Gas turbine blade cooling effect test device

Abstract

The present invention provides a gas turbine blade cooling effectiveness test device. The gas turbine blade cooling effectiveness test device comprises: a combustion chamber assembly, a turbine cylinder, a mounting frame assembly, and a cooling assembly. The combustion chamber assembly comprises a combustion chamber cylinder and a combustion chamber. The combustion chamber cylinder comprises a first chamber and an air inlet. The combustion chamber comprises an air inlet, a fuel inlet, and a gas outlet. The gas outlet is located within the first chamber, and the air inlet connects the first chamber with the combustion chamber. The turbine cylinder comprises a second chamber and an exhaust port. The turbine cylinder is connected to the combustion chamber cylinder, and the second chamber is connected to the first chamber. The mounting frame assembly comprises a mounting frame and a cooling air pipeline. The mounting frame is used to mount turbine blades. The cooling air pipeline is used to pass cooling air into the turbine blades. The mounting frame is mounted on the combustion chamber. The cooling assembly is used to cool the combustion gas. The gas turbine blade cooling effectiveness test device of the present invention can simulate full-temperature and full-pressure operating conditions and also has the advantage of high reusability.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a gas turbine blade cooling effect test device. Background Art

[0002] During the development of gas turbine blades, cooling effect tests are conducted on the turbine blades. In related technologies, volute dry-burning and water-cooling cooling effect test pieces are usually used for cooling effect tests. The water-cooled cooling effect test piece requires different test sections to be designed according to the blade shape during the test, resulting in a low reuse rate of the test structure. The volute dry-burning cooling effect test piece uses a water-cooling jacket for cooling, which causes the wall temperature of the combustion chamber outlet section to be too low, affecting the gas temperature distribution and making it impossible to simulate full-temperature and full-pressure operating conditions. Summary of the Invention

[0003] The present invention aims to solve one of the technical problems in the related art at least to a certain extent.

[0004] To this end, an embodiment of the present invention provides a gas turbine blade cooling effect test device, which can simulate full-temperature and full-pressure working conditions and has the advantage of high reuse rate.

[0005] The gas turbine blade cooling effect test device of the embodiment of the present invention comprises: a combustion chamber assembly, the combustion chamber assembly comprises a combustion chamber cylinder and a combustion chamber, the combustion chamber cylinder comprises a first cavity and an air inlet, the air inlet connects the first cavity with the outside, the combustion chamber is detachably connected to the combustion chamber cylinder, at least a portion of the combustion chamber is placed in the first cavity, the combustion chamber comprises an air inlet, a fuel inlet and a gas outlet, the fuel inlet is arranged at one end of the combustion chamber along the length direction of the combustion chamber, the gas outlet is arranged at the other end of the combustion chamber along the length direction of the combustion chamber, the gas outlet is located in the first cavity, the air inlet connects the first cavity and the combustion chamber; a turbine cylinder, the turbine cylinder comprises a second cavity and an exhaust port, the turbine cylinder is connected to the combustion chamber cylinder and the second cavity It is connected to the first chamber, and the exhaust port is connected to the second chamber and the outside world; a mounting frame assembly, the mounting frame assembly includes a mounting frame and a cooling air pipeline, the mounting frame includes a mounting area, the mounting area is used to install the turbine blades, and the cooling air pipeline is used to introduce cooling air into the turbine blades, the mounting frame is detachably mounted at the other end of the combustion chamber, and the mounting frame is sealed with the combustion chamber cylinder, the mounting area is connected to the second chamber and the gas outlet, so that the gas discharged from the gas outlet passes through the mounting area into the second chamber; and a cooling assembly, at least a part of the cooling assembly is arranged in the second chamber, the cooling assembly includes a spray part, the spray part is arranged in the second chamber, and the spray part is arranged adjacent to the mounting frame to cool the gas passing through the mounting area.

[0006] The gas turbine blade cooling effect test device of the embodiment of the present invention cools the combustion gas generated in the combustion chamber through a cooling component, which can effectively protect the test device and ensure that the test device can simulate full temperature and full pressure working conditions.

[0007] In addition, the gas turbine blade cooling effect test device of the embodiment of the present invention can also replace the corresponding installation frame according to blades of different sizes without replacing other components. Therefore, other components of the test device can be reused, thereby improving the reuse rate.

[0008] Therefore, the gas turbine blade cooling effect test device of the embodiment of the present invention can simulate full-temperature and full-pressure working conditions and also has the advantage of high reuse rate.

[0009] In some embodiments, the cooling component includes an annular bushing, which is arranged in the second chamber, and a first cooling zone is formed between the outer wall surface of the annular bushing and the inner wall surface of the second chamber. The annular bushing includes an annular shell, and the annular shell encloses a second cooling zone. The second cooling zone is connected to the installation area and the exhaust port, so that the gas discharged from the gas outlet passes through the installation area and enters the second cooling zone. The spray part is arranged in the second cooling zone.

[0010] In some embodiments, the annular sleeve includes a main section and an extension section, the main section is adjacent to the mounting frame, the extension section passes through the exhaust port, an annular gap is formed between the outer wall surface of the extension section and the inner wall surface of the exhaust port, the annular gap connects the first cooling zone and the outside world, and the extension section is used to discharge the gas in the second cooling zone.

[0011] In some embodiments, the main body section includes a first section and a second section, the first section is adjacent to the first chamber, and the radial dimension of the second section gradually decreases in the direction in which the gas is discharged.

[0012] In some embodiments, a baffle is further included. The baffle is disposed in the second cooling zone, and the baffle and the spray element are disposed opposite to each other in the radial direction of the annular sleeve.

[0013] In some embodiments, a concave guide surface is provided on a side of the deflector adjacent to the spray element.

[0014] In some embodiments, the guide surface is a concave arc surface.

[0015] In some embodiments, the guide surface includes a first guide surface, a second guide surface, and a third guide surface arranged in sequence along the length direction of the combustion chamber, the first guide surface is adjacent to the mounting frame, the extension direction of the normal of the second guide surface is perpendicular to the length direction of the combustion chamber, and the extension direction of the normal of the first guide surface and the third guide surface forms an acute angle with the length direction of the combustion chamber.

[0016] In some embodiments, the baffle has a water cooling cavity, and the baffle is provided with a water inlet and a water outlet, and the water inlet and the water outlet are both connected to the water cooling cavity so that cooling liquid can be introduced into the water cooling cavity through the water inlet.

[0017] In some embodiments, the deflector includes a main body, a first bending portion and a second bending portion, the main body is located between the first bending portion and the second bending portion, the first bending portion is arranged adjacent to the mounting frame, and the angle between at least one of the first bending portion and the second bending portion and the main body is greater than 90 degrees and less than 180 degrees. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 The figure is a schematic structural diagram of a gas turbine blade cooling effect test device according to an embodiment of the present invention.

[0019] Figure 2 It is a structural schematic diagram of a gas turbine blade cooling effect test device according to another embodiment of the present invention.

[0020] Figure 3 The figure is a schematic structural diagram of a baffle of a gas turbine blade cooling effect test device according to an embodiment of the present invention.

[0021] Figure 4 The figure is a schematic structural diagram of a baffle of a gas turbine blade cooling effect test device according to an embodiment of the present invention.

[0022] Figure 5 The present invention is a schematic structural diagram of an annular sleeve of a gas turbine blade cooling effect test device according to an embodiment of the present invention.

[0023] Reference numerals:

[0024] Turbine blades 100;

[0025] Combustion chamber assembly 1; combustion chamber cylinder 11; first cavity 111; air inlet 112; combustion chamber 12; fuel inlet 121;

[0026] Turbine cylinder 2; first cooling zone 211; exhaust port 22;

[0027] Mounting frame assembly 3; mounting frame 31; mounting area 311;

[0028] Spraying element 41 ; annular bushing 42 ; main body section 421 ; first section 4211 ; second section 4212 ; extended section 422 ; second cooling zone 423 ; baffle 43 ; guide surface 431 ; first guide surface 4311 ; second guide surface 4312 ; third guide surface 4313 . DETAILED DESCRIPTION

[0029] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0030] like Figure 1-Figure 5 As shown, the cooling effect test device for a gas turbine blade 100 according to an embodiment of the present invention comprises: a combustion chamber assembly 1, a turbine cylinder 2, a mounting frame 31 assembly 3 and a cooling assembly.

[0031] The combustion chamber assembly 1 includes a combustion chamber cylinder 11 and a combustion chamber 12. The combustion chamber cylinder 11 includes a first chamber 111 and an air inlet 112. The air inlet 112 connects the first chamber 111 with the outside. The combustion chamber 12 is detachably connected to the combustion chamber cylinder 11. At least part of the combustion chamber 12 is placed in the first chamber 111. The combustion chamber 12 includes an air inlet (not shown in the figure), a fuel inlet 121 and a gas outlet (not shown in the figure). The fuel inlet 121 is provided in the combustion chamber 12 along the length direction of the combustion chamber 12 (such as Figure 1 The gas outlet is provided at one end of the combustion chamber 12 along the other end of the length direction of the combustion chamber 12, the gas outlet is located in the first chamber 111, and the air inlet connects the first chamber 111 and the combustion chamber 12.

[0032] Specifically, if Figure 1 As shown, the fuel inlet 121 is located at the right end of the combustion chamber 12, and the gas outlet is located at the left end of the combustion chamber 12. Air within the first chamber 111 can enter the combustion chamber 12 through the air inlet, thereby providing air for the combustion chamber 12. Furthermore, the air entering through the air inlet can also be used to cool the transition section of the combustion chamber 12, thereby preventing the transition section from overheating and ensuring stable operation of the combustion chamber 12.

[0033] It is understood that the combustion chamber 12 can be completely placed in the first chamber 111, or, as shown in FIG. Figure 1 or Figure 2 As shown, part of the combustion chamber 12 is placed in the first chamber 111, and the other part of the combustion chamber 12 is placed outside the combustion chamber cylinder 11. The combustion chamber 12 is detachably connected to the combustion chamber cylinder 11 to facilitate the installation of other components on the combustion chamber 12.

[0034] The turbine cylinder 2 includes a second chamber and an exhaust port 22. The turbine cylinder 2 is connected to the combustion chamber cylinder 11 and the second chamber is connected to the first chamber 111. The exhaust port 22 connects the second chamber with the outside. Figure 1 As shown, the exhaust port 22 is provided at the left end of the turbine cylinder 2 , and the right end of the turbine cylinder 2 is connected to the left end of the combustion chamber 12 .

[0035] The mounting frame 31 assembly 3 includes the mounting frame 31 and a cooling air pipeline (not shown). The mounting frame 31 includes a mounting area 311 for mounting turbine blades 100. The cooling air pipeline is used to supply cooling air to the turbine blades 100. The mounting frame 31 is removably mounted at the other end of the combustion chamber 12 and is sealed to the combustion chamber cylinder 11. The mounting area 311 connects the second chamber with the gas outlet so that the gas discharged from the gas outlet passes through the mounting area 311 and enters the second chamber. At least a portion of the cooling assembly is disposed within the second chamber. The cooling assembly includes a spray element 41 disposed within the second chamber and adjacent to the mounting frame 31 to cool the gas passing through the mounting area 311.

[0036] Specifically, if Figure 1 As shown, the mounting frame 31 is detachably mounted on the left end of the combustion chamber 12. The outer wall of the mounting frame 31 is sealed to the combustion chamber cylinder 11 to prevent the gas discharged from the gas outlet from entering the first chamber 111. The cooling assembly can be entirely located in the second chamber, or a portion of the cooling assembly can be located in the second chamber, while the other portion of the cooling assembly can be located outside the turbine cylinder 2. The spray member 41 can be a spray ring disposed around the mounting frame 31. The spray ring includes a water inlet and multiple water spray outlets. The water inlet can be connected to an external water pump via a pipe so that cold water can be introduced into the spray member 41 when the water pump is started. The cold water in the spray ring can be sprayed out through the multiple water spray outlets to cool the gas passing through the mounting area 311.

[0037] It should be noted that the cooling air pipeline can be supplied by an external air source, that is, one end of the cooling air pipeline is connected to the cooling air channel of the turbine blade 100, and the other end of the cooling air pipeline is connected to the air source. For example, the air outlet of the external air pump is connected to the end of the cooling air pipeline. When the air pump is running, the external gas can be passed into the turbine blade 100 through the cooling air pipeline.

[0038] Optionally, a cold air inlet is provided on the mounting frame 31, connecting the first chamber 111 with one end of the cold air pipeline. That is, during testing, air is introduced into the first chamber 111 through the air inlet 112. A portion of the air in the first chamber 111 can enter the combustion chamber 12 through the air inlet, while another portion of the air in the first chamber 111 can be passed through the cold air inlet and the cold air pipeline into the interior of the turbine blade 100, thereby providing cooling for the turbine blade 100. There may also be multiple cold air inlets, with at least one cold air inlet connected to one end of the cold air pipeline, and the other cold air inlets connecting the first chamber 111 with the mounting area 311. This allows the air in the first chamber 111 to enter the mounting area 311 through the other cold air inlets during testing, cooling other components within the mounting area 311.

[0039] It can be understood that, according to the test requirements, the turbine blade 100 is installed in the installation area 311, and the turbine blade 100 has a certain deflection angle, and then the installation frame 31 is installed at the left end of the combustion chamber 12, so that the gas discharged from the gas outlet passes through the turbine blade 100 and is discharged to the second chamber at a certain angle, which is conducive to the cooling component to cool the gas passing through the turbine blade 100, thereby effectively protecting the test device and ensuring that the test device can simulate full-temperature and full-pressure working conditions.

[0040] It should be noted that multiple mounting frames 31 can be designed according to the different shapes or sizes of turbine blades 100, so that different mounting frames 31 can be installed with matching turbine blades 100. In other words, when testing blades of different shapes or sizes, only the mounting frame 31 that matches the turbine blade 100 needs to be replaced, without having to replace other components. The remaining components of the test device can be reused, thereby improving the reuse rate.

[0041] Therefore, the cooling effect test device for the gas turbine blade 100 according to the embodiment of the present invention can simulate full-temperature and full-pressure test conditions and has the advantage of high reuse rate.

[0042] In other embodiments, Figure 2 As shown, the cooling component includes an annular bushing 42, which is arranged in the second chamber. A first cooling zone 211 is formed between the outer wall surface of the annular bushing 42 and the inner wall surface of the second chamber (that is, part of the second chamber forms the first cooling zone 211). The annular bushing 42 includes an annular shell, which encloses a second cooling zone 423. The second cooling zone 423 is connected to the installation area 311 and the exhaust port 22, so that the gas discharged from the gas outlet passes through the installation area 311 and enters the second cooling zone 423. The spray element 41 is arranged in the second cooling zone 423.

[0043] It is understandable that there is a gap between the annular bushing 42 and the turbine cylinder 2 (i.e., the first cooling zone 211), which can prevent the gas from directly impacting the inner wall of the turbine cylinder 2, thereby helping to protect the internal structure of the turbine cylinder 2. Among them, cold air can also be introduced into the first cooling zone 211 to further cool the annular bushing 42. For example, an air pump is used to introduce gas into the first cooling zone 211, that is, a pipeline is used to connect the first cooling zone 211 and the air outlet of the air pump. When the air pump is working, air can be introduced into the first cooling zone 211 through the pipeline, thereby achieving cooling of the annular bushing 42. Figure 1 As shown, the right end of the annular sleeve 42 is connected to the inner wall of the turbine cylinder 2 so that the gas discharged from the gas outlet passes through the installation area 311 and enters the second cooling area 423.

[0044] In some embodiments, the annular sleeve 42 includes a main section 421 and an extension section 422. The main section 421 is adjacent to the mounting frame 31, and the extension section 422 passes through the exhaust port 22. An annular gap is formed between the outer wall surface of the extension section 422 and the inner wall surface of the exhaust port 22. The annular gap connects the first cooling zone 211 and the outside world. The extension section 422 is used to discharge the gas in the second cooling zone 423.

[0045] Specifically, if Figure 1 As shown, the main section 421 is connected to the turbine cylinder 2, and the interior space of the extended section 422 forms an outlet for exhausting the gas. In other words, the gas discharged from the gas outlet can be discharged to the outside through the installation area 311, the second cooling area 423, and the outlet of the extended section 422 in sequence. Of course, an air pump can also be used to introduce gas into the first cooling area 211 to cool the annular liner 42.

[0046] In some embodiments, the main body section 421 includes a first section 4211 and a second section 4212 . The first section 4211 is adjacent to the first chamber 111 , and the radial dimension of the second section 4212 gradually decreases in the direction of exhaust of the gas.

[0047] It is understandable that if Figure 1 and Figure 5 As shown, the first section 4211 is connected to the turbine cylinder 2, and the radial dimension of the second section 4212 gradually decreases from right to left, which can increase the flow rate of the gas. That is, since the radial dimension of the first section 4211 is larger than the radial dimension in the second section 4212 and the radial dimension of the second section 4212 gradually decreases from right to left, the flow rate of the gas in the first section 4211 is smaller than the flow rate of the second section 4212, thereby maintaining a negative pressure state in the second cooling zone 423, which is beneficial to the discharge of the gas in the second cooling zone 423.

[0048] In some embodiments, the cooling assembly further includes a baffle 43 . The baffle 43 is disposed in the second cooling zone 423 . The baffle 43 and the spray element 41 are disposed opposite to each other in the radial direction of the annular bushing 42 .

[0049] It is understandable that if Figure 1 、 Figure 3 and Figure 4 As shown, the annular sleeve 42 is located below the spray element 41, the right end of the baffle 43 can be connected to the turbine cylinder 2, and the right end of the baffle 43 can also be connected to the annular sleeve 42. The baffle 43 is used to change the exhaust direction of the gas, which is beneficial to the discharge of the gas.

[0050] In some embodiments, a concave guide surface 431 is provided on one side of the baffle 43 adjacent to the spray element 41 . That is, the guide surface 431 is formed on the upper surface of the baffle 43 .

[0051] It is understandable that if Figure 1 、 Figure 3 and Figure 4 As shown, because turbine blades 100 have a certain deflection angle, the gas passing through mounting area 311 directly impacts guide surface 431 of deflector 43. The concave guide surface 431 deflects the gas impinging on deflector 43 toward exhaust. In other words, when the gas passing through mounting area 311 impacts the concave guide surface 431, the gas flow direction changes. The concave guide surface 431 further facilitates deflection of the gas flow toward exhaust, thereby facilitating gas discharge.

[0052] Optionally, the guide surface 431 is a concave arc. In other words, the guide surface 431 can be configured differently based on the actual internal structure of the turbine cylinder 2, thereby deflecting the gas toward exhaust. Furthermore, the outer contour and installation position of the baffle 43 can be modified based on the internal structure of the turbine cylinder 2. Specifically, the upper surface of the baffle 43 forms the guide surface 431, which is used to redirect the gas flow. Other structures of the baffle 43 do not affect the gas flow. Therefore, the shape of the baffle 43 can be modified accordingly based on the internal structure of the turbine cylinder 2.

[0053] It should be noted that the outer surface of the baffle 43 is provided with a TBC coating, thereby improving the overall performance of the baffle 43. Preferably, the thickness of the TBC coating is greater than or equal to 0.2 mm and less than or equal to 3 mm.

[0054] In some embodiments, as Figure 1 、 Figure 3 and Figure 4 As shown, the guide surface 431 includes a first guide surface 4311, a second guide surface 4312 and a third guide surface 4313 which are arranged in sequence in the longitudinal direction of the combustion chamber 12. The first guide surface 4311 is adjacent to the mounting frame 31, and the normal of the second guide surface 4312 extends in a direction perpendicular to the longitudinal direction of the combustion chamber 12. The angles between the extension directions of the normals of the first guide surface 4311 and the third guide surface 4313 and the longitudinal direction of the combustion chamber 12 are acute angles.

[0055] It is understood that the second guide surface 4312 is parallel to the horizontal plane, while the first guide surface 4311 and the third guide surface 4313 are at a certain angle to the horizontal plane. During experiments, the gas passing through the mounting area 311 sequentially impacted the first guide surface 4311, the second guide surface 4312, and the third guide surface 4313. The gas deflection angle can be varied by changing the angle between the normal extension direction of the first guide surface 4311 and the third guide surface 4313 and the longitudinal direction of the combustion chamber 12, depending on the deflection angle of the turbine blade 100 (i.e., the deflection of the gas passing through the mounting area 311), thereby redirecting the gas flow toward exhaust.

[0056] In some embodiments, the baffle 43 has a water cooling cavity, and the baffle 43 is provided with a water inlet and a water outlet, both of which are connected to the water cooling cavity so that cooling liquid can be introduced into the water cooling cavity through the water inlet.

[0057] Specifically, the outline of the water-cooling chamber is roughly equal to the outline of the baffle 43, and the water inlet and outlet are spaced apart in the left and right directions so that the cold water entering the baffle 43 through the water inlet can better exchange heat with the gas, thereby further reducing the gas temperature.

[0058] It can be understood that the water inlet can be connected to the water pump through a pipe, and the water outlet can be connected to the water tank through a pipe, so that after the water pump is started, cold water is discharged into the water tank through the water inlet, water cooling chamber and drain outlet in sequence to achieve further cooling of the gas.

[0059] In some embodiments, as Figure 1 、 Figure 3 and Figure 4 As shown, the deflector 43 includes a main body, a first bending portion and a second bending portion, the main body is located between the first bending portion and the second bending portion, the first bending portion is arranged adjacent to the mounting frame 31, and the angle formed between at least one of the first bending portion and the second bending portion and the main body is greater than 90 degrees and less than 180 degrees.

[0060] Specifically, the upper surface of the first bend forms a first guide surface 4311, the upper surface of the main body forms a second guide surface 4312, and the upper surface of the second bend forms a third guide surface 4313. The profile of the baffle 43 is generally the same as the inner wall profile of the second cooling zone 423. A gap exists between the lower wall of the baffle 43 and the inner wall of the annular liner 42, facilitating heat exchange between the gas and the annular liner 42, thereby helping to reduce the gas temperature.

[0061] It can be understood that the angle formed between the first bending portion and the main body is greater than 90 degrees and less than 180 degrees, or the angle formed between the second bending portion and the main body is greater than 90 degrees and less than 180 degrees, or the angle formed between the first bending portion and the second bending portion and the main body is greater than 90 degrees and less than 180 degrees.

[0062] Preferably, if Figure 1 、 Figure 3 and Figure 4As shown, the angles formed between the first and second bends and the main body are both greater than 90 degrees and less than 180 degrees. This means that when the gas strikes the first guide surface 4311, it deflects and flows toward the second guide surface 4312. At this point, the gas flow is generally below the outlet of the extension section. When the gas strikes the third guide surface 4313, it deflects again. At this point, the gas flow direction is substantially aligned with the exhaust direction, thus further facilitating gas discharge.

[0063] It can be understood that when the fuel gas enters the turbine cylinder 2 through the mounting frame 21, it is affected by the deflection angle of the blade channel of the turbine blade 100 in the mounting frame 21, causing the fuel gas to be directed onto the deflector 43. Due to the contour of the deflector 43, the fuel gas will be directed to the exhaust port 22 of the turbine cylinder 2.

[0064] 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" and the like to indicate orientations or positional relationships based on the orientations or positional relationships 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 operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0065] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0066] In the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0067] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0068] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples without contradiction.

[0069] Although the above embodiments have been shown and described, it is understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. Changes, modifications, substitutions and variations of the above embodiments by those skilled in the art are all within the scope of protection of the present invention.

Claims

1. A gas turbine blade cooling effect test device, characterized in that: include: A combustion chamber assembly, the combustion chamber assembly comprising a combustion chamber cylinder and a combustion chamber, the combustion chamber cylinder comprising a first chamber and an air inlet, the air inlet connecting the first chamber with the outside, The combustion chamber is detachably connected to the combustion chamber cylinder, at least a portion of the combustion chamber is disposed in the first chamber, the combustion chamber comprises an air inlet, a fuel inlet, and a gas outlet, the fuel inlet being disposed at one end of the combustion chamber along the length direction of the combustion chamber, the gas outlet being disposed at the other end of the combustion chamber along the length direction of the combustion chamber, the gas outlet being located in the first chamber, and the air inlet communicating with the first chamber and the combustion chamber; a turbine cylinder, the turbine cylinder comprising a second chamber and an exhaust port, the turbine cylinder being connected to the combustion chamber cylinder and the second chamber being in communication with the first chamber, the exhaust port being in communication with the second chamber and the outside; a mounting frame assembly, the mounting frame assembly comprising a mounting frame and a cooling air pipeline, the mounting frame comprising a mounting area, the mounting area being used to mount the turbine blades, the cooling air pipeline being used to introduce cooling air into the turbine blades, the mounting frame being detachably mounted at the other end of the combustion chamber, the mounting frame being sealingly connected to the combustion chamber cylinder, the mounting area being connected between the second chamber and the gas outlet, so that gas discharged from the gas outlet passes through the mounting area and enters the second chamber; and A cooling component, at least part of which is arranged in the second chamber, and the cooling component includes a spray member, which is arranged in the second chamber and adjacent to the installation frame to cool the gas passing through the installation area.

2. The gas turbine blade cooling effect test device according to claim 1, characterized in that: The cooling component includes an annular bushing, which is arranged in the second chamber. A first cooling zone is formed between the outer wall surface of the annular bushing and the inner wall surface of the second chamber. The annular bushing includes an annular shell, which encloses a second cooling zone. The second cooling zone is connected to the installation area and the exhaust port so that the gas discharged from the gas outlet passes through the installation area and enters the second cooling zone. The spray element is arranged in the second cooling zone.

3. The gas turbine blade cooling effect test device according to claim 2, characterized in that: The annular sleeve includes a main section and an extension section, the main section is adjacent to the mounting frame, the extension section passes through the exhaust port, an annular gap is formed between the outer wall surface of the extension section and the inner wall surface of the exhaust port, the annular gap connects the first cooling zone and the outside world, and the extension section is used to discharge the gas in the second cooling zone.

4. The gas turbine blade cooling effect test device according to claim 3, characterized in that: The main body section includes a first section and a second section, the first section is adjacent to the first chamber, and the radial dimension of the second section gradually decreases in the direction in which the gas is discharged.

5. The gas turbine blade cooling effect test device according to claim 2, characterized in that: It also includes a baffle, which is arranged in the second cooling zone. The baffle and the spraying member are arranged opposite to each other in the radial direction of the annular sleeve.

6. The gas turbine blade cooling effect test device according to claim 5, characterized in that: A concave guide surface is provided on one side of the baffle adjacent to the spraying element.

7. The gas turbine blade cooling effect test device according to claim 6, characterized in that: The guide surface is a concave arc surface.

8. The gas turbine blade cooling effect test device according to claim 6, characterized in that: The guide surface includes a first guide surface, a second guide surface and a third guide surface arranged in sequence in the longitudinal direction of the combustion chamber, the first guide surface is adjacent to the mounting frame, the extension direction of the normal of the second guide surface is perpendicular to the longitudinal direction of the combustion chamber, and the angles formed between the extension directions of the normals of the first guide surface and the third guide surface and the longitudinal direction of the combustion chamber are acute angles.

9. The gas turbine blade cooling effect test device according to any one of claims 5 to 8, characterized in that: The baffle has a water cooling cavity. The baffle is provided with a water inlet and a water outlet. The water inlet and the water outlet are both connected to the water cooling cavity so that cooling liquid can be introduced into the water cooling cavity through the water inlet.

10. The gas turbine blade cooling effect test device according to claim 9, characterized in that: The deflector includes a main body, a first bending portion and a second bending portion, the main body is located between the first bending portion and the second bending portion, the first bending portion is arranged adjacent to the mounting frame, and the angle formed between at least one of the first bending portion and the second bending portion and the main body is greater than 90 degrees and less than 180 degrees.

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