Gas turbine blade test piece structure with cooling element easy to replace and cold air adjustable

Abstract

The invention belongs to the technical field of gas turbine blade cooling, and particularly discloses a gas turbine blade test piece structure with easy-to-replace cooling elements and adjustable cold air, which comprises a blade platform, a blade and a connecting part, and is characterized in that the blade and the connecting part are respectively arranged on two sides of the blade platform and are detachably connected with the blade platform; the connecting part, the blade platform and the blades are each provided with an airflow channel, and the airflow channels are sequentially communicated. According to the method, the problems that in the prior art, the difference from the actual operation condition is large, the design time period is long, and the economic cost is high are solved, the mutual influence between different areas and different forms of cooling is considered on the blade structure, the actual operation condition of the blade is restored, and the blade structure is subjected to modular design. And an adjustable cooling structure is designed on each module, so that the blades of various different structures can be conveniently tested, the model research and development cost is reduced, the experiment efficiency of researching the cooling effect is improved, and a basis is provided for later structure 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 the field of modern energy conversion and power. Their turbine blades are directly exposed to high-temperature and high-pressure gas environments, and are subject to huge heat loads and complex mechanical stresses. As gas turbines develop towards high efficiency and high power, the turbine inlet temperature continues to rise, far exceeding the tolerance limit of blade materials. This extreme operating condition poses a severe challenge 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, and covers the surface of the blade downstream of the hole under the push and squeeze of the high-temperature mainstream, 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 heat 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 heat 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 of all, 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 and 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 needs to be reprocessed. In particular, when conducting optimal design of multiple cooling structure combinations, it is necessary to process, manufacture and test blade simulations of various different structures, 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 deficiencies in the prior art and facilitates testing of blades of 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, thus providing a basis for subsequent structural optimization, effectively reducing the model development cost and improving the experimental efficiency of studying the cooling effect.

[0007] To achieve the above object, the specific technical solution provided by the present invention is as follows:

[0008] A test piece structure of a gas turbine blade with easy replacement of cooling elements and adjustable cold air, comprising:

[0009] A blade platform, a blade and a connecting part, the blade and the connecting part 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 part, the blade platform and the blade, and the air flow channels are connected in sequence;

[0010] The blade includes a blade body, a leading edge air film orifice plate, a trailing edge split 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 air film orifice plate and the trailing edge split slot plate are respectively arranged on the front and back sides of the blade body and are detachably connected to the blade platform; the blade cover plate includes a cover plate main body and a leading edge tip cooling orifice plate, a third row of channel tip cooling orifice plates in the middle chord, a tip cooling orifice plate in the turning area of the middle chord and a trailing edge tip cooling orifice plate which are arranged in sequence and are all detachably connected to the cover plate main body;

[0011] At least one first adjusting structure is arranged at the air flow channel outlet on the blade platform, and the first adjusting structure is used to adjust the flow area and pre-whirl. Air flow channel outlets are arranged on the leading edge tip cooling orifice plate, the third row of channel tip cooling orifice plates in the middle chord, the tip cooling orifice plate in the turning area of the middle chord, the trailing edge tip cooling orifice plate, the leading edge air film orifice plate and the trailing edge split slot plate. A second adjusting structure is arranged at the air flow channel outlet on the blade body, and the second adjusting structure is used to adjust the flow area.

[0012] Further, the first adjusting structure and the second adjusting structure have the same structure, and both include 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 at the air flow channel inlet / air flow channel outlet. The 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 sheets are connected to the control component, and the control component is used to adjust the voltage applied to the high-temperature resistant soft pressure-sensitive sheets. When the voltage on the high-temperature resistant soft pressure-sensitive sheets changes, it acts on the high-temperature resistant soft pressure-sensitive layer to cause it to deform.

[0013] Further, the leading edge tip cooling orifice plate, the third row of channel tip cooling orifice plates in the middle chord, the tip cooling orifice plate in the turning area of the middle chord and the trailing edge tip cooling orifice plate have the same structure, and all include a first fixing plate and a first spoiler plate. The first fixing plate and the first spoiler plate are detachably connected. The first spoiler plate includes a first plate body and a plurality of first spoiler structures arranged on the first plate body.

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

[0015] Furthermore, the suction surface spoiler for the leading edge cooling channel, the pressure surface spoiler for the leading edge cooling channel, the suction surface spoiler for the third row of cooling channels in the mid-chord, the pressure surface spoiler for the third row of cooling channels in the mid-chord, the suction surface spoiler for the second row of cooling channels in the mid-chord, the pressure surface spoiler for the second row of cooling channels in the mid-chord, the suction surface spoiler for the first row of cooling channels in the mid-chord, the pressure surface spoiler for the first row of cooling channels in the mid-chord, the suction surface spoiler for the trailing edge cooling channel, and the pressure surface spoiler for the trailing edge cooling channel have the same structure, and each includes a second fixing plate and a plurality of second spoiler structures provided on the second fixing plate.

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

[0017] Furthermore, the blade platform includes a detachable upper blade platform and a lower blade platform. A total air distribution chamber is provided between the upper blade platform and the lower blade platform. The total air distribution chamber is used to buffer and store cooling gas, and the total air distribution chamber is respectively communicated with the air flow channels on the blade and the connecting part.

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

[0019] Compared with the prior art, the test piece structure of the gas turbine blade with easy replacement of 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, truly restoring the actual operating conditions 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 a single blade, facilitating the testing of blades with multiple different structures. This not only verifies the cooling performance of different cooling structures but also effectively reduces the model R & D cost and improves the experimental efficiency of studying the cooling effect, providing a basis for subsequent structural optimization. At the same time, by adjusting the first adjustment structure, the control of the flow area and pre-whirl degree is achieved, thereby accurately regulating the cold air ratio and the cold air inflow direction in multiple regions. By adjusting the second adjustment structure, the control of the flow area is achieved to adapt to the adjustment of cooling requirements under variable operating conditions, enabling the test piece structure to have a unique multi-region cold air adjustable function, which can provide a higher optimization design dimension for the R & D of high-temperature blades of gas turbines, with strong practicality and worthy of promotion. Brief Description of the Drawings

[0021] Figure 1 Schematic diagram of the overall structure of the present invention;

[0022] Figure 2 Schematic diagram of the structure of the blade cover plate of the present invention;

[0023] Figure 3 Schematic diagram of the structure of the cover plate main body of the present invention;

[0024] Figure 4 Stereogram of the blade cover plate of the present invention;

[0025] Figure 5 Cross-sectional view of the upper layer blade cover plate of the leading edge blade tip cooling hole of the present invention;

[0026] Figure 6 Schematic assembly diagram of the blade of the present invention;

[0027] Figure 7 Schematic diagram of the structure of the blade main body of the present invention;

[0028] Figure 8 Schematic diagram of the structure of the suction surface spoiler of the leading edge cooling channel of the present invention;

[0029] Figure 9 Schematic diagram of the structure of the pressure surface spoiler of the leading edge cooling channel of the present invention;

[0030] Figure 10 Schematic diagram of the structure of the suction surface spoiler of the mid-chord cooling channel of the present invention;

[0031] Figure 11 Schematic diagram of the structure of the pressure surface spoiler of the mid-chord cooling channel of the present invention;

[0032] Figure 12 Schematic structural diagram of the suction surface spoiler of the trailing edge cooling channel of the present invention;

[0033] Figure 13 Schematic structural diagram of the pressure surface spoiler of the trailing edge cooling channel of the present invention;

[0034] Figure 14 Schematic structural diagram of the slot connection structure of the present invention;

[0035] Figure 15 First perspective three-dimensional view of the leading edge film hole plate of the present invention;

[0036] Figure 16 Second perspective three-dimensional view of the leading edge film hole plate of the present invention;

[0037] Figure 17 First perspective three-dimensional view of the trailing edge split slot plate of the present invention;

[0038] Figure 18 Second perspective three-dimensional view of the trailing edge split slot plate of the present invention;

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

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

[0041] Figure 21 Top view of the lower platform of the blade and the connecting part of the present invention;

[0042] Figure 22 Bottom view of the lower platform of the blade and the connecting part of the present invention;

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

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

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

[0046] Reference numerals:

[0047] 1. Leading-edge tip cooling hole plate, 2. Third row of mid-chord passage tip cooling hole plate, 3. Mid-chord turning region tip cooling hole plate, 4. Trailing-edge tip cooling hole plate, 5. Cover plate body, 6. Leading-edge film cooling hole plate, 7. Trailing-edge split 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 tip cooling hole, 1-G2. Lower spoiler of leading-edge tip cooling hole, 2-G1. Upper blade cover plate of third row of mid-chord passage tip cooling hole, 2-G2. Lower spoiler of third row of mid-chord passage tip cooling hole, 3-G1. Upper blade cover plate of mid-chord turning region, 3-G2. Lower spoiler of mid-chord turning region, 4-G1. Upper blade cover plate of trailing-edge tip cooling hole, 4-G2. Lower spoiler of trailing-edge tip cooling hole, 1-R1. Spoiler structure of lower spoiler of leading-edge tip cooling hole, 2-R1. Spoiler structure of lower spoiler of third row of mid-chord passage tip cooling hole, 3-R1. Spoiler structure of lower spoiler of mid-chord turning region, 4-R1. Spoiler structure of lower spoiler of trailing-edge tip cooling hole, 11S. Suction surface spoiler of leading-edge cooling channel, 11P. Pressure surface spoiler of leading-edge cooling channel, 12S. Suction surface spoiler of third row of mid-chord cooling channel, 12P. Pressure surface spoiler of third row of mid-chord cooling channel, 13S. Suction surface spoiler of second row of mid-chord cooling channel, 13P. Pressure surface spoiler of second row of mid-chord cooling channel, 14S. Suction surface spoiler of first row of mid-chord cooling channel, 14P. Pressure surface spoiler of first row of mid-chord cooling channel, 15S. Suction surface spoiler of trailing-edge cooling channel, 15P. Pressure surface spoiler of trailing-edge cooling channel, 11S-R2. Spoiler structure of suction surface spoiler of leading-edge cooling channel, 11P-R2. Spoiler structure of pressure surface spoiler of leading-edge cooling channel, 12S-R2. Spoiler structure of suction surface spoiler of third row of mid-chord cooling channel, 12P-R2. Spoiler structure of pressure surface spoiler of third row of mid-chord cooling channel, 13S-R2. Spoiler structure of suction surface spoiler of second row of mid-chord cooling channel, 13P-R2. Spoiler structure of pressure surface spoiler of second row of mid-chord cooling channel, 14S-R2. Spoiler structure of suction surface spoiler of first row of mid-chord cooling channel, 14P-R2. Spoiler structure of pressure surface spoiler of first row of mid-chord cooling channel, 15S-R3. Spoiler structure of suction surface spoiler of trailing-edge cooling channel, 15P-R3. Spoiler structure of pressure surface spoiler of trailing-edge cooling channel, 6-Q1. Leading-edge film cooling hole, 7-Q1. Trailing-edge split slot, 16A. Leading-edge cooling channel inlet hole, 16B. Mid-chord cooling channel inlet hole, 16C. Trailing-edge cooling channel inlet hole, 17A. Upper air distribution chamber, 17B. Lower air distribution chamber, 18. Cold air delivery channel, D1. Sealing groove, Y1. High-temperature resistant soft pressure-sensitive sheet for tip cooling hole, YM1. High-temperature resistant soft pressure-sensitive layer for tip cooling hole, Y2. High-temperature resistant soft pressure-sensitive sheet for blade upper platform inlet hole, YM2. High-temperature resistant soft pressure-sensitive layer for blade upper platform inlet hole. Detailed implementation mode

[0048] In order to enable those skilled in the art to better understand and implement the technical solution of the present invention, the technical solution of the present invention will be clearly and elaborately described below in conjunction with Figures 1 to 25 , etc.

[0049] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings. It is 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 operated in a specific orientation, and thus should not be construed as a limitation to the present invention.

[0050] In addition, it should be further noted that in the description of the embodiments of the present invention, unless otherwise specified, " / " means "or". For example, A / B may mean A or B. The "and / or" in the text only describes the association relationship of the associated objects, indicating that there can be three relationships. For example, A and / or B may mean: A exists alone, A and B exist simultaneously, and B exists alone. In addition, in the description of the embodiments of the present invention, "a plurality" means two or more than two.

[0051] The following terms "first", "second", "third", "fourth" are only used for descriptive purposes and should not be construed as implying or indicating relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first", "second", "third", "fourth" may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise specified, the meaning of "a plurality" is two or more than two.

[0052] The present invention provides a test piece structure for a gas turbine blade with an easily replaceable cooling element and adjustable cold air, as Figure 1 shown. Its main structure includes a blade platform, a blade, and a connecting part 19. Specifically, the blade and the connecting part 19 are respectively arranged on both sides of the blade platform and are detachably connected to the blade platform. Airflow channels are respectively arranged on the connecting part 19, the blade platform, and the blade, and the airflow channels are connected in sequence.

[0053] Specifically, the blade includes a blade body 8, a leading-edge air film orifice plate 6, a trailing-edge split slot plate 7, and a blade cover plate. Among them, 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 orifice plate 6 and the trailing-edge split slot plate 7 are respectively arranged on the front and back sides of the blade body 8 and are detachably connected to the blade platform. The blade cover plate includes a cover plate main body 5 and a leading-edge tip cooling orifice plate 1, a mid-chord third row channel tip cooling orifice plate 2, a mid-chord turning area tip cooling orifice plate 3, and a trailing-edge tip cooling orifice plate 4 that are arranged in sequence and are all detachably connected to the cover plate main body 5.

[0054] Further, at least one first adjustment structure is arranged at the air flow channel inlet on the blade body 8. The first adjustment structure is used to adjust the flow area and pre-rotation degree. Air flow channel outlets are arranged on the leading-edge tip cooling orifice plate 1, the mid-chord third row channel tip cooling orifice plate 2, the mid-chord turning area tip cooling orifice plate 3, the trailing-edge tip cooling orifice plate 4, the leading-edge air film orifice plate 6, and the trailing-edge split slot plate 7. A second adjustment structure is arranged on the air flow channel outlet. The second adjustment structure is used to adjust the flow area.

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

[0056] As a further refinement scheme of this embodiment, specifically, the blade platform includes a blade upper platform 9 and a blade lower platform 10. The blade upper platform 9 and the blade lower platform 10 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 the cooling gas. The total air distribution chamber 17 is respectively communicated with the air flow channels on the blade and the connecting part 19.

[0057] The blade upper platform 9 is fixed to the blade body 8, and the leading-edge air film orifice plate 6 and the trailing-edge split slot plate 7 are respectively fixed to the blade body 8. The blade lower platform 10 is fixedly connected to the connecting part 19. The above connection methods are all realized by countersunk head screws, which are convenient for disassembly and assembly.

[0058] The structure of the blade cover plate is as Figure 2 shown. The cover plate main body 5 is fixedly connected to the blade body 8 by bolts. The structure of the separate cover plate main body 5 is as Figure 3As shown, four card mounting hole structures are provided thereon, and a leading edge tip cooling hole plate 1, a mid-chord third row passage tip cooling hole plate 2, a mid-chord turning region tip cooling hole plate 3, and a trailing edge tip cooling hole plate 4 are respectively and correspondingly arranged in the four card mounting hole structures. The structure of the assembled blade cover plate is as Figure 4 shown.

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

[0060] As Figure 2 shown, it shows the leading edge tip cooling hole upper blade cover plate 1-G1, the leading edge tip cooling hole lower spoiler plate 1-G2, the mid-chord third row passage tip cooling hole upper blade cover plate 2-G1, the mid-chord third row passage tip cooling hole lower spoiler plate 2-G2, the mid-chord turning region upper blade cover plate 3-G1, the mid-chord turning region lower spoiler plate 3-G2, the trailing edge tip cooling hole upper blade cover plate 4-G1, and the trailing edge tip cooling hole lower spoiler plate 4-G2.

[0061] Taking the leading edge tip cooling hole plate 1 as an example, the leading edge tip cooling hole plate 1 includes a leading edge tip cooling hole upper blade cover plate 1-G1 and a leading edge tip cooling hole lower spoiler plate 1-G2 that are detachably connected, and a plurality of first spoiler structures are provided on the leading edge tip cooling hole lower spoiler plate 1-G2.

[0062] Specifically, the leading edge tip cooling hole upper blade cover plate 1-G1, the mid-chord third row passage tip cooling hole upper blade cover plate 2-G1, the mid-chord turning region upper blade cover plate 3-G1, and the trailing edge tip cooling hole upper blade cover plate 4-G1 are fixedly connected to the cover plate main body 5 by bolts.

[0063] The leading edge tip cooling hole lower spoiler plate 1-G2, the mid-chord third row passage tip cooling hole lower spoiler plate 2-G2, the mid-chord turning region lower spoiler plate 3-G2, and the trailing edge tip cooling hole lower spoiler plate 4-G2 are fixedly connected to the leading edge tip cooling hole upper blade cover plate 1-G1, the mid-chord third row passage tip cooling hole upper blade cover plate 2-G1, the mid-chord turning region upper blade cover plate 3-G1, and the trailing edge tip cooling hole upper blade cover plate 4-G1 by bolts.

[0064] The turbulator structures of the lower spoiler for the leading-edge blade tip cooling holes 1-R1, the turbulator structures of the lower spoiler for the third row of mid-chord channel blade tip cooling holes 2-R1, the turbulator structures of the lower spoiler for the mid-chord turning area 3-R1, and the turbulator structures of the lower spoiler for the trailing-edge blade tip cooling holes 4-R1 are shown in spherical sockets and can be replaced with heat transfer enhancement structures such as ribs, spherical protrusions, and fins. In the experiment, by simply replacing the above cooling components, the shape and size of the cooling holes in different areas of the blade tip of the test piece and the change of the turbulator structure can be realized.

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

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

[0067] By adjusting the voltage applied to the high-temperature resistant soft pressure-sensitive sheet Y1 for the blade tip cooling hole through the control component, the thickness of the high-temperature resistant soft pressure-sensitive layer YM1 for the blade tip cooling hole is controlled, thereby adjusting the gas flow area, and further controlling the opening degree of the blade tip film holes. Here, the flow rate is changed by changing the gas flow area to facilitate controlling the gas discharge flow rate.

[0068] The second adjustment structures are provided on the upper blade cover plate 2-G1 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, and the upper blade cover plate 4-G1 of the trailing-edge blade tip cooling holes. The second adjustment structure is used to adjust the flow area of the air flow channel outlet, and the air outlet volume of the four blade tip air holes can be respectively regulated, so as to realize the outflow ratio of the blade tip cooling holes in different areas.

[0069] The blade structure is as Figure 6 and Figure 7As shown, the blade body 8 is a hollow structure, and 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 14S, a mid-chord first row cooling channel pressure surface spoiler 14P, a trailing-edge cooling channel suction surface spoiler 15S, and a trailing-edge cooling channel pressure surface spoiler 15P are detachably connected to the inner wall of the blade body 8.

[0070] Specifically, as Figure 6 shown, there is one spoiler on each of the suction surface side and the pressure surface side of the leading-edge cooling channel, namely the leading-edge cooling channel suction surface spoiler 11S and the leading-edge cooling channel pressure surface spoiler 11P, which are respectively connected to the blade body 8 through a slot connection structure. Taking the mid-chord cooling channel as an example with a three-row cooling channel structure, there are three spoilers on each of the suction surface side and the pressure surface side, namely 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, and the mid-chord first row cooling channel pressure surface spoiler 14P. There is one spoiler on each of the suction surface side and the pressure surface side of the trailing-edge cooling channel, namely the trailing-edge cooling channel suction surface spoiler 15S and the trailing-edge cooling channel pressure surface spoiler 15P.

[0071] The structure of the leading-edge cooling channel suction surface spoiler 11S is as Figure 8 shown, and the structure of the leading-edge cooling channel pressure surface spoiler 11P is as Figure 9 shown. Among them, the connection methods of 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, the trailing-edge cooling channel pressure surface spoiler 15P, the leading-edge air film hole plate 6, and the trailing-edge split slot plate 7 with the blade body 8 all adopt a slot structure, as Figure 14 shown. As Figures 8 to 13As shown, the spoiler structures of the suction surface of the leading-edge cooling channel 11S-R2, the spoiler structures of the pressure surface of the leading-edge cooling channel 11P-R2, the spoiler structures of the suction surface of the third cooling channel in the mid-chord 12S-R2, the spoiler structures of the pressure surface of the third cooling channel in the mid-chord 12P-R2, the spoiler structures of the suction surface of the second cooling channel in the mid-chord 13S-R2, the spoiler structures of the pressure surface of the second cooling channel in the mid-chord 13P-R2, the spoiler structures of the suction surface of the first cooling channel in the mid-chord 14S-R2, and the spoiler structures of the pressure surface of the first cooling channel in the mid-chord 14P-R2 are schematically shown by fins, and their specific structures can be replaced with various heat transfer enhancement structures such as rib columns, spherical protrusions, and spherical sockets according to requirements. The spoiler structures of the suction surface of the trailing-edge cooling channel 15S-R3 and the spoiler structures of the pressure surface of the trailing-edge cooling channel 15P-R3 are schematically shown by rib columns, and their specific structures can also be replaced with various heat transfer enhancement structures such as fins, spherical protrusions, and fins according to requirements.

[0072] As Figures 15 to 18 shown, the leading-edge film hole plate 6 and the trailing-edge split slot plate 7 are provided with a number of leading-edge film holes 6-Q1 and trailing-edge split slots 7-Q1, and the leading-edge film hole plate 6 and the trailing-edge split slot plate 7 with different numbers, shapes, and arrangement forms can be flexibly replaced according to research needs.

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

[0074] Specifically, the cross-sectional shape of the air inlet channel can be rectangular, circular, or a shape similar to the internal cooling channel. The figure shows a schematic of a rectangular cooling channel. The blade body 8 and the upper platform 9 of the blade are fixedly connected by bolts. The leading-edge film hole plate 6 and the trailing-edge split slot plate 7 are fixedly connected to the upper platform 9 of the blade by bolts.

[0075] The lower platform 10 of the blade is as Figure 21 and Figure 22As shown in the figure. Inside the lower platform 10 of the blade, there is a lower air distribution chamber 17B. The bottom of the lower air distribution chamber 17B is fixedly connected to the connecting part 19 by bolts. Inside the connecting part 19, there is a cold air delivery channel 18. The connecting part 19 can be flexibly designed and adaptively processed according to the actual requirements of different test systems for the shape of the air supply channel, the shape of the connection port, the rotation radius, etc., 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 fixedly connected 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 for buffering and storing the cooling gas delivered from the cold air delivery channel 18. A sealing groove D1 is opened 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 the cold air in the total air distribution chamber 17 from leaking.

[0076] Figure 23 It is a cross-sectional structure of the upper platform 9 of the blade along the radial direction. First adjustment structures are arranged on the channel wall surfaces 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-rotation degree of the air flow, and can also adjust the flow channel shapes 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 too much. Specifically, the first adjustment structure includes a high-temperature resistant soft pressure-sensitive layer YM2 and several high-temperature resistant soft pressure-sensitive sheets Y2 of the blade upper platform air inlet hole arranged on the air flow channel. The several high-temperature resistant soft pressure-sensitive sheets Y2 of the blade upper platform are evenly arranged between the air flow channel and the high-temperature resistant soft pressure-sensitive layer YM2 of the blade upper platform air inlet hole. The high-temperature resistant soft pressure-sensitive sheet Y2 of the blade upper platform is connected to an external control component. The control component is used to adjust the voltage of the high-temperature resistant soft pressure-sensitive sheet Y2 of the blade upper platform air inlet hole, and can independently control the high-temperature resistant soft pressure-sensitive sheet Y2 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, and then control the high-temperature resistant soft pressure-sensitive layer YM2 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, so as to independently regulate the flow rate of the cold air entering 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, and 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 16B of the mid-chord cooling channel and the trailing edge cooling channel air inlet hole 16C are similar to the high-temperature resistant soft pressure-sensitive film 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 hole 16A, the mid-chord cooling channel air inlet hole 16B and the trailing edge cooling channel air inlet hole 16C, the channel walls around each air inlet are also arranged with a blade upper platform air inlet hole high temperature resistant soft pressure-sensitive layer YM2 and a number of blade upper platform air inlet hole high temperature resistant soft pressure-sensitive sheets Y2. By applying different voltages to the blade upper platform air inlet hole 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 hole 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 a specific part. 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 air inlet 16A, the mid-chord cooling channel air inlet 16B, and the trailing edge cooling channel air inlet 16C, the airflow incidence adjustment in any direction and angle can be achieved, thereby achieving the cold air pre-swirl adjustment at the entrances of different internal cooling channels, and then studying the influence of the cold air inlet pre-swirl on the heat transfer. In particular, based on the test results, when it is known that the temperature at a certain cooling channel position is high and needs to be focused on cooling, the voltage of the high-temperature resistant soft pressure-sensitive sheet Y2 of the air inlet of the blade platform can be adjusted to change the pre-swirl degree of the gas before entering the cooling channel, so as to achieve directional enhanced cooling in the area where heat transfer is deteriorated.

[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 condition;

[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 split slot plate 7 into the blade body 8 and fasten them to the blade upper platform 9 by bolts;

[0085] Step 4: Insert the selected 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, and trailing-edge cooling channel pressure surface spoiler 15P into the corresponding positions of the blade body 8 through the provided slot structures respectively;

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

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

[0088] Step 7: Fasten the cover plate body 5 to the leading-edge film hole plate 6, trailing-edge split slot plate 7, and blade body 8 by bolts respectively;

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

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

[0091] (2) Cooling element replacement method

[0092] ① For the leading-edge tip cooling hole upper layer blade cover plate 1-G1 / mid-chord third row channel tip cooling hole upper layer blade cover plate 2-G1 / mid-chord turning area upper layer blade cover plate 3-G1 / trailing-edge tip cooling hole upper layer blade cover plate 4-G1, the replacement methods of the above cooling elements are the same. The following takes the leading-edge tip cooling hole upper layer blade cover plate 1-G1 as an example for illustration:

[0093] Step 1: Remove the tip cooling hole plate bolts and take off the leading-edge tip cooling hole plate 1;

[0094] Step 2: Remove the bolts of the lower spoiler, and take off the lower spoiler 1-G2 of the leading edge blade tip cooling holes;

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

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

[0097] ②Lower spoiler 1-G2 of the leading edge blade tip cooling holes / lower spoiler 2-G2 of the third row of channel blade tips in the middle chord / lower spoiler 3-G2 of the turning area in the middle chord / lower spoiler 4-G2 of the trailing edge blade tip cooling holes. The replacement methods of the above cooling components are the same. The following takes the lower spoiler 1-G2 of the leading edge blade tip cooling holes as an example for description:

[0098] Step 1: Remove the bolts of the blade tip cooling hole plate, and take off the blade tip cooling hole plate 1;

[0099] Step 2: Remove the bolts of the lower spoiler, and take off the lower spoiler 1-G2 of the leading edge blade tip cooling holes;

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

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

[0102] ③Leading edge film hole plate 6 / trailing edge split slot plate 7. The replacement methods of the above cooling components are the same. The following takes the leading edge film hole plate 6 as an example for description:

[0103] Step 1: Remove the bolts of the blade cover plate, and take off the blade tip blade cover plate;

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

[0105] Step 3: Remove the bolts in the hole plate, and take off the leading edge film hole 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 upper part;

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

[0108] Step 6: Fasten and connect the lower blade platform 10 with the upper blade platform 9 with bolts;

[0109] Step 7: Fasten and connect the blade cover plate at the blade tip with the selected leading-edge film hole plate 6, trailing-edge split 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 / Third row of cooling channels in the mid-chord suction surface spoiler 12S / Third row of cooling channels in the mid-chord pressure surface spoiler 12P / Second row of cooling channels in the mid-chord suction surface spoiler 13S / Second row of cooling channels in the mid-chord pressure surface spoiler 13P / First row of cooling channels in the mid-chord suction surface spoiler 14S / First row of cooling channels in the mid-chord pressure surface spoiler 14P / Trailing-edge cooling channel suction surface spoiler 15S / Trailing-edge cooling channel pressure surface spoiler 15P. The replacement methods of the above cooling components are the same. The following takes the leading-edge cooling channel suction surface spoiler 11S as an example for illustration:

[0111] Step 1: Remove the blade cover plate bolts and take off the blade cover plate at the blade tip.

[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 cover plate at the blade tip on the leading-edge film hole plate 6, trailing-edge split slot plate 7, and blade body 8 through the blade cover plate bolts.

[0115] ⑤ Connection part 19:

[0116] Step 1: Remove the bolts in the blade platform and take off the lower blade platform 10 and the connected connection part 19.

[0117] Step 2: Remove the bolts in the air distribution chamber and take off the connection part 19.

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

[0119] Step 4: Assemble the assembled lower blade platform 10 and connection part 19 on the upper blade platform 9 by bolts.

[0120] The flow process of the cold air is as Figure 25As shown in the figure. The cold air enters the main air distribution chamber 17 through the cold air delivery channel 18 formed inside the connecting part 19 from the cold air inlet. After stabilizing the air flow in the main air distribution chamber 17, it flows into the corresponding internal cooling channels through 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 respectively. Among them, by adjusting the high-temperature resistant soft pressure-sensitive sheet Y2 on the upper platform air inlet hole of the blade, the thickness of the high-temperature resistant soft pressure-sensitive layer YM2 on the upper platform air inlet hole of the blade is changed, so as to adjust the air intake flow rate and pre-whirl degree of the above three air inlet holes.

[0121] For leading-edge cooling, the cooling gas flows into the leading-edge cooling channel through the leading-edge cooling channel air inlet hole 16A, and exchanges heat with the leading-edge cooling channel suction surface spoiler 11S and the leading-edge cooling channel pressure surface spoiler 11P. A 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. Another part of the cold air impacts the lower spoiler 1-G2 of the leading-edge tip cooling hole and exchanges heat, and finally is discharged through the leading-edge tip cooling hole formed 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 air inlet hole 16B, and exchanges heat with the mid-chord first row of cooling channel suction surface spoiler 14S and the mid-chord first row of cooling channel pressure surface spoiler 14P. Then it impacts the lower spoiler 3-G2 in the mid-chord turning area and exchanges heat. A part of the cold air is discharged through the mid-chord turning area tip cooling hole formed on the mid-chord turning area tip cooling hole plate 3. Another part of the cold air flows into the second row of mid-chord cooling channels after passing through the first turning area, and exchanges heat with the mid-chord second row of cooling channel suction surface spoiler 13S and the mid-chord second row of cooling channel pressure surface spoiler 13P. Then it flows into the third row of mid-chord cooling channels through the second turning area, and exchanges heat with the mid-chord third row of cooling channel suction surface spoiler 12S and the mid-chord third row of cooling channel pressure surface spoiler 12P. Then it impacts the lower spoiler 2-G2 of the mid-chord third row of channel tip cooling holes and exchanges heat, and finally is discharged through the mid-chord third row of channel tip cooling holes formed on the mid-chord third row of channel tip cooling hole plate 2;

[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. A part of the cold air flows out through the trailing-edge split slot 7-Q1 and covers the outer surface of the blade to form a cooling air film. Another part of the cold air impacts the lower spoiler 4-G2 of the trailing-edge tip cooling hole and exchanges heat, and finally is discharged through the trailing-edge tip cooling hole formed on the trailing-edge tip cooling hole plate 4.

[0124] Compared with the prior art, the test piece structure of the gas turbine blade with easy-to-replace cooling elements and adjustable cold air of the present invention has the following advantages:

[0125] 1. The present invention not only has a scaled blade profile, but also has complete internal and external cooling structures similar to real blades, such as leading-edge film cooling, mid-chord channel cooling, trailing-edge split cooling, and tip cooling, etc., which can simulate the interaction between different regions and different forms of cooling during 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 elements of gas turbine blades. For the leading-edge cooling channel, it has a modular structure with replaceable heat transfer wall surface enhanced heat transfer structures for internal cooling channels, replaceable leading-edge tip cooling holes, replaceable leading-edge tip heat transfer wall surface enhanced heat transfer structures, and replaceable leading-edge film holes; taking the mid-chord cooling channel with three rows of channels as an example, it has a modular structure with replaceable heat transfer wall surface enhanced heat transfer structures for three rows of internal cooling channels, replaceable tip cooling holes in the turning area, replaceable tip heat transfer wall surface enhanced heat transfer structures in the turning area, replaceable tip cooling holes in the third row of channels, and replaceable tip heat transfer wall surface enhanced heat transfer structures in the third row of channels; for the trailing-edge cooling channel, it has a modular structure with replaceable heat transfer wall surface enhanced heat transfer structures for internal cooling channels, replaceable trailing-edge tip cooling holes, replaceable trailing-edge tip heat transfer wall surface enhanced heat transfer structures, and replaceable trailing-edge split slots.

[0127] The structure provided by the present invention only needs to simply replace the corresponding cooling elements during the test to quickly change the cooling scheme of the entire turbine blade, without manufacturing the entire complex blade. It can not only test the optimal cooling structure for different regions of cooling, but also couple all cooling methods of the blade. Through low-cost and rapid tests, a large number of different blade structures and working conditions can be tested to obtain a blade cooling performance test database, thereby obtaining the optimal combined blade cooling design scheme, greatly reducing the blade R & D cost and improving the R & D efficiency, and providing strong support for the development of efficient and low-drag gas turbine blade cooling technology.

[0128] 3. The present invention can achieve precise zoning control of the cold air outflow cross-sectional shape, flow rate, and pre-rotation degree. By adjusting the first adjustment structure, the control of the flow area and pre-rotation degree can be realized, thereby precisely regulating the cold air ratio in multiple regions. By adjusting the second adjustment structure, the control of the flow area can be achieved to adapt to the adjustment of the cooling demand under variable operating conditions. This structure has the following advantages: (1) It can adjust the cold air flow rates flowing into the inlets of different internal cooling channels of the blade and flowing out of the cooling holes in different regions at the blade tip, realizing precise adjustment of the cold air ratio among multiple regions; (2) It can adjust the direction and angle of the cold air flowing into the inlets of different internal cooling channels, realizing independent adjustment of the pre-rotation degrees of multiple inlet cold air streams. Therefore, the present invention has a unique multi-region cold air adjustable function, which can provide a higher optimization design dimension for the research and development of high-temperature blades of gas turbines, has strong practicability, and is worthy of promotion.

[0129] It can be understood that the present invention is described through some embodiments. Those skilled in the art know that without departing from the spirit and scope of the present invention, various changes or equivalent replacements can be made to these features and embodiments.

[0130] In addition, under the teaching of the present invention, these features and embodiments can be modified to adapt to specific situations and materials without departing from the spirit and scope of the present invention. Therefore, the present invention is not limited by the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of the present invention belong to the scope protected by the present invention.

Claims

1. The test piece structure of a gas turbine blade with an easily replaceable cooling element and adjustable cold air, characterized in that It includes a blade platform, a blade and a connecting part (19). The blade and the connecting part (19) are respectively arranged on both sides of the blade platform and are detachably connected to the blade platform. Airflow channels are respectively arranged on the connecting part (19), the blade platform and the blade, and the airflow channels are communicated in sequence; The blade includes a blade body (8), a leading-edge film cooling 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). The other end of the blade body (8) is detachably connected to the blade platform. The leading-edge film cooling 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 tip cooling hole plate (1), a third row of channel tip cooling hole plate (2) in the middle chord, a tip cooling hole plate (3) in the turning area of the middle chord and a trailing-edge 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 adjusting structure is arranged at the airflow channel outlet on the blade platform. The first adjusting structure is used to adjust the flow area and the pre-whirl degree. Airflow channel outlets are arranged on the leading-edge tip cooling hole plate (1), the third row of channel tip cooling hole plate (2) in the middle chord, the tip cooling hole plate (3) in the turning area of the middle chord, the trailing-edge tip cooling hole plate (4), the leading-edge film cooling hole plate (6) and the trailing-edge split slot plate (7). A second adjusting structure is arranged at the airflow channel outlet on the blade body. The second adjusting structure is used to adjust the flow area.

2. The structure of the turbine blade test piece with easily replaceable cooling elements and adjustable cold air according to claim 1, characterized in that, The first adjusting structure and the second adjusting structure have the same structure, and both include 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 at the airflow channel inlet / airflow channel outlet. The 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. 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 structure of the test piece of the gas turbine blade with easy replacement of the cooling element and adjustable cold air according to claim 1, characterized in that, The leading-edge tip cooling hole plate (1), the third row of channel tip cooling hole plate (2) in the middle chord, the tip cooling hole plate (3) in the turning area of the middle chord and the trailing-edge tip cooling hole plate (4) have the same structure, and all include a first fixing plate and a first spoiler. The first fixing plate and the first spoiler are detachably connected. The first spoiler includes a first plate body and a plurality of first spoiler structures arranged on the first plate body.

4. The structure of the gas turbine blade test piece with easily replaceable cooling elements and adjustable cold air according to claim 3, characterized in that, The blade body (8) is of a hollow structure, and a suction surface spoiler (11S) of the leading edge cooling channel, a pressure surface spoiler (11P) of the leading edge cooling channel, a suction surface spoiler (12S) of the third row of the mid-chord cooling channel, a pressure surface spoiler (12P) of the third row of the mid-chord cooling channel, a suction surface spoiler (13S) of the second row of the mid-chord cooling channel, a pressure surface spoiler (13P) of the second row of the mid-chord cooling channel, a suction surface spoiler (14S) of the first row of the mid-chord cooling channel, a pressure surface spoiler (14P) of the first row of the mid-chord cooling channel, a suction surface spoiler (15S) of the trailing edge cooling channel, and a pressure surface spoiler (15P) of the trailing edge cooling channel are detachably connected to the inner wall of the blade body (8).

5. The structure of the test piece of the gas turbine blade with easy replacement of the cooling element and adjustable cold air according to claim 4, characterized in that, The suction surface spoiler (11S) of the leading edge cooling channel, the pressure surface spoiler (11P) of the leading edge cooling channel, the suction surface spoiler (12S) of the third row of the mid-chord cooling channel, the pressure surface spoiler (12P) of the third row of the mid-chord cooling channel, the suction surface spoiler (13S) of the second row of the mid-chord cooling channel, the pressure surface spoiler (13P) of the second row of the mid-chord cooling channel, the suction surface spoiler (14S) of the first row of the mid-chord cooling channel, the pressure surface spoiler (14P) of the first row of the mid-chord cooling channel, the suction surface spoiler (15S) of the trailing edge cooling channel, and the pressure surface spoiler (15P) of the trailing edge cooling channel have the same structure, and each includes a second fixing plate and a plurality of second spoiler structures arranged on the second fixing plate.

6. The structure of the gas turbine blade test piece with easily replaceable cooling elements and adjustable cold air according to claim 5, characterized in that, The first spoiler structure and the second spoiler structure are one of a ball socket, a fin, a ball protrusion, and a fin.

7. The structure of the test piece of the gas turbine blade with easy replacement of the cooling element and adjustable cold air according to claim 1, characterized in that, The blade platform includes a blade upper platform (9) and a blade lower platform (10) that are detachably connected. A total air distribution chamber (17) is formed between the blade upper platform (9) and the blade lower platform (10). The total air distribution chamber (17) is used for buffering and storing cooling gas, and the total air distribution chamber (17) is communicated with the air flow channels on the blade and the connecting part (19) respectively.

8. The structure of the test piece of the gas turbine blade with easy replacement of the cooling element and adjustable cold air according to claim 7, characterized in that, A sealing structure is arranged between the blade upper platform (9) and the blade lower platform (10).

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