A turbine guide vane

Abstract

The application belongs to the technical field of aero-engines, and specifically discloses a turbine guide vane. The ejection pipe is communicated with the first cooling chamber, the middle part of the ejection pipe is provided with a reduced-diameter section, the high-pressure air inlet is arranged on the side of the ejection pipe away from the first cooling chamber and communicated with the first cooling chamber, so that a low-pressure area is formed at the outlet of the ejection pipe after the gas passes through the reduced-diameter section; the connecting part is arranged on the outer side of the ejection pipe and the two parts enclose the low-pressure air inlet chamber communicated with the first cooling chamber, the low-pressure air inlet is arranged at the connecting part and communicated with the low-pressure air inlet chamber, so that the gas in the engine nacelle passes through the low-pressure air inlet and then enters the first cooling chamber through the low-pressure area, thereby realizing the ejection function, improving the refrigeration effect on the vane without increasing the bleed air ratio of the external cold air of the engine, avoiding the phenomenon of reducing the engine performance, and improving the practicability of the turbine guide vane.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, in particular to a turbine guide vane. BACKGROUND

[0002] In order to improve performance and power, aero-engines and gas turbines continuously increase engine cycle parameters, and the temperature resistance of turbine blade metal materials cannot meet the increase of engine cycle parameters, so the heat protection demand of turbine blades is increasing. Since the average annual increase of the temperature resistance of turbine blade metal is not more than 5℃, which is far lower than the increase of turbine inlet temperature, in order to reduce the metal temperature, the turbine blade inner cavity is hollowed out for cooling design, different cooling structures are designed according to the heat exchange intensity of different positions of the blade, and finally the purpose of reducing the metal temperature and improving the service life of the turbine blade is achieved.

[0003] The existing turbine guide vane cooling mainly includes multi-cavity circulation convection cooling, impact cooling, air film cooling, split joint cooling, etc. Due to the restriction of the blade profile structure, different cooling units are used at different positions of the turbine guide. For high cycle parameter turbine guides, the leading edge of the blade is usually cooled by impact + air film, the mid-chord region of the blade is cooled by impact + boss cooling structure, and the trailing edge region is cooled by spoiler column cooling form. At present, this technology is very mature and has been widely used in large, medium and small aero-engines.

[0004] However, with the further increase of the temperature in front of the turbine of the aero-engine, the cooling form through the optimization of the inner cavity cooling structure to strengthen heat exchange and reduce the blade metal temperature is limited, and only passive full air film cooling can be used to reduce the blade temperature, which also increases the cold gas bleed air ratio and causes the performance of the engine to decrease. SUMMARY

[0005] Therefore, the technical problem to be solved by the present application is that in the prior art, with the further increase of the temperature in front of the turbine of the aero-engine, only passive full air film cooling can be used to reduce the blade temperature, which increases the cold gas bleed air ratio and reduces the performance of the engine.

[0006] Therefore, the present application provides a turbine guide vane, comprising:

[0007] a blade body having a mid-chord, the mid-chord having a first cooling chamber;

[0008] An ejector structure is mounted on the blade body, the ejector structure comprising an ejector pipe, a high-pressure air inlet, a connecting part and a low-pressure air inlet, a middle part of the ejector pipe is provided with a reduced diameter section, one side of the ejector pipe close to the first cooling chamber is communicated with the first cooling chamber, the high-pressure air inlet is arranged on the side of the ejector pipe away from the first cooling chamber and communicated with the ejector pipe, the connecting part is connected with the ejector pipe and arranged on the outside of the ejector pipe, a low-pressure air inlet chamber communicated with the first cooling chamber is enclosed between the connecting part and the ejector pipe, and the low-pressure air inlet is arranged on the connecting part and communicated with the low-pressure air inlet chamber.

[0009] Optionally, the turbine guide vane,

[0010] The blade body also has a leading edge and a trailing edge, the leading edge has a second cooling chamber, and the trailing edge has a third cooling chamber.

[0011] The blade body also has a leading edge and a trailing edge, the leading edge has a second cooling chamber, and the trailing edge has a third cooling chamber.

[0012] Optionally, the turbine guide vane,

[0013] The second partition plate is arranged in the second cooling chamber and connected with the inner wall surface of the leading edge to form a first double-wall structure.

[0014] Optionally, the turbine guide vane,

[0015] One end of the second partition plate is connected with the first partition plate, the other end extends away from the first partition plate and is adaptively connected with the inner wall surface of the leading edge.

[0016] Optionally, the turbine guide vane,

[0017] The middle chord comprises a middle chord back and a middle chord basin, and the middle chord basin is arranged opposite to the middle chord back.

[0018] The partition plate assembly further comprises a plurality of third partition plates, a plurality of the third partition plates are arranged in the first cooling chamber, one third partition plate is arranged close to the inner wall surface of the middle chord back, and one third partition plate is arranged close to the inner wall surface of the middle chord basin, forming at least two oppositely arranged second double-wall structures.

[0019] Optionally, the turbine guide vane,

[0020] One end of any one of the third partition plates is connected with one of the first partition plates, and the other end extends towards a direction away from the first partition plate until connected with another first partition plate, and the third partition plate is adaptively arranged with the inner wall surface of the middle chord.

[0021] Optionally, the turbine guide vane,

[0022] Any partition plate in the partition plate assembly is provided with a plurality of impact holes.

[0023] Optionally, the turbine guide vane,

[0024] The trailing edge further has a communication structure for communicating the third cooling chamber with the outside;

[0025] Further comprising a spoiler arranged in the third cooling chamber;

[0026] A flow guide is arranged between the spoiler and the communication structure.

[0027] Optionally, the turbine guide vane,

[0028] The leading edge is provided with a plurality of film holes to communicate the second cooling chamber with the outside; and / or

[0029] The middle chord is provided with a plurality of film holes to communicate the first cooling chamber with the outside.

[0030] Optionally, the turbine guide vane,

[0031] The connecting portion has a sleeve structure;

[0032] The low-pressure air inlet is provided with a plurality of low-pressure air inlets which are circumferentially distributed on the connecting portion.

[0033] The technical scheme provided by the present application has the following advantages:

[0034] The turbine guide vane provided by the present application comprises a vane body and an injection structure. The vane body has a middle chord, and the middle chord has a first cooling chamber. The injection structure is mounted on the vane body. The injection structure comprises an injection pipeline, a high-pressure air inlet, a connecting portion and a low-pressure air inlet. A middle part of the injection pipeline is provided with a reduced diameter section. One side of the injection pipeline close to the first cooling chamber is in communication with the first cooling chamber. The high-pressure air inlet is arranged on the side of the injection pipeline away from the first cooling chamber, and the high-pressure air inlet is in communication with the injection pipeline. The connecting portion is connected with the injection pipeline and arranged on the outside of the injection pipeline. A low-pressure air inlet chamber in communication with the first cooling chamber is formed between the connecting portion and the injection pipeline. The low-pressure air inlet is arranged on the connecting portion and in communication with the low-pressure air inlet chamber.

[0035] The turbine guide vane of the structure, by communicating the injection pipe with the first cooling chamber, providing the middle of the injection pipe with a reduced diameter section, and setting the high-pressure air inlet on the side of the injection pipe away from the first cooling chamber and communicating with the first cooling chamber, so that the gas after passing through the reduced diameter section of the injection pipe will form a low-pressure area at the outlet; and by setting the connecting part on the outside of the injection pipe and the two enclosing a low-pressure air inlet chamber communicating with the first cooling chamber, setting the low-pressure air inlet at the connecting part communicating with the low-pressure air inlet chamber, so that the gas in the engine nacelle will pass through the low-pressure air inlet and enter the first cooling chamber through the low-pressure area, thereby realizing the injection function. Compared with the existing scheme of cooling the blade by adopting a full gas film cooling structure, the turbine guide vane of the structure reuses the gas in the engine nacelle by adding an injection structure, without the need to increase the bleed air ratio of the external cold gas to improve the refrigeration effect on the blade, avoiding the phenomenon of reducing the engine performance, and improving the practicality of the turbine guide vane. BRIEF DESCRIPTION OF DRAWINGS

[0036] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the drawings needed in the specific embodiments or the prior art description will be briefly introduced below. Obviously, the drawings in the following description are some embodiments of the present application, and those skilled in the art can also obtain other drawings according to these drawings without creative labor.

[0037] Figure 1 is a top view of the turbine guide vane provided in the present application;

[0038] Figure 2 is Figure 1 a sectional view of section A-A;

[0039] Figure 3 is Figure 2 a sectional view of section B-B;

[0040] Figure 4 is Figure 2 a sectional view of section C-C;

[0041] Figure 5 is a flow diagram of the cold gas in the turbine guide vane provided in the present application;

[0042] Figure 6 is a top view of the turbine guide vane provided in the present application;

[0043] BRIEF DESCRIPTION OF DRAWINGS

[0044] 1-blade body; 11-middle chord; 111-first cooling chamber; 112-middle chord blade back; 113-middle chord blade pot; 12-leading edge; 121-second cooling chamber; 13-trailing edge; 131-third cooling chamber; 132-communication structure; 14-film hole;

[0045] 2-ejector structure; 201-ejector pipe; 202-high pressure inlet; 203-connection; 204-low pressure inlet; 205-low pressure inlet chamber;

[0046] 3-baffle assembly; 31-first baffle; 32-second baffle; 33-third baffle; 34-impact hole;

[0047] 4-turbulence generator;

[0048] 5-flow guide. DETAILED DESCRIPTION

[0049] The technical solutions of the present application will be described clearly and completely below in conjunction with the drawings. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0050] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", "third" are only for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0051] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0052] In addition, the technical features involved in the different embodiments of the present application described below can be combined with each other as long as they do not conflict with each other.

[0053] Example 1

[0054] The embodiment provides a turbine guide vane, which comprises a vane body 1 and an ejector structure 2. Figures 1 to 6 As shown, the vane body 1 has a middle chord 11, and the middle chord 11 has a first cooling chamber 111; the ejector structure 2 is installed on the vane body 1, and the ejector structure 2 comprises an ejector pipe 201, a high-pressure air inlet 202, a connecting part 203 and a low-pressure air inlet 204, the middle part of the ejector pipe 201 is provided with a reduced diameter section, the side of the ejector pipe 201 close to the first cooling chamber 111 is in communication with the first cooling chamber 111, the high-pressure air inlet 202 is arranged on the side of the ejector pipe 201 away from the first cooling chamber 111, and the high-pressure air inlet 202 is in communication with the ejector pipe 201, the connecting part 203 is connected with the ejector pipe 201 and arranged on the outer side of the ejector pipe 201, and the low-pressure air inlet chamber 205 in communication with the first cooling chamber 111 is enclosed between the connecting part 203 and the ejector pipe 201, and the low-pressure air inlet 204 is arranged on the connecting part 203 and in communication with the low-pressure air inlet chamber 205.

[0055] The turbine guide vane has the advantages that the ejector pipe 201 is in communication with the first cooling chamber 111, the middle part of the ejector pipe 201 is provided with a reduced diameter section, the high-pressure air inlet 202 is arranged on the side of the ejector pipe 201 away from the first cooling chamber 111 and in communication with the first cooling chamber 111, so that the gas passing through the reduced diameter section of the ejector pipe 201 forms a low-pressure area at the outlet; the connecting part 203 is arranged on the outer side of the ejector pipe 201, and the low-pressure air inlet chamber 205 in communication with the first cooling chamber 111 is enclosed between the connecting part 203 and the ejector pipe 201, and the low-pressure air inlet 204 is arranged on the connecting part 203 and in communication with the low-pressure air inlet chamber 205, so that the gas in the engine nacelle passes through the low-pressure air inlet 204 and enters the first cooling chamber 111 through the low-pressure area, thereby realizing the ejector function. Compared with the prior art in which the vane is cooled by adopting a full gas film heat dissipation structure, the turbine guide vane has the advantages that the gas in the engine nacelle is reused by adding the ejector structure 2, the refrigeration effect on the vane can be improved without increasing the bleed air ratio of the external cold gas of the engine, the phenomenon of reducing the performance of the engine is avoided, and the practicability of the turbine guide vane is improved.

[0056] As shown in Figure 1 , Figure 4 and Figure 5As shown in

[0057] Still as Figure 1 、 Figure 4 and Figure 5 shown, the turbine guide vane provided by the embodiment has a second cooling chamber 121 in the leading edge 12 and a third cooling chamber 131 in the trailing edge 13. In addition, the partition assembly 3 includes a second partition 32. The second partition 32 is arranged in the second cooling chamber 121 and connected with the inner wall surface of the leading edge 12 to form a first double-wall structure.

[0058] It should be noted that in the embodiment, one end of the second partition 32 is connected with the first partition 31, and the other end extends away from the first partition 31 and is connected with the inner wall surface of the leading edge 12.

[0059] Further, the turbine guide vane provided by the embodiment does not limit the shape of the leading edge 12. In order to retain the use habit of the existing turbine guide vane, the leading edge 12 is partially provided with an arc-shaped structure. At this time, the second partition 32 also has an arc-shaped structure. The second partition 32 and the inner wall surface of the leading edge 12 form a first double-wall structure. The first double-wall structure is internally provided with an impact chamber. One end of the impact chamber is communicated with the second cooling chamber 121 through an impact hole 34, and the other end is communicated with the outside through a film hole 14.

[0060] It should be noted that in the embodiment, according to experiments, the pressure in the blade basin area of the leading edge 12 is high. At this time, in order to reduce the loss of cold gas, only the film hole 14 is arranged in the blade basin area of the leading edge 12 to realize spray cooling. At the same time, since the pressure in the blade area of the leading edge 12 is low, the first double-wall structure is arranged in the blade area of the leading edge 12, so that the cold gas enters the impact chamber in the first double-wall structure through the double-wall impact hole 34 and then flows out through the film hole 14, realizing cooling.

[0061] As Figures 1 to 6As shown, the turbine guide vane provided by the embodiment comprises a middle chord 11, which comprises a middle chord blade back 112 and a middle chord blade basin 113. At this time, the middle chord blade basin 113 is arranged relative to the middle chord blade back 112; the baffle assembly 3 further comprises a plurality of third baffles 33, which are arranged in the first cooling chamber 111, one third baffle 33 is arranged close to the inner wall surface of the middle chord blade back 112, and one third baffle 33 is arranged close to the inner wall surface of the middle chord blade basin 113, forming at least two oppositely arranged second double-wall structures.

[0062] It can be explained that the number of third baffles 33 of the turbine guide vane provided by the embodiment is not limited, and can be two or more. As one of the embodiments, two third baffles 33 are arranged. At this time, one third baffle 33 is arranged close to the middle chord blade back 112 and forms a second double-wall structure together with the middle chord blade back 112, and the other third baffle 33 is arranged close to the middle chord blade basin 113 and forms a second second double-wall structure together with the middle chord blade basin 113.

[0063] Further, the turbine guide vane provided by the embodiment is characterized in that one end of any third baffle 33 is connected with one first baffle 31, the other end thereof extends away from the first baffle 31 until connected with another first baffle 31, and the third baffle 33 is adaptively arranged with the inner wall surface of the middle chord 11.

[0064] It can be explained that the turbine guide vane provided by the embodiment is characterized in that the two first baffles 31 in the baffle assembly 3 are each provided with a plurality of impact holes 34. The number of impact holes 34 is not limited in the embodiment, and as one of the embodiments, two groups of impact holes 34 are arranged. Specifically, the first baffle 31 arranged close to the second cooling chamber 121 is provided with one group of impact holes 34, so as to communicate the first cooling chamber 111 and the second cooling chamber 121; the first baffle 31 arranged close to the third cooling chamber 131 is provided with one group of impact holes 34, so as to communicate the first cooling chamber 111 and the third cooling chamber 131. It should be noted that the adjacent impact holes 34 in any group are arranged in a spaced manner along the direction of the high-pressure air inlet 202 towards the first cooling chamber 111.

[0065] As shown in Figure 4 and Figure 6 As shown, the turbine guide vane provided by the embodiment further comprises a communication structure 132 for communicating the third cooling chamber 131 with the outside; at this time, a turbulence piece 4 is further arranged in the third cooling chamber 131 in order to strengthen heat exchange; if it is necessary to control the flow direction of the cold air, a flow guide piece 5 is further arranged between the turbulence piece 4 and the communication structure 132.

[0066] In one implementation, the connecting structure 132 is a central split.

[0067] Still Figure 4 and Figure 6 As shown, in order to retain the usage habits of turbine blades, the turbine guide vane provided in this embodiment should have multiple film cooling holes 14 on the leading edge 12 to connect the second cooling chamber 121 with the outside. At this time, the cold air in the second cooling chamber 121 flows into the first double-wall structure for enhanced heat exchange, and then flows to the outside after passing through the film cooling holes 14. At the same time, multiple film cooling holes 14 should also be opened at the middle chord 11 to connect the first cooling chamber 111 with the outside. At this time, the cold air in the first cooling chamber 111 flows into the second double-wall structure for enhanced heat exchange, and then flows to the outside after passing through the film cooling holes 14.

[0068] It can be noted that the turbine guide vane provided in the above embodiment has a sleeve structure in the connecting part 203; multiple low-pressure air inlets 204 are provided, and the low-pressure air inlets 204 are evenly distributed on the connecting part 203 around the circumference.

[0069] The turbine guide vane provided in this embodiment, when in use, shows the following schematic diagram of the cool air flow. Figure 5 and Figure 6 As shown, a portion of the cool air enters the ejector pipe 201 from the high-pressure air inlet 202 and enters the first cooling chamber 111, while another portion of the gas inside the engine nacelle enters the first cooling chamber 111 as another type of cool air through the low-pressure air inlet 204, and the two portions of cool air are mixed. The mixed cold air has multiple branches that cool the leading edge 12, the middle chord 11, and the trailing edge 13 respectively. Specifically, a portion of the cold air enters the second cooling chamber 121 through the impact hole 34 in the first partition 31 located near the second cooling chamber 121, and then flows out to the outside through the air film hole 14 in the blade basin area of ​​the leading edge 12 and the first double-wall structure in the blade back area of ​​the leading edge 12, thereby cooling the leading edge 12 of the blade; a portion of the cold air flows out to the outside after passing through two second double-wall structures, thereby cooling the middle chord 11 of the blade; and a portion of the cold air, after passing through the third cooling chamber 131, first passes through the turbulence element 4 to increase the heat exchange capacity, and then flows out through the connecting structure 132 of the trailing edge 13 after being guided by the flow guide 5, thereby cooling the trailing edge 13 of the blade.

[0070] By dividing the mixed cold air into multiple branches to cool the leading edge 12, the middle chord 11 and the trailing edge 13 respectively, the temperature gradient between different regions of the turbine blade can be effectively reduced, the thermal stress of the turbine guide blade can be significantly reduced, and the engineering application value of the turbine guide blade can be improved.

[0071] Obviously, the above embodiments are merely example for clearly illustrating but not limitation to the embodiments. Based on the above description, other different forms of changes or variations can be made by those skilled in the art. Here, all the embodiments need not and can not be enumerated. The obvious changes or variations derived from the above description are still within the protection scope of the present application.

Claims

1. A turbine guide vane, characterized by, The turbine guide vane comprises: a blade body (1) having a mid-chord (11) with a first cooling chamber (111); an ejector structure (2) mounted on the blade body (1), the ejector structure (2) comprising an ejector pipe (201), a high-pressure air inlet (202), a connecting portion (203) and a low-pressure air inlet (204), a middle portion of the ejector pipe (201) being provided with a reduced-diameter section, the ejector pipe (201) being in communication with the first cooling chamber (111) at a side close to the first cooling chamber (111), the high-pressure air inlet (202) being provided at a side of the ejector pipe (201) away from the first cooling chamber (111) and in communication with the ejector pipe (201), the connecting portion (203) being connected with the ejector pipe (201) and provided at an outer side of the ejector pipe (201), a low-pressure air inlet chamber (205) in communication with the first cooling chamber (111) being enclosed between the connecting portion (203) and the ejector pipe (201), the low-pressure air inlet (204) being provided on the connecting portion (203) and in communication with the low-pressure air inlet chamber (205); wherein the connecting portion (203) is in a sleeve structure, and the low-pressure air inlet (204) is provided in a plurality of numbers and is circumferentially and uniformly distributed on the connecting portion (203).

2. The turbine guide vane according to claim 1, wherein: the blade body (1) further has a leading edge (12) with a second cooling chamber (121) and a trailing edge (13) with a third cooling chamber (131); further comprising a partition assembly (3) comprising a plurality of first partitions (31), one of the first partitions (31) being arranged between the first cooling chamber (111) and the second cooling chamber (121), and one of the first partitions (31) being arranged between the first cooling chamber (111) and the third cooling chamber (131).

3. The turbine guide vane according to claim 2, wherein: the partition assembly (3) further comprises a second partition (32) arranged in the second cooling chamber (121) and connected with an inner wall surface of the leading edge (12) to form a first double-wall structure.

4. The turbine guide vane according to claim 3, wherein: one end of the second partition (32) is connected with the first partition (31), and the other end extends away from the first partition (31) and is adaptively connected with the inner wall surface of the leading edge (12).

5. The turbine guide vane according to claim 2, wherein: the mid-chord (11) comprises a mid-chord blade back (112) and a mid-chord blade pan (113), and the mid-chord blade pan (113) is arranged opposite to the mid-chord blade back (112). The baffle assembly (3) further comprises a plurality of third baffles (33), the plurality of third baffles (33) are arranged in the first cooling chamber (111), one third baffle (33) is arranged close to the inner wall surface of the mid-chord back (112), and one third baffle (33) is arranged close to the inner wall surface of the mid-chord back (113), forming at least two oppositely arranged second double-wall structures.

6. The turbine guide vane of claim 5, wherein, One end of any of the third baffles (33) is connected with one of the first baffles (31), the other end extends away from the first baffle (31) until connected with another first baffle (31), and the third baffle (33) is contoured to the inner wall surface of the mid-chord (11).

7. The turbine guide vane of any of claims 2-6, wherein, Any of the baffles in the baffle assembly (3) is provided with a plurality of impact holes (34).

8. The turbine guide vane of any of claims 2-6, wherein, The trailing edge (13) further has a communication structure (132) for communicating the third cooling chamber (131) with the outside; Further comprising a spoiler (4) arranged in the third cooling chamber (131); A flow guide (5) is arranged between the spoiler (4) and the communication structure (132).

9. The turbine guide vane of any of claims 2-6, wherein, The leading edge (12) is provided with a plurality of film holes (14) to communicate the second cooling chamber (121) with the outside; and / or The mid-chord (11) is provided with a plurality of film holes (14) to communicate the first cooling chamber (111) with the outside.

10. The turbine guide vane of claim 1, wherein, The connecting portion (203) has a sleeve structure; The low-pressure inlet (204) is provided with a plurality of low-pressure inlets (204) circumferentially distributed on the connecting portion (203).

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