Turbine guide vane cooling structure

Abstract

The utility model belongs to the field of turbine guide vane cooling, and particularly relates to a turbine guide vane cooling structure which comprises an upper edge plate, a lower edge plate and a vane body, the vane body is arranged between the upper edge plate and the lower edge plate, and the interior of the vane body is hollow. Two spacing ribs are arranged in the hollow part at intervals in the direction from the front edge to the tail edge of the blade body, and the hollow part is divided into three cooling cavities by the two spacing ribs; the spacing rib is provided with a circulating hole communicated with two adjacent cooling cavities, and the tail edge of the blade body is provided with a tail edge groove communicated with the rear cooling cavity; the upper edge plate is provided with a first air inlet communicated with the front cooling cavity, and the lower edge plate is provided with a second air inlet communicated with the middle cooling cavity. The cooling blade has the advantages of simple structure, high structural strength of the blade body, capability of achieving a partitioned cooling effect and good cooling effect.

Description

Technical Field

[0001] The utility model belongs to the field of turbine guide blade cooling, in particular to a turbine guide blade cooling structure. Background Art

[0002] Gas turbine engines are the main power units of aircraft. Increasing the temperature before the turbine can greatly increase the thrust of the engine and reduce fuel consumption. At present, the temperature of the gas before the turbine of advanced gas turbine engines is as high as 1800K~2000K, while the maximum temperature resistance of modern third-generation single-crystal high-temperature alloys does not exceed 1400K. In order to ensure the normal, reliable and long-term operation of turbine blades in extremely harsh environments, effective thermal protection measures must be taken, including spraying thermal insulation coatings, developing new high-temperature resistant materials, and adopting advanced blade cooling technology. Spraying thermal insulation coatings generally does not reduce the temperature of the blade substrate by more than 30K, and the current spraying technology makes it difficult to maintain uniform coating thickness. Spraying thermal barrier coatings on small-sized blades has a greater impact on the performance of gas turbine engines. The temperature resistance of new materials increases at a rate of about 8K per year, which is much lower than the average annual growth rate of about 20K of the gas temperature before the turbine, and the cost of materials increases exponentially with the increase of their temperature resistance. The application of blade cooling technology has the most obvious effect on increasing the gas temperature before the turbine.

[0003] The cooling measure usually adopted for gas turbine blades is to draw out a part of the low-temperature high-pressure air from the compressor, and introduce the high-pressure air into the cooling air cavity of each stage of turbine blades through the air system, thereby cooling the turbine blades. The cooling methods commonly used for turbine blades in service are enhanced convection cooling, impingement cooling, air film cooling and cooling with thermal barrier coating.

[0004] The traditional gas turbine guide vane cooling technology design has the following main drawbacks:

[0005] 1) The cooling efficiency of turbine guide blades is low, and a large amount of cooling gas is required to achieve the desired cooling effect. At the same time, the increasing amount of cooling gas leads to a decrease in the gas involved in the cycle work, and the mixing loss of cooling gas and fuel gas increases, making the flow and flow field structure in the blade cascade flow channel more complicated, which is not conducive to the performance of the gas turbine engine;

[0006] 2) There is a large temperature difference between the blade basin and the back of the turbine guide vane, and the side wall has a large temperature gradient along the chord direction. The cooling air enters the cooling air cavity through a cooling air inlet and flows out from each air film hole. It is difficult to control the amount of cooling air flowing out of each air film hole, and the temperature difference between the blade basin and the back side cannot be effectively reduced. The temperature gradient of the guide vane side wall along the chord direction cannot be effectively reduced, and the problem of non-uniform deformation caused by thermal stress of the guide vane cannot be effectively overcome. Utility Model Content

[0007] The technical problem to be solved by the utility model is to provide a turbine guide blade cooling structure with a simple structure and the function of zoned cooling and good cooling effect.

[0008] The utility model provides a turbine guide blade cooling structure, comprising an upper edge plate, a lower edge plate and a blade body, wherein the blade body is arranged between the upper edge plate and the lower edge plate, and the interior of the blade body is hollow;

[0009] Two spacer ribs are arranged in the hollow along the direction from the leading edge to the trailing edge of the blade body, namely a front spacer rib and a rear spacer rib, and the two spacer ribs divide the hollow into three cooling chambers, namely a front cooling chamber, a middle cooling chamber, and a rear cooling chamber;

[0010] The spacer rib is provided with a flow hole connecting two adjacent cooling cavities, and the trailing edge of the blade body is provided with a trailing edge groove connecting the rear cooling cavity;

[0011] The upper edge plate or the lower edge plate is provided with a first air inlet connected to the front cooling cavity, and the lower edge plate or the upper edge plate is provided with a second air inlet connected to the middle cooling cavity.

[0012] Furthermore, the blade body is made of sweat-inducing material.

[0013] Furthermore, the flow area of ​​the sweating material in the front cooling cavity is larger than the flow area of ​​the flow holes on the front partition ribs, and the flow area of ​​the sweating material in the middle cooling cavity is larger than the flow area of ​​the flow holes on the rear partition ribs.

[0014] Furthermore, the flow area of ​​the flow holes on the front partition rib is greater than the flow area of ​​the flow holes on the rear partition rib.

[0015] Furthermore, a plurality of the flow holes are arranged on the spacer rib, and the plurality of flow holes are arranged at intervals along the height and / or thickness direction of the blade body.

[0016] Furthermore, the first air inlet is in communication with the inner ring cooling air of the combustion chamber, and the second air inlet is in communication with the outer ring cooling air of the combustion chamber.

[0017] Furthermore, a plurality of slot hole ribs are arranged at intervals in the trailing edge slot, and a trailing edge slot hole is formed between two adjacent slot hole ribs.

[0018] Furthermore, the rear cooling cavity is a gradually shrinking structure along the direction from the leading edge to the trailing edge.

[0019] Furthermore, a plurality of flow columns are staggeredly arranged in the rear cooling cavity along the direction from the leading edge to the trailing edge.

[0020] Furthermore, protrusions are arranged on the inner wall of the rear cooling cavity in an alternating manner with the flow columns.

[0021] The turbine guide blade cooling structure provided by the utility model has the following effects:

[0022] 1. The two spacer ribs are used to strengthen the structural strength of the blade on the one hand, and on the other hand, they can transfer the heat of the blade basin and the blade back, conduct the high temperature of the pressure surface to the suction surface, reduce the non-uniform deformation of the blade due to thermal stress, and extend the service life of the structure. On the other hand, the hollow can be divided into three cooling cavities, and as part of the wall of the three cooling cavities, the material used in the cooling cavity can be reduced to ensure the weight of the blade.

[0023] 2. During specific use, the air pressure of the cooling medium injected into the first air inlet is higher than the air pressure of the cooling medium injected into the second air inlet. On the one hand, the cooling medium in the front cooling cavity can flow into the middle cooling cavity through the flow holes, and the cooling medium in the middle cooling cavity can flow into the rear cooling cavity through the flow holes. The cooling medium in the rear cooling cavity finally flows out of the blade through the trailing edge groove. On the other hand, different parts of the blade can be cooled in different areas to make the overall temperature of the blade close, thereby reducing the non-uniform deformation of the blade caused by thermal stress and extending the service life of the structure.

[0024] 3. One end of the flow hole will suck in the cooling medium, and the other end will form a jet to eject the cooling medium, both of which will increase the disturbance of the cooling medium in the cooling cavity, thereby increasing the contact between the cooling medium and the inner wall of the cooling cavity, thereby improving the heat exchange effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Attached Figure 1 It is a schematic diagram of the structure of the utility model;

[0026] Attached Figure 2 It is a front cross-sectional view of the utility model;

[0027] Attached Figure 3 It is a partial schematic diagram of the trailing edge of the utility model;

[0028] Attached Figure 4 It is a cross-sectional view of the trailing edge of the utility model.

[0029] In the figure, 11-upper edge plate; 12-lower edge plate; 13-blade body; 131-blade basin; 132-blade back; 133-leading edge; 134-trailing edge; 14-hollow; 15-spacer rib; 15a-front spacer rib; 15b-rear spacer rib; 16-cooling cavity; 16a-front cooling cavity; 16b-middle cooling cavity; 16c-rear cooling cavity; 17-flow hole; 18-first air inlet; 19-second air inlet; 110-slot rib; 111-trailing edge slot; 112-flow column; 113-protrusion; 114-trailing edge slot. DETAILED DESCRIPTION

[0030] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0031] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back...) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0032] In addition, in the present invention, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0033] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0034] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0035] As attached Figure 1 -Attached Figure 4As shown, the utility model provides a turbine guide blade cooling structure, comprising an upper edge plate 11, a lower edge plate 12 and a blade body 13, wherein the blade body 13 is arranged between the upper edge plate 11 and the lower edge plate 12, and the blade body 13 is hollow inside 14, wherein the blade body 13 comprises a blade basin 131, a blade back 132, a leading edge 133 and a trailing edge 134, the blade basin 131 connects the leading edge 133 and the trailing edge 134 and is arranged toward the high-temperature combustion gas to form a pressure surface, and the blade back 13 2 The leading edge 133 and the trailing edge 134 are connected and arranged opposite to the pressure surface to form a suction surface; and the blade body 13 is hollow 14 inside, that is, the blade basin 131, the blade back 132, the leading edge 133, and the trailing edge 134 are all plate structures, and are formed by the upper edge plate 11 and the lower edge plate 12 to enclose the hollow 14, so that the weight of the blade 1 can be greatly reduced. In specific production, the blade basin 131, the blade back 132, the leading edge 133 and the trailing edge 134 are preferably integrally formed;

[0036] Two spacer ribs 15 are arranged in the hollow 14 along the direction from the leading edge 133 to the trailing edge 134 of the blade body 13, which are respectively a front spacer rib 15a and a rear spacer rib 15b. The two spacer ribs 15 divide the hollow 14 into three cooling chambers 16, which are respectively a front cooling chamber 16a, a middle cooling chamber 16b, and a rear cooling chamber 16c. That is, the two spacer ribs 15 are used to strengthen the structural strength of the blade body 13 on the one hand, and on the other hand, they can transfer the heat of the blade basin 131 and the blade back 132, and conduct the high temperature of the pressure surface to the suction surface, thereby reducing the non-uniform deformation of the blade body 13 caused by thermal stress and extending the service life of the structure. On the other hand, the hollow 14 can also be divided into three cooling chambers 16, and as part of the cavity wall of the three cooling chambers 16, the material used for the cooling chamber 16 is reduced to ensure the weight of the blade; preferably, the spacer ribs 15 are made of materials with good thermal conductivity;

[0037] The spacer rib 15 is provided with a flow hole 17 connecting two adjacent cooling chambers 16, and the trailing edge 134 of the blade body 13 is provided with a trailing edge groove 114 connecting the rear cooling chamber 16c. The flow hole 17 can make the two adjacent cooling chambers 16 communicate with each other. When the air pressure of the cooling medium in one cooling chamber 16 is greater than the air pressure of the cooling medium in the other cooling chamber 16, the cooling medium in the cooling chamber 16 with high air pressure will flow into the cooling chamber 16 with low air pressure through the flow hole 17, and finally flow out from the trailing edge groove 114, so that new cooling medium can enter the cooling chamber 16. In this way, one end of the flow hole 17 will suck in the cooling medium, and the other end will form a jet to eject the cooling medium, which will increase the disturbance of the cooling medium in the cooling chamber 16, thereby improving the contact between the cooling medium and the inner wall of the cooling chamber 16, thereby improving the heat exchange effect;

[0038] The upper edge plate 11 or the lower edge plate 12 is provided with a first air inlet 18 connected to the front cooling cavity 16a, and the lower edge plate 12 or the upper edge plate 11 is provided with a second air inlet 19 connected to the middle cooling cavity 16b. In actual use, the air pressure of the cooling medium injected into the first air inlet 18 is higher than the air pressure of the cooling medium injected into the second air inlet 19, so that the cooling medium in the front cooling cavity 16a flows into the middle cooling cavity 16b through the flow hole 17, and the cooling medium in the middle cooling cavity 16b flows into the rear cooling cavity 16c through the flow hole 17, and the cooling medium in the rear cooling cavity 16c finally flows out of the blade body 13 through the trailing edge groove 114.

[0039] The turbine guide blade cooling structure provided by the utility model has the following effects:

[0040] 1. The two spacer ribs 15 are used to strengthen the structural strength of the blade body 13 on the one hand, and on the other hand, they can transfer the heat of the blade basin 131 and the blade back 132, conduct the high temperature of the pressure surface to the suction surface, reduce the non-uniform deformation of the blade body 13 caused by thermal stress, and extend the service life of the structure. On the other hand, the hollow 14 can also be divided into three cooling cavities 16, and as part of the cavity wall of the three cooling cavities 16, the material used for the cooling cavity 16 is reduced to ensure the weight of the blade.

[0041] 2. During specific use, the air pressure of the cooling medium injected into the first air inlet 18 is higher than the air pressure of the cooling medium injected into the second air inlet 19. On the one hand, the cooling medium in the front cooling cavity 16a can flow into the middle cooling cavity 16b through the flow hole 17, and the cooling medium in the middle cooling cavity 16b can flow into the rear cooling cavity 16c through the flow hole 17. The cooling medium in the rear cooling cavity 16c finally flows out of the blade 13 through the trailing edge groove 114. On the other hand, different parts of the blade 13 can be cooled in different areas to make the overall temperature of the blade 13 close, thereby reducing the non-uniform deformation of the blade 13 caused by thermal stress and extending the service life of the structure.

[0042] 3. One end of the flow hole 17 will suck in the cooling medium, and the other end will form a jet to eject the cooling medium, both of which will increase the disturbance of the cooling medium in the cooling cavity 16, thereby increasing the contact between the cooling medium and the inner wall of the cooling cavity 16, thereby improving the heat exchange effect.

[0043] In one embodiment, the blade body 13 is made of sweating material, that is, when the cooling medium entering the front cooling cavity 16a and the middle cooling cavity 16b meets sufficient air pressure, it can sweat and cool the wall surface of the blade body 13, and form an air film on the outer wall of the blade body 13, and then the air film is insulated, which greatly improves the cooling effect of the blade body 13. Preferably, the blade body 13 is made of porous ceramic-based composite materials with a porosity of 10%-30%. In addition, the upper edge plate 11, the lower edge plate 12 and the spacer ribs 15 are made of non-sweating materials. In this embodiment, a part of the cooling medium entering the cooling cavity 16 flows out of the blade body 13 through sweating, and the other part flows into the adjacent cooling cavity 16 through the flow hole 17, and flows out of the blade body 13 through the trailing edge groove 114.

[0044] In one embodiment, the flow area of ​​the sweating material in the front cooling chamber 16a is larger than the flow area of ​​the flow hole 17 on the front partition rib 15a, that is, most of the cooling medium entering the front cooling chamber 16a sweats out, and a small part flows into the middle cooling chamber 16b through the flow hole 17, and the flow area of ​​the sweating material in the middle cooling chamber 16b is larger than the flow area of ​​the flow hole 17 on the rear partition rib 15b, that is, most of the cooling medium entering the middle cooling chamber 16a sweats out, and a small part flows into the rear cooling chamber 16c through the flow hole 17, so that the main function of the flow hole 17 is to increase the disturbance of the cooling medium in the cooling chamber 16 and provide cooling medium to the rear cooling chamber 16c.

[0045] In one embodiment, the flow area of ​​the flow hole 17 on the front partition rib 15a is greater than the flow area of ​​the flow hole 17 on the rear partition rib 15b, so that when the cooling gas flows in the cooling cavity, a pressure gradient is formed due to the reduction in the flow area, the degree of gas turbulence is increased, and the effect of enhanced heat exchange cooling is achieved.

[0046] In one embodiment, the first air inlet 18 is connected to the inner ring cooling air of the combustion chamber, and the second air inlet 19 is connected to the outer ring cooling air of the combustion chamber, that is, the air pressure of the cooling medium injected into the first air inlet 18 is higher than the air pressure of the cooling medium injected into the second air inlet 19, and the temperature of the cooling medium injected into the first air inlet 18 is lower than the temperature of the cooling medium injected into the second air inlet 19.

[0047] In one embodiment, a plurality of the flow holes 17 are arranged on the spacer ribs 15 , and the plurality of flow holes 17 are spaced apart along the height and / or thickness direction of the blade body 13 , thereby improving the mixing of the cooling medium in the blade body 13 and improving the heat exchange effect.

[0048] In one of the embodiments, a plurality of slot ribs 110 are spaced apart in the trailing edge slot 114, and a trailing edge slot 111 is formed between two adjacent slot ribs 110. In this embodiment, one end of the slot rib 110 is connected to the blade basin 131, and the other end is connected to the blade back 132, thereby improving the connection structural strength between the blade basin 131 and the blade back 132.

[0049] In one embodiment, the rear cooling cavity 16c is a gradually shrinking structure along the direction from the leading edge 133 to the trailing edge 134 , that is, the cavity width of the rear cooling cavity 16c gradually decreases along the direction from the leading edge 133 to the trailing edge 134 .

[0050] In one of the embodiments, a plurality of flow columns 112 are alternately arranged in the direction from the leading edge 133 to the trailing edge 134 in the rear cooling cavity 16c. One end of the flow column 112 is connected to the blade basin 131, and the other end is connected to the blade back 132. This can not only improve the connection strength between the blade basin 131 and the blade back 132, but also increase the flow of the gaseous cooling medium flowing from the flow hole 26 to the trailing edge groove 114, thereby improving the cooling effect.

[0051] In one embodiment, protrusions 113 are arranged on the inner wall of the rear cooling cavity 16c and are staggered with the flow columns 112. The protrusions 113 further improve the flow of the cooling medium and avoid laminar flow on the wall surfaces of the blade basin 131 and the blade back 132, which affects the heat dissipation effect.

[0052] The above is only an embodiment and does not limit the present invention in any way. Any person skilled in the art can make many possible changes, modifications or modifications to the present invention without departing from the scope of the present invention by using the above disclosed technical contents. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the present invention should fall within the scope of protection of the present invention.

Claims

1. A turbine guide blade cooling structure, characterized in that: It comprises an upper edge plate (11), a lower edge plate (12) and a blade body (13), wherein the blade body (13) is arranged between the upper edge plate (11) and the lower edge plate (12), and the blade body (13) is hollow inside (14); Two spacer ribs (15) are arranged in the hollow (14) along the direction from the leading edge (133) to the trailing edge (134) of the blade body (13), respectively being a front spacer rib (15a) and a rear spacer rib (15b); the two spacer ribs (15) divide the hollow (14) into three cooling chambers (16), respectively being a front cooling chamber (16a), a middle cooling chamber (16b), and a rear cooling chamber (16c); The spacer rib (15) is provided with a flow hole (17) communicating with two adjacent cooling cavities (16), and the trailing edge (134) of the blade body (13) is provided with a trailing edge groove (114) communicating with the rear cooling cavity (16c); The upper edge plate (11) or the lower edge plate (12) is provided with a first air inlet (18) connected to the front cooling cavity (16a), and the lower edge plate (12) or the upper edge plate (11) is provided with a second air inlet (19) connected to the middle cooling cavity (16b).

2. The turbine guide vane cooling structure according to claim 1, characterized in that: The blade body (13) is made of sweat-inducing material.

3. The turbine guide vane cooling structure according to claim 2, characterized in that: The flow area of ​​the sweating material in the front cooling cavity (16a) is greater than the flow area of ​​the flow holes (17) on the front partition rib (15a), and the flow area of ​​the sweating material in the middle cooling cavity (16b) is greater than the flow area of ​​the flow holes (17) on the rear partition rib (15b).

4. The turbine guide vane cooling structure according to claim 3, characterized in that: The flow area of ​​the flow holes (17) on the front spacer rib (15a) is greater than the flow area of ​​the flow holes (17) on the rear spacer rib (15b).

5. The turbine guide vane cooling structure according to any one of claims 1 to 4, characterized in that: A plurality of the flow holes (17) are arranged on the spacer rib (15), and the plurality of flow holes (17) are arranged at intervals along the height and / or thickness direction of the blade body (13).

6. The turbine guide vane cooling structure according to any one of claims 1 to 4, characterized in that: The first air inlet (18) is in communication with the inner ring cooling air of the combustion chamber, and the second air inlet (19) is in communication with the outer ring cooling air of the combustion chamber.

7. The turbine guide vane cooling structure according to any one of claims 1 to 4, characterized in that: A plurality of slot hole ribs (110) are arranged at intervals in the trailing edge slot (114), and a trailing edge slot hole (111) is formed between two adjacent slot hole ribs (110).

8. The turbine guide vane cooling structure according to any one of claims 1 to 4, characterized in that: The rear cooling cavity (16c) is a gradually shrinking structure along the direction from the leading edge (133) to the trailing edge (134).

9. The turbine guide vane cooling structure according to claim 8, characterized in that: A plurality of flow columns (112) are arranged in an alternating manner in the rear cooling cavity (16c) along a direction from a leading edge (133) to a trailing edge (134).

10. The turbine guide vane cooling structure according to claim 9, characterized in that: Protrusions (113) are arranged on the inner wall of the rear cooling cavity (16c) in an alternating manner with the flow-around columns (112).

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