Turbine blade with adjustable cooling structure and aircraft engine

Abstract

The present invention provides a turbine blade and an aircraft engine with an adjustable cooling structure. A cold air cavity, an air inlet hole, and an air film hole are provided in the turbine blade. A cold air regulating structure is provided in the cold air cavity, and an impact hole is provided on the cold air regulating structure. An arc-shaped guide structure is provided on the outside of the turbine blade, and the arc-shaped guide structure is fixedly connected to the cold air regulating structure. A control mechanism is provided on the arc-shaped guide structure, and the control mechanism drives the arc-shaped guide structure to rotate in the direction of rotation of the turbine blade or in the opposite direction of rotation of the turbine blade. The turbine blade and the aircraft engine designed by the present invention actively adjust the cooling form of the turbine blade according to the different working states of the gas engine, so as to change the cooling effect of the blade in real time, so as to meet the cooling requirements of the gas engine under different working states, and ensure that the gas turbine operates stably and efficiently in a wide range.

Description

Technical Field

[0001] The invention belongs to the field of aeroengines, and relates to a structure design technology of high-temperature components of a gas turbine, and in particular to a turbine blade with an adjustable cooling structure and an aeroengine. Background Art

[0002] A gas turbine is a thermodynamic mechanical device that uses air as the working medium. It is widely used in aircraft, ship and vehicle propulsion, as well as power generation, oil pumping and many other industrial fields. The core components of a gas turbine include a compressor, a combustion chamber and a turbine. In pursuit of high performance, the inlet airflow temperature of modern advanced gas turbine turbines has far exceeded the temperature resistance limit of the materials used to manufacture turbine blades. Therefore, effective cooling measures must be adopted to reduce the overall temperature level and local temperature difference of the turbine blades, thereby ensuring that the turbine can work safely, stably and for a long life.

[0003] At present, the cooling measure commonly used for gas turbine turbine blades is to draw out a portion of 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 more typical cooling structure of turbine blades is one or more of impingement cooling, rough rib cooling, spoiler column cooling, and air film cooling.

[0004] However, as the operating envelope of gas turbines continues to expand, the operating temperature, pressure, and flow range of gas turbine components continue to increase. When the gas turbine is in different working states, the degree of cooling required for the turbine blades is significantly different. The traditional turbine blade cooling structure is fixed and cannot be adjusted according to the cooling requirements, resulting in a decrease in the instantaneous thermal efficiency of the gas turbine. Therefore, there is an urgent need for a turbine blade whose cooling effect can be adjusted in real time, so that the gas turbine can achieve stable and efficient operation in a wide range. Summary of the invention

[0005] The object of the present invention is to provide a turbine blade and an aircraft engine with an adjustable cooling structure, which actively adjusts the cooling form of the turbine blade according to the different working conditions of the gas turbine, so as to change the cooling effect of the blade in real time, so as to meet the cooling requirements of the gas turbine under different working conditions and ensure that the gas turbine operates stably and efficiently in a wide range.

[0006] The technical solution to achieve the purpose of the invention is as follows:

[0007] In a first aspect, the present invention provides a turbine blade with an adjustable cooling structure, wherein a cold air cavity is provided in the turbine blade, and an air inlet hole and an air film hole connected to the cold air cavity are provided on the turbine blade. A cold air regulating structure is provided in the cold air cavity, and the cold air regulating structure divides the cold air cavity into an air inlet cavity and an air outlet cavity, wherein the air inlet cavity is connected to the air inlet hole, and the air outlet cavity is connected to the air film hole, and an impact hole connecting the air inlet cavity and the air outlet cavity is provided on the cold air regulating structure;

[0008] An arc guide structure is provided outside the turbine blade, the arc guide structure is connected to the cold air regulating structure, and a control mechanism is provided on the arc guide structure, which drives the arc guide structure to rotate in the same direction of rotation of the turbine blade or in the opposite direction of rotation of the turbine blade.

[0009] Further, the turbine blade includes a blade body, a blade upper end wall, and a blade lower end wall;

[0010] The cold air cavity is located in the blade body, including the leading edge cold air cavity and the mid-chord cold air cavity;

[0011] The air inlet holes are arranged on the upper end wall of the blade, including a first air inlet hole communicating with the leading edge cold air cavity and a second air inlet hole communicating with the mid-chord cold air cavity;

[0012] The air film holes are arranged on the blade body, and include a first air film hole communicated with the leading edge cold air cavity and a second air film hole communicated with the mid-chord cold air cavity.

[0013] In an optional embodiment, a cold air regulating structure is provided in the leading edge cold air cavity, the cold air regulating structure comprises a first cold air regulating plate, and the first cold air regulating plate is fixedly connected to the arc-shaped guide structure via a connecting component;

[0014] The first cold air regulating plate is arranged along the direction from the upper end wall of the blade to the lower end wall of the blade, and two sides of the first cold air regulating plate are in contact with the inner wall of the leading edge cold air cavity.

[0015] In an optional embodiment, a cold air regulating structure is provided in the middle chord cold air cavity, and the cold air regulating structure includes a second cold air regulating plate and a third cold air regulating plate, and the second cold air regulating plate is close to the suction surface of the blade body, and the third cold air regulating plate is close to the pressure surface of the blade body;

[0016] A connecting piece is provided between the second cold air regulating plate and the third cold air regulating plate, and the connecting piece is fixedly connected to the arc-shaped guiding structure via a connecting assembly.

[0017] Further, the connection assembly includes a connecting rod and an extension shaft;

[0018] The connecting rod is parallel to the arc-shaped guiding structure, and one end of the connecting rod is hinged on the arc-shaped guiding structure, and the other end is fixedly connected to an extending shaft perpendicular to the connecting rod, and the other end of the extending shaft is fixedly connected to the cold air regulating structure.

[0019] Further, the arc-shaped guide structure includes a first arc-shaped guide member and a second arc-shaped guide member which are parallel to each other and have the same structure;

[0020] The first arc-shaped guide member and the second arc-shaped guide member are located at two ends of the outside of the turbine blade and are both fixedly connected to the cold air regulating structure.

[0021] In a second aspect, the present invention provides an aircraft engine, including a turbine, wherein a plurality of stages of turbine blades are provided in the turbine, and each stage of turbine blades is composed of a plurality of turbine blades with adjustable cooling structures as described in the first aspect.

[0022] Furthermore, the arc-shaped guide structures of each turbine blade of each stage of turbine blades are sequentially connected or integrally formed to form an annular guide structure, and the annular guide structure is coaxial with the turbine.

[0023] Compared with the prior art, the beneficial effects of the present invention are as follows: the turbine blades designed by the present invention and the aircraft engine containing the turbine blades can be adjusted in time according to the cooling requirements of the turbine blades when the aircraft engine is in different working states. By changing the impact jet angle and / or impact distance, the cooling effect of the blades can be adjusted in real time, so that the aircraft engine can work stably and efficiently in all states, thereby significantly improving the robustness of the wide-range aircraft engine operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for describing the embodiments are briefly introduced below.

[0025] Figure 1 It is a schematic diagram of the structure of a turbine blade with an adjustable cooling structure in a specific implementation manner;

[0026] Figure 2 is a two-dimensional schematic diagram of a turbine blade in a specific implementation manner;

[0027] Figure 3 is a schematic diagram of a cold air regulating structure in a leading edge cold air cavity in a specific implementation manner;

[0028] Figure 4a is a two-dimensional schematic diagram of a cold air regulating structure in a cold air cavity at the leading edge of a turbine blade in a specific implementation manner;

[0029] Figure 4b , Figure 4c , Figure 4d They are schematic diagrams of positions of different stationary points on the impact target surface of the cold air regulating structure in the leading edge cold air cavity in a specific embodiment;

[0030] Figure 5 It is a schematic diagram of a cold air regulating structure in a mid-chord cold air cavity of a turbine blade in a specific implementation manner;

[0031] Figure 6 It is a two-dimensional schematic diagram of the cold air regulating structure in the middle string cold air cavity in a specific implementation manner;

[0032] Figure 7It is a two-dimensional schematic diagram of the internal cooling air regulating structure provided in both the leading edge cooling air cavity and the mid-chord cooling air cavity of the turbine blade in a specific implementation manner;

[0033] Figure 8 A schematic diagram of an annular guide structure of an aircraft engine in a specific implementation manner;

[0034] Among them, 101. blade body; 102. upper end of blade; 103. lower end wall of blade; 104. suction surface; 105. pressure surface; 201. leading edge cold air cavity; 202. mid-chord cold air cavity; 301. first air inlet hole; 302. second air inlet hole; 401. first air film hole; 402. second air film hole; 501. first cold air adjustment plate; 502. second cold air adjustment plate; 503. third cold air adjustment plate; 601. connecting member; 602. connecting rod; 603. extension shaft; 701. first arc guide; 802. second arc guide 702; 800. annular guide structure; 800. control mechanism; 900. impact hole. DETAILED DESCRIPTION

[0035] The present invention will be further described below in conjunction with specific embodiments, and the advantages and features of the present invention will become clearer as the description proceeds. However, these embodiments are exemplary only and do not constitute any limitation to the scope of the present invention. It should be understood by those skilled in the art that the details and forms of the technical solution of the present invention may be modified or replaced without departing from the spirit and scope of the present invention, but these modifications and replacements all fall within the scope of protection of the present invention.

[0036] The present invention provides a turbine blade with an adjustable cooling structure, wherein a cold air cavity is provided in the turbine blade, and an air inlet hole and an air film hole connected to the cold air cavity are provided on the turbine blade, a cold air regulating structure is provided in the cold air cavity, the cold air regulating structure divides the cold air cavity into an air inlet cavity and an air outlet cavity, the air inlet cavity is connected to the air inlet hole, the air outlet cavity is connected to the air film hole, and an impact hole connecting the air inlet cavity and the air outlet cavity is opened on the cold air regulating structure.

[0037] Among them, an arc guide structure is provided on the outside of the turbine blade, the arc guide structure is fixedly connected to the cold air regulating structure, and a control mechanism is provided on the arc guide structure, which drives the arc guide structure to rotate in the same direction of rotation of the turbine blade or in the opposite direction of rotation of the turbine blade.

[0038] The principle of the turbine blade with adjustable cooling structure is: first, the control mechanism obtains the cooling demand of the turbine blade, and controls the arc-shaped guide structure to rotate along or against the rotation direction of the turbine blade; secondly, when the arc-shaped guide structure rotates, the position of the cold air regulating structure in the cold air cavity changes. At this time, the relative position (angle and / or distance) of the impact hole and the air film hole on the cold air regulating structure changes; finally, the cold air is input from the air inlet cavity to the air outlet cavity, and then discharged through the air film hole to adjust the cooling effect of the turbine blade, thereby achieving the purpose of adjusting the cooling effect in real time according to the working conditions.

[0039] In one embodiment, see Figure 1 and Figure 2 As shown, the turbine blade includes a blade body 101 , a blade upper end wall 102 , and a blade lower end wall 103 .

[0040] The cold air cavity is located in the blade body 101, including the leading edge cold air cavity 201 and the mid-chord cold air cavity 202. The air inlet hole is provided on the upper end wall 102 of the blade, including the first air inlet hole 301 communicating with the leading edge cold air cavity 201 and the second air inlet hole 302 communicating with the mid-chord cold air cavity 202. The air film hole is provided on the blade body 101, including the first air film hole 401 communicating with the leading edge cold air cavity 201 and the second air film hole 402 communicating with the mid-chord cold air cavity 202.

[0041] In the first embodiment of the cold air conditioning structure, see Figure 3 As shown, a cold air regulating structure is provided in the leading edge cold air cavity 201, and the cold air regulating structure comprises a first cold air regulating plate 501, and the first cold air regulating plate 501 is fixedly connected to the arc-shaped guiding structure via a connecting component.

[0042] The first cold air regulating plate 501 is disposed along the direction from the upper end wall 102 of the blade to the lower end wall 103 of the blade, and two sides of the first cold air regulating plate 501 are in contact with the inner wall of the leading edge cold air cavity 201 .

[0043] In one embodiment of the arc-shaped guide structure, it includes a first arc-shaped guide member 701 , and the first arc-shaped guide member 701 is disposed on the outer side of the blade upper end wall 102 .

[0044] In a preferred embodiment of the arc-shaped guide structure, see Figure 3 As shown, the arc guide structure includes a first arc guide member 701 and a second arc guide member 702 which are parallel to each other and have the same structure. The first arc guide member 701 and the second arc guide member 702 are located at both ends of the outside of the turbine blade and are fixedly connected to the first cold air adjustment plate 501 via a connecting assembly.

[0045] See also Figure 3As shown, the connecting assembly includes a connecting rod 602 and an extension shaft 603. The connecting rod 602 is parallel to the arc-shaped guide structure, and one end of the connecting rod is hinged on the arc-shaped guide structure, and the other end is fixedly connected to the extension shaft 603 perpendicular to it, and the other end of the extension shaft 603 is fixedly connected to the air conditioning structure.

[0046] When the arc-shaped guide structure has only the first arc-shaped guide member 701 , a through hole is opened on the upper end wall 102 of the blade for the extension shaft 603 to pass through. One end of the extension shaft 603 is fixed to the connecting rod 602 , and the other end passes through the through hole and is fixed to the first cold air regulating plate 501 .

[0047] When the arc-shaped guide structure has a first arc-shaped guide member 701 and a second arc-shaped guide member 702 , the first arc-shaped guide member 701 and the second arc-shaped guide member 702 are both fixed with a connecting rod 602 , and at this time, there may be one or two extension shafts 603 .

[0048] Specifically, when there is one extension shaft 603, one end of the extension shaft 603 is fixed to the connecting rod 602 on the first arc-shaped guide 701, and the other end is fixed to the connecting rod 602 of the second arc-shaped guide 702, and the extension shaft 603 is also fixed to the first cold air regulating plate 501 (it can be welded to the first cold air regulating plate 501, or it can be integrally formed with the first cold air regulating plate 501);

[0049] When there are two extension shafts 603, one end of the extension shaft 603 is fixed to the connecting rod 602 of the first arc guide 701 / the second arc guide 702, and the other end is fixed to the first cold air adjustment plate 501 (it can be welded to the first cold air adjustment plate 501, or it can be integrally formed with the first cold air adjustment plate 501). It should be noted here that when there are two extension shafts 603, it is necessary to ensure that the two extension shafts 603 are on the same center line.

[0050] The adjustment principle of the first cold air adjustment plate 501 in the leading edge cold air cavity 201 is: first, the control mechanism obtains the cooling demand of the turbine blades and controls the arc-shaped guide structure to rotate along or against the rotation direction of the turbine blades; second, when the arc-shaped guide structure rotates, the angle of the first cold air adjustment plate 501 in the cold air cavity changes (see Figure 4a As shown), at this time, the angle between the impact hole 900 on the first cold air adjustment plate 501 and the first air film hole 401 changes; finally, when the cold air is input from the air inlet cavity to the air outlet cavity through the impact hole 900, the direction of the impact jet changes, thereby changing the position of the stationary point on the impact hole 900 on the target surface (see Figure 4b , 4c , 4d), thereby changing the cooling effect of the leading edge wall of the blade.

[0051] In the second embodiment of the cold air conditioning structure, see 2, Figure 5 , Figure 6 As shown, a cold air regulating structure is provided in the mid-chord cold air cavity 202, and the cold air regulating structure includes a second cold air regulating plate 502 and a third cold air regulating plate 503, and the second cold air regulating plate 502 is close to the suction surface 104 of the blade body 101, and the third cold air regulating plate 503 is close to the pressure surface 105 of the blade body 101. A connecting member 601 is provided between the second cold air regulating plate 502 and the third cold air regulating plate 503, and the connecting member 601 is fixedly connected to the arc-shaped guide structure through a connecting assembly.

[0052] It should be noted that the arc-shaped guide structure and the structure of the connecting assembly of this embodiment are the same as those of the first cold air regulating plate 501 in the front edge cold air cavity 201, and will not be described in detail here. At the same time, the connecting member 601 can be a connecting plate or a connecting block. To maintain the stability of the cold air regulating structure, the extension shaft 603 is fixed to the middle of the connecting member 601, and the extension shaft 603 and the connecting member 601 can be welded or integrally formed, which is not limited by the present invention.

[0053] The regulating principle of the second cold air regulating plate 502 and the third cold air regulating plate 503 in the middle string cold air cavity 202 is: first, the control mechanism obtains the cooling demand of the turbine blades, and controls the arc-shaped guide structure to rotate along or against the rotation direction of the turbine blades; second, when the arc-shaped guide structure rotates, the extension shaft 603 rotates, so that the relative position of the connecting member 601 in the middle string cold air cavity 202 also changes, and the connecting member 601 makes the second cold air regulating plate 502 and the third cold air regulating plate 503 approach or move away from each other (see Figure 6 As shown), at this time, the area of ​​the air inlet cavity increases and the area of ​​the air outlet cavity decreases (or the area of ​​the air inlet cavity decreases and the area of ​​the air outlet cavity increases), the distance between the second cold air adjustment plate 502 and the third cold air adjustment plate 503 and the inner wall of the mid-chord cold air cavity 202 (i.e., the jet impact distance) is shortened or increased, and the jet impact distance between the impact hole 900 on the second cold air adjustment plate 502 and the third cold air adjustment plate 503 and the second air film hole 402; finally, when the cold air is input from the air inlet cavity through the impact hole 900 to the air outlet cavity, the impact jet distance changes, thereby changing the cooling effect of the mid-chord wall of the blade.

[0054] In the third embodiment of the arc guide structure, see Figure 1 and Figure 7 As shown, cold air regulating structures are provided in the mid-chord cold air cavity 202 and the leading edge cold air cavity 201. The structure and principle of the cold air regulating structures refer to the first embodiment and the second embodiment mentioned above.

[0055] The present invention also provides an aeroengine, including a turbine, wherein a plurality of stages of turbine blades are arranged in the turbine, and each stage of turbine blades is composed of a plurality of turbine blades with the above-mentioned adjustable cooling structure.

[0056] Among them, see Figure 8 As shown, the arc-shaped guide structures of each turbine blade of each stage of turbine blades are sequentially connected or integrally formed to form an annular guide structure 800, and the annular guide structure 800 is coaxial with the turbine. In the working state of the aircraft engine, the control mechanism 801 obtains instructions from the whole machine control system, and according to the cooling demand, the annular guide structure 800 is rotated in the same direction or opposite direction relative to the rotating shaft in real time, and the circumferential position of the annular guide structure 800 is adjusted, and then the relative position of the cold air adjustment structure in the cold air cavity is adjusted, so as to adjust the position (i.e., angle) and / or distance of the impact target surface, and realize the adjustment of the cooling effect.

[0057] It should be noted that the multi-stage turbine blades in the turbine include moving blades and stationary blades, and the cold air regulating structure, arc-shaped guide structure, and connecting assembly of the present invention can be used in both stationary blades and moving blades. For example, when it is used in stationary blades, it is only necessary to make the control mechanism 801 adjust the circumferential angle of the annular guide structure 800 according to the different working conditions of the aircraft engine; when it is used in moving blades, the annular guide structure 800 needs to rotate synchronously with the moving blades. When the cooling effect needs to be adjusted in different working conditions of the aircraft engine, the circumferential angle of the annular guide structure 800 can be adjusted according to the needs.

[0058] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

[0059] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A turbine blade with an adjustable cooling structure, wherein a cold air cavity is provided in the turbine blade, and an air inlet hole and an air film hole communicating with the cold air cavity are provided on the turbine blade, characterized in that: A cold air regulating structure is provided in the cold air cavity, and the cold air regulating structure divides the cold air cavity into an air inlet cavity and an air outlet cavity, the air inlet cavity is connected with the air inlet hole, the air outlet cavity is connected with the air film hole, and an impact hole connecting the air inlet cavity and the air outlet cavity is opened on the cold air regulating structure; An arc-shaped guide structure is provided outside the turbine blade, the arc-shaped guide structure is connected to the cold air regulating structure, and a control mechanism is provided on the arc-shaped guide structure, and the control mechanism drives the arc-shaped guide structure to rotate in the same direction of rotation of the turbine blade or in the opposite direction of rotation of the turbine blade.

2. The turbine blade with adjustable cooling structure according to claim 1, characterized in that: The turbine blade comprises a blade body (101), a blade upper end wall (102), and a blade lower end wall (103); The cold air cavity is located in the blade body (101), and comprises a leading edge cold air cavity (201) and a mid-chord cold air cavity (202); The air inlet holes are provided on the upper end wall (102) of the blade, and include a first air inlet hole (301) communicating with the leading edge cold air cavity (201) and a second air inlet hole (302) communicating with the mid-chord cold air cavity (202); The air film holes are opened on the blade body (101), and include a first air film hole (401) connected to the leading edge cold air cavity (201) and a second air film hole (402) connected to the mid-chord cold air cavity (202).

3. The turbine blade with adjustable cooling structure according to claim 2, characterized in that: The cold air regulating structure is provided in the front edge cold air cavity (201), the cold air regulating structure comprises a first cold air regulating plate (501), and the first cold air regulating plate (501) is fixedly connected to the arc-shaped guide structure via a connecting component; The first cold air regulating plate (501) is arranged along the direction from the upper end wall (102) of the blade to the lower end wall (103) of the blade, and two sides of the first cold air regulating plate (501) are in contact with the inner wall of the leading edge cold air cavity (201).

4. The turbine blade with adjustable cooling structure according to claim 2 or 3, characterized in that: The cold air regulating structure is provided in the middle chord cold air cavity (202), and the cold air regulating structure comprises a second cold air regulating plate (502) and a third cold air regulating plate (503), wherein the second cold air regulating plate (502) is close to the suction surface (104) of the blade body (101), and the third cold air regulating plate (503) is close to the pressure surface (105) of the blade body (101); A connecting piece (601) is provided between the second cold air regulating plate (502) and the third cold air regulating plate (503), and the connecting piece (601) is fixedly connected to the arc-shaped guiding structure via a connecting assembly.

5. The turbine blade with adjustable cooling structure according to claim 4, characterized in that: The connecting assembly comprises a connecting rod (602) and an extension shaft (603); The connecting rod (602) is parallel to the arc-shaped guide structure, and one end of it is hinged on the arc-shaped guide structure, and the other end is fixedly connected to the extending shaft (603) perpendicular thereto, and the other end of the extending shaft (603) is fixedly connected to the cold air regulating structure.

6. The turbine blade with adjustable cooling structure according to claim 1, characterized in that: The arc-shaped guiding structure comprises a first arc-shaped guiding member (701) and a second arc-shaped guiding member (702) which are parallel to each other and have the same structure; The first arc-shaped guide (701) and the second arc-shaped guide (702) are located at two ends of the outside of the turbine blade and are both fixedly connected to the cold air regulating structure.

7. An aircraft engine, comprising a turbine, characterized in that: The turbine is provided with multiple stages of turbine blades, and each stage of turbine blades is composed of a plurality of turbine blades with adjustable cooling structures as described in any one of claims 1 to 6.

8. The aircraft engine according to claim 7, characterized in that: The arc-shaped guide structures of each turbine blade of each stage of turbine blades are sequentially connected or integrally formed to form an annular guide structure (800), and the annular guide structure (800) is coaxial with the turbine.

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