Rotary internal cavity air supply cooling blade and aero-engine

Abstract

The application discloses a rotary internal cavity air supply cooling blade and an aero-engine, and belongs to the technical field of aero-engines. The rotary internal cavity air supply cooling blade comprises a blade, and an internal cavity of the blade is divided into a front cavity and a rear cavity by a cavity partition plate. A leading edge cold air inflow hole is formed in a side wall of the front cavity, a trailing edge cold air inflow hole is formed in a side wall of the rear cavity, a trailing edge cold air outflow hole and a trailing edge cold air return hole are formed in the side wall on the other side, an internal cavity exhaust hole is formed in a blade boss of the blade body close to the trailing edge cold air return hole, the trailing edge cold air outflow hole is used for exhausting cold air in the rear cavity, the trailing edge cold air return hole is used for returning part of cold air exhausted from the trailing edge cold air outflow hole to the rear cavity, and the internal cavity exhaust hole is used for exhausting another part of cold air. By adopting the cavity partition configuration for the whole blade, the leading edge and the trailing edge exhaust air from different positions, the blade is independently cooled, the internal cavity of the blade is extended to the outside of the blade, and therefore, the multifunctional use of the cold air is realized, and the cold air utilization rate is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, in particular, to a rotary internal cavity air supply cooling blade. In addition, the present application also relates to an aero-engine comprising the above blade cooling structure. BACKGROUND

[0002] The information provided in this section is for the purpose of generally presenting the context of the application. The work of the presently named inventors, to the extent the descriptions are described in this section, and the descriptions of the various aspects of the art that might be described in this section, are not, and are not to be construed as, prior art to the application.

[0003] With the development of aero-engines, the temperature before the turbine is continuously increasing, while the blade has limited ability to withstand the temperature. If the blade works in a high-temperature environment for a long time, the service life of the blade will be seriously affected, and it is easy to produce fracture, ablation and other dangers. The transition section is the first blade impacted by the power turbine after the main gas passes through the gas turbine, and it is also the first to be affected. Therefore, developing more advanced cooling methods for the transition section is particularly important for the long-term use and normal operation of the engine. The existing transition section blade cooling design usually adopts a cooling form of multiple reflux + turbulence column. The cooling gas flows into the blade from the air supply hole, rotates in the internal cavity of the blade, and is discharged through the tail edge split after the turbulence column area, so as to achieve the purpose of cooling the blade.

[0004] The cooling of the blade by the cooling gas is mainly through heat exchange with the blade when the cooling gas flows in the internal cavity of the blade. The blade needs to be reduced to a certain specific temperature, and enough heat needs to be transferred. In order to increase the heat absorbed by the cooling gas and the blade during heat exchange, the amount of cooling gas is usually increased, so that more cooling gas exchanges heat with the blade, thereby taking away more heat, or different cooling forms are used to increase the heat exchange capacity of the cooling gas, so that the same mass flow of cooling gas can absorb more heat.

[0005] Please refer to the accompanying drawings Figure 2 shown in the drawings, the existing transition section blade cooling structure usually arranges air supply holes at the leading edge, and the cooling gas flows into the blade through the air supply holes at the leading edge, and then flows in the rotary channel, so as to flow through the entire blade and finally be discharged from the trailing edge. This results in that the same cooling gas cools the transition section blade from beginning to end, and the fine cooling of different regions of the blade cannot be achieved. At the same time, the cooling gas always flows in the internal cavity of the transition section blade, and can only exchange heat with the blade, which has a single function and low utilization rate of the cooling gas.

[0006] In the prior art, a turbine guide vane and a cold gas guide member of a front cold gas cavity thereof disclosed in a patent with the publication number CN117489418A includes a vane body and a cold gas guide member; the vane body is respectively provided with a basin side film hole, a front film hole and a back side film hole on a front cold gas cavity wall; the vane body is provided with an air inlet at both ends; the cold gas guide member is arranged in the front cold gas cavity and divides the front cold gas cavity into a leading edge cooling cavity, a back cooling cavity and a vane basin cooling cavity; the leading edge cooling cavity is communicated with one air inlet, the back cooling cavity and the vane basin cooling cavity are communicated with another air inlet; different cooling cavities correspond to different film holes. The scheme separates the cold gas sent to the front edge, the vane basin and the back of the vane body, and can control the cold gas flow by separation, injects cold gas of different temperatures to different temperature parts to improve the cold gas efficiency.

[0007] However, the cooling structure of the vane in the prior art cannot realize the multi-functional use of the cold gas, the cold gas utilization rate is difficult to be further improved, the function of the vane inner cavity is single, and the overall temperature distribution of the vane is difficult to maintain high uniformity.

[0008] It should be noted that the information disclosed in the above background section is only used to strengthen the understanding of the background of the present application, and therefore can include information that does not constitute prior art known to those of ordinary skill in the art. SUMMARY

[0009] In view of at least one of the above technical problems, the present application provides a rotary inner cavity gas supply cooling vane, which can realize the multi-functional use of the cold gas, improve the cold gas utilization rate, by adopting a separate cavity configuration for the whole vane, introducing air from different positions at the leading edge and the trailing edge, independently cooling the vane, and extending the vane inner cavity to the outside of the vane.

[0010] The present application also provides an aero-engine comprising the above rotary inner cavity gas supply cooling vane.

[0011] According to an aspect of the present application, a rotary internal cavity air supply cooling blade is provided, comprising a blade body, a plurality of trailing edge split slots are arranged at the trailing edge end of the blade body, characterized in that a trailing edge cold air inlet hole is arranged on the side wall of one side of the blade body, a trailing edge cold air outlet hole and a trailing edge cold air return hole are arranged on the side wall of the other side of the blade body, a blade body boss is arranged on the outer side of the blade body near the trailing edge cold air return hole, the blade body boss is used to enclose a return cavity on the outer side of the blade body, an internal cavity exhaust hole is arranged on the blade body boss, the internal cavity exhaust hole is communicated with the trailing edge cold air return hole, the trailing edge cold air inlet hole is used to introduce cold air into the internal cavity of the blade body, the trailing edge cold air outlet hole is used to exhaust the cold air in the internal cavity of the blade body to the return cavity, the trailing edge cold air return hole is used to return part of the cold air in the return cavity to the internal cavity of the blade body and guide the cold air to be finally exhausted from the trailing edge split slot, and the internal cavity exhaust hole is used to exhaust another part of the cold air in the return cavity to a preset position to cool or seal other parts of the aero-engine.

[0012] In some embodiments of the present application, the internal cavity of the blade body is provided with a cavity separation plate, the cavity separation plate separates the internal cavity of the blade body into a front cavity and a rear cavity, a leading edge cold air inlet hole is arranged on the side wall of the front cavity, the leading edge cold air inlet hole is used to introduce cold air into the front cavity, and a leading edge air film hole is arranged on the side wall of the front cavity, the leading edge air film hole is used to exhaust the cold air of the front cavity.

[0013] In some embodiments of the present application, the leading edge cold air inlet hole and the trailing edge cold air inlet hole are located on the same side of the blade.

[0014] In some embodiments of the present application, the internal cavity exhaust hole is also used to connect an external cold air source and introduce cold air into the internal cavity of the blade body through the trailing edge cold air return hole when the cold air in the internal cavity of the blade body is insufficient.

[0015] In some embodiments of the present application, a plurality of staggered leading edge separation plates are arranged in the front cavity, the plurality of leading edge separation plates are used to sequentially separate a plurality of flow channels in the front cavity, two adjacent flow channels are connected end to end to form a leading edge return channel which is arranged in a snake shape and repeatedly changes direction through the plurality of flow channels, an inlet of the leading edge return channel is communicated with the leading edge cold air inlet hole, and an outlet of the leading edge return channel is communicated with the leading edge air film hole.

[0016] In some embodiments of the present application, the return cavity gradually widens along the direction from the trailing edge cold air outlet hole to the trailing edge cold air return hole, so as to guide the airflow to flow in the direction of the trailing edge cold air return hole and the internal cavity exhaust hole, and not to flow back along the trailing edge cold air outlet hole.

[0017] In some embodiments of the present application, a plurality of trailing edge spoiler columns are arranged in the rear cavity.

[0018] In some embodiments of the present application, the diameter of the trailing edge spoiler column ranges from 2 mm to 4 mm.

[0019] In some embodiments of the present application, the air outlet channels are arranged along the air outlet direction of the split slots between the adjacent trailing edge spoiler columns and are in communication with the split slots.

[0020] In some embodiments of the present application, the width of the air outlet channels ranges from 2 to 6 mm.

[0021] In some embodiments of the present application, the spacing between the air outlet channels along the air outlet direction of the trailing edge spoiler columns ranges from 3 to 8 mm.

[0022] According to another aspect of the present application, an aero-engine is also provided, which comprises the rotary internal cavity air supply cooling blade described above.

[0023] The present application has the following beneficial effects:

[0024] The rotary internal cavity air supply cooling blade of the present application separates the internal cavity of the blade into a front cavity and a rear cavity by the cavity partition plate, and the front cavity and the rear cavity are respectively provided with a leading edge cold air inlet hole and a trailing edge cold air inlet hole, so that the leading edge and the trailing edge can be supplied with air from different positions, the front and rear sections can independently cool the blade, the amount of air introduced can be flexibly controlled, the utilization rate of the cold air can be effectively improved, and the uniformity of the temperature distribution of the whole blade can be ensured. Meanwhile, the cold air in the rear cavity flows out of the blade through the trailing edge cold air outlet hole and is then divided, part of the cold air can flow out through the internal cavity air outlet hole for cooling other components or for sealing, and the remaining cold air flows back into the rear cavity through the trailing edge cold air return hole for subsequent cooling.

[0025] The cavity partition configuration adopted by the blade of the present application can independently divide the cooling of the front cavity and the rear cavity, realize on-demand distribution, the cooling demand of the front cavity is greater, the air can be introduced from a position with lower temperature for cooling, the temperature of the rear cavity is already low, and the air can be introduced from a position with slightly higher temperature for cooling, so that the uniformity of the temperature distribution of the whole blade is realized. Since the front cavity and the rear cavity are independent of each other, different cooling forms can be adopted, for example, the front cavity is cooled by oil or water, and the rear cavity is cooled by air, and optimization and improvement can be made according to needs. The present application adopts the design of an extended rotary internal cavity, so that the cold air is not limited to the inside of the blade, thereby making the cold air realize more functions and improving the utilization rate. If the amount of cold air is insufficient, the cold air can be supplemented in this way, and the temperature of the cold air supplemented subsequently can be adjusted according to needs, so that the temperature of the cold air in the internal cavity of the blade can be maintained at a low level.

[0026] The aero-engine of the present application also has the above-mentioned beneficial effects. It also includes that the cold air can exchange heat with other engine components adjacent to the blade, such as the bearing seat, while flowing through the blade, thereby improving the utilization rate of the cold air. Since the cold air realizes the function of cooling the bearing seat, it is not necessary to additionally design the cooling of the bearing seat. At the same time, the cold air can also play the role of inter-stage sealing. According to actual needs, the cold air can be introduced or supplemented. If the temperature of the subsequent part of the trailing edge is already low, part of the cold air can be introduced into other parts to play the role of cooling or sealing; if the temperature of the subsequent part of the trailing edge is still high, the cold air can be supplemented to make the final cooling effect reach the expected value.

[0027] Of course, implementing any product of the present application does not necessarily need to achieve all the advantages described above at the same time. In addition to the purposes, features and advantages described above, the present application has other purposes, features and advantages. The present application will be further described in detail below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0028] The accompanying drawings, which form a part of the present application, are intended to provide further understanding of the present application, and the illustrative embodiments of the present application and their description serve the purpose of explaining the present application. The accompanying drawings do not constitute an inappropriate limitation on the present application. In the drawings:

[0029] Figure 1 is a structural schematic view of the front cavity and the rear cavity of the blade of the preferred embodiment of the present application;

[0030] Figure 2 is a schematic view of the traditional blade inner cavity air supply cooling;

[0031] Figure 3 is a schematic view of the preferred embodiment of the present application for supplementing cold air through the inner cavity exhaust air hole;

[0032] Figure 4 is a structural schematic view of the blade inner cavity of the preferred embodiment of the present application;

[0033] Legend: 1000, blade; 100, front cavity; 101, leading edge cold air inlet hole; 102, leading edge partition plate; 103, leading edge recirculation passage; 104, leading edge air film hole; 200, rear cavity; 201, trailing edge cold air inlet hole; 202, trailing edge cold air outlet hole; 203, trailing edge cold air return hole; 204, trailing edge spoiler column; 205, trailing edge cold air passage; 206, trailing edge split joint; 300, cavity partition plate; 400, blade boss; 401, inner cavity exhaust air hole. DETAILED DESCRIPTION

[0034] The embodiments of the present application will be described in detail below with reference to the drawings, but the present application can be implemented in various different ways as defined and covered below.

[0035] Figure 1 is a structural schematic diagram of the front cavity and the rear cavity of the blade of the preferred embodiment of the present application; Figure 2 is a schematic diagram of traditional blade inner cavity air supply cooling; Figure 3 is a schematic diagram of the preferred embodiment of the present application for supplementing cooling air through the inner cavity exhaust air hole; Figure 4 is a structural schematic diagram of the blade inner cavity of the preferred embodiment of the present application.

[0036] A rotary inner cavity air supply cooling blade, comprising a blade body, a plurality of trailing edge split slots 206 are provided at the trailing edge end of the blade body, characterized in that a trailing edge cold air inlet hole 201 is provided on the side wall of one of the opposite sides of the blade body, a trailing edge cold air outlet hole 202 and a trailing edge cold air return hole 203 are provided at intervals on the side wall of the other side, a blade body boss 400 is provided on the outer side of the blade body near the trailing edge cold air return hole 203, the blade body boss 400 is used to enclose a return cavity on the outer side of the blade body, an inner cavity exhaust air hole 401 is provided on the blade body boss 400, the inner cavity exhaust air hole 401 is in communication with the trailing edge cold air return hole 203, the trailing edge cold air inlet hole 201 is used to introduce cold air into the inner cavity of the blade body, the trailing edge cold air outlet hole 202 is used to exhaust the cold air in the inner cavity of the blade body to the return cavity, the trailing edge cold air return hole 203 is used to return part of the cold air in the return cavity to the inner cavity of the blade body and guide the cold air to be finally exhausted from the trailing edge split slot 206, and the inner cavity exhaust air hole 401 is used to exhaust another part of the cold air in the return cavity to a preset position to cool or seal other parts of the aero-engine.

[0037] The inner cavity of the blade body of the present application is provided with a cavity partition plate 300, which divides the inner cavity of the blade body into a front cavity 100 and a rear cavity 200; a leading edge cold air inlet hole 101 is provided on the side wall of the front cavity 100, which is used to introduce cold air into the front cavity 100; a leading edge air film hole 104 is provided on the side wall of the front cavity 100, which is used to exhaust the cold air of the front cavity 100.

[0038] The present application particularly relates to a cooling structure of a transition section blade with rotary inner cavity air supply cooling. In view of the problems of large cooling air demand and high cooling requirement of the current turbine transition section blade, a blade air supply cooling structure with rotary inner cavity is innovatively designed. By extending the inner cavity of the transition section blade to the outside of the transition section blade, the multifunction, multipurpose and high utilization of the cold air are realized. The "transition section blade" refers to the first blade impacted by the power turbine after the main flow gas passes through the gas turbine. Of course, the cooling structure of the present application is not limited to the transition section blade.

[0039] The rotating inner cavity gas supply cooling blade separates the inner cavity of the blade 1000 into the front cavity 100 and the rear cavity 200 through the cavity partition 300, the front cavity 100 and the rear cavity 200 are respectively provided with the leading edge cold gas inflow hole 101 and the trailing edge cold gas inflow hole 201, the leading edge and the trailing edge are supplied with air from different positions, the front and rear sections can independently cool the blade 1000, the amount of cold air introduced is flexibly controlled, the utilization rate of the cold air is effectively improved, and the uniformity of the temperature distribution of the whole blade 1000 is ensured. At the same time, the cold air in the rear cavity 200 flows out of the blade body through the trailing edge cold gas outflow hole 202, part of the cold air can flow out through the inner cavity exhaust air hole 401, and is used for cooling other components or sealing; the remaining cold air flows back into the rear cavity 200 through the trailing edge cold air return hole 203, and is cooled subsequently.

[0040] The cavity partition configuration adopted by the blade 1000 can independently divide the cooling of the front cavity 100 and the rear cavity 200, realize on-demand distribution, the cooling demand of the front cavity 100 is greater, the cold air can be introduced from a position with a lower temperature to cool it, the temperature of the rear cavity 200 is already lower, and the cold air can be introduced from a position with a slightly higher temperature to cool it, so that the uniformity of the overall temperature distribution of the blade body is realized. Since the front cavity 100 and the rear cavity 200 are independent of each other, different cooling forms can be adopted, for example, oil cooling or water cooling is adopted for the front cavity 100, and air cooling is adopted for the rear cavity 200, and optimization and improvement are made according to needs.

[0041] Preferably, referring to Figure 3 As shown in the figure, the inner cavity exhaust air hole 401 is also used for connecting an external cold air source and introducing the cold air into the inner cavity of the blade body through the trailing edge cold air return hole 203 when the cold air in the inner cavity of the blade body is insufficient, and specifically, the inner cavity exhaust air hole 401 is also used for connecting an external cold air source and introducing the cold air into the rear cavity 200 through the trailing edge cold air return hole 203 when the cold air in the rear cavity 200 is insufficient.

[0042] It can be understood that the inner cavity exhaust air hole 401 not only has a conventional exhaust function, but also can be reversely used as an air inlet of the cold air. Since the inner cavity exhaust air hole 401 is close to the trailing edge cold air return hole 203 and communicates with the trailing edge cold air return hole 203, when the cold air in the rear cavity 200 is insufficient, the inner cavity exhaust air hole 401 can be connected to an external cold air source to introduce air to the trailing edge cold air return hole 203. Since the airflow direction of the trailing edge cold air return hole 203 remains unchanged and always flows back to the rear cavity 200, the function of the inner cavity exhaust air hole 401 can be switched between exhaust and air introduction, so that the amount of cold air returned through the trailing edge cold air return hole 203 can be regulated and controlled to meet the needs of different cooling conditions of the rear cavity 200, effectively improve the utilization rate of the cold air, and achieve better cooling effect.

[0043] The application adopts the design of an extended rotary inner cavity, so that the cold air is not limited to the inside of the blade 1000, thereby enabling the cold air to realize more functions (a part of the cold air can be discharged through the inner cavity exhaust bleed hole 401 to expand the application of the cold air, such as heat exchange with other engine components adjacent to the blade body, such as a bearing seat), improving the utilization rate of the cold air, and if the amount of cold air is insufficient, the cold air can also be supplemented in this way (the inner cavity exhaust bleed hole 401 can also be reversely used as an air bleed inlet), and the temperature of the cold air in the inner cavity of the blade body can be maintained at a low level by adjusting the temperature of the subsequently supplemented mixed cold air as needed.

[0044] Preferably, as shown in Figure 1 The front edge cold air inlet hole 101 and the trailing edge cold air inlet hole 201 are located on the same side of the blade body.

[0045] It can be understood that, in order to facilitate the simultaneous introduction of the cooling air source into the front cavity 100 and the rear cavity 200, reduce the overflow of the cold air, and reduce the space occupation of the cold air channel, the front edge cold air inlet hole 101 and the trailing edge cold air inlet hole 201 are located on the same side of the blade body, which facilitates the smooth simultaneous air intake of the cold air into the front cavity 100 and the rear cavity 200.

[0046] Optionally, the front edge cold air inlet hole 101 and the trailing edge cold air inlet hole 201 are distributed on opposite sides of the cavity partition plate 300, which can realize the simultaneous introduction of the cold air from the blade body into the front cavity 100 and the rear cavity 200, respectively, and realize the exhaust of the cold air in the front cavity 100 from the front edge film hole 104 and the exhaust of the cold air in the rear cavity 200 from the trailing edge split joint 206, thereby realizing the effect of two-stage exhaust cooling of the blade body, which is beneficial to improve the cooling effect.

[0047] Preferably, as shown in Figure 4 The front cavity 100 is provided with a plurality of front edge partition plates 102 arranged in a staggered manner, and the plurality of front edge partition plates 102 are used to sequentially partition a plurality of flow guide channels in the front cavity 100. The two adjacent flow guide channels are connected end to end to form a front edge loop channel 103 in a snake shape through the plurality of flow guide channels. The inlet of the front edge loop channel 103 is communicated with the front edge cold air inlet hole 101, and the outlet of the front edge loop channel 103 is communicated with the front edge film hole 104.

[0048] It can be understood that the cold air outlets between the adjacent front edge partition plates 102 and the inner wall of the front cavity 100 are arranged in a staggered manner, thereby realizing a looped and reciprocating flow path of the cold air after entering the front cavity 100 from the front edge cold air inlet hole 101, greatly improving the flow time of the cold air in the front cavity 100, and each front edge partition plate 102 also effectively improves the contact area of the cold air with the whole blade body, which is beneficial to improve the cooling effect.

[0049] Preferably, the backflow cavity gradually widens along the direction from the cold air outflow hole 202 to the cold air backflow hole 203 of the trailing edge, so as to guide the air flow to flow in the direction of the cold air backflow hole 203 and the inner cavity exhaust hole 401, and not to backflow along the cold air outflow hole 202.

[0050] It can be understood that, by optimizing the internal structure of the backflow cavity, the backflow cavity gradually widens along the direction from the cold air outflow hole 202 to the cold air backflow hole 203, that is, when the cold air outflow hole 202 outflows, the air flow pressure along the direction from the cold air outflow hole 202 to the cold air backflow hole 203 gradually decreases, so that the outflow gas of the cold air outflow hole 202 is more easily flowed in the direction of the cold air backflow hole 203 and the inner cavity exhaust hole 401, and not to backflow along the cold air outflow hole 202, which is beneficial to ensure the exhaust efficiency of the cold air, and further ensure the cooling effect.

[0051] Preferably, as shown in Figure 4 , a plurality of trailing edge spoiler columns 204 are arranged in the rear cavity 200.

[0052] It can be understood that the trailing edge spoiler column 204 arranged in the rear cavity 200 can effectively enhance the cooling effect. The trailing edge spoiler column 204 not only can reduce the flow rate of the cold air and prolong the residence time of the cold air in the rear cavity 200, but also can greatly increase the contact area of the cold air with the whole rear cavity 200, which is beneficial to improve the heat exchange effect and enhance the cooling effect.

[0053] In the preferred embodiment, the diameter of the trailing edge spoiler column 204 ranges from 2mm to 4mm.

[0054] It can be understood that the diameter of the trailing edge spoiler column 204 should not be too large. If the diameter of the trailing edge spoiler column 204 is too large, heat accumulation will be formed at the central position of the trailing edge spoiler column 204, which is not easy to dissipate, resulting in heat concentration at the connection between the trailing edge spoiler column 204 and the blade, which is not conducive to ensuring the uniformity of the temperature distribution of the whole blade. Meanwhile, considering that the trailing edge spoiler column 204 needs to avoid blocking the trailing edge split joint 206 and reducing the interference of the cold air smoothly passing through the trailing edge split joint 206 to be discharged, the application provides a preferred diameter range of the trailing edge spoiler column 204, which can ensure the air flow deceleration effect and heat dissipation effect of the trailing edge spoiler column 204.

[0055] Preferably, as shown in Figure 4 , the adjacent trailing edge spoiler columns 204 are spaced apart along the outflow direction of the trailing edge split joint 206 to form an outflow channel, and the outflow channel is in communication with the trailing edge split joint 206. Specifically, the width of the outflow channel ranges from 2mm to 6mm.

[0056] It can be understood that, in order to avoid the tail edge spoiler 204 from blocking the tail edge split 206, causing the smooth flow of cold air from the tail edge split 206 to be affected, and affecting the cooling and heat dissipation effect, the tail edge spoilers 204 are arranged in an array, and each adjacent tail edge spoiler 204 along the air outlet direction of the tail edge split 206 also forms an air outlet channel, so that the cold air can be smoothly exhausted from the tail edge split 206 after passing through the air outlet channel. It should be noted that the tail edge split 206 is a plurality of spaced-apart gap outlets, and therefore each air outlet channel is arranged one-to-one corresponding to each tail edge split 206. Considering the diameter of the tail edge spoiler 204 and the width of the tail edge split 206, the width of the air outlet channel should not be too large, otherwise the deceleration and buffering effect of the tail edge spoiler 204 will be weakened; similarly, the width of the air outlet channel should not be too small, otherwise it will affect the smooth flow of cold air. The application provides an optimal width range of the air outlet channel, which can ensure the buffering effect of the tail edge spoiler 204 and the exhaust and heat dissipation effect of the cold air at the same time.

[0057] Of course, the application also does not exclude the scheme of misaligning the air outlet channel and the tail edge split 206, especially when the width of the air outlet channel is much larger than the width of the tail edge split 206, misaligning does not affect the smooth exhaust of cold air.

[0058] In the preferred embodiment, the spacing between each row of tail edge spoilers 204 along the air outlet direction of the air outlet channel is 3-8mm.

[0059] It can be understood that, since the tail edge spoilers 204 are arranged in multiple rows along the air outlet direction of the air outlet channel, if the spacing between each row of tail edge spoilers 204 is too small, most of the airflow will be directly exhausted from the air outlet channel, which is not conducive to achieving the buffering and deceleration effect of the airflow, and affects the heat dissipation effect of the tail edge spoiler 204; if the spacing is too large, due to the limited space, the number of tail edge spoilers 204 will necessarily be reduced, which is not conducive to achieving better heat dissipation effect. Considering these factors, the application provides an optimal spacing range between each row of tail edge spoilers 204 along the air outlet direction of the air outlet channel, which can ensure the buffering and heat dissipation effect of the tail edge spoiler 204 at the same time.

[0060] According to another aspect of the application, an aero-engine is also provided, which comprises the above-mentioned rotary inner cavity air supply cooling blade.

[0061] The aero-engine also has the above beneficial effects. The cold air can also exchange heat with other engine components adjacent to the blade, such as the bearing seat, while flowing through the blade, thereby improving the utilization rate of the cold air. Since the cold air achieves the function of cooling the bearing seat, the bearing seat does not need to be cooled additionally. Meanwhile, the cold air can also play the role of inter-stage sealing. According to actual needs, the cold air can be introduced or supplemented. If the temperature of the trailing edge is already low, part of the cold air can be introduced into other parts to play the role of cooling or sealing. If the temperature of the trailing edge is still high, the cold air can be supplemented to make the final cooling effect reach the desired value.

[0062] It should be noted that in this document, the terms "comprising", "including", or any other variant thereof are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements recited, but can also include other elements not expressly listed or inherent to such process, method, article, or apparatus.

[0063] The principles and implementation modes of the present application are described by using specific examples in this document, and the above examples are only used to help understand the method of the present application and its core idea. The above description is only the preferred implementation mode of the present application. It should be pointed out that due to the limited nature of the language expression, there are infinite specific structures, and for ordinary skilled persons in the technical field, some improvements, refinements or changes can be made without departing from the principles of the present application, or the above technical features can be combined in an appropriate manner. These improvements, refinements, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, shall be regarded as the protection of the present application.

Claims

1. A swivelling internal cavity gas supply cooling blade comprising a blade body, a plurality of trailing edge split slots (206) being provided at spaced intervals at the trailing edge extremity of the blade body, characterised in that, The side wall of one of the opposite sides of the blade body is provided with a trailing edge cold air inflow hole (201), and the side wall of the other side is provided with a trailing edge cold air outflow hole (202) and a trailing edge cold air return hole (203) at intervals. The outer side of the blade body is provided with a blade body boss (400) near the trailing edge cold air return hole (203), which is used to enclose a return cavity on the outer side of the blade body. The blade body boss (400) is provided with an inner cavity exhaust hole (401) which is in communication with the trailing edge cold air return hole (203). The trailing edge cold air inflow hole (201) is used to introduce cold air into the inner cavity of the blade body. The trailing edge cold air outflow hole (202) is used to exhaust the cold air in the inner cavity of the blade body to the return cavity. The trailing edge cold air return hole (203) is used to return part of the cold air in the return cavity to the inner cavity of the blade body and guide the cold air to finally exhaust from the trailing edge split joint (206). The inner cavity exhaust hole (401) is used to exhaust another part of the cold air in the return cavity to a predetermined position to cool or seal other parts of the aircraft engine.

2. A swivelling internal cavity gas cooled blade according to claim 1, characterised in that, The inner cavity of the blade body is provided with a cavity partition plate (300) which divides the inner cavity of the blade body into a front cavity (100) and a rear cavity (200). The side wall of the front cavity (100) is provided with a leading edge cold air inflow hole (101) which is used to introduce cold air into the front cavity (100). The side wall of the front cavity (100) is provided with a leading edge air film hole (104) which is used to exhaust the cold air in the front cavity (100).

3. A swivelling internal-cooled vane according to claim 2, wherein, The leading edge cold air inflow hole (101) and the trailing edge cold air inflow hole (201) are located on the same side of the blade body.

4. A swivelling internal cavity gas cooled blade according to claim 1, wherein, The inner cavity exhaust hole (401) is also used to connect an external cold air source when the cold air in the inner cavity of the blade body is insufficient and introduce the cold air into the inner cavity of the blade body through the trailing edge cold air return hole (203).

5. A swivelling internal cavity gas cooled blade according to claim 2, wherein, The front cavity (100) is provided with a plurality of staggered leading edge partition plates (102) at intervals. The plurality of leading edge partition plates (102) are used to sequentially divide a plurality of flow channels in the front cavity (100). The adjacent two flow channels are connected end to end to form a leading edge return channel (103) which is arranged in a snake shape and has multiple reciprocating changes. The inlet of the leading edge return channel (103) is in communication with the leading edge cold air inflow hole (101), and the outlet of the leading edge return channel (103) is in communication with the leading edge air film hole (104).

6. A swivelling internal cavity gas cooled blade according to claim 1, wherein, The return cavity gradually widens along the trailing edge cold air outflow hole (202) towards the trailing edge cold air return hole (203), thereby guiding the airflow to flow towards the trailing edge cold air return hole (203) and the inner cavity exhaust hole (401), and preventing the airflow from flowing back along the trailing edge cold air outflow hole (202).

7. A swivelling internal cavity gas cooled blade according to claim 1 wherein, A plurality of trailing edge spoiler columns (204) are arranged in an array in the rear cavity (200). The diameter of the trailing edge spoiler column (204) ranges from 2 to 4 mm.

8. A swivelling internal-cooled gas cooled blade according to claim 7, wherein, Adjacent trailing edge spoiler columns (204) are arranged at intervals along the gas outlet direction of the trailing edge split joint (206) to form an air outlet channel. The air outlet channel is in communication with the trailing edge split joint (206), and the width of the air outlet channel ranges from 2 to 6 mm.

9. A swivelling internal-cooled vane according to claim 8, wherein, The distance between the trailing edge spoiler columns (204) in the direction of the gas outlet along the gas outlet channel is 3-8 mm.

10. An aeroengine characterised in that, A gas turbine engine comprising a rotary inner cavity gas supply cooling vane as claimed in any of claims 1 to 9.

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