High-pressure turbine air-cooled working blade and gas turbine engine

Abstract

The utility model provides a high-pressure turbine air-cooled working blade and a gas turbine engine. The high-pressure turbine air-cooled working blade comprises a blade body which forms the outer contour of the high-pressure turbine working blade and is internally hollow to form a blade body cavity; the partition plates extend in the radial direction of the blade body, the partition plates comprise three circumferential partition plates, the three circumferential partition plates are sequentially arranged at intervals in the direction from the front edge of the blade body to the tail edge of the blade body, and a cavity of the blade body is divided into four independent cooling flow paths; the four cooling flow paths comprise the front cooling flow path, the middle front cooling flow path, the middle rear cooling flow path and the tail cooling flow path which are sequentially arranged from the front edge of the blade body to the tail edge of the blade body, and the utilization efficiency of inner cooling gas is improved.

Description

Technical Field

[0001] The present application relates to the technical field of gas turbine engines, and particularly to a high-pressure turbine air-cooled working blade and a gas turbine engine. Background Art

[0002] During the operation of a gas turbine engine, air enters the compressor and is compressed stage by stage to convert the air into high-pressure gas, which is then sent into the combustion chamber, and the compressed air is heated to form high-temperature gas. The high-temperature and high-pressure gas entering the high-pressure turbine passes through the turbine blades of each stage in turn, driving the entire high-pressure turbine to rotate and providing power for the high-pressure compressor.

[0003] Increasing the inlet temperature of the high-pressure turbine is an important means to improve the performance of a gas turbine engine. At present, the turbine inlet temperature has exceeded the allowable temperature of the blade material. Therefore, using air-cooling technology to cool the blades is an important means to increase the working temperature of the turbine blades.

[0004] Currently, the cooling technologies for turbine blades include enhanced heat transfer cooling technologies such as film cooling, impingement cooling, and convection cooling. Film cooling is a cooling technology in which cooling air is ejected from the film holes on the blade surface to cover the blade surface, isolating the solid wall surface from the high-temperature gas. Impingement cooling is an efficient cooling technology in which the impinging air flow jets on the inner wall surface of the blade. Convection cooling is a cooling method in which the cooling gas is directly introduced into the blade interior. High-pressure turbine blades usually adopt a compound cooling method. The high-pressure turbine working blades usually use a serpentine channel to distribute cooling holes throughout the interior space of the blade, and various microstructures are often arranged in the internal cooling channels to enhance the heat transfer on the inner surface. However, with the current arrangement of the serpentine channel, the utilization ability of the cooling gas in the channel is insufficient, resulting in a low internal heat transfer efficiency.

[0005] The above statements are only used to provide background technical information related to the present application, and do not necessarily constitute prior art. Summary of the Utility Model

[0006] The purpose of the present application is to provide a high-pressure turbine air-cooled working blade, aiming to improve the cooling effect of the high-pressure turbine air-cooled working blade.

[0007] The first aspect of the present application provides a high-pressure turbine air-cooled working blade, including:

[0008] A blade body, the blade body forming the outer contour of the high-pressure turbine air-cooled working blade and having a hollow interior to form a blade body cavity; and

[0009] Multiple partition plates, the partition plates extending radially along the blade body, the multiple partition plates including three circumferential partition plates, the three circumferential partition plates being arranged at intervals in sequence along the direction from the leading edge of the blade body to the trailing edge of the blade body, and dividing the blade body cavity into four independent cooling flow paths, the four cooling flow paths including a front cooling flow path, a middle front cooling flow path, a middle rear cooling flow path, and a tail cooling flow path arranged in sequence from the leading edge of the blade body to the trailing edge of the blade body.

[0010] In the high-pressure turbine air-cooled working blade of some embodiments, in the three independent cooling flow paths of the front cooling flow path, the middle front cooling flow path, and the middle rear cooling flow path, each of the cooling flow paths has at least three cooling cavities separated by at least two of the partition plates.

[0011] In the high-pressure turbine air-cooled working blade of some embodiments, each of the front cooling flow path, the middle front cooling flow path, and the middle rear cooling flow path includes at least two cooling cavities in which only one side channel wall is formed by the side wall of the blade body.

[0012] In the high-pressure turbine air-cooled working blade of some embodiments, the multiple partition plates further include a plurality of front inner partition plates, the plurality of front inner partition plates dividing the front cooling flow path into four front cooling cavities extending radially, the four front cooling cavities including a first front cooling cavity near the leading edge side, a second front cooling cavity near the pressure surface of the blade body located between the first front cooling cavity and the middle front cooling flow path, a third front cooling cavity near the suction surface of the blade body located between the first front cooling cavity and the middle front cooling flow path, and a fourth front cooling cavity arranged in sequence from the leading edge of the blade body to the trailing edge of the blade body; wherein,

[0013] A front air inlet hole for high-pressure cooling gas to enter is provided on the radial inner side of the second front cooling cavity;

[0014] The second front cooling cavity and the third front cooling cavity have a communication hole on the radial outer side of the blade body;

[0015] The third front cooling cavity and the fourth front cooling cavity have a communication hole on the radial inner side of the blade body;

[0016] A leading edge impingement cooling hole is provided on the front inner partition plate located between the first front cooling cavity and the second front cooling cavity, and the leading edge impingement cooling hole is configured to spray high-pressure cooling gas towards the inner wall of the blade body forming the channel wall of the first front cooling cavity;

[0017] The blade body of the channel wall forming the second front cooling cavity is provided with first front film holes;

[0018] The blade body of the channel wall forming the first front cooling cavity is provided with second front film holes;

[0019] The blade body of the channel wall forming the fourth front cooling cavity is provided with third front film holes.

[0020] In the high-pressure turbine air-cooled working blades of some embodiments,

[0021] Multiple said first front film holes form at least one set of first front film holes distributed radially along the blade body; and / or

[0022] Multiple said second front film holes form at least one set of second front film holes distributed radially along the blade body, and the at least one set of second front film holes includes at least one of a first set of second front film holes, a second set of second front film holes, and a third set of second front film holes; wherein, the first set of second front film holes is arranged on the pressure surface near the leading edge, the second set of second front film holes is arranged on the leading edge, and the third set of second front film holes is arranged on the suction surface near the leading edge; and / or

[0023] Multiple said third front film holes form at least one set of third front film holes distributed radially along the blade body.

[0024] In the high-pressure turbine air-cooled working blades of some embodiments, the multiple partition plates further include multiple middle front inner partition plates, and the multiple middle front inner partition plates divide the middle front cooling flow path into three middle front cooling cavities extending radially. The three middle front cooling cavities include a first middle front cooling cavity near the trailing edge, a second middle front cooling cavity located on the side of the first middle front cooling cavity close to the front cooling flow path and close to the suction surface of the blade body, and a third middle front cooling cavity located on the side of the first middle front cooling cavity close to the front cooling flow path and close to the pressure surface of the blade body; wherein,

[0025] A middle front inlet hole for high-pressure cooling gas to enter is provided on the radial inner side of the first middle front cooling cavity;

[0026] The first middle front cooling cavity and the second middle front cooling cavity have a communication hole on the radial outer side of the blade body;

[0027] The second middle front cooling cavity and the third middle front cooling cavity have a communication hole on the radial inner side of the blade body;

[0028] The blade body forming the channel wall of the front-middle cooling cavity of the third part is provided with front-middle film holes.

[0029] In the high-pressure turbine air-cooled working blades of some embodiments, multiple ones of the front-middle film holes form at least one group of front-middle film holes distributed radially along the blade body.

[0030] In the high-pressure turbine air-cooled working blades of some embodiments, the multiple partition plates further include multiple rear-middle inner partition plates, and the multiple rear-middle inner partition plates divide the rear-middle cooling flow path into three rear-middle cooling cavities extending radially. The three rear-middle cooling cavities include a first rear-middle cooling cavity close to the tail cooling flow path, a second rear-middle cooling cavity located between the first front-middle cooling cavity and the first rear-middle cooling cavity and close to the suction surface, and a third rear-middle cooling cavity located between the first front-middle cooling cavity and the first rear-middle cooling cavity, on the leading edge side and close to the pressure surface; wherein,

[0031] A rear-middle air inlet hole for high-pressure cooling gas to enter is provided on the radially inner side of the first rear-middle cooling cavity;

[0032] The first rear-middle cooling cavity and the second rear-middle cooling cavity have a communication hole on the radially outer side of the blade body;

[0033] The second rear-middle cooling cavity and the third rear-middle cooling cavity have a communication hole on the radially inner side of the blade body;

[0034] The blade body forming the channel wall of the third rear-middle cooling cavity is provided with rear-middle film holes.

[0035] In the high-pressure turbine air-cooled working blades of some embodiments, multiple ones of the rear-middle film holes form at least one group of rear-middle film holes distributed radially along the blade body.

[0036] In the high-pressure turbine air-cooled working blades of some embodiments,

[0037] A first tail film hole is provided on the pressure surface of the blade body forming the cavity wall of the tail cooling flow path; and / or

[0038] A split structure is provided on the trailing edge of the blade body forming the cavity wall of the tail cooling flow path.

[0039] The second aspect of the present application provides a gas turbine engine, including a high-pressure turbine, and the high-pressure turbine working blade as described in the first aspect of the present application.

[0040] Based on the high-pressure turbine air-cooled working blade provided by the present application, the blade body cavity of the blade body is separated into four independent front cooling flow paths, middle front cooling flow paths, middle rear cooling flow paths, and tail cooling flow paths arranged in sequence from the leading edge to the trailing edge of the blade body by three circumferential partition plates. This is conducive to setting the cooling flow paths of each cooling flow path according to the cooling requirements of the positions where each cooling flow path is located, improving the utilization efficiency of the internal cooling gas, and thus improving the cooling effect of the high-pressure turbine air-cooled working blade.

[0041] The gas turbine engine provided by the present application has the advantages of the high-pressure turbine working blade provided by the present application.

[0042] Through the following detailed description of the exemplary embodiments of the present application with reference to the accompanying drawings, other features and advantages of the present application will become clear. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The exemplary embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation of the present application. In the drawings:

[0044] Figure 1 is a schematic structural diagram of the high-pressure turbine air-cooled working blade of the embodiment of the present application.

[0045] Figure 2 is a schematic cross-sectional structural diagram of the high-pressure turbine air-cooled working blade of the embodiment of the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0046] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and in no way restricts the present application and its application or use. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present application.

[0047] Unless otherwise specifically stated, the relative arrangements, numerical expressions, and numerical values of the components and steps set forth in these embodiments do not limit the scope of the present application. At the same time, it should be understood that, for the sake of convenience of description, the dimensions of the various parts shown in the drawings are not drawn in actual proportional relationships. Technologies, methods, and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, the said technologies, methods, and devices should be regarded as part of the description. In all the examples shown and discussed here, any specific values should be construed as merely exemplary and not as a limitation. Therefore, other examples of the exemplary embodiments may have different values. It should be noted that like reference numerals and letters denote like items in the following drawings, and thus, once an item is defined in one drawing, it does not need to be further discussed in subsequent drawings.

[0048] In the description of the present application, it should be understood that the use of terms such as "first" and "second" to limit components is only for the convenience of differentiating the corresponding components. Without further statement, the above terms have no special meaning and thus should not be construed as limiting the scope of protection of the present application.

[0049] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the orientation terms is generally based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present application and simplifying the description. Without contrary description, these orientation terms do not indicate and imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation. Therefore, it should not be construed as limiting the scope of protection of the present application; the orientation terms "inside" and "outside" refer to the inside and outside relative to the contour of each component itself.

[0050] In addition, the technical features involved in different embodiments of the present application described below can be combined with each other as long as they do not conflict with each other.

[0051] The "axial direction" in the present application refers to the direction along the axis of the gas turbine engine of the high-pressure turbine air-cooled working blade, the "radial direction" refers to the direction extending from the central axis of the gas turbine engine to the outer periphery of the gas turbine engine, that is, the radial direction of the high-pressure turbine air-cooled working blade and its blade body, and the "circumferential direction" is the direction perpendicular to both the "axial direction" and the "radial direction" at the same time.

[0052] As Figure 1 and Figure 2 shown, an embodiment of the present application provides a high-pressure turbine air-cooled working blade (also referred to as a working blade).

[0053] The high-pressure turbine air-cooled working blade 1 includes a blade body 101 and a plurality of partitions 102.

[0054] The blade body 101 forms the external contour of the high-pressure turbine air-cooled working blade and is hollow inside to form a blade body cavity.

[0055] The partition plates 102 extend radially along the blade body 101. Multiple partition plates 102 include three circumferential partition plates. The three circumferential partition plates are arranged at intervals in sequence along the direction from the leading edge 4 of the blade body 101 to the trailing edge 5 of the blade body 101, dividing the blade body cavity into four independent cooling flow paths. The four cooling flow paths include a front cooling flow path, a middle-front cooling flow path, a middle-rear cooling flow path, and a tail cooling flow path K arranged in sequence from the leading edge 4 of the blade body 101 to the trailing edge 5 of the blade body 101.

[0056] In the high-pressure turbine air-cooled working blade according to the embodiment of the present application, the blade body cavity of the blade body 101 is divided into a front cooling flow path, a middle-front cooling flow path, a middle-rear cooling flow path, and a tail cooling flow path K that are independent of each other and are arranged in sequence from the leading edge 4 of the blade body 101 to the trailing edge 5 of the blade body 101 by three circumferential partition plates, which is beneficial to setting the cooling flow paths of each cooling flow path according to the cooling requirements of the positions where each cooling flow path is located, improving the utilization efficiency of the internal cooling gas, and thus improving the cooling effect of the high-pressure turbine air-cooled working blade 1.

[0057] As Figure 1 and Figure 2 shown, in the high-pressure turbine air-cooled working blade of some embodiments, in each of the three independent cooling flow paths of the front cooling flow path, the middle-front cooling flow path, and the middle-rear cooling flow path, each cooling flow path has at least three cooling cavities separated by at least two partition plates 102.

[0058] This setting is beneficial to reasonably organize the internal flow channels in the corresponding cooling cavities, providing different cooling fluid passing sequences for different blade cooling parts with different cooling requirements, so that different blade cooling parts obtain reasonable cooling effects.

[0059] As Figure 1 and Figure 2 shown, in the high-pressure turbine air-cooled working blade of some embodiments, in each of the front cooling flow path, the middle-front cooling flow path, and the middle-rear cooling flow path, each cooling flow path includes at least two cooling cavities in which only one side channel wall is formed by the side wall of the blade body 101.

[0060] This setting is beneficial to setting appropriate cooling methods for the side walls of different parts of the blade body 101 in the high-temperature area of the working blade 1 to improve the cooling effect of the working blade 1.

[0061] As Figure 1 and Figure 2As shown, in the high-pressure turbine air-cooled working blades of some embodiments, multiple partitions 102 further include multiple front inner partitions. The multiple front inner partitions divide the front cooling flow path into four front cooling chambers extending radially. The four front cooling chambers include a first front cooling chamber A near the leading edge 4, a second front cooling chamber B near the pressure surface 2 of the blade body 101 located between the first front cooling chamber A and the front cooling flow path near the middle, a third front cooling chamber C and a fourth front cooling chamber D arranged in sequence from the leading edge 4 to the trailing edge 5 of the blade body 101 near the suction surface 3 of the blade body 101 and located between the first front cooling chamber A and the front cooling flow path near the middle.

[0062] A front air inlet hole for the entry of high-pressure cooling gas is provided on the radially inner side of the second front cooling chamber B.

[0063] The second front cooling chamber B and the third front cooling chamber C have a communication hole on the radially outer side of the blade body 101.

[0064] The third front cooling chamber C and the fourth front cooling chamber D have a communication hole on the radially inner side of the blade body 101.

[0065] Leading edge impingement cooling holes 11 are provided on the front inner partition located between the first front cooling chamber A and the second front cooling chamber B, and the leading edge impingement cooling holes 11 are configured to spray high-pressure cooling gas towards the inner wall of the blade body 101 of the channel wall forming the first front cooling chamber A.

[0066] First front film holes are provided on the blade body 101 of the channel wall forming the second front cooling chamber B.

[0067] Second front film holes are provided on the blade body 101 of the channel wall forming the first front cooling chamber A.

[0068] Third front film holes are provided on the blade body 101 of the channel wall forming the fourth front cooling chamber D.

[0069] Through the above structural design of the front cooling flow path, efficient cooling of the leading edge portion of the working blade 1 can be achieved.

[0070] Such as Figure 1 and Figure 2As shown, in the high-pressure turbine air-cooled working blade 1 of some embodiments, the multiple partitions 102 further include multiple front-middle inner partitions. The multiple front-middle inner partitions divide the front-middle cooling flow path into three front-middle cooling cavities extending radially. The three front-middle cooling cavities include a first front-middle cooling cavity E near the trailing edge 5, a second front-middle cooling cavity F located on the side of the first front-middle cooling cavity E near the front cooling flow path and near the suction surface 3 of the blade body 101, and a third front-middle cooling cavity G located on the side of the first front-middle cooling cavity E near the front cooling flow path and near the pressure surface 2 of the blade body 101.

[0071] A front-middle air inlet hole for the entry of high-pressure cooling gas is provided on the radially inner side of the first front-middle cooling cavity E.

[0072] The first front-middle cooling cavity E and the second front-middle cooling cavity F have a communication hole on the radially outer side of the blade body 101.

[0073] The second front-middle cooling cavity F and the third front-middle cooling cavity G have a communication hole on the radially inner side of the blade body 101.

[0074] Middle-front film holes 66 are provided on the blade body 101 forming the channel wall of the third front-middle cooling cavity G.

[0075] Through the above structural design of the front-middle cooling flow path, efficient cooling of the front-middle part of the working blade 1 can be achieved.

[0076] As Figure 1 and Figure 2 shown, in the high-pressure turbine air-cooled working blade 1 of some embodiments, the multiple partitions 102 further include multiple rear-middle inner partitions. The multiple rear-middle inner partitions 102 divide the rear-middle cooling flow path into three rear-middle cooling cavities extending radially. The three rear-middle cooling cavities include a first rear-middle cooling cavity H near the tail cooling flow path K, a second rear-middle cooling cavity I located between the first front-middle cooling cavity E and the first rear-middle cooling cavity H and near the suction surface 3, and a third rear-middle cooling cavity J located between the first front-middle cooling cavity E and the first rear-middle cooling cavity H and near the pressure surface 2.

[0077] A rear-middle air inlet hole for the entry of high-pressure cooling gas is provided on the radially inner side of the first rear-middle cooling cavity H.

[0078] The first rear-middle cooling cavity H and the second rear-middle cooling cavity I have a communication hole on the radially outer side of the blade body 101.

[0079] The second rear-middle cooling cavity I and the third rear-middle cooling cavity J have a communication hole on the radially inner side of the blade body 101.

[0080] The blade body 101 forming the channel wall of the third rear middle cooling cavity J is provided with rear middle film holes 67.

[0081] Through the above structural design of the rear middle cooling flow path, efficient cooling of the rear middle part of the working blade 1 can be achieved.

[0082] As Figure 1 and Figure 2 shown, in the high-pressure turbine air-cooled working blade 1 of some embodiments, the pressure surface 2 of the blade body 101 forming the cavity wall of the trailing cooling flow path K is provided with first trailing film holes; and / or the trailing edge 5 of the blade body 101 forming the cavity wall of the trailing cooling flow path K is provided with a split structure 9.

[0083] Through the above structural design of the trailing cooling flow path, efficient cooling of the trailing part of the working blade 1 can be achieved.

[0084] The embodiment of the present application also provides a gas turbine engine, including a high-pressure turbine, and the high-pressure turbine is the high-pressure turbine air-cooled working blade 1 of the embodiment of the present application.

[0085] The gas turbine engine provided by the present application has the advantages of the high-pressure turbine air-cooled working blade provided by the present application.

[0086] The following Figures 1 to 2 further describes the high-pressure turbine air-cooled working blade of the embodiment of the present application. Figure 1 is a schematic structural diagram of the high-pressure turbine air-cooled working blade of the embodiment of the present application. Figure 1 In Figure 2 is a schematic cross-sectional structural diagram of the high-pressure turbine air-cooled working blade of the embodiment of the present application.

[0087] The working blade 1 includes a pressure surface 2 and a suction surface 3. The pressure surface 2 is concave, the suction surface 3 is convex, and the pressure surface 2 and the suction surface 3 are first connected at the leading edge 4, separated axially, and then reconnected at the trailing edge 5.

[0088] As Figure 1 shown, inside the hollow blade body 101 of the high-pressure turbine air-cooled working blade, a plurality of partition plates 102 along the blade radius are arranged in sequence from the blade leading edge 4 to the blade trailing edge 5. The plurality of partition plates 102 include three circumferential partition plates 102. The three circumferential partition plates 102 divide the blade body cavity of the blade body 101 into four independent cooling flow paths. The four cooling flow paths include a front cooling flow path, a front middle cooling flow path, a rear middle cooling flow path, and a trailing cooling flow path K arranged in sequence from the leading edge 4 of the blade body 101 to the trailing edge 5 of the blade body 101. An independent cooling flow path is formed inside each cooling flow path, independent of other cooling flow paths.

[0089] Among the first three cooling flow paths from the leading edge 4 to the trailing edge 5 of the blade body 101, namely the front cooling flow path, the middle front cooling flow path, and the middle rear cooling flow path, there is a chordal partition in each to separate at least part of the space on the pressure side 2 and the suction side 3 of each cooling flow path, so that each cooling flow path in the front cooling flow path, the middle front cooling flow path, and the middle rear cooling flow path includes at least two cooling cavities with only one side channel wall formed by the side wall of the blade body 101. Among them, such cooling cavities in the front cooling flow path are the second front cooling cavity B, the third front cooling cavity C, and the fourth front cooling cavity D. Such cooling cavities in the middle front cooling flow path are the second middle front cooling cavity F and the third middle front cooling cavity G. Such cooling cavities in the middle rear cooling flow path are the third middle rear cooling cavity J and the second middle rear cooling cavity I.

[0090] The working blade 1 includes multiple groups of film holes 6. Each group of film holes 6 is radially distributed between the blade bottom 7 and the blade tip 8 along the pressure side 2 or the suction side 3, for discharging the cooling air of the high-pressure turbine air-cooled working blade 1 to cool the high-pressure turbine air-cooled working blade 1. As Figure 1 and Figure 2 shown, the multiple groups of film holes 6 include a group of first front film holes 61 communicated with the second front cooling cavity B, three groups of second front film holes 62 - 64 communicated with the first front cooling cavity A, a group of third front film holes 65 communicated with the fourth front cooling cavity D, a group of middle front film holes 66 communicated with the third middle front cooling cavity G, a group of middle rear film holes 67 communicated with the third middle rear cooling cavity J, and a group of first tail film holes 68 communicated with the tail cooling flow path K.

[0091] The high-pressure turbine air-cooled working blade 1 further includes multiple split slot structures 9. The split slot structures 9 are radially distributed at the trailing edge 5 position of the high-pressure turbine air-cooled working blade 1, and the cooling gas discharged by the split slot structures 9 cools the blade trailing edge 5.

[0092] The following will respectively elaborate on the four cooling flow paths in detail.

[0093] The blade body cavity of the blade body 101 of the high-pressure turbine air-cooled working blade 1 is divided into four independent cooling flow paths by three circumferential partitions 102, which are respectively the front cooling flow path, the middle front cooling flow path, the middle rear cooling flow path, and the tail cooling flow path K arranged in sequence from the leading edge 4 to the trailing edge 5 of the blade body 101. Each cooling flow path internally forms an independent cooling flow path. The interiors of the front cooling flow path, the middle front cooling flow path, the middle rear cooling flow path, and the tail cooling flow path K respectively form the first cooling flow path 20, the second cooling flow path 30, the third cooling flow path 40, and the fourth cooling flow path 50.

[0094] The front cooling flow path is located at the leading edge 4 and the gill region of the high-pressure turbine air-cooled working blade 1. The first cooling flow path 20 of the front cooling flow path adopts a four-channel cooling structure of a serpentine channel combined with leading-edge impingement cooling holes. A plurality of front inner partitions 102 divide the front cooling flow path into four front cooling cavities extending radially. The four front cooling cavities include a first front cooling cavity A near the leading edge 4, a second front cooling cavity B near the pressure surface 2 of the blade body 101 located between the first front cooling cavity A and the adjacent middle front cooling flow path, a third front cooling cavity C and a fourth front cooling cavity D arranged in sequence from the leading edge 4 to the trailing edge 5 of the blade body 101 near the suction surface 3 of the blade body 101 and located between the first front cooling cavity A and the adjacent middle front cooling flow path. Leading-edge impingement cooling holes 11 are provided on the front inner partition 102 between the first front cooling cavity A and the second front cooling cavity B, so that the first front cooling cavity A forms an impingement chamber. The impingement chamber is near the leading edge 4 of the high-pressure turbine air-cooled working blade 1. The first front cooling cavity A and the second front cooling cavity B distributed radially along the blade body 101 are connected through the leading-edge impingement cooling holes 11. The second front cooling cavity B penetrates the high-pressure turbine air-cooled working blade 1 radially from the blade bottom 7 to the blade tip 8, and a front air inlet hole for the second front cooling cavity B is provided at the blade bottom 7. The third front cooling cavity C is connected to the second front cooling cavity B through a communication hole at the blade tip 8. The third front cooling cavity C is a channel extending from the radially outer side to the radially inner side along the cooling gas flow direction, and the fourth front cooling cavity D is a channel extending from the radially inner side to the radially outer side along the cooling gas flow direction. The third front cooling cavity C and the fourth front cooling cavity D are connected through a communication hole at the blade bottom 7.

[0095] The high-pressure cooling air of the first cooling flow path 20 enters the second front cooling cavity B from the blade root 12 and flows radially. During the flow process, part of the cooling gas flows out of the blade body 101 from the first front film holes 61 and is divided into two gas streams in the second front cooling cavity B. One gas stream flows through the transverse leading-edge impingement cooling holes 11 into the first front cooling cavity A to perform impingement cooling on the leading edge 4. Then, the cooling air flows out from the first to third groups of second front film holes 62 - 64, and the outflowing cooling gas covers the area near the leading edge 4 of the blade body 101 to isolate the metal matrix near the leading edge 4 of the blade body 101 from the combustion gas. The other gas stream flows radially outward in the second front cooling cavity B to the blade tip 8, then flows in the direction of the suction surface 3 and makes a 180-degree turn towards the radially inner side, enters the third front cooling cavity C, and flows radially towards the radially inner side in the third front cooling cavity C. The cooling gas flows in the direction towards the trailing edge 5 at the blade bottom 7 and makes a 180-degree turn towards the radially outer side, enters the fourth front cooling cavity D, and then the cooling air flows out of the blade body 101 from the third front film holes 65.

[0096] The cooling gas entering the first front cooling cavity A from the leading edge impingement cooling holes 11 forms impingement cooling on the vicinity of the leading edge 4 of the blade body 101. The cooling gas flowing along the second front cooling cavity B, the third front cooling cavity C, and the fourth front cooling cavity D forms convective cooling on the blade body 101. The cooling air flowing out of the blade body 101 from the first front film holes 61, the first to third groups of second front film holes 62-64, and the third front film holes 65 forms film cooling on the blade body 101.

[0097] The middle-front cooling flow path is located between the front cooling flow path and the middle-rear cooling flow path, near the high curvature of the high-pressure turbine air-cooled working blade 1. A plurality of middle-front inner partitions 102 divide the middle-front cooling flow path into three middle-front cooling cavities extending radially. The three middle-front cooling cavities include a first middle-front cooling cavity E near the front cooling flow path, a second middle-front cooling cavity F on the suction surface 3 side of the blade body 101 and near the leading edge 4 of the first middle-front cooling cavity E, and a third middle-front cooling cavity G on the pressure surface 2 side of the blade body 101 and near the leading edge 4 of the first middle-front cooling cavity E.

[0098] In the second cooling flow path 30 corresponding to the middle-front cooling flow path, the first middle-front cooling cavity E, the second middle-front cooling cavity F, and the third middle-front cooling cavity G sequentially form a three-cavity serpentine turning flow path with two turns. The first middle-front cooling cavity E and the third middle-front cooling cavity G are channels extending from the radially inner side to the radially outer side along the cooling gas flow direction. The second middle-front cooling cavity F is a chamber extending from the radially outer side to the radially inner side along the cooling gas flow direction. A middle-front air inlet hole is provided on the radially inner side of the first middle-front cooling cavity E. The first middle-front cooling cavity E and the second middle-front cooling cavity F are connected through a communication hole on the radially outer side of the blade body 101. The second middle-front cooling cavity F and the third middle-front cooling cavity G are connected through a communication hole on the radially inner side of the blade body 101. A group of middle-front film holes 66 are provided on the blade body 101 of the channel wall of the third middle-front cooling cavity G.

[0099] The high-pressure cooling air of the second cooling flow path 30 enters the first middle-front cooling cavity E from the blade root 12 and flows radially from the radially inner side to the radially outer side, flows in the direction of the leading edge 4 at the blade tip 8 and makes a 180-degree turn, enters the second middle-front cooling cavity F, flows from the radially outer side to the radially inner side in the second middle-front cooling cavity F, flows in the direction of the pressure surface 2 at the blade bottom 7 and makes a 180-degree turn, enters the third middle-front cooling cavity G, flows from the radially inner side to the radially outer side in the third middle-front cooling cavity G, and flows out of the blade body 101 from the middle-front film holes 66 during the flow process.

[0100] In the second cooling flow path 30, the cooling gas flowing along the first middle front cooling cavity E, the second middle front cooling cavity F and the third middle front cooling cavity G forms convection cooling on the blade body 101. When the cooling gas flows out of the blade body 101 from the middle front air film hole 66, the blade body 101 forms air film cooling.

[0101] The middle rear cooling flow path is located between the middle front cooling flow path and the tail cooling flow path, and is located in the area near the trailing edge 5 of the blade body 101. A plurality of middle rear inner baffles 102 divide the middle rear cooling flow path into three middle rear cooling cavities extending radially, and the three middle rear cooling cavities include a first middle rear cooling cavity H near the tail cooling flow path K, a third middle rear cooling cavity J located on the side of the first middle rear cooling cavity H near the leading edge 4 and near the pressure surface 2 of the blade body 101, and a second middle rear cooling cavity I located on the side of the first middle front cooling cavity E near the trailing edge 5 and near the suction surface 3 of the blade body 101.

[0102] In the third cooling flow path 40 corresponding to the middle rear cooling flow path, the first middle rear cooling cavity H, the second middle rear cooling cavity I and the third middle rear cooling cavity J are all two-fold three-cavity serpentine rotating flow paths. The first middle rear cooling cavity H and the third middle rear cooling cavity J are channels extending from the radial inside to the radial outside along the flow direction of the cooling gas, and the second middle rear cooling cavity I is a channel extending from the radial outside to the radial inside. A middle rear air inlet hole is provided on the radial inside of the first middle rear cooling cavity H. The first middle rear cooling cavity H is connected to the second middle rear cooling cavity I on the radial outside of the blade body 101 through a connecting hole. The second middle rear cooling cavity I is connected to the third middle rear cooling cavity J on the radial inside of the blade body 101 through a connecting hole. A group of middle rear air film holes 67 are provided on the blade body 101 of the channel wall of the third middle rear cooling cavity J.

[0103] The high-pressure cooling air of the third cooling flow path 40 enters the first middle cooling cavity H from the blade root 12 and flows radially from the radial inside to the radial outside. The first middle cooling cavity H is located in the area downstream of the suction surface 3 where the cooling gas coverage is poor. As the first flow channel of the third cooling flow path 40, the cooling airflow temperature is low and this area can be cooled well. The cooling airflow flows in the first middle cooling cavity H to the blade tip 8 and makes a 180-degree turn in the direction toward the leading edge 4, enters the second middle cooling cavity I, and flows in the second middle cooling cavity I from the radial outside to the radial inside, flows in the direction toward the pressure surface 3 at the blade bottom 7 and makes a 180-degree turn, enters the third middle cooling cavity J, and flows in the third middle cooling cavity J from the radial inside to the radial outside, and flows out of the blade body 101 from the middle film hole 67 during the flow.

[0104] In the third cooling flow path 40, the cooling gas flowing along the rear cooling cavity H in the first middle part, the rear cooling cavity I in the second middle part, and the rear cooling cavity J in the third middle part forms convective cooling for the blade main body 101. When flowing out of the blade main body 101 from the rear middle part film holes 67, it forms film cooling for the blade main body 101.

[0105] The trailing edge cooling flow path K is located in the trailing edge 5 region and is a separate cooling flow path extending from the radially inner side to the radially outer side, corresponding to the fourth cooling flow path 50.

[0106] The fourth cooling flow path 50 is the end cooling flow path of the high-pressure turbine air-cooled working blade 1. High-pressure cooling air enters the trailing edge cooling flow path K from the blade bottom 7 and flows radially from the radially inner side to the radially outer side. During the flowing process, the cooling air flows out from the first trailing edge film holes 68 on the pressure surface 2 and the split structure 9 of the trailing edge 5, thereby cooling the trailing edge 5.

[0107] According to the above description, the high-pressure turbine air-cooled working blade and the gas turbine engine having the same in the embodiment of the present application have at least one of the following advantages:

[0108] The blade main body cavity of the blade main body is separated into a front cooling flow path, a front middle cooling flow path, a rear middle cooling flow path, and a trailing edge cooling flow path that are arranged in sequence from the leading edge to the trailing edge of the blade main body and are independent of each other by three circumferential partition plates, which is conducive to separately designing the cooling flow paths of each cooling flow path according to the cooling requirements of the positions where each cooling flow path is located, thereby improving the cooling effect of the high-pressure turbine air-cooled working blade.

[0109] Based on the hollow blade main body, a number of independent cooling cavities extending along the blade radius are distributed inside the blade main body. The cooling gas flows in the cooling cavities and flows out from the film holes or split structures. Through the convective heat transfer of the air flow and the function of the film to isolate the combustion gas, the heat on the combustion gas side of the working blade is taken away, thereby achieving the cooling effect of the high-pressure turbine air-cooled working blade, and the high-pressure turbine inlet temperature can be further increased.

[0110] By designing the cooling schemes of each cooling flow path, the cooling efficiency of the cooling gas can be improved without increasing the cooling gas flow rate, and the temperature gradient on the surface of the working blade can be reduced.

[0111] The front cooling flow path adopts a cooling flow path with four channels, which can increase the cooling gas flow rate of the channels close to the pressure surface, enhance the convective heat transfer coefficient of the cooling gas, and enhance the internal cooling capacity. The cooling gas flows through the second front cooling cavity on the pressure surface side and then enters the third and fourth front cooling cavities on the suction surface side. After multi-channel turning, while improving the convective cooling efficiency of the cooling gas, it can effectively reduce the pressure of the cooling gas, thereby reducing the blowing ratio of the cooling gas flowing out on the suction surface, avoiding the cooling gas from flying up, increasing the coverage ability of the cooling gas, and improving the cooling efficiency.

[0112] The front-middle cooling flow path and the rear-middle cooling flow path each have three channels, a total of six channels, which can better control the flow path of the cooling gas and the cooling gas flow rate, enhance the internal flow cooling ability, and then cool the area near the trailing edge of the suction surface where the cooling gas film coverage is relatively weak.

[0113] The trailing-edge cooling flow path extends radially from the blade root to the blade tip and can cool the outer wall of the blade body of the entire trailing edge.

[0114] The working blade can better control the distribution of the cooling flow path, reduce the temperature gradient. On the other hand, it can control the blowing ratio of the film holes by adjusting the cooling flow path and enhance the coverage ability of the film holes.

[0115] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application and are not intended to limit them; although the present application has been described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand that it is still possible to modify the specific implementation manners of the present application or perform equivalent replacements for some technical features, and they should all be covered within the scope of the technical solutions claimed in the present application.

Claims

1. A high-pressure turbine air-cooled working blade, characterized in that, Comprising: A blade body (101), the blade body (101) forming the outer contour of the high-pressure turbine air-cooled working blade and being hollow inside to form a blade body cavity; And Multiple partition plates (102), the partition plates (102) extending radially along the blade body (101), the multiple partition plates (102) including three circumferential partition plates, the three circumferential partition plates being arranged at intervals in sequence along the direction from the leading edge (4) of the blade body (101) to the trailing edge (5) of the blade body (101), separating the blade body cavity into four independent cooling flow paths, the four cooling flow paths including a front cooling flow path, a middle-front cooling flow path, a middle-back cooling flow path, and a tail cooling flow path (K) arranged in sequence from the leading edge (4) of the blade body (101) to the trailing edge (5) of the blade body (101); Wherein, in the three independent cooling flow paths of the front cooling flow path, the middle-front cooling flow path, and the middle-back cooling flow path, each of the cooling flow paths has at least three cooling cavities separated by at least two of the partition plates (102).

2. The high-pressure turbine air-cooled working blade according to claim 1, characterized in that In each of the front cooling flow path, the middle-front cooling flow path, and the middle-back cooling flow path, there are included at least two cooling cavities in which only one side channel wall is formed by the side wall of the blade body (101).

3. The high-pressure turbine air-cooled working blade according to claim 1, characterized in that, The multiple partition plates (102) further include a plurality of front inner partition plates, the plurality of front inner partition plates separating the front cooling flow path into four radially extending front cooling cavities, the four front cooling cavities including a first front cooling cavity (A) close to the leading edge (4) side, a second front cooling cavity (B) close to the pressure surface (2) of the blade body (101) and located between the first front cooling cavity (A) and the middle-front cooling flow path, a third front cooling cavity (C) close to the suction surface (3) of the blade body (101) and located between the first front cooling cavity (A) and the middle-front cooling flow path, and a fourth front cooling cavity (D) arranged in sequence from the leading edge (4) of the blade body (101) to the trailing edge (5) of the blade body (101); wherein, A front air inlet hole for the entry of high-pressure cooling gas is provided on the radially inner side of the second front cooling cavity (B); The second front cooling cavity (B) and the third front cooling cavity (C) have a communication hole on the radially outer side of the blade body (101); The third front cooling cavity (C) and the fourth front cooling cavity (D) have a communication hole on the radially inner side of the blade body (101); A leading edge impingement cooling hole (11) is provided on the front inner partition plate located between the first front cooling cavity (A) and the second front cooling cavity (B), and the leading edge impingement cooling hole (11) is configured to jet high-pressure cooling gas towards the inner wall of the blade body (101) of the channel wall forming the first front cooling cavity (A); A first front film hole is provided on the blade body (101) of the channel wall forming the second front cooling cavity (B); The blade body (101) forming the channel wall of the first front cooling cavity (A) is provided with second front film holes; The blade body (101) forming the channel wall of the fourth front cooling cavity (D) is provided with third front film holes.

4. The high-pressure turbine air-cooled working blade according to claim 3, wherein a plurality of the first front film holes form at least one set of first front film holes (61) radially distributed along the blade body (101); and / or a plurality of the second front film holes form at least one set of second front film holes radially distributed along the blade body (101), and the at least one set of second front film holes includes at least one of a first set of second front film holes (62), a second set of second front film holes (63), and a third set of second front film holes (64); wherein, the first set of second front film holes (62) is arranged on the pressure surface (2) close to the leading edge (4), the second set of second front film holes (63) is arranged on the leading edge (4), and the third set of second front film holes (64) is arranged on the suction surface (3) close to the leading edge (4); and / or a plurality of the third front film holes form at least one set of third front film holes (65) radially distributed along the blade body (101).

5. The high-pressure turbine air-cooled working blade according to claim 1, wherein, The plurality of partition plates (102) further includes a plurality of front-inner partition plates in the middle part, and the plurality of front-inner partition plates in the middle part divide the front-middle cooling flow path into three front-middle cooling cavities extending radially. The three front-middle cooling cavities include a first front-middle cooling cavity (E) close to the trailing edge (5), a second front-middle cooling cavity (F) located on the side of the first front-middle cooling cavity (E) close to the front cooling flow path and close to the suction surface (3) of the blade body (101), and a third front-middle cooling cavity (G) located on the side of the first front-middle cooling cavity (E) close to the front cooling flow path and close to the pressure surface (2) of the blade body (101); wherein, a front-middle air inlet for the high-pressure cooling gas to enter is provided on the radial inner side of the first front-middle cooling cavity (E); the first front-middle cooling cavity (E) and the second front-middle cooling cavity (F) have a communication hole on the radial outer side of the blade body (101); the second front-middle cooling cavity (F) and the third front-middle cooling cavity (G) have a communication hole on the radial inner side of the blade body (101); the blade body (101) forming the channel wall of the third front-middle cooling cavity (G) is provided with front-middle film holes.

6. The high-pressure turbine air-cooled working blade according to claim 5, wherein a plurality of the front-middle film holes form at least one set of front-middle film holes (66) radially distributed along the blade body (101).

7. The high-pressure turbine air-cooled working blade according to claim 5, wherein, The multiple partition plates (102) further include multiple middle-rear inner partition plates. The multiple middle-rear inner partition plates (102) divide the middle-rear cooling flow path into three middle-rear cooling cavities extending radially. The three middle-rear cooling cavities include a first middle-rear cooling cavity (H) close to the tail cooling flow path (K), a second middle-rear cooling cavity (I) located between the first middle-front cooling cavity (E) and the first middle-rear cooling cavity (H) and close to the suction surface (3), and a third middle-rear cooling cavity (J) located between the first middle-front cooling cavity (E) and the first middle-rear cooling cavity (H) and close to the pressure surface (2); wherein, A middle-rear air inlet hole for the entry of high-pressure cooling gas is provided on the radially inner side of the first middle-rear cooling cavity (H); The first middle-rear cooling cavity (H) and the second middle-rear cooling cavity (I) have a communication hole on the radially outer side of the blade body (101); The second middle-rear cooling cavity (I) and the third middle-rear cooling cavity (J) have a communication hole on the radially inner side of the blade body (101); Middle-rear film holes are provided on the blade body (101) forming the channel wall of the third middle-rear cooling cavity (J).

8. The high-pressure turbine air-cooled working blade according to claim 7, wherein, The multiple middle-rear film holes form at least one group of middle-rear film holes (67) distributed radially along the blade body (101).

9. The high-pressure turbine air-cooled working blade according to any one of claims 1 to 8, wherein, A first tail film hole is provided on the pressure surface (2) of the blade body (101) forming the cavity wall of the tail cooling flow path (K); and / or A split structure (9) is provided on the trailing edge (5) of the blade body (101) forming the cavity wall of the tail cooling flow path (K).

10. A gas turbine engine, characterized in that, A high-pressure turbine is included, and the high-pressure turbine includes the high-pressure turbine working blade according to any one of claims 1 to 9.

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