer to the leading edge of the blade body in the chordal direction than the second chamber, and / or The third chamber is located closer to the leading edge of the blade body in the chordal direction than the fourth chamber.

4. The impingement-type transparent blade for upper and lower air intake of a gas turbine according to any one of claims 2-3, characterized in that, The first baffle and the second baffle are aligned chordally on the blade body.

5. The impact-type transparent blade suitable for upper and lower air intakes of a gas turbine according to claim 4, characterized in that, The first partition and the second partition are an integral structure.

6. The impingement-type transparent blade for upper and lower air intake of a gas turbine according to any one of claims 1-3, characterized in that, The dimension of the first cooling cavity in the height direction of the blade body is equal to the dimension of the second cooling cavity in the height direction of the blade body.

7. The impingement-type transparent blade for upper and lower air intake of a gas turbine according to any one of claims 1-2, characterized in that, The blade body has a cooling chamber, and the transparent flat blade also includes a central partition. The central partition extends along the chord of the blade body and is disposed in the cooling chamber, dividing the cooling chamber into a first cooling chamber and a second cooling chamber.

8. The impingement-type transparent blade for upper and lower air intake of a gas turbine according to claim 7, characterized in that, The blade body includes: The blade body has a cavity; and A bushing is disposed within the cavity, defining an annular chamber between the bushing and the blade body, and defining a cooling chamber. The first air inlet and the second air inlet are both disposed on the bushing. The bushing has a plurality of first jet holes. The first cooling chamber and the annular chamber are connected through a portion of the first jet holes, and the second cooling chamber and the annular chamber are connected through another portion of the first jet holes.

9. The impact-type transparent blade for upper and lower air intake of a gas turbine according to claim 8, characterized in that, The blade body has a leading edge and a trailing edge opposite each other in its chord direction. The blade body is provided with a trailing edge slit, which communicates with the annular chamber so that the cooling gas in the annular chamber can be discharged through the trailing edge slit.

10. The impact-type transparent blade for upper and lower air intake of a gas turbine according to claim 9, characterized in that, Also includes: A seventh partition is disposed within the cavity. The seventh partition extends along the height direction of the blade body to divide the cavity into an installation cavity and a trailing edge cooling cavity. The installation cavity is disposed closer to the leading edge of the blade body in the chordal direction than the trailing edge cooling cavity. The bushing is disposed within the installation cavity. The trailing edge slit communicates with the trailing edge cooling cavity. The seventh partition is provided with a second jet hole extending along the chordal direction of the blade body.

11. The impingement-type transparent blade suitable for upper and lower air intakes of a gas turbine according to claim 10, characterized in that, Also includes: The eighth partition is disposed in the trailing edge cooling cavity. The eighth partition extends along the height direction of the blade body to divide the trailing edge cooling cavity into a first cooling part and a second cooling part. The first cooling part is disposed in the chordal direction of the blade body closer to the leading edge than the second cooling part. The trailing edge slit communicates with the second cooling part. The eighth partition is provided with a third jet hole extending along the chordal direction of the blade body.

12. The impact-type transparent blade suitable for upper and lower air intakes of a gas turbine according to claim 11, characterized in that, The second cooling section is provided with multiple heat dissipation columns.

13. A turbine, characterized in that, Includes the permeable stoker blades suitable for the upper and lower air intakes of a gas turbine, as described in any one of claims 1-12.

14. A gas turbine, characterized in that, Including the turbine as described in claim 13.

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