Gas engine turbine blade test piece structure with easily replaceable cooling elements and adjustable cooling air

Abstract

The present invention belongs to the technical field of gas turbine blade cooling, and specifically discloses a test piece structure for a gas turbine blade with easily replaceable cooling elements and adjustable cooling air, comprising a blade platform, a blade, and a connecting portion, wherein the blade and the connecting portion are respectively arranged on both sides of the blade platform and are detachably connected to the blade platform, and airflow channels are respectively provided on the connecting portion, the blade platform, and the blade, and the airflow channels are sequentially connected. The present invention solves the problem that the existing technology is significantly different from the actual operating conditions, the design time cycle is long, and the economic cost is high. The present invention considers the mutual influence between different areas and different forms of cooling in the blade structure, restores the actual operating conditions of the blade, and through modular design of the blade structure and designing an adjustable cooling structure on each module, facilitates the testing of blades of various different structures, reduces the cost of model development, and improves the experimental efficiency of studying the cooling effect, providing a basis for later structural optimization.

Description

Technical Field

[0001] The invention belongs to the technical field of gas turbine blade cooling, and relates to a gas turbine blade test piece structure with easily replaceable cooling elements and adjustable cold air. Background Art

[0002] Heavy-duty gas turbines are core equipment in modern energy conversion and power generation. Their turbine blades are directly exposed to high-temperature, high-pressure gas environments, subjecting them to enormous thermal loads and complex mechanical stresses. As gas turbines evolve toward higher efficiency and power, turbine inlet temperatures continue to rise, far exceeding the tolerance limits of blade materials. These extreme operating conditions pose significant challenges to blade cooling technology.

[0003] The cooling technology of gas turbine blades usually combines external cooling and internal cooling to form a complex cooling system. Among them, film cooling is the most common external cooling method for blades. The cooling medium inside the blade flows out through a number of film holes opened on its surface. Under the push and squeeze of the high-temperature mainstream, it covers the surface of the blade downstream of the hole, forming a layer of cold air film, which blocks the high-temperature combustion gas from the blade. At the same time, the cold air film can also exchange heat with the blade surface to take away part of the heat, thereby reducing the thermal load of the blade. The internal cooling of the blade focuses on the heat transfer between the cooling medium and the wall of the internal channel of the blade. By optimizing the design of the channel structure, the heat transfer performance is improved, and the uniformity of the temperature field is improved, thereby effectively reducing the thermal load of the blade. Although a lot of research has been carried out in the field of high-temperature blade cooling, there are still many shortcomings:

[0004] First, the current research objects of high-temperature blade cooling are mostly simple modular channels for a certain local area, without considering the mutual influence between different areas and different forms of cooling. The research results are far from the actual operating conditions with actual blade shapes and complete complex cooling structures, and it is difficult to provide theoretical support and application basis for the development of gas turbine blade cooling technology.

[0005] Secondly, a large number of tests need to be carried out during the turbine blade design stage. Whenever the design structure changes, the blade simulation parts need to be reprocessed. In particular, when conducting optimal design of multiple cooling structure combinations, blade simulation parts of various different structures need to be processed, manufactured and tested, resulting in a long design cycle and high economic costs. Summary of the Invention

[0006] The gas turbine blade test piece structure with easily replaceable cooling elements and adjustable cooling air provided by the present invention solves the shortcomings of the existing technology and facilitates testing of blades with various different structures. It can not only verify the cooling performance of different cooling structures, but also effectively reduce the model development cost and improve the experimental efficiency of studying the cooling effect, provide a basis for subsequent structural optimization, effectively reduce the model development cost and improve the experimental efficiency of studying the cooling effect.

[0007] To achieve the above objectives, the specific technical solutions provided by the present invention are as follows:

[0008] The test piece structure of a gas turbine blade with easily replaceable cooling elements and adjustable cooling air comprises:

[0009] A blade platform, a blade, and a connecting portion, wherein the blade and the connecting portion are respectively arranged on both sides of the blade platform and are detachably connected to the blade platform, and air flow channels are respectively provided on the connecting portion, the blade platform, and the blade, and the air flow channels are sequentially connected;

[0010] The blade includes a blade body, a leading edge film hole plate, a trailing edge slit slot plate and a blade cover plate. The blade cover plate is detachably connected to one end of the blade body, and the other end of the blade body is detachably connected to the blade platform. The leading edge film hole plate and the trailing edge slit slot plate are respectively arranged on the front and rear sides of the blade body and are detachably connected to the blade platform. The blade cover plate includes a cover plate body and a leading edge blade tip cooling hole plate, a mid-chord third row channel blade tip cooling hole plate, a mid-chord turning area blade tip cooling hole plate and a trailing edge blade tip cooling hole plate, which are arranged in sequence and are all detachably connected to the cover plate body.

[0011] At least one first adjustment structure is provided on the air flow channel outlet on the blade platform, and the first adjustment structure is used to adjust the flow area and pre-rotation. The leading edge blade tip cooling hole plate, the mid-chord third row channel blade tip cooling hole plate, the mid-chord turning area blade tip cooling hole plate, the trailing edge blade tip cooling hole plate, the leading edge air film hole plate and the trailing edge slit slot plate are all provided with air flow channel outlets. A second adjustment structure is provided on the air flow channel outlet on the blade body, and the second adjustment structure is used to adjust the flow area.

[0012] Furthermore, the structures of the first adjustment structure and the second adjustment structure are the same, both including a control component, a high-temperature resistant soft pressure-sensitive layer and a plurality of high-temperature resistant soft pressure-sensitive sheets, the high-temperature resistant soft pressure-sensitive layer is arranged circumferentially around the air flow channel inlet / air flow channel outlet, and a plurality of high-temperature resistant soft pressure-sensitive sheets are arranged between the air flow channel and the high-temperature resistant soft pressure-sensitive layer, the high-temperature resistant soft pressure-sensitive sheet is connected to the control component, and the control component is used to adjust the voltage applied to the high-temperature resistant soft pressure-sensitive sheet. When the voltage on the high-temperature resistant soft pressure-sensitive sheet changes, it acts on the high-temperature resistant soft pressure-sensitive layer to cause it to deform.

[0013] Furthermore, the leading edge blade tip cooling hole plate, the mid-chord third row channel blade tip cooling hole plate, the mid-chord turning area blade tip cooling hole plate, and the trailing edge blade tip cooling hole plate have the same structure and all include a first fixed plate and a first spoiler. The first fixed plate and the first spoiler are detachably connected, and the first spoiler includes a first plate body and a plurality of first spoiler structures arranged on the first plate body.

[0014] Furthermore, the blade body is a hollow structure, and the inner wall of the blade body is detachably connected with a leading edge cooling channel suction surface spoiler, a leading edge cooling channel pressure surface spoiler, a cooling channel suction surface spoiler in the third row at mid-chord, a cooling channel pressure surface spoiler in the third row at mid-chord, a cooling channel suction surface spoiler in the second row at mid-chord, a cooling channel pressure surface spoiler in the second row at mid-chord, a cooling channel suction surface spoiler in the first row at mid-chord, a cooling channel pressure surface spoiler in the first row at mid-chord, a trailing edge cooling channel suction surface spoiler and a trailing edge cooling channel pressure surface spoiler.

[0015] Furthermore, the leading edge cooling channel suction surface spoiler, the leading edge cooling channel pressure surface spoiler, the cooling channel suction surface spoiler in the third row at mid-chord, the cooling channel pressure surface spoiler in the third row at mid-chord, the cooling channel suction surface spoiler in the second row at mid-chord, the cooling channel pressure surface spoiler in the second row at mid-chord, the cooling channel suction surface spoiler in the first row at mid-chord, the cooling channel pressure surface spoiler in the first row at mid-chord, the trailing edge cooling channel suction surface spoiler and the trailing edge cooling channel pressure surface spoiler have the same structure and all include a second fixed plate and a plurality of second spoiler structures arranged on the second fixed plate.

[0016] Furthermore, the first spoiler structure and the second spoiler structure are one of a ball socket, a rib, a ball protrusion and a fin.

[0017] Furthermore, the blade platform includes a detachably connected blade upper platform and a blade lower platform, and a main air distribution chamber is opened between the blade upper platform and the blade lower platform. The main air distribution chamber is used to buffer and store cooling gas, and the main air distribution chamber is respectively connected to the air flow channels on the blade and the connecting part.

[0018] Furthermore, a sealing structure is provided between the blade upper platform and the blade lower platform.

[0019] Compared with the prior art, the gas turbine blade test piece structure with easily replaceable cooling elements and adjustable cooling air of the present invention has the following advantages:

[0020] The blade structure takes into account the mutual influence between different regions and different forms of cooling, and truly restores the actual operation of the blade. By modularizing the blade structure and designing adjustable cooling structures on each module, a variety of different structures can be reflected on this blade, which facilitates the testing of blades with various different structures. It can not only verify the cooling performance of different cooling structures, but also effectively reduce the cost of model development and improve the experimental efficiency of studying cooling effects, providing a basis for later structural optimization. At the same time, by adjusting the first adjustment structure, the flow area and pre-rotation can be controlled, thereby accurately controlling the cooling ratio and cooling inflow direction of multiple regions. By adjusting the second adjustment structure, the flow area can be controlled to adapt to the adjustment of cooling requirements under variable operating conditions. The test piece structure has a unique multi-region cooling adjustable function, which can provide a higher optimization design dimension for the research and development of high-temperature blades of gas turbines. It is highly practical and worthy of promotion. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0022] Figure 2 It is a structural schematic diagram of the blade cover of the present invention;

[0023] Figure 3 It is a structural schematic diagram of the cover plate body of the present invention;

[0024] Figure 4 A three-dimensional diagram of a blade cover plate of the present invention;

[0025] Figure 5 A cross-sectional view of an upper blade cover plate of a leading edge blade tip cooling hole according to the present invention;

[0026] Figure 6 It is a schematic diagram of the assembly of the blade of the present invention;

[0027] Figure 7 This is a schematic structural diagram of a blade body according to the present invention;

[0028] Figure 8 This is a schematic structural diagram of the suction surface spoiler of the leading edge cooling channel of the present invention;

[0029] Figure 9 This is a schematic structural diagram of the pressure surface spoiler of the leading edge cooling channel of the present invention;

[0030] Figure 10 This is a schematic structural diagram of the mid-chord cooling channel suction surface spoiler of the present invention;

[0031] Figure 11 This is a schematic structural diagram of the pressure surface spoiler of the mid-chord cooling channel of the present invention;

[0032] Figure 12 This is a schematic structural diagram of the suction surface spoiler of the trailing edge cooling channel of the present invention;

[0033] Figure 13 This is a schematic structural diagram of the pressure surface spoiler of the trailing edge cooling channel of the present invention;

[0034] Figure 14 This is a schematic diagram of the slot-type connection structure of the present invention;

[0035] Figure 15 A first-perspective perspective view of the leading edge air film orifice plate of the present invention;

[0036] Figure 16 A second perspective view of the leading edge air film orifice plate of the present invention;

[0037] Figure 17 A first perspective view of the trailing edge slot plate of the present invention;

[0038] Figure 18 A second perspective view of the trailing edge slot plate of the present invention;

[0039] Figure 19 A top view of the upper platform of the blade of the present invention;

[0040] Figure 20 A bottom view of the upper platform of the blade of the present invention;

[0041] Figure 21 A top view of the lower platform and connection portion of the blade of the present invention;

[0042] Figure 22 A bottom view of the lower platform and connecting portion of the blade of the present invention;

[0043] Figure 23 Schematic diagram of the cross-sectional structure of the upper platform of the blade of the present invention along the radial direction;

[0044] Figure 24 Schematic diagram of the cross-sectional structure of the upper platform of the blade along the AA direction of the present invention;

[0045] Figure 25 Schematic diagram of the cooling air flow process of the present invention.

[0046] Reference numerals:

[0047] 1. Leading edge blade tip cooling hole plate, 2. Blade tip cooling hole plate in the third row of mid-chord channels, 3. Blade tip cooling hole plate in the mid-chord turning area, 4. Trailing edge blade tip cooling hole plate, 5. Cover plate body, 6. Leading edge film hole plate, 7. Trailing edge slot plate, 8. Blade body, 9. Blade upper platform, 10. Blade lower platform, 19. Connecting part, 1-G1, upper blade cover plate of leading edge blade tip cooling hole, 1-G2, lower spoiler of leading edge blade tip cooling hole, 2-G1, upper blade cover plate of blade tip cooling hole in the third row of mid-chord channels, 2-G2, lower spoiler of blade tip cooling hole in the third row of mid-chord channels, 3-G1, upper blade cover plate in the mid-chord turning area, 3-G2, lower spoiler in the mid-chord turning area, 4-G1, upper blade cover of trailing edge blade tip cooling hole Plate, 4-G2, lower spoiler of trailing edge blade tip cooling hole, 1-R1, spoiler structure of lower spoiler of leading edge blade tip cooling hole, 2-R1, spoiler structure of lower spoiler of blade tip cooling hole in the third row of mid-chord channel, 3-R1, spoiler structure of lower spoiler of mid-chord turning area, 4-R1, spoiler structure of lower spoiler of trailing edge blade tip cooling hole, 11S, spoiler of suction surface of leading edge cooling channel, 11P, spoiler of pressure surface of leading edge cooling channel, 12S, spoiler of suction surface of third row of mid-chord cooling channel, 12P, spoiler of pressure surface of third row of mid-chord cooling channel, 13S, spoiler of suction surface of second row of mid-chord cooling channel, 13P, spoiler of pressure surface of second row of mid-chord cooling channel, 14S, spoiler of suction surface of first row of mid-chord cooling channel , 14P, the first row of cooling channel pressure surface spoiler at the mid-chord, 15S, the suction surface spoiler at the trailing edge cooling channel, 15P, the pressure surface spoiler at the trailing edge cooling channel, 11S-R2, the spoiler structure of the suction surface spoiler at the leading edge cooling channel, 11P-R2, the spoiler structure of the pressure surface spoiler at the leading edge cooling channel, 12S-R2, the spoiler structure of the suction surface spoiler at the third row of cooling channel at the mid-chord, 12P-R2, the spoiler structure of the pressure surface spoiler at the third row of cooling channel at the mid-chord, 13S-R2, the spoiler structure of the suction surface spoiler at the second row of cooling channel at the mid-chord, 13P-R2, the spoiler structure of the pressure surface spoiler at the second row of cooling channel at the mid-chord, 14S-R2, the spoiler structure of the suction surface spoiler at the first row of cooling channel at the mid-chord, 14P-R2, The spoiler structure of the pressure surface spoiler of the first row of cooling channels at the mid-chord, 15S-R3, the spoiler structure of the suction surface spoiler of the trailing edge cooling channel, 15P-R3, the spoiler structure of the pressure surface spoiler of the trailing edge cooling channel, 6-Q1, the leading edge film hole, 7-Q1, the trailing edge slit groove, 16A, the leading edge cooling channel air inlet, 16B, the mid-chord cooling channel air inlet, 16C, the trailing edge cooling channel air inlet, 17A, the upper air distribution chamber, 17B, the lower air distribution chamber, 18, the cold air delivery channel, D1, the sealing groove, Y1, the high-temperature resistant soft pressure-sensitive sheet for the blade tip cooling hole, YM1, the high-temperature resistant soft pressure-sensitive layer for the blade tip cooling hole, Y2, the high-temperature resistant soft pressure-sensitive sheet for the blade upper platform air inlet, YM2, the high-temperature resistant soft pressure-sensitive layer for the blade upper platform air inlet. DETAILED DESCRIPTION

[0048] In order to enable those skilled in the art to better understand the technical solution of the present invention and to implement it, the following Figures 1 to 25 , clearly and comprehensively describe the technical solutions in the present invention.

[0049] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as limiting the present invention.

[0050] In addition, it should be further explained that in the description of the embodiments of the present invention, unless otherwise specified, " / " means or, for example, A / B can mean A or B: "and / or" in the text only describes the association relationship of associated objects, indicating that there can be three relationships, for example, A and / or B can mean: A exists alone, A and B exist at the same time, and B exists alone. In addition, in the description of the embodiments of the present invention, "multiple" refers to two or more than two.

[0051] The terms "first," "second," "third," and "fourth" below are used for descriptive purposes only and should not be understood to imply or suggest relative importance or implicitly indicate the number of the technical features indicated. Thus, features qualified as "first," "second," "third," and "fourth" may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0052] The present invention provides a combustion engine turbine blade test piece structure with easily replaceable cooling elements and adjustable cooling air, such as Figure 1 As shown, its main structure includes a blade platform, blades and a connecting portion 19. Specifically, the blades and the connecting portion 19 are respectively arranged on both sides of the blade platform and are detachably connected to the blade platform. The connecting portion 19, the blade platform and the blades are respectively provided with air flow channels, and the air flow channels are sequentially connected.

[0053] Specifically, the blade includes a blade body 8, a leading edge film hole plate 6, a trailing edge slit slot plate 7, and a blade cover plate. The blade cover plate is detachably connected to one end of the blade body 8, and the other end of the blade body 8 is detachably connected to the blade platform. The leading edge film hole plate 6 and the trailing edge slit slot plate 7 are respectively arranged on the front and rear sides of the blade body 8 and are detachably connected to the blade platform. The blade cover plate includes a cover plate body 5 and a leading edge tip cooling hole plate 1, a mid-chord third row channel tip cooling hole plate 2, a mid-chord turning area tip cooling hole plate 3, and a trailing edge tip cooling hole plate 4, which are arranged in sequence and detachably connected to the cover plate body 5.

[0054] Furthermore, at least one first adjustment structure is provided on the air flow channel inlet on the blade body 8, and the first adjustment structure is used to adjust the flow area and pre-rotation. The leading edge blade tip cooling hole plate 1, the mid-chord third row channel blade tip cooling hole plate 2, the mid-chord turning area blade tip cooling hole plate 3, the trailing edge blade tip cooling hole plate 4, the leading edge air film hole plate 6 and the trailing edge slit slot plate 7 are all provided with air flow channel outlets, and a second adjustment structure is provided on the air flow channel outlet, and the second adjustment structure is used to adjust the flow area.

[0055] As a further refinement of this embodiment, specifically, the first adjustment structure and the second adjustment structure have the same structure, both including a control component, a high-temperature resistant soft pressure-sensitive layer and a plurality of high-temperature resistant soft pressure-sensitive sheets. The high-temperature resistant soft pressure-sensitive layer is arranged circumferentially around the airflow channel inlet / airflow channel outlet, and a plurality of high-temperature resistant soft pressure-sensitive sheets are arranged between the airflow channel and the high-temperature resistant soft pressure-sensitive layer. The high-temperature resistant soft pressure-sensitive sheet is connected to the control component, and the control component is used to adjust the voltage applied to the high-temperature resistant soft pressure-sensitive sheet. When the voltage on the high-temperature resistant soft pressure-sensitive sheet changes, it acts on the high-temperature resistant soft pressure-sensitive layer to cause it to deform.

[0056] As a further refinement of this embodiment, specifically, the blade platform includes a blade upper platform 9 and a blade lower platform 10, which are detachably connected. A total air distribution chamber 17 is provided between the blade upper platform 9 and the blade lower platform 10. The total air distribution chamber 17 is used to buffer and store cooling gas, and the total air distribution chamber 17 is respectively connected to the air flow channels on the blade and the connecting part 19.

[0057] The upper blade platform 9 is fixed to the blade body 8, and the leading edge air film hole plate 6 and the trailing edge slit slot plate 7 are respectively fixed to the blade body 8. The lower blade platform 10 is fixedly connected to the connecting portion 19, and the above connection methods are all realized by countersunk screws, which is easy to realize disassembly and assembly.

[0058] The structure of the blade cover is as follows Figure 2 As shown, the cover plate body 5 and the blade body 8 are fastened together by bolts. The structure of the separate cover plate body 5 is as shown in FIG. Figure 3As shown, there are four card-mounted hole structures on it, and the four card-mounted hole structures are respectively provided with a leading edge blade tip cooling hole plate 1, a mid-chord third row channel blade tip cooling hole plate 2, a mid-chord turning area blade tip cooling hole plate 3 and a trailing edge blade tip cooling hole plate 4. The structure of the assembled blade cover is as shown in FIG. Figure 4 shown.

[0059] The leading edge blade tip cooling hole plate 1, the mid-chord third row channel blade tip cooling hole plate 2, the mid-chord turning area blade tip cooling hole plate 3, and the trailing edge blade tip cooling hole plate 4 have the same structure and all include a first fixed plate and a first spoiler that are detachably connected. The first spoiler includes a first plate body and a plurality of first spoiler structures arranged on the first plate body.

[0060] like Figure 2 As shown, the upper blade cover plate 1-G1 of the leading edge blade tip cooling hole, the lower spoiler 1-G2 of the leading edge blade tip cooling hole, the upper blade cover plate 2-G1 of the third row of mid-chord channel blade tip cooling holes, the lower spoiler 2-G2 of the third row of mid-chord channel blade tip cooling holes, the upper blade cover plate 3-G1 of the mid-chord turning area, the lower spoiler 3-G2 of the mid-chord turning area, the upper blade cover plate 4-G1 of the trailing edge blade tip cooling hole, and the lower spoiler 4-G2 of the trailing edge blade tip cooling hole are shown.

[0061] Taking the leading edge blade tip cooling hole plate 1 as an example, the leading edge blade tip cooling hole plate 1 includes a detachably connected leading edge blade tip cooling hole upper blade cover plate 1-G1 and a leading edge blade tip cooling hole lower layer spoiler plate 1-G2, and the leading edge blade tip cooling hole lower layer spoiler plate 1-G2 is provided with multiple first spoiler structures.

[0062] Specifically, the upper blade cover plate 1-G1 of the leading edge blade tip cooling hole, the upper blade cover plate 2-G1 of the mid-chord third row channel blade tip cooling hole, the upper blade cover plate 3-G1 of the mid-chord turning area, and the upper blade cover plate 4-G1 of the trailing edge blade tip cooling hole are fastened to the cover plate body 5 by bolts.

[0063] The lower layer spoiler 1-G2 of the leading edge blade tip cooling hole, the lower layer spoiler 2-G2 of the mid-chord third row channel blade tip cooling hole, the lower layer spoiler 3-G2 of the mid-chord turning area, and the lower layer spoiler 4-G2 of the trailing edge blade tip cooling hole are fastened together with the upper layer blade cover 1-G1 of the leading edge blade tip cooling hole, the upper layer blade cover 2-G1 of the mid-chord third row channel blade tip cooling hole, the upper layer blade cover 3-G1 of the mid-chord turning area, and the upper layer blade cover 4-G1 of the trailing edge blade tip cooling hole by bolts.

[0064] The lower spoiler structure 1-R1 for the leading edge tip cooling holes, the lower spoiler structure 2-R1 for the third row of mid-chord duct tip cooling holes, the lower spoiler structure 3-R1 for the mid-chord turning area, and the lower spoiler structure 4-R1 for the trailing edge tip cooling holes are represented by spherical sockets. These can be replaced with ribs, spherical bumps, fins, and other heat transfer enhancements. During testing, simply replacing these cooling components allowed the shape and size of the cooling holes and the spoiler structure to be modified in different areas of the test blade tip.

[0065] The cross-sectional view of the upper blade cover 1-G1 of the leading edge blade tip cooling hole is as follows Figure 5 As shown. A second regulating structure is provided at the outlet of the airflow channel on the leading edge tip cooling hole plate 1. The second regulating structure is used to adjust the flow area of ​​the airflow channel outlet. Specifically, the second regulating structure includes a tip cooling hole high-temperature resistant soft pressure-sensitive sheet Y1 and a tip cooling hole high-temperature resistant soft pressure-sensitive layer YM1.

[0066] The voltage on the high-temperature resistant soft pressure-sensitive sheet Y1 of the blade tip cooling hole is provided by the control component of the peripheral device. The high-temperature resistant soft pressure-sensitive layer YM1 of the blade tip cooling hole is a material that is very sensitive to voltage. When the voltage loaded on the high-temperature resistant soft pressure-sensitive sheet Y1 of the blade tip cooling hole increases, the high-temperature resistant soft pressure-sensitive layer YM1 of the blade tip cooling hole will become thicker. When the voltage loaded on the high-temperature resistant soft pressure-sensitive sheet Y1 of the blade tip cooling hole decreases, the high-temperature resistant soft pressure-sensitive layer YM1 of the blade tip cooling hole will become thinner.

[0067] The voltage applied to the high-temperature resistant soft pressure-sensitive sheet Y1 of the blade tip cooling hole is adjusted by the control component, thereby controlling the thickness of the high-temperature resistant soft pressure-sensitive layer YM1 of the blade tip cooling hole, thereby adjusting the gas flow area, and then controlling the opening of the blade tip air film hole. Here, the flow rate is changed by changing the gas flow area, so as to control the gas discharge flow rate.

[0068] A second adjustment structure is provided on the upper blade cover plate 2-G1 of the blade tip cooling holes in the third row of the mid-chord channel, the upper blade cover plate 3-G1 in the mid-chord turning area, and the upper blade cover plate 4-G1 of the blade tip cooling holes at the trailing edge. The second adjustment structure is used to adjust the flow area of ​​the airflow channel outlet, and can regulate the air outlet volume of the four blade tip airflow holes respectively, thereby realizing the outflow ratio of the blade tip cooling holes in different areas.

[0069] Leaf structure Figure 6 and Figure 7As shown, the blade body 8 is a hollow structure, and the inner wall of the blade body 8 is detachably connected with a leading edge cooling channel suction surface spoiler 11S, a leading edge cooling channel pressure surface spoiler 11P, a cooling channel suction surface spoiler 12S in the third row at mid-chord, a cooling channel pressure surface spoiler 12P in the third row at mid-chord, a cooling channel suction surface spoiler 13S in the second row at mid-chord, a cooling channel pressure surface spoiler 13P in the second row at mid-chord, a cooling channel suction surface spoiler 14S in the first row at mid-chord, a cooling channel pressure surface spoiler 14P in the first row at mid-chord, a trailing edge cooling channel suction surface spoiler 15S and a trailing edge cooling channel pressure surface spoiler 15P.

[0070] Specifically, such as Figure 6 As shown, the leading edge cooling channel has a spoiler on each of the suction and pressure sides: a leading edge cooling channel suction side spoiler 11S and a leading edge cooling channel pressure side spoiler 11P, respectively. These spoilers are connected to the blade body 8 via slot-type connection structures. A mid-chord cooling channel structure with three rows of cooling channels is shown as an example. Each of the suction and pressure sides has three spoilers: a mid-chord third row of cooling channels suction side spoiler 12S, a mid-chord third row of cooling channels pressure side spoiler 12P, a mid-chord second row of cooling channels suction side spoiler 13S, a mid-chord second row of cooling channels pressure side spoiler 13P, a mid-chord first row of cooling channels suction side spoiler 14S, and a mid-chord first row of cooling channels pressure side spoiler 14P. The trailing edge cooling channel has a spoiler on each of the suction and pressure sides: a trailing edge cooling channel suction side spoiler 15S and a trailing edge cooling channel pressure side spoiler 15P.

[0071] The structure of the leading edge cooling channel suction surface spoiler 11S is as follows Figure 8 As shown, the structure of the leading edge cooling channel pressure surface spoiler 11P is as follows Figure 9 As shown. Among them, the leading edge cooling channel suction surface spoiler 11S, the leading edge cooling channel pressure surface spoiler 11P, the cooling channel suction surface spoiler 12S in the third row at the mid-chord, the cooling channel pressure surface spoiler 12P in the third row at the mid-chord, the cooling channel suction surface spoiler 13S in the second row at the mid-chord, the cooling channel pressure surface spoiler 13P in the second row at the mid-chord, the cooling channel suction surface spoiler 14S in the first row at the mid-chord, the cooling channel pressure surface spoiler 14P in the first row at the mid-chord, the trailing edge cooling channel suction surface spoiler 15S, the trailing edge cooling channel pressure surface spoiler 15P, the leading edge film hole plate 6 and the trailing edge slit slot plate 7 are all connected to the blade body 8 in a slot-type structure, as shown in FIG. Figure 14 As shown. Figures 8 to 13As shown, the leading edge cooling channel suction surface spoiler structure 11S-R2, the leading edge cooling channel pressure surface spoiler structure 11P-R2, the cooling channel suction surface spoiler structure 12S-R2 in the third row of mid-chord, the cooling channel pressure surface spoiler structure 12P-R2 in the third row of mid-chord, the cooling channel suction surface spoiler structure 13S-R2 in the second row of mid-chord, the cooling channel pressure surface spoiler structure 13P-R2 in the second row of mid-chord, the cooling channel suction surface spoiler structure 14S-R2 in the first row of mid-chord, and the cooling channel pressure surface spoiler structure 14P-R2 in the first row of mid-chord are represented by fins, and their specific structures can be replaced with various heat exchange enhancement structures such as ribs, spherical protrusions, and ball sockets as needed. The spoiler structure 15S-R3 on the suction side of the trailing edge cooling channel and the spoiler structure 15P-R3 on the pressure side of the trailing edge cooling channel are represented by rib columns. Their specific structures can also be replaced with various types of heat exchange enhancement structures such as ribs, spherical protrusions, and fins according to needs.

[0072] like Figures 15 to 18 As shown, the leading edge air film hole plate 6 and the trailing edge slit slot plate 7 are provided with a number of leading edge air film holes 6-Q1 and trailing edge slit slots 7-Q1. The leading edge air film hole plates 6 and the trailing edge slit slot plates 7 with different numbers, shapes and arrangements can be flexibly replaced according to research requirements.

[0073] The upper platform 9 of the blade is as follows Figure 19 and Figure 20 As shown, the upper platform 9 of the blade has an upper air distribution chamber 17A inside, and the top of the upper air distribution chamber 17A is provided with a leading edge cooling channel air inlet 16A, a mid-chord cooling channel air inlet 16B and a trailing edge cooling channel air inlet 16C at positions corresponding to different internal cooling channels.

[0074] Specifically, the cross-sectional shape of the inlet passage can be rectangular, circular, or similar to the internal cooling passage. The figure shows a schematic diagram of a rectangular cooling passage. The blade body 8 is fastened to the blade upper platform 9 via bolts. The leading edge film orifice plate 6 and the trailing edge slot plate 7 are also fastened to the blade upper platform 9 via bolts.

[0075] The lower platform 10 of the blade is as follows Figure 21 and Figure 22As shown. The lower air distribution chamber 17B is provided inside the lower platform 10 of the blade. The bottom of the lower air distribution chamber 17B is fastened to the connecting part 19 by bolts, and a cold air delivery channel 18 is provided inside the connecting part 19. The connecting part 19 can be flexibly designed and adapted to the shape of the air supply channel, the shape of the connection port, the rotation radius, etc. according to the actual needs of different test systems, and can be simply replaced according to specific test requirements to ensure that the connecting part 19 can effectively adapt to various working conditions and usage situations. The lower platform 10 of the blade is fastened to the upper platform 9 of the blade by bolts, thereby connecting the upper air distribution chamber 17A and the lower air distribution chamber 17B to form a total air distribution chamber 17, which is used to buffer and store the cooling gas delivered from the cold air delivery channel 18. A sealing groove D1 is provided in the middle of the lower platform 10 of the blade, and sealing is achieved by placing a sealing gasket in the sealing groove D1 to prevent cold air leakage from the total air distribution chamber 17.

[0076] Figure 23 The radial cross-sectional structure of the platform 9 on the blade is provided with a first adjustment structure on the channel walls around the leading edge cooling channel air inlet hole 16A, the mid-chord cooling channel air inlet hole 16B and the trailing edge cooling channel air inlet hole 16C. The first adjustment structure is used to adjust the flow area and pre-swirl of the airflow, and can also adjust the flow channel shape of the leading edge cooling channel air inlet hole 16A, the mid-chord cooling channel air inlet hole 16B and the trailing edge cooling channel air inlet hole 16C.

[0077] Taking one of them as an example, the others will not be elaborated in detail. Specifically, the first regulating structure includes a blade upper platform air inlet, a blade upper platform air inlet, a high temperature resistant soft pressure-sensitive layer YM2 and a plurality of blade upper platform air inlets, a blade upper platform air inlet, a high temperature resistant soft pressure-sensitive sheet Y2, arranged on the air flow channel, and the plurality of blade upper platform air inlet, a high temperature resistant soft pressure-sensitive sheet Y2 are evenly distributed between the air flow channel and the blade upper platform air inlet, a blade upper platform air inlet, a high temperature resistant soft pressure-sensitive sheet Y2 is connected to an external control component, and the control component is used to adjust the voltage of the blade upper platform air inlet, a blade upper platform air inlet, a high temperature resistant soft pressure-sensitive sheet Y2, The high-temperature resistant soft pressure-sensitive sheet Y2 of the blade upper platform air inlet holes of the leading edge cooling channel air inlet holes 16A, the mid-chord cooling channel air inlet holes 16B and the trailing edge cooling channel air inlet holes 16C can be independently controlled, and then the high-temperature resistant soft pressure-sensitive layer YM2 of the blade upper platform air inlet holes of the leading edge cooling channel air inlet holes 16A, the mid-chord cooling channel air inlet holes 16B and the trailing edge cooling channel air inlet holes 16C can be controlled, thereby independently regulating the flow rate of cold air entering the leading edge cooling channel air inlet holes 16A, the mid-chord cooling channel air inlet holes 16B and the trailing edge cooling channel air inlet holes 16C to achieve different cold air ratios.

[0078] The structures and control principles of the first adjustment structures set in the other places mentioned above are the same. The high-temperature resistant soft pressure-sensitive layer YM2 of the blade upper platform air inlet hole of the mid-chord cooling channel air inlet hole 16B and the trailing edge cooling channel air inlet hole 16C are similar to the high-temperature resistant soft pressure-sensitive piece Y2 of the blade upper platform air inlet hole and the leading edge cooling channel air inlet hole 16A.

[0079] At the same time, along the air inlet direction (radial direction) of the leading edge cooling channel air inlet 16A, the mid-chord cooling channel air inlet 16B and the trailing edge cooling channel air inlet 16C, the channel walls around each air inlet are also arranged with a blade upper platform air inlet high temperature resistant soft pressure-sensitive layer YM2 and several blade upper platform air inlet high temperature resistant soft pressure-sensitive sheets Y2. By applying different voltages to the blade upper platform air inlet high temperature resistant soft pressure-sensitive sheet Y2 to change the pre-rotation degree of the cold air entering the cooling channel, changing the thickness of the blade upper platform air inlet high temperature resistant soft pressure-sensitive layer YM2, and changing the flow direction of the gas before entering the cooling channel, the cold air can be blown to the wall at different angles to achieve the purpose of cooling specific parts. The specific adjustment method is shown in the figure. Figure 24 As shown. By adjusting the radial slopes of the four surfaces of the leading edge cooling channel inlet 16A, the mid-chord cooling channel inlet 16B, and the trailing edge cooling channel inlet 16C, airflow inflow can be adjusted in any direction and angle, thereby achieving cold air pre-swirl adjustment at the inlets of different internal cooling channels, and then studying the effect of cold air inlet pre-swirl on heat transfer. In particular, based on experimental results, when it is known that the temperature at a certain cooling channel location is high and requires intensive cooling, the voltage of the high-temperature resistant soft pressure-sensitive plate Y2 on the blade platform inlet can be adjusted to change the pre-swirl of the gas before entering the cooling channel, achieving directional enhanced cooling in areas with deteriorated heat transfer.

[0080] Test piece assembly and cooling element replacement method:

[0081] (1) Test piece overall assembly method:

[0082] Step 1: Select the cooling element corresponding to the test conditions;

[0083] Step 2: Fasten the blade body 8 and the blade upper platform 9 with bolts;

[0084] Step 3: Insert the selected leading edge air film hole plate 6 and trailing edge slit slot plate 7 into the blade body 8 and fasten them to the blade upper platform 9 with bolts;

[0085] Step 4: insert the selected leading edge cooling channel suction surface spoiler 11S, leading edge cooling channel pressure surface spoiler 11P, cooling channel suction surface spoiler 12S in the third row at mid-chord, cooling channel pressure surface spoiler 12P in the third row at mid-chord, cooling channel suction surface spoiler 13S in the second row at mid-chord, cooling channel pressure surface spoiler 13P in the second row at mid-chord, cooling channel suction surface spoiler 14S in the first row at mid-chord, cooling channel pressure surface spoiler 14P in the first row at mid-chord, trailing edge cooling channel suction surface spoiler 15S, and trailing edge cooling channel pressure surface spoiler 15P into corresponding positions of the blade body 8 through the provided slot structure;

[0086] Step 5: Install the selected leading edge blade tip cooling hole lower layer spoiler 1-G2, mid-chord third row channel blade tip cooling hole lower layer spoiler 2-G2, mid-chord turning area lower layer spoiler 3-G2, and trailing edge blade tip cooling hole lower layer spoiler 4-G2 onto the leading edge blade tip cooling hole upper layer blade cover 1-G1, mid-chord third row channel blade tip cooling hole upper layer blade cover 2-G1, mid-chord turning area upper layer blade cover 3-G1, and trailing edge blade tip cooling hole upper layer blade cover 4-G1 respectively by screws;

[0087] Step 6: Fasten the assembled leading edge blade tip cooling hole upper blade cover plate 1-G1, mid-chord third row channel blade tip cooling hole upper blade cover plate 2-G1, mid-chord turning area upper blade cover plate 3-G1, and trailing edge blade tip cooling hole upper blade cover plate 4-G1 to the cover plate body 5 by bolts;

[0088] Step 7: The cover plate body 5 is fastened to the leading edge air film hole plate 6, the trailing edge slit slot plate 7, and the blade body 8 respectively by bolts;

[0089] Step 8: Fix the selected connection part 19 to the blade lower platform 10 by bolts;

[0090] Step 9: Place a sealing ring in the sealing groove D1, and connect the blade upper platform 9 and the blade lower platform 10 through the blade platform bolts. The installation is completed.

[0091] (2) Cooling element replacement method

[0092] ① The replacement methods for the leading edge blade tip cooling hole upper blade cover 1-G1 / the mid-chord third row channel blade tip cooling hole upper blade cover 2-G1 / the mid-chord turning area upper blade cover 3-G1 / the trailing edge blade tip cooling hole upper blade cover 4-G1 are the same. The following is an example of the replacement of the leading edge blade tip cooling hole upper blade cover 1-G1:

[0093] Step 1: Remove the blade tip cooling hole plate bolts and remove the leading edge blade tip cooling hole plate 1;

[0094] Step 2: Remove the lower spoiler bolts and remove the lower spoiler 1-G2 of the leading edge blade tip cooling hole;

[0095] Step 3: Fasten the newly selected leading edge blade tip cooling hole upper blade cover 1-G1 and the original leading edge blade tip cooling hole lower spoiler 1-G2 with bolts;

[0096] Step 4: Assemble the assembled leading edge blade tip cooling hole upper blade cover plate 1-G1 on the cover plate body 5 using bolts.

[0097] ② The following cooling components are replaced in the same way: the lower spoiler 1-G2 of the leading edge blade tip cooling hole, the lower spoiler 2-G2 of the third row of mid-chord blade tip cooling hole, the lower spoiler 3-G2 of the mid-chord turning area, and the lower spoiler 4-G2 of the trailing edge blade tip cooling hole. The following uses the lower spoiler 1-G2 of the leading edge blade tip cooling hole as an example to illustrate:

[0098] Step 1: Remove the blade tip cooling hole plate bolts and remove the leading edge blade tip cooling hole plate 1;

[0099] Step 2: Remove the lower spoiler bolts and remove the lower spoiler 1-G2 of the leading edge blade tip cooling hole;

[0100] Step 3: Fasten the newly selected leading edge blade tip cooling hole lower layer spoiler 1-G2 and leading edge blade tip cooling hole upper layer blade cover 1-G1 with bolts;

[0101] Step 4: Assemble the assembled leading edge blade tip cooling hole upper blade cover plate 1-G1 on the cover plate body 5 using bolts.

[0102] ③ Leading edge air film orifice plate 6 / trailing edge slit slot plate 7. The replacement method of the above cooling components is the same. The following is an example of the leading edge air film orifice plate 6:

[0103] Step 1: Remove the blade cover bolts and remove the blade cover;

[0104] Step 2: Remove the bolts in the blade platform and remove the blade lower platform 10;

[0105] Step 3: Remove the bolts in the orifice plate and remove the leading edge air film orifice plate 6 from the top;

[0106] Step 4: Insert the newly selected leading edge film hole plate 6 into the blade body 8 from the top;

[0107] Step 5: Assemble the newly selected leading edge film orifice plate 6 on the blade body 8 and the blade upper platform 9 with bolts;

[0108] Step 6: The blade lower platform 10 is fastened to the blade upper platform 9 by bolts;

[0109] Step 7: The blade top cover plate is fastened to the selected leading edge air film hole plate 6, trailing edge slit slot plate 7, and blade body 8 by bolts.

[0110] ④ Leading edge cooling channel suction surface spoiler 11S / Leading edge cooling channel pressure surface spoiler 11P / Mid-chord third row cooling channel suction surface spoiler 12S / Mid-chord third row cooling channel pressure surface spoiler 12P / Mid-chord second row cooling channel suction surface spoiler 13S / Mid-chord second row cooling channel pressure surface spoiler 13P / Mid-chord first row cooling channel suction surface spoiler 14S / Mid-chord first row cooling channel pressure surface spoiler 14P / Trailing edge cooling channel suction surface spoiler 15S / Trailing edge cooling channel pressure surface spoiler 15P. The replacement method of the above cooling components is the same. The following is an example of the leading edge cooling channel suction surface spoiler 11S:

[0111] Step 1: Remove the blade cover bolts and remove the blade cover;

[0112] Step 2: Pull out the leading edge cooling channel suction surface spoiler 11S from the top;

[0113] Step 3: insert the newly selected leading edge cooling channel suction surface spoiler 11S into the original position;

[0114] Step 4: Reinstall the blade top blade cover plate on the leading edge air film hole plate 6, the trailing edge slit slot plate 7, and the blade body 8 through the blade cover plate bolts.

[0115] ⑤Connection 19:

[0116] Step 1: Remove the bolts in the blade platform, remove the blade lower platform 10 and the connected connection part 19;

[0117] Step 2: Remove the bolts in the valve chamber and remove the connecting part 19;

[0118] Step 3: Assemble the newly selected connection part 19 on the blade lower platform 10 by bolts;

[0119] Step 4: Assemble the assembled blade lower platform 10 and connecting portion 19 on the blade upper platform 9 by means of bolts.

[0120] The flow of cold air is as follows Figure 25As shown in FIG. Cold air enters the main air distribution chamber 17 from the cooling medium inlet through the cold air delivery channel 18 opened in the connecting portion 19. After the airflow stabilizes in the main air distribution chamber 17, it flows into the corresponding internal cooling channels through the leading edge cooling channel air inlet 16A, the mid-chord cooling channel air inlet 16B, and the trailing edge cooling channel air inlet 16C. The thickness of the high-temperature resistant soft pressure-sensitive layer YM2 of the blade upper platform air inlet is changed by adjusting the high-temperature resistant soft pressure-sensitive sheet Y2 of the blade upper platform air inlet, thereby adjusting the air intake flow rate and pre-swirl degree of the above three air inlets.

[0121] For leading edge cooling, the cooling gas flows into the leading edge cooling channel through the leading edge cooling channel air inlet 16A and exchanges heat with the leading edge cooling channel suction side spoiler 11S and the leading edge cooling channel pressure side spoiler 11P. Part of the cold air is discharged through the leading edge film hole 6-Q1 and forms a cold air film on the outer surface of the blade. The other part of the cold air hits the lower spoiler 1-G2 of the leading edge tip cooling hole and exchanges heat, and is finally discharged through the leading edge tip cooling hole opened on the leading edge tip cooling hole plate 1.

[0122] For mid-chord cooling, the cooling gas flows into the first row of mid-chord cooling channels through the mid-chord cooling channel inlet hole 16B, and exchanges heat with the suction surface spoiler 14S and the pressure surface spoiler 14P of the first row of mid-chord cooling channels. Then, it hits the lower spoiler 3-G2 of the mid-chord turning area and exchanges heat. Part of the cooling gas is discharged through the mid-chord turning area blade tip cooling hole opened on the mid-chord turning area blade tip cooling hole plate 3. The other part of the cooling gas flows into the second row of mid-chord cooling channels after passing through the first turning area and exchanges heat with the mid-chord cooling channel. The air then exchanges heat with the suction side spoiler 13S of the second row of cooling channels at the chord and the pressure side spoiler 13P of the second row of cooling channels at the mid-chord. The air then flows through the second turning area into the third row of cooling channels at the mid-chord, exchanges heat with the suction side spoiler 12S and the pressure side spoiler 12P of the third row of cooling channels at the mid-chord, and then strikes the lower spoiler 2-G2 of the tip cooling hole of the third row of channels at the mid-chord and exchanges heat, and finally is discharged through the tip cooling hole of the third row of channels at the mid-chord, provided on the tip cooling hole plate 2 of the third row of channels at the mid-chord.

[0123] For trailing edge cooling, the cooling gas flows into the trailing edge cooling channel through the trailing edge cooling channel air inlet hole 16C, and exchanges heat with the trailing edge cooling channel suction surface spoiler 15S and the trailing edge cooling channel pressure surface spoiler 15P. Part of the cold air flows out through the trailing edge slit groove 7-Q1 and covers the outer surface of the blade to form a cooling air film. The other part of the cold air impacts the lower spoiler 4-G2 of the trailing edge blade tip cooling hole and exchanges heat, and is finally discharged through the trailing edge blade tip cooling hole opened on the trailing edge blade tip cooling hole plate 4.

[0124] Compared with the prior art, the gas turbine blade test piece structure with easily replaceable cooling elements and adjustable cooling air of the present invention has the following advantages:

[0125] 1. The present invention not only has a modeled blade profile, but also has complete internal and external cooling structures similar to those of real blades, such as leading edge film cooling, mid-chord channel cooling, trailing edge slit cooling, and blade tip cooling. It can simulate the interaction between different areas and different forms of cooling in the actual operation of high-temperature turbine blades. Compared with traditional simplified models, the research results obtained based on the present invention are closer to the actual operating conditions and can provide higher reference, application and promotion value for blade cooling design.

[0126] 2. The present invention realizes the modularization and setting of multi-region cooling components of gas turbine turbine blades. For the leading edge cooling channel, it has a modular structure with replaceable internal cooling channel heat transfer wall surface enhanced heat exchange structure, replaceable leading edge blade tip cooling holes, replaceable leading edge blade tip heat transfer wall surface enhanced heat exchange structure, and replaceable leading edge air film holes; taking the mid-chord cooling channel with three rows of channels as an example, it has a modular structure with replaceable three rows of internal cooling channel heat transfer wall surface enhanced heat exchange structure, replaceable turning area blade tip cooling holes, replaceable turning area blade tip heat transfer wall surface enhanced heat exchange structure, replaceable third row channel blade tip cooling holes, and replaceable third row channel blade tip heat transfer wall surface enhanced heat exchange structure; for the trailing edge cooling channel, it has a modular structure with replaceable internal cooling channel heat transfer wall surface enhanced heat exchange structure, replaceable trailing edge blade tip cooling holes, replaceable trailing edge blade tip heat transfer wall surface enhanced heat exchange structure, and replaceable trailing edge slit groove.

[0127] The structure provided by the present invention only requires simple replacement of corresponding cooling elements during testing to achieve rapid changes in the cooling scheme of the entire turbine blade, without the need to manufacture the entire complex blade. It can not only test the optimal cooling structure for cooling in different areas, but also couple all cooling methods of the blade. Through low-cost and rapid testing, a large number of different blade structures and working conditions can be tested, and a blade cooling performance test database can be obtained, thereby obtaining the optimal blade combination cooling design scheme, which greatly reduces the blade R&D cost and improves the R&D efficiency, and provides strong support for the development of high-efficiency and low-resistance combustion turbine blade cooling technology.

[0128] 3. The present invention can achieve precise control of the cross-sectional shape, flow rate and pre-rotation of the cold air outflow. By adjusting the first adjustment structure, the flow area and pre-rotation can be controlled, thereby precisely controlling the cold air ratio in multiple regions. By adjusting the second adjustment structure, the flow area can be controlled to adapt to the adjustment of cooling requirements under variable working conditions. This structure has the following advantages: (1) The cold air flow rate flowing into the inlets of different internal cooling channels of the blade and out of the cooling holes in different areas of the blade top can be adjusted to achieve precise adjustment of the cold air ratio between multiple regions; (2) The direction and angle of the cold air inflow at the inlets of different internal cooling channels can be adjusted to achieve independent adjustment of the pre-rotation of multiple inlet cold air. Therefore, the unique multi-region cold air adjustable function of the present invention can provide a higher optimization design dimension for the research and development of high-temperature blades of gas turbines, has strong practicality, and is worthy of promotion.

[0129] It will be understood that the present invention is described through some embodiments, and those skilled in the art will appreciate that various changes or equivalent substitutions may be made to these features and embodiments without departing from the spirit and scope of the present invention.

[0130] Furthermore, these features and embodiments may be modified to suit specific circumstances and materials under the teachings of the present invention without departing from the spirit and scope of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of the present invention are intended to be protected by the present invention.

Claims

1. A test piece structure for a gas turbine blade with easily replaceable cooling elements and adjustable cooling air, characterized in that: It comprises a blade platform, a blade and a connecting portion (19), wherein the blade and the connecting portion (19) are respectively arranged on both sides of the blade platform and are detachably connected to the blade platform, and air flow channels are respectively arranged on the connecting portion (19), the blade platform and the blade, and the air flow channels are sequentially connected; The blade includes a blade body (8), a leading edge air film hole plate (6), a trailing edge split slot plate (7) and a blade cover plate, the blade cover plate is detachably connected to one end of the blade body (8), and the other end of the blade body (8) is detachably connected to the blade platform, the leading edge air film hole plate (6) and the trailing edge split slot plate (7) are respectively arranged on the front and rear sides of the blade body (8) and are detachably connected to the blade platform; the blade cover plate includes a cover plate body (5) and a leading edge blade tip cooling hole plate (1), a mid-chord third row channel blade tip cooling hole plate (2), a mid-chord turning area blade tip cooling hole plate (3) and a trailing edge blade tip cooling hole plate (4) which are arranged in sequence and are all detachably connected to the cover plate body (5); At least one first regulating structure is provided at the outlet of the airflow channel on the blade platform, the first regulating structure being used to regulate the flow area and pre-rotation; the leading edge blade tip cooling hole plate (1), the mid-chord third row channel blade tip cooling hole plate (2), the mid-chord turning area blade tip cooling hole plate (3), the trailing edge blade tip cooling hole plate (4), the leading edge air film hole plate (6) and the trailing edge slit slot plate (7) are all provided with airflow channel outlets; the airflow channel outlet on the blade body is provided with a second regulating structure, the second regulating structure being used to regulate the flow area; The leading edge blade tip cooling hole plate (1), the mid-chord third row channel blade tip cooling hole plate (2), the mid-chord turning area blade tip cooling hole plate (3), and the trailing edge blade tip cooling hole plate (4) have the same structure and all include a first fixed plate and a first spoiler, the first fixed plate and the first spoiler are detachably connected, and the first spoiler includes a first plate body and a plurality of first spoiler structures arranged on the first plate body; the blade body (8) is a hollow structure, and the inner wall of the blade body (8) is detachably connected with a leading edge cooling channel suction surface spoiler (11S), a leading edge cooling channel pressure surface spoiler (11P), a mid-chord third row cooling channel suction surface spoiler (12S), a mid-chord third row cooling channel pressure surface spoiler (12P), a mid-chord second row cooling channel suction surface spoiler (13S), a mid-chord second row cooling channel pressure surface spoiler (13P), a mid-chord first row cooling channel suction surface spoiler (11S), and a mid-chord first row cooling channel pressure surface spoiler (11P). The spoiler (14S), the mid-chord first row cooling channel pressure surface spoiler (14P), the trailing edge cooling channel suction surface spoiler (15S) and the trailing edge cooling channel pressure surface spoiler (15P); the leading edge cooling channel suction surface spoiler (11S), the leading edge cooling channel pressure surface spoiler (11P), the mid-chord third row cooling channel suction surface spoiler (12S), the mid-chord third row cooling channel pressure surface spoiler (12P), the mid-chord second row cooling channel suction surface spoiler (13S), the mid-chord second row cooling channel pressure surface spoiler (13P), the mid-chord first row cooling channel suction surface spoiler (14S), the mid-chord first row cooling channel pressure surface spoiler (14P), the trailing edge cooling channel suction surface spoiler (15S) and the trailing edge cooling channel pressure surface spoiler (15P) have the same structure and all include a second fixed plate and a plurality of second spoiler structures arranged on the second fixed plate.

2. The gas turbine blade test piece structure with easily replaceable cooling elements and adjustable cooling according to claim 1 is characterized in that: The structures of the first adjustment structure and the second adjustment structure are the same, both including a control component, a high-temperature resistant soft pressure-sensitive layer and a plurality of high-temperature resistant soft pressure-sensitive sheets. The high-temperature resistant soft pressure-sensitive layer is arranged circumferentially around the air flow channel inlet / air flow channel outlet, and a plurality of high-temperature resistant soft pressure-sensitive sheets are arranged between the air flow channel and the high-temperature resistant soft pressure-sensitive layer. The high-temperature resistant soft pressure-sensitive sheet is connected to the control component, and the control component is used to adjust the voltage applied to the high-temperature resistant soft pressure-sensitive sheet. When the voltage on the high-temperature resistant soft pressure-sensitive sheet changes, it acts on the high-temperature resistant soft pressure-sensitive layer to cause it to deform.

3. The combustion engine turbine blade test piece structure with easily replaceable cooling elements and adjustable cooling according to claim 1 is characterized in that: The first spoiler structure and the second spoiler structure are one of a ball socket, a rib, a ball protrusion and a fin.

4. The combustion engine turbine blade test piece structure with easily replaceable cooling elements and adjustable cooling according to claim 1 is characterized in that: The blade platform comprises a detachably connected blade upper platform (9) and a blade lower platform (10), a main air distribution chamber (17) is provided between the blade upper platform (9) and the blade lower platform (10), the main air distribution chamber (17) is used to buffer and store cooling gas, and the main air distribution chamber (17) is communicated with the air flow channels on the blade and the connecting portion (19), respectively.

5. The combustion engine turbine blade test piece structure with easily replaceable cooling elements and adjustable cooling air according to claim 4 is characterized in that: A sealing structure is provided between the blade upper platform (9) and the blade lower platform (10).

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