Rotary inner cavity air supply cooling blade and aero-engine

Abstract

The invention discloses a rotary inner cavity air supply cooling blade and an aero-engine, and belongs to the technical field of aero-engines, the rotary inner cavity air supply cooling blade comprises a blade, and a cavity dividing partition plate divides a blade inner cavity into a front cavity and a rear cavity; a front edge cold air inflow hole is formed in the side wall of the front cavity, a tail edge cold air inflow hole is formed in the side wall of the rear cavity, a tail edge cold air outflow hole and a tail edge cold air backflow hole are formed in the side wall of the other side at intervals, and an inner cavity exhausting and guiding hole is formed in a blade body boss, close to the tail edge cold air backflow hole, of a blade body of the blade. The trailing edge cold air outflow hole is used for exhausting cold air in the rear cavity, the trailing edge cold air backflow hole is used for enabling part of cold air exhausted by the trailing edge cold air outflow hole to flow back to the rear cavity, and the inner cavity exhausting and guiding hole is used for exhausting the other part of cold air. The whole blade is of a cavity dividing structure, the front edge and the tail edge are used for guiding air from different positions, the blade is independently cooled, the inner cavity of the blade extends to the outer portion of the blade, and therefore the multifunctional purpose of cold air is achieved, and the cold air utilization rate is increased.

Description

Technical Field

[0001] The present application relates to the technical field of aeroengines, and in particular, to a rotating inner cavity air supply cooling blade. In addition, the present application also relates to an aeroengine comprising the blade cooling structure. Background Art

[0002] The information provided in this section is for the purpose of generally presenting the background of the present application. To the extent described in this section, the work of the presently named inventors and aspects of the description that may not constitute prior art at the time of filing are neither explicitly nor implicitly admitted to be prior art to the present application.

[0003] With the development of aircraft engines, the temperature before the turbine continues to increase, while the blades have limited tolerance to temperature. If the blades work in a high temperature environment for a long time, it will seriously affect the service life of the blades, and it is easy to cause dangers such as breakage and ablation. The transition section is the first blade to be impacted by the power turbine after the mainstream gas passes through the gas turbine, and it is also the first to be affected. Therefore, the development of 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 multi-cavity reflux + spoiler column. The cold air flows in from the air supply hole, swirls inside the blade, and is discharged through the trailing edge slit after passing through the spoiler column area, thereby achieving the purpose of cooling the blade.

[0004] The cooling of the blades by cold air is mainly done by exchanging heat with the blades when flowing through the inner cavity of the blades. If the blades need to be lowered to a certain temperature, they need to transfer enough heat. In order to increase the amount of heat absorbed by the cold air in the heat exchange with the blades, the amount of cold air is usually increased, so that more cold air can exchange heat with the blades and take away more heat, or different cooling forms are used to increase the heat exchange capacity of the cold air, so that the same mass flow of cold air can absorb more heat.

[0005] Please refer to the instruction manual Figure 2 As shown, the existing transition section blade cooling structure usually arranges air supply holes at the leading edge. Cold air flows in through the air supply holes at the leading edge, then flows in the rotating channel, flows through the entire blade, and finally is discharged from the trailing edge. This results in the same cold air cooling the transition section blade from beginning to end, and it is impossible to achieve refined cooling of different areas of the blade. At the same time, the cold air always flows inside the transition section blade and can only exchange heat with the blade. It has a single function and a low cold air utilization rate.

[0006] In the prior art, a Chinese patent with the patent publication number CN117489418A discloses a turbine guide blade and a cold air guide for its front cold air cavity, including a blade body and a cold air guide; the front cold air cavity wall of the blade body is provided with basin-side air film holes, front air film holes, and back-side air film holes respectively; air inlets are provided at both inner and outer ends of the blade body; the cold air guide is provided in the front cold air cavity, and the front cold air cavity is divided into a leading edge cooling cavity, a blade back cooling cavity, and a blade basin cooling cavity; the leading edge cooling cavity is connected to one air inlet, and the blade back cooling cavity and the blade basin cooling cavity are connected to another air inlet; different cooling cavities are connected to different air film holes. This solution separates the cold air at the leading edge, blade basin, and blade back of the front cold air cavity of the blade body, and can control the cold air flow by separation, and inject cold air of different temperatures into different temperature parts to improve the cooling efficiency.

[0007] However, most of the cooling structures of blades in the prior art cannot realize the multiple functional utilization of cold air. There are problems such as difficulty in further improving the utilization rate of cold air, single function of the blade cavity, and difficulty in maintaining high uniformity of the overall temperature distribution of the blade.

[0008] It should be noted that the information disclosed in the above background technology section is only used to enhance the understanding of the background of the present application, and therefore may include information that does not constitute the prior art known to ordinary technicians in the field. Summary of the invention

[0009] In view of at least one of the above technical problems, the present application provides a rotating inner cavity air supply cooling blade. The blade can be cooled independently by adopting a divided cavity configuration for the entire blade, drawing air from different positions at the leading edge and the trailing edge, and extending the inner cavity of the blade to the outside of the blade, thereby realizing the multifunctional use of cold air and improving the utilization rate of cold air.

[0010] The present application also provides an aircraft engine comprising the above-mentioned rotating inner cavity air supply cooling blades.

[0011] According to one aspect of the present application, a rotating inner cavity air supply cooling blade is provided, comprising a blade body, a plurality of trailing edge slits are arranged at intervals at the trailing edge end of the blade body, and the blade body is characterized in that a trailing edge cooling air inlet hole is arranged on the side wall of one of the opposite sides of the blade body, and a trailing edge cooling air outlet hole and a trailing edge cooling air return hole are arranged at intervals on the side wall of the other side, and a blade body boss is arranged on the outer side of the blade body near the trailing edge cooling air return hole, and the blade body boss is used to enclose the return cavity on the outer side of the blade body, and an inner The cavity row air intake holes, the inner cavity row air intake holes are connected with the trailing edge cold air return holes, the trailing edge cold air inlet holes are used to introduce cold air into the inner cavity of the blade body, the trailing edge cold air outlet holes are used to discharge the cold air in the inner cavity of the blade body to the return cavity, the trailing edge cold air return holes are used to return a 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 discharged from the trailing edge split, and the inner cavity row air intake holes are used to discharge another part of the cold air in the return cavity to a preset position to cool or seal other components of the aircraft engine.

[0012] In some embodiments of the present application, the inner cavity of the blade body is provided with a cavity partition, which divides the inner cavity of the blade body into a front cavity and a rear cavity; a leading edge cold air inlet hole is provided on the side wall of the front cavity, and the leading edge cold air inlet hole is used to introduce cold air into the front cavity; a leading edge air film hole is provided on the side wall of the front cavity, and the leading edge air film hole is used to discharge the cold air in 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 inner cavity air discharge holes are also used to connect an external cold air source and introduce cold air into the inner cavity of the blade body through the trailing edge cold air return holes when the inner cavity of the blade body is insufficiently cold.

[0015] In some embodiments of the present application, a plurality of leading edge baffles are arranged in an alternating manner in the front cavity, and the plurality of leading edge baffles are used to sequentially separate a plurality of drainage channels in the front cavity. Two adjacent drainage channels are connected end to end to form a leading edge loop channel that makes multiple reciprocating changes and is arranged in a serpentine shape through the plurality of drainage channels. The inlet of the leading edge loop channel is connected to the leading edge cold air inlet hole, and the outlet of the leading edge loop channel is connected to the leading edge air film hole.

[0016] In some embodiments of the present application, the reflow cavity gradually widens along the direction from the trailing edge cold air outlet hole to the trailing edge cold air return hole, thereby guiding the airflow to flow toward the trailing edge cold air return hole and the inner cavity air discharge hole, and will not 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 an array in the rear cavity.

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

[0019] In some embodiments of the present application, adjacent trailing edge spoiler columns are spaced apart along the air outlet direction of the trailing edge split and form an air outlet channel, and the air outlet channel is connected to the trailing edge split.

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

[0021] In some embodiments of the present application, the spacing between each row of trailing edge spoiler columns along the air outlet direction of the air outlet channel is 3-8 mm.

[0022] According to another aspect of the present application, an aircraft engine is also provided, which includes the above-mentioned rotating inner cavity air supply cooling blade.

[0023] This application has the following beneficial effects:

[0024] The present application uses a rotating inner cavity air supply cooling blade to separate the inner cavity of the blade into a front cavity and a rear cavity through a cavity partition. 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 draw air from different positions. The front and rear sections can cool the blade independently, which is convenient for flexible control of the amount of cold air introduced, effectively improves the utilization rate of cold air, and ensures the uniformity of the temperature distribution of the blade as a whole. At the same time, the cold air in the rear cavity flows out of the blade through the trailing edge cold air outlet hole and is diverted. Part of the cold air can flow out from the inner cavity exhaust air hole for cooling other components or sealing; the remaining cold air flows back into the rear cavity through the trailing edge cold air return hole for subsequent cooling.

[0025] The split-chamber configuration adopted by the blade of the present application can make the cooling of the front chamber and the rear chamber independently distinguishable, and realize on-demand distribution. The front chamber has a greater cooling demand, and air can be drawn from a lower temperature position to cool it. The temperature of the rear chamber is already low, and air can be drawn from a slightly higher temperature position to cool it, thereby achieving uniform temperature distribution of the blade as a whole. Since the front chamber and the rear chamber are independent of each other, the two can adopt different cooling forms, such as oil cooling or water cooling for the front chamber and air cooling for the rear chamber, and optimization and improvement can be carried out as needed. The present application adopts the design of an extended rotary inner cavity, so that the cold air is not limited to the inside of the blade, so that the cold air can realize more functions and improve utilization. If the amount of cold air is insufficient, it can also be supplemented in this way, and the temperature of the cold air in the blade cavity can be maintained at a low level by adjusting the temperature of the subsequent supplementary mixed cold air as needed.

[0026] The aircraft engine of the present application also has the above-mentioned beneficial effects. It also includes realizing that while the cold air flows through the blades, it can also exchange heat with other engine components adjacent to the blades, such as the bearing seat, thereby improving the utilization rate of the cold air. Since the cold air realizes the function of cooling the bearing seat, there is no need to design a cooling system for the bearing seat separately. At the same time, the cooling can also play the role of interstage sealing. According to actual needs, the cold air can be diverted 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 a role in cooling or sealing; if the temperature of the subsequent part of the trailing edge is still high, the cold air can be supplemented so that the final cooling effect reaches the expected value.

[0027] Of course, any product implementing this 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, this application also has other purposes, features and advantages. The following will further describe this application in detail with reference to the figures. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The drawings constituting a part of the present application are used to provide a further understanding of the present application. The illustrative embodiments and descriptions of the present application are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

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

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

[0031] Figure 3 It is a schematic diagram of supplementing cold air through the inner cavity exhaust air holes in the preferred embodiment of the present application;

[0032] Figure 4 This is a schematic diagram of the structure of the blade inner cavity of the preferred embodiment of the present application;

[0033] Legend: 1000, blade; 100, front cavity; 101, leading edge cooling air inlet hole; 102, leading edge baffle; 103, leading edge loop channel; 104, leading edge air film hole; 200, rear cavity; 201, trailing edge cooling air inlet hole; 202, trailing edge cooling air outlet hole; 203, trailing edge cooling air return hole; 204, trailing edge spoiler column; 205, trailing edge cooling air channel; 206, trailing edge slit; 300, cavity partition; 400, blade body boss; 401, inner cavity exhaust air hole. DETAILED DESCRIPTION

[0034] The embodiments of the present application are described in detail below in conjunction with the accompanying drawings, but the present application can be implemented in a variety of different ways defined and covered below.

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

[0036] A rotary inner cavity air supply cooling blade comprises a blade body, a plurality of trailing edge slits 206 are arranged at intervals at the trailing edge end of the blade body, and the blade body is characterized in that a trailing edge cold air inlet hole 201 is arranged on the side wall of one of the two opposite sides of the blade body, and a trailing edge cold air outlet hole 202 and a trailing edge cold air return hole 203 are arranged at intervals on the side wall of the other side, and a blade body boss 400 is arranged on the outer side of the blade body near the trailing edge cold air return hole 203, and the blade body boss 400 is used to enclose the outer side of the blade body to form a return cavity, and the blade body boss 400 is provided with an inner cavity exhaust air hole 401. 01, the inner cavity exhaust air holes 401 are connected with the trailing edge cold air return holes 203, the trailing edge cold air inlet holes 201 are used to introduce cold air into the inner cavity of the blade body, the trailing edge cold air outlet holes 202 are used to discharge the cold air in the inner cavity of the blade body to the return cavity, the trailing edge cold air return holes 203 are used to return a 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 discharged from the trailing edge slit 206, the inner cavity exhaust air holes 401 are used to discharge another part of the cold air in the return cavity to a preset position to cool or seal other components of the aircraft engine.

[0037] The inner cavity of the blade body of the present application is provided with a cavity partition 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 opened on the side wall of the front cavity 100, and the leading edge cold air inlet hole 101 is used to introduce cold air into the front cavity 100; the side wall of the front cavity 100 is opened with a leading edge air film hole 104, and the leading edge air film hole 104 is used to discharge the cold air from the front cavity 100.

[0038] The present application particularly relates to a cooling structure for transition section blades with a rotating inner cavity for air supply cooling. In view of the current large demand for cooling cold air and high cooling requirements for turbine transition section blades, an innovative blade air supply cooling structure with a rotating inner cavity is designed. By extending the inner cavity of the transition section blades to the outside of the transition section blades, the multifunctional, multi-purpose and high utilization rate of the cold air is achieved. The "transition section blade" refers to the first blade that impacts the power turbine after the mainstream fuel gas passes through the gas turbine. Of course, the cooling structure of the present application is not limited to the application of transition section blades.

[0039] The rotary inner cavity air supply cooling blade of the present application is used to divide the inner cavity of the blade 1000 into a front cavity 100 and a rear cavity 200 through a cavity partition 300. The front cavity 100 and the rear cavity 200 are respectively provided with a leading edge cold air inlet hole 101 and a trailing edge cold air inlet hole 201, so that the leading edge and the trailing edge can be induced to draw air from different positions. The front and rear sections can independently cool the blade 1000, which is convenient for flexible control of the amount of cold air introduced, effectively improves the utilization rate of cold air, and ensures the uniformity of the overall temperature distribution of the blade 1000. At the same time, the cold air in the rear cavity 200 flows out of the blade body through the trailing edge cold air outlet hole 202 for diversion. Part of the cold air can flow out from the inner cavity exhaust air hole 401 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 for subsequent cooling.

[0040] The split-chamber configuration adopted by the blade 1000 of the present application can make the cooling of the front chamber 100 and the rear chamber 200 independently distinguishable, and realize on-demand distribution. The front chamber 100 has a greater cooling demand, and air can be drawn from a lower temperature position to cool it. The temperature of the rear chamber 200 is already low, and air can be drawn from a slightly higher temperature position to cool it, thereby achieving uniform temperature distribution of the entire blade body. Since the front chamber 100 and the rear chamber 200 are independent of each other, they can adopt different cooling forms, such as oil cooling or water cooling for the front chamber 100 and air cooling for the rear chamber 200, and optimization and improvement can be carried out as needed.

[0041] Preferably, please refer to Figure 3 As shown, the inner cavity air discharge holes 401 are also used to connect an external cold air source and introduce cold air into the inner cavity of the blade body through the trailing edge cold air return holes 203 when the inner cavity of the blade body is short of cold air. Specifically, the inner cavity air discharge holes 401 are also used to connect an external cold air source and introduce cold air into the rear cavity 200 through the trailing edge cold air return holes 203 when the rear cavity 200 is short of cold air.

[0042] It can be understood that the inner cavity air discharge hole 401 not only has a conventional exhaust function, but can also be used as an air inlet for cold air in reverse. Since the inner cavity air discharge hole 401 is close to the trailing edge cold air return hole 203 and is connected to the trailing edge cold air return hole 203, when the rear cavity 200 is short of cold air, an external cold air source can be connected to the trailing edge cold air return hole 203 through the inner cavity air discharge hole 401 to draw air. Since the air flow direction of the trailing edge cold air return hole 203 remains unchanged, cold air is always returned to the rear cavity 200. Therefore, by switching the exhaust or air intake function of the inner cavity air discharge hole 401, the amount of cold air refluxed from the trailing edge cold air return hole 203 can be regulated to meet the needs of different cooling conditions of the rear cavity 200, effectively improve the utilization rate of cold air, and achieve better cooling effect.

[0043] The present application adopts an extended rotating inner cavity design so that the cold air is not limited to the inside of the blade 1000, so that the cold air can achieve more functions (a part of the cold air can be discharged through the inner cavity air discharge holes 401 to expand the functional applications of the cold air, such as heat exchange with other engine components adjacent to the blade body, such as the bearing seat), and the cold air utilization rate is improved. If the amount of cold air is insufficient, it can be supplemented in this way (the inner cavity air discharge holes 401 can also be reversed as an air inlet), and the cold air temperature in the inner cavity of the blade body can be maintained at a low level by adjusting the temperature of the subsequent supplementary mixed cold air as needed.

[0044] Preferably, please refer to Figure 1 As shown, the leading 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 cooling air sources into the front cavity 100 and the rear cavity 200, reduce the overflow of cold air, and reduce the space occupied by the cold air channel, the leading 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, so as to facilitate the smooth and synchronous intake of cold air into the front cavity 100 and the rear cavity 200.

[0046] Optionally, the leading edge cooling air inlet hole 101 and the trailing edge cooling air inlet hole 201 are distributed on opposite sides of the dividing cavity partition 300, so that cooling air can be introduced from the middle of the blade body into the front cavity 100 and the rear cavity 200 respectively and synchronously, and the cooling air in the front cavity 100 is exhausted from the front leading edge air film hole 104, and the cooling air in the rear cavity 200 is finally discharged from the trailing edge slit 206 at the rear, thereby achieving the effect of exhaust cooling of the two sections inside the blade body to both ends respectively, which is beneficial to improving the cooling effect.

[0047] Preferably, please refer to Figure 4 As shown, a plurality of leading edge baffles 102 arranged in a staggered manner are arranged in the front cavity 100 at intervals, and the plurality of leading edge baffles 102 are used to sequentially separate a plurality of drainage channels in the front cavity 100, and two adjacent drainage channels are connected end to end to form a leading edge loop channel 103 that makes multiple reciprocating changes and is arranged in a serpentine shape through the plurality of drainage channels, the inlet of the leading edge loop channel 103 is connected to the leading edge cold air inlet hole 101, and the outlet of the leading edge loop channel 103 is connected to the leading edge air film hole 104.

[0048] It can be understood that the cold air outlets between adjacent leading edge baffles 102 and the inner wall of the front cavity 100 are staggered, so that the flow of the cold air from the leading edge cold air inlet hole 101 into the front cavity 100 is a reciprocating route, which greatly increases the flow time of the cold air in the front cavity 100. At the same time, each leading edge baffle 102 also effectively increases the contact area between the cold air and the entire blade body, which is beneficial to improving the cooling effect.

[0049] Preferably, the reflux cavity gradually widens along the trailing edge cold air outlet hole 202 toward the trailing edge cold air reflux hole 203 , thereby guiding the airflow toward the trailing edge cold air reflux hole 203 and the inner cavity air exhaust hole 401 , and will not reflux along the trailing edge cold air outlet hole 202 .

[0050] It can be understood that by optimizing the internal structure of the reflux chamber, the reflux chamber gradually widens along the direction of the trailing edge cold air outlet hole 202 toward the trailing edge cold air return hole 203, that is, when the trailing edge cold air outlet hole 202 flows out, the air flow pressure in the reflux chamber along the direction of the trailing edge cold air outlet hole 202 toward the trailing edge cold air return hole 203 gradually decreases, making it easier for the outflowing gas of the trailing edge cold air outlet hole 202 to flow in the direction of the trailing edge cold air return hole 203 and the inner cavity exhaust air hole 401, and will not flow back along the trailing edge cold air outlet hole 202, which is beneficial to ensuring the discharge efficiency of the cold air and thus ensuring the cooling effect.

[0051] Preferably, please refer to Figure 4 As shown, a plurality of trailing edge spoiler columns 204 are arranged in an array in the rear cavity 200 .

[0052] It is understandable that the trailing edge spoiler columns 204 are arranged in an array in the rear cavity 200, which can effectively enhance the cooling effect. The trailing edge spoiler columns 204 can not only reduce the flow rate of the cold air and extend the residence time of the cold air in the rear cavity 200, but also greatly increase the contact area between the cold air and the rear cavity 200 as a whole, which is conducive to improving the heat exchange effect and enhancing the cooling effect.

[0053] In the preferred embodiment, the diameter of the trailing edge spoiler column 204 is in the range of 2-4 mm.

[0054] It is understandable 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, it is easy to cause heat accumulation in the center of the trailing edge spoiler column 204, which is not easy to dissipate heat, resulting in heat concentration at the connection between the trailing edge spoiler column 204 and the blade body, which is not conducive to ensuring the uniformity of the temperature distribution of the blade body as a whole. At the same time, considering that the trailing edge spoiler column 204 needs to avoid blocking the trailing edge split 206 to reduce interference with the smooth discharge of cold air through the trailing edge split 206, the present application provides a preferred diameter range of the trailing edge spoiler column 204, which can simultaneously ensure the airflow deceleration effect and heat dissipation effect of the trailing edge spoiler column 204.

[0055] Preferably, please refer to Figure 4 As shown, adjacent trailing edge spoiler columns 204 are spaced apart along the air outlet direction of the trailing edge split 206 to form an air outlet channel, and the air outlet channel is connected to the trailing edge split 206. Specifically, the width of the air outlet channel ranges from 2 to 6 mm.

[0056] It is understandable that in order to prevent the trailing edge spoiler column 204 from blocking the trailing edge split slit 206, thereby interfering with the smooth outflow of cold air from the trailing edge split slit 206 and affecting the cooling and heat dissipation effect, while the trailing edge spoiler column 204 is arranged in an array, each adjacent trailing edge spoiler column 204 along the air outlet direction of the trailing edge split slit 206 also forms a series of air outlet channels, so that the cold air can be smoothly exhausted from the outlet of the trailing edge split slit 206 after passing through the air outlet channels. It should be noted that the trailing edge split slit 206 is a plurality of gap outlets arranged at intervals, so each air outlet channel is arranged in a one-to-one correspondence with each trailing edge split slit 206. In consideration of the diameter of the trailing edge spoiler column 204 and the width of the trailing edge slit 206, the width of the air outlet channel should not be too large, otherwise the deceleration and buffering effect of the trailing edge spoiler column 204 will be weakened; similarly, the width of the air outlet channel should not be too small to avoid affecting the smooth flow of cold air. The present application provides an optimal width range of the air outlet channel, which can simultaneously ensure the buffering effect of the trailing edge spoiler column 204 and the discharge and heat dissipation effect of the cold air.

[0057] Of course, the present application does not exclude the solution of staggered arrangement of the air outlet channel and the trailing edge slit 206 , especially when the width of the air outlet channel is much larger than the width of the trailing edge slit 206 , the staggered arrangement does not affect the smooth exhaust of cold air.

[0058] In this preferred embodiment, the spacing between each row of trailing edge spoiler columns 204 along the outlet direction of the outlet channel is 3-8 mm.

[0059] It is understandable that, since the trailing edge spoiler columns 204 are arranged in multiple rows along the outlet direction of the outlet channel, if the spacing between the rows of trailing edge spoiler columns 204 is too small, most of the airflow will be directly discharged from the outlet channel, which is not conducive to achieving the buffering and deceleration effect of the airflow, and affects the heat dissipation enhancement effect of the trailing edge spoiler columns 204; if the spacing is too large, due to limited space, the number of trailing edge spoiler columns 204 is bound to be reduced, which is not conducive to achieving a better heat dissipation effect. Taking these factors into consideration, the present application provides a preferred spacing range between the rows of trailing edge spoiler columns 204 along the outlet direction of the outlet channel, which can simultaneously ensure the buffering reduction and heat dissipation effects of the trailing edge spoiler columns 204.

[0060] According to another aspect of the present application, an aircraft engine is also provided, which includes the above-mentioned rotating inner cavity air supply cooling blade.

[0061] The aircraft engine of the present application also has the above-mentioned beneficial effects. It also includes realizing that while the cold air flows through the blade body, it can also exchange heat with other engine components adjacent to the blade body, such as the bearing seat, thereby improving the utilization rate of the cold air. Since the cold air realizes the function of cooling the bearing seat, there is no need to design a cooling system for the bearing seat separately. At the same time, the cooling can also play the role of interstage sealing. According to actual needs, the cold air can be diverted 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 a role in cooling or sealing; if the temperature of the subsequent part of the trailing edge is still high, the cold air can be supplemented so that the final cooling effect reaches the expected value.

[0062] It should be noted that, in this article, the terms "comprises", "includes" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or apparatus.

[0063] This article uses specific examples to illustrate the principles and implementation methods of this application. The above examples are only used to help understand the method and its core ideas of this application. The above is only the preferred implementation method of this application. It should be pointed out that due to the limitations of textual expression and the objective existence of infinite specific structures, ordinary technicians in this technical field can make several improvements, modifications or changes without departing from the principles of this application, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, should be regarded as the protection of this application.

Claims

1. A rotating inner cavity air supply cooling blade, comprising a blade body, wherein a plurality of trailing edge slits (206) are provided at intervals at the trailing edge end of the blade body, wherein: A trailing edge cooling air inlet hole (201) is provided on the side wall of one of the two opposite sides of the blade, and a trailing edge cooling air outlet hole (202) and a trailing edge cooling air return hole (203) are provided 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 cooling air return hole (203). The blade body boss (400) is used to enclose the outer side of the blade body to form a return cavity. An inner cavity air discharge hole (401) is provided on the blade body boss (400). The inner cavity air discharge hole (401) and the trailing edge cooling air return hole (203) is connected, 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 discharge the cold air in the inner cavity of the blade body to the reflow cavity, the trailing edge cold air reflow hole (203) is used to return a part of the cold air in the reflow cavity to the inner cavity of the blade body and guide the cold air to be finally discharged from the trailing edge slit (206), and the inner cavity exhaust air hole (401) is used to discharge another part of the cold air in the reflow cavity to a preset position so as to cool or seal other components of the aircraft engine.

2. The rotating inner cavity air supply cooling blade according to claim 1, characterized in that: The inner cavity of the blade body is provided with a cavity partition (300), and the cavity partition (300) 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 opened on the side wall of the front cavity (100), and the leading edge cold air inlet hole (101) 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), and the leading edge air film hole (104) is used to discharge the cold air in the front cavity (100).

3. The rotating inner cavity air supply cooling blade according to claim 2, characterized in that: The leading 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.

4. The rotating inner cavity air supply cooling blade according to claim 1, characterized in that: The inner cavity air discharge holes (401) are also used to connect to an external cold air source when the inner cavity of the blade body is insufficiently cold, and to introduce cold air into the inner cavity of the blade body through the trailing edge cold air return holes (203).

5. The rotating inner cavity air supply cooling blade according to claim 2, characterized in that: A plurality of staggered leading edge baffles (102) are arranged at intervals in the front cavity (100), and the plurality of leading edge baffles (102) are used to sequentially separate a plurality of drainage channels in the front cavity (100). Two adjacent drainage channels are connected end to end to form a leading edge loop channel (103) that changes direction multiple times and is arranged in a serpentine shape through the plurality of drainage channels. The inlet of the leading edge loop channel (103) is connected to the leading edge cold air inlet hole (101), and the outlet of the leading edge loop channel (103) is connected to the leading edge air film hole (104).

6. The rotating inner cavity air supply cooling blade according to claim 1, characterized in that: The reflux cavity gradually widens along the direction from the trailing edge cold air outlet hole (202) to the trailing edge cold air return hole (203), thereby guiding the airflow to flow in the direction of the trailing edge cold air return hole (203) and the inner cavity exhaust air hole (401), and will not flow back along the trailing edge cold air outlet hole (202).

7. The rotating inner cavity air supply cooling blade according to claim 1, characterized in that: A plurality of trailing edge spoiler columns (204) are arranged in an array in the rear cavity (200), and the diameter of the trailing edge spoiler columns (204) ranges from 2 to 4 mm.

8. The rotating inner cavity air supply cooling blade according to claim 7, characterized in that: Adjacent trailing edge spoiler columns (204) are arranged at intervals along the air outlet direction of the trailing edge split slit (206) to form an air outlet channel, the air outlet channel is connected to the trailing edge split slit (206), and the width of the air outlet channel ranges from 2 to 6 mm.

9. The rotating inner cavity air supply cooling blade according to claim 8, characterized in that: The spacing between each row of trailing edge spoiler columns (204) along the air outlet direction of the air outlet channel is 3-8 mm.

10. An aircraft engine, characterized in that: It comprises the rotating inner cavity air supply cooling blade as described in any one of claims 1-9.

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