A blade engine coupling test section and test system

Abstract

The application provides a blade heat engine coupling test section and a test system. The test section comprises: a first cover body provided with a through hole; a second cover body detachably connected with the first cover body to form a gas passage with open ends; one end of a pull rod is used to enter the gas passage through the through hole and is connected with a blade crown of a blade to be tested, the other end of the pull rod is used to be connected with an output end of a tension machine, a tenon of the blade to be tested is detachably installed in a mortise of the second cover body; a sleeve is arranged at the through hole outside the first cover body and is used for sleeving and sealing the pull rod; a fixed mounting part is arranged on the outer wall surface of the first cover body and / or the second cover body and is used for position fixing of the first cover body and / or the second cover body. The gas passage is convenient for providing a high-temperature gas environment for the blade to be tested; the pull rod is sealed by the sleeve to prevent gas leakage; the fixed mounting part is convenient for applying mechanical load to the blade to be tested by using the tension machine; and the reliability and accuracy of the test result are effectively improved.

Description

Technical Field

[0001] This invention relates to the technical field of aero-engines, and more specifically to a blade thermo-mechanical coupling test section and test system. Background Technology

[0002] With the rapid development of the modern aviation industry and the urgent needs of national defense, increasingly higher requirements are being placed on the performance of aero-engines. Aero-engine turbine blades are subjected to rapid scouring by high-temperature exhaust gases during startup and rapid cooling during shutdown. During the startup-shutdown cycle, the large temperature gradient on the blades generates significant thermal stress, leading to thermal fatigue. Therefore, thermal shock tests are necessary to assess the blades' resistance to thermal shock. Furthermore, the high-speed rotation of the blades generates substantial centrifugal loads. The combined effect of the temperature gradient and mechanical loads results in thermomechanical coupled fatigue of the blades. Therefore, thermomechanical coupled tests are required to assess the thermomechanical fatigue performance of the blades.

[0003] Currently, traditional methods for thermo-mechanical coupling fatigue testing of turbine blades are insufficient to simulate the temperature field experienced by turbine blades in actual engine operation, hindering further improvements in the reliability and accuracy of the test results. Therefore, it is necessary to provide a blade thermo-mechanical coupling test section and test system. Summary of the Invention

[0004] One aspect of this specification discloses a blade thermo-mechanical coupling test section, comprising: a first cover having a through hole; a second cover detachably connected to the first cover to form a gas passage open at both ends; a pull rod, one end of which is used to enter the gas passage through the through hole and connect to the blade crown of the blade to be tested, and the other end of which is used to connect to the output end of a tensile testing machine, wherein the tenon of the blade to be tested is detachably installed in the tenon groove of the second cover; a sleeve disposed at the through hole on the outside of the first cover and for sealing the pull rod; and a fixing mounting part disposed on the outer wall surface of the first cover and / or the second cover for fixing the position of the first cover and / or the second cover.

[0005] In some embodiments, the fixing mounting portion is a lug formed by extending outward from the outer wall surface of the first cover and / or the second cover, or a reinforcing rib with a through hole.

[0006] In some embodiments, the first cover includes an upper cover plate and two side wall plates connected to the upper cover plate, the second cover includes a lower cover plate, one end of the two side wall plates is connected to the upper cover plate, and the other end is detachably connected to the lower cover plate to form a gas passage together, and the fixed installation part is provided on the outer wall surface of the two side wall plates.

[0007] In some embodiments, the connecting surfaces between the side wall panel and the lower cover plate are respectively mating concave and convex surfaces.

[0008] In some embodiments, pneumatic sealing channels are symmetrically provided on both sides of the sleeve. The air outlet of the pneumatic sealing channel is connected to the through hole. The cross-sectional area of ​​the gap between the surface of the pull rod and the through hole is smaller than the cross-sectional area of ​​the air outlet of the pneumatic sealing channel, and the area ratio of the two is 1:S, where S is greater than or equal to 10.

[0009] In some embodiments, at least one liner blade with the same shape and structure as the blade under test is installed on the inner side of the second cover in the transverse direction of the gas passage to simulate the actual working environment of the blade under test.

[0010] In some embodiments, the second cover is provided with a cold air pipe, which is connected to the inner cavity of the blade to be tested and the inner cavity of each of the supporting blades.

[0011] In some embodiments, the end of the pull rod connected to the blade under test is provided with a cold air groove, which communicates with the inner cavity to discharge the cold air passing through the inner cavity of the blade under test.

[0012] In some embodiments, there is a gap between the lining blade and the inner wall surface of the first cover, and the gap communicates with the inner cavity of the lining blade.

[0013] Another aspect of the embodiments of this specification discloses a blade thermo-mechanical coupling test system, comprising: a blade thermo-mechanical coupling test section as described in any of the above embodiments; a combustion section connected to the blade thermo-mechanical coupling test section to provide high-temperature fuel gas; an oil supply system connected to the combustion section to provide fuel oil; an air supply system connected to the combustion section to provide compressed air; and a cooling system connected to the blade thermo-mechanical coupling test section to provide a cooling medium.

[0014] The embodiments described in this specification can achieve at least the following beneficial effects:

[0015] The first and second covers form a gas passage for testing the blade under test, facilitating the provision of a high-temperature gas environment for the blade. The sleeve seals the position of the tie rod, effectively preventing gas leakage. The fixed mounting part fixes the position of the first and / or second covers, facilitating the application of mechanical loads to the blade under test using a tensile testing machine, thus enabling the detection of the mechanical loads on the blade. This method can accurately simulate the aerodynamic environment of turbine blades during actual engine operation, as well as the thermo-mechanical coupling state when blade temperature, cascade temperature, and centrifugal force load are simultaneously applied, thereby effectively improving the reliability and accuracy of the test results. Attached Figure Description

[0016] Figure 1 This is an application scenario diagram of the blade thermo-mechanical coupling test system involved in some embodiments of this specification.

[0017] Figure 2 This is a schematic diagram of the structure of the blade thermo-mechanical coupling test system involved in some embodiments of this specification.

[0018] Figure 3 This is a schematic diagram of the structure of the blade thermo-mechanical coupling test section involved in some embodiments of this specification.

[0019] Figure 4 This is an exemplary assembly diagram of the upper cover plate, side wall plate and lower cover plate involved in some embodiments of this specification.

[0020] Figure 5 This is a three-dimensional schematic diagram of the blade thermo-mechanical coupling test section involved in some embodiments of this specification.

[0021] Figure 6 This is a schematic diagram illustrating the combination of the intake passage, gas passage, and exhaust passage involved in some embodiments of this specification.

[0022] Figure 7 This is a schematic diagram of the structure of the blade to be tested involved in some embodiments of this specification.

[0023] Figure 8 for Figure 3 A magnified view of a portion of point A in the middle.

[0024] Figure 9 for Figure 3 A magnified view of a portion of point B in the middle.

[0025] Figure 10 This is a schematic diagram of the liquid cooling channel involved in some embodiments of this specification.

[0026] Figure label:

[0027] 100. Blade thermo-mechanical coupling test system; 110. Blade thermo-mechanical coupling test section; 120. Combustion section; 130. Fuel supply system; 140. Air supply system; 150. Cooling system; 160. Exhaust section;

[0028] 210. First cover; 211. Upper cover plate; 212. Side wall plate; 220. Second cover; 221. Lower cover plate; 222. Coupled wire channel; 230. Pull rod; 240. Sleeve; 241. Grate sealing structure; 250. Fixed mounting part; 260. Pneumatic sealing channel; 270. Cold air pipeline; 280. Blade to be tested; 281. Supporting blade; 290. Gas passage;

[0029] 310. Air intake passage; 320. Exhaust passage; 330. Liquid inlet pipe; 340. Liquid outlet pipe;

[0030] 410. Air conditioning slot; 420. Through hole; 430. Gap;

[0031] 510. Liquid cooling channel; 520. Honeycomb cooling structure. Detailed Implementation

[0032] The technical solution of this specification is described in further detail below with reference to the accompanying drawings, but the scope of protection of this specification is not limited to what is described below.

[0033] To make the objectives, technical solutions, and advantages of the embodiments in this specification clearer, the technical solutions in the embodiments of this specification will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments in this specification, not all of them. Based on the embodiments in this specification, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this specification. Therefore, the following detailed description of the embodiments of this specification provided in the accompanying drawings is not intended to limit the scope of the claimed specification, but merely to represent selected embodiments of this specification. Based on the embodiments in this specification, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this specification.

[0034] In the description of this specification, it should be understood that the terms indicating orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings and are used only for the convenience of describing this specification and simplifying the description, and are not intended to indicate or imply that the equipment or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this specification.

[0035] In this specification, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this specification according to the specific circumstances.

[0036] In this specification, unless otherwise expressly specified and limited, the presence of a first feature above or below a second feature may include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top of" the first feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. Conversely, "below," "beneath," and "below" the first feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0037] The present invention will be further described below with reference to embodiments. These embodiments are merely some, not all, of the embodiments of the present invention. Other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are all within the protection scope of the present invention.

[0038] Please refer to the accompanying drawings, which show the structure of the embodiment selected by the present invention. This is for illustrative purposes only and is not limited to this structure in the patent application.

[0039] Figure 1 The diagram illustrates application scenarios of the blade thermo-mechanical coupling test system 100 according to some embodiments of the present invention. Figure 2 A schematic diagram of the structure of a blade thermo-mechanical coupling test system 100 according to some embodiments of the present invention is shown.

[0040] like Figure 1 As shown, in some application scenarios, the blade thermo-mechanical coupling test system 100 may include a blade thermo-mechanical coupling test section 110, a combustion section 120, an oil supply system 130, an air supply system 140, and a cooling system 150.

[0041] The blade thermo-mechanical coupling test section 110 is used to provide a high-temperature combustion environment for the blade 280 under test and to apply mechanical loads to the blade 280 under test.

[0042] In this specification, high-temperature gas specifically refers to gas with a temperature above 1500K, and high-temperature environment specifically refers to an environment with a temperature above 1500K.

[0043] The combustion section 120 is used to supply high-temperature gas to the blade thermo-mechanical coupling test section 110, providing a high-temperature gas test environment for the blade 280 under test.

[0044] In some embodiments, such as Figure 2As shown, the combustion section 120 includes an electric heater and a combustion chamber. The front end of the combustion chamber is connected to the electric heater, and the rear end of the combustion chamber is connected to the blade thermo-mechanical coupling test section 110. The combustion chamber is used to provide high-temperature combustion gas with a temperature above 1500K, and even up to 2000K, specifically for the blade thermo-mechanical coupling test section 110. By adjusting the temperature of the combustion gas, the temperature cyclic load test of the blade 280 under test can be achieved.

[0045] In some embodiments, a thermocouple is connected between the combustion chamber and the electric heater, and a thermocouple is connected between the combustion chamber and the blade thermo-mechanical coupling test section 110.

[0046] The fuel supply system 130 is used to supply fuel to the combustion section 120.

[0047] In some embodiments, such as Figure 2 As shown, the fuel supply system 130 includes an aviation kerosene tank, a fuel pump, a vortex flow meter, and a pressure gauge. The aviation kerosene tank, fuel pump, vortex flow meter, pressure gauge, and combustion chamber are sequentially connected to supply kerosene to the combustion chamber.

[0048] The air supply system 140 is used to supply compressed air to the combustion chamber.

[0049] In some embodiments, such as Figure 2 As shown, the air supply system 140 includes an air compressor, an air tank, a main valve, a solenoid valve, a flow meter, and a pressure gauge. The air compressor, air tank, main valve, solenoid valve, flow meter, pressure gauge, and electric heater are connected in sequence to supply compressed air to the electric heater.

[0050] In some embodiments, a thermocouple is connected between the flow meter and the pressure gauge.

[0051] The cooling system 150 is used to provide a cooling medium for the blade thermo-mechanical coupling test section 110.

[0052] In some embodiments, such as Figure 2 As shown, the cooling system 150 includes an air compressor, an air tank, a throttle valve, a refrigerator, a flow meter, and a pressure gauge. The air compressor, air tank, throttle valve, refrigerator, flow meter, pressure gauge, and blade thermo-mechanical coupling test section 110 are sequentially connected and supplied with cooling air to the blade thermo-mechanical coupling test section 110; this part is equivalent to the cooling system.

[0053] In some embodiments, a thermocouple is connected between the pressure gauge and the blade thermo-mechanical coupling test section 110.

[0054] In some embodiments, such as Figure 2As shown, the cooling system 150 also includes a cooling water tank, a water pump, and valves. The cooling water tank, water pump, valves, and blade thermo-mechanical coupling test section 110 are connected to form a circulating water cooling channel to provide cooling water for the blade thermo-mechanical coupling test section 110; this part is equivalent to a water cooling system.

[0055] In some embodiments, a PT100 temperature sensor is connected between the blade thermo-mechanical coupling test section 110 and the cooling water tank.

[0056] In some embodiments, the blade thermo-mechanical coupling test system 100 may further include an exhaust section 160, which is connected to the blade thermo-mechanical coupling test section 110 to exhaust the high-temperature combustion gas after the test.

[0057] In some embodiments, such as Figure 2 As shown, the exhaust section 160 includes a solenoid valve and a induced draft fan. The blade thermo-mechanical coupling test section 110, the solenoid valve, and the induced draft fan are connected to discharge the high-temperature gas after the test.

[0058] In some embodiments, the exhaust fan is equipped with a sound-absorbing canopy.

[0059] In some embodiments, the blade thermo-mechanical coupling test system 100 may further include a control system, which is connected to thermocouples, vortex flow meters, oil pumps, pressure gauges, main valves, solenoid valves, electric heaters, air compressors, throttle valves, flow meters, water pumps, and valves to control various parameters involved in the test process, such as the flow rate and velocity of fuel oil, the flow rate, velocity, and pressure of high-temperature combustion gas, the flow rate, velocity, and pressure of cold air, the flow rate, velocity, and pressure of cooling water, etc.

[0060] Figure 3 This is a schematic diagram of the structure of the blade thermo-mechanical coupling test section 110 involved in some embodiments of this specification. Figure 4 This is an exemplary assembly diagram of the upper cover plate 211, side wall plate 212 and lower cover plate 221 involved in some embodiments of this specification. Figure 5 This is a three-dimensional schematic diagram of the blade thermo-mechanical coupling test section 110 involved in some embodiments of this specification.

[0061] like Figure 3 As shown, the blade thermo-mechanical coupling test section 110 may include a first cover 210, a second cover 220, a tie rod 230, a sleeve 240, and a fixed mounting part 250.

[0062] In some embodiments, the first cover 210 and the second cover 220 are detachably connected to form a gas passage 290 with openings at both ends.

[0063] In some embodiments, the first cover 210 includes an upper cover plate 211 and two side wall plates 212 connected to the upper cover plate 211, and the second cover 220 includes a lower cover plate 221. One end of the two side wall plates 212 is connected to the upper cover plate 211, and the other end is detachably connected to the lower cover plate 221 to form a gas passage 290 together.

[0064] In some embodiments, the second cover 220 is provided with a thermocouple channel 222, which contains two thermocouples for detecting the temperature of the end and middle of the blade 280 to be tested, respectively.

[0065] In some embodiments, the thermocouple first enters the gas passage 290 and then extends to the end and middle of the blade 280 to be tested for temperature detection.

[0066] In some embodiments, the tie rod 230 is used to provide tangential force to the blade under test under the drive of a power source such as a tension testing machine, so as to simulate the tangential load on the blade under test when it rotates.

[0067] In some embodiments, the connection end between the tie rod 230 and the blade to be tested is integrally cast, that is, the connection between the two is integrally formed; to avoid the high temperature gas burning the connection between the tie rod 230 and the blade to be tested, which would cause the connection to break.

[0068] In some embodiments, a toothed sealing structure 241 is provided between the sleeve 240 and the tie rod 230 sleeved inside it.

[0069] In some embodiments, the inner cavity of the sleeve 240 may be cylindrical or cuboid. Accordingly, the grate sealing structure 241 is generally cylindrical or cuboid.

[0070] In some embodiments, the upper cover plate 211 is welded to the side wall panels 212 respectively to achieve a fixed connection. In other embodiments, the upper cover plate 211 and the side wall panels 212 are integrally formed.

[0071] In some embodiments, the connection portion of the upper cover plate 211 and the side wall plate 212 extends horizontally outward to form a flange, and the flanges are welded together to achieve a fixed connection.

[0072] In some embodiments, the shape of the connection surface between the top cover plate 211 and the side wall plate 212 may be one or more combinations of sawtooth, corrugated and rectangular shapes to minimize gas leakage.

[0073] In some embodiments, such as Figure 4 As shown, the connection between the top cover plate 211 and the side wall plate 212 extends horizontally outward and then vertically to form a right-angle boss, which is then fixedly connected by welding to minimize gas leakage.

[0074] In some embodiments, the connection between the upper cover plate 211 and the side wall plate 212 is made by bolting and then welding.

[0075] In some embodiments, the top cover plate 211 is detachably connected to the two side wall plates 212 by fasteners such as bolts and nuts.

[0076] In some embodiments, the lower cover plate 221 is detachably connected to the two side wall plates 212 by fasteners such as bolts and nuts.

[0077] In some embodiments, the connection between the lower cover plate 221 and the side wall plate 212 extends horizontally outward to form a flange, and the flanges are connected by bolts.

[0078] In some embodiments, such as Figure 4 As shown, the connection between the lower cover plate 221 and the side wall plate 212 extends horizontally outward and then vertically to form a right-angle boss, and the right-angle bosses are connected by bolts.

[0079] In some embodiments, the connecting surfaces between the lower cover plate 221 and the side wall plate 212 are respectively mating concave and convex surfaces.

[0080] In some embodiments, the irregularities in the uneven surface are one or more combinations of sawtooth, corrugated, and rectangular shapes.

[0081] In some embodiments, the fixing mounting part 250 is used to fix the position of the first cover 210 and / or the second cover 220.

[0082] In some embodiments, the fixing mounting portion 250 is disposed on the outer wall surface of the first cover 210 and / or the second cover 220.

[0083] In some embodiments, the fixing mounting portion 250 is a lug formed by extending outward from the outer wall surface of the first cover 210 and / or the second cover 220, or a reinforcing rib with a through hole.

[0084] In some embodiments, the lifting lugs can be provided on the outer wall surface of the two side wall panels 212. The blade thermo-mechanical coupling test section 110 can be installed on the mounting base (clamp) of the tensile testing machine through the lifting lugs, so that when the tensile testing machine applies mechanical load to the blade 280 under test through the tie rod 230, it can accurately detect the tensile force (mechanical load) on the blade 280 under test.

[0085] In some embodiments, the fixed mounting part 250 is used to connect to a tensile testing machine so that the lower cover plate 221 is suspended.

[0086] In some embodiments, the fixed mounting part 250 is used for detachable or fixed connection with the outside world, so that the lower cover plate 221 is suspended.

[0087] In some embodiments, the bottom side of the lower cover plate 221 is provided with a connector for connecting to a tensile testing machine, so that the lower cover plate 221 is suspended.

[0088] With the lower cover plate 221 suspended, it is convenient to accurately adjust the force applied by the tensioning machine of the pull rod 230 and the tensioning machine of the lower cover plate 221.

[0089] In some embodiments, the thickness of the lower cover plate 221 is at least 1.5 times greater than the height of the blade 280 under test, and the thickness of the upper cover plate 211 exceeds 0.5 times the height of the blade 280 under test. The upper cover plate 211 is a non-load-bearing component, but because the blade cascade environment is a high-temperature and high-pressure environment, the upper cover plate 211 should also maintain a certain thickness to ensure structural reliability.

[0090] The lower cover plate 221 and the upper cover plate 211 are assembled from metal plates of a certain thickness. The specific thickness can be set according to actual needs, and this design includes, but is not limited to, the following advantages:

[0091] The first advantage is that the cover plate is thick enough, so the wall rigidity is large enough that even if the internal pressure of the blade cascade reaches 30 to 50 atmospheres, it is difficult to damage the wall structure of the blade thermo-mechanical coupling test section 110.

[0092] The second advantage is that the thermal inertia of the wall of the blade thermo-mechanical coupling test section 110 is large enough, which means that there is no need to spray water to cool the wall of the blade thermo-mechanical coupling test section 110 during the experiment, because the strength of the blade thermo-mechanical coupling test section 110 itself can meet the test requirements.

[0093] The third benefit is that it can improve the thermal fatigue characteristics of the blade thermo-mechanical coupling test section 110, making the life of the blade thermo-mechanical coupling test section 110 much longer than the life of the blade under test 280, which ensures the safety of the test equipment in the fatigue test.

[0094] The fourth advantage is that the stiffness of the blade thermo-mechanical coupling test section 110 is much greater than that of the blade under test 280. This means that when the blade under test 280 is subjected to tension or compression, the blade thermo-mechanical coupling test section 110 can still remain stable and will not undergo large deformation, thus affecting the deformation and load of the blade under test 280.

[0095] In some embodiments, at least one liner blade 281 with the same shape and structure as the blade under test 280 is installed on the inner side of the second cover 220 in the transverse direction of the gas passage 290 to simulate the actual working environment of the blade under test 280.

[0096] The lateral direction refers to the horizontal direction that is perpendicular or substantially perpendicular to the length direction of the pull rod 230, and this horizontal direction is perpendicular or substantially perpendicular to the direction in which the gas enters the gas passage 290; substantially perpendicular means that the two directions can vary within a range of 90°±5°; the lateral direction can be referenced. Figure 3 The middle arrow points in the directions C and D.

[0097] In some embodiments, there are 2n auxiliary blades 281, which are symmetrically arranged on the left and right sides of the blade 280 to be tested. 2n refers to an integer multiple of 2, such as 2, 4, 6, 8, 10, etc.

[0098] In some embodiments, the inner surface of the second cover 220 is arc-shaped. Specifically, the inner surface of the second cover 220 refers to the common mounting surface where the blade under test 280 and multiple supporting blades 281 are located, in order to realistically simulate the actual working environment of the blade under test 280 and effectively improve the reliability of the test.

[0099] In some embodiments, both the blade to be tested 280 and the supporting blade 281 can be detachably mounted on the inner side of the second cover 220. The detachable form is a detachable connection structure such as a mortise and tenon joint (tenon and mortise).

[0100] In some embodiments, the second cover 220 is provided with a cooling air pipe 270, which is connected to the inner cavity of the blade under test 280 and the inner cavities of each of the supporting blades 281. The air inlet of the cooling air pipe 270 is connected to the cooling system in the cooling system 150 to supply cooling air to the inner cavities of the blade under test 280 and the inner cavities of each of the supporting blades 281. The temperature of this cooling air is close to the actual engine cooling air temperature, with a difference between them between -1℃ and 1℃, or between -3℃ and 3℃.

[0101] Figure 6 This is a schematic diagram showing the combination of the intake passage 310, the gas passage 290 and the exhaust passage 320 involved in some embodiments of this specification. Figure 7 This is a schematic diagram of the structure of the blade 280 to be tested involved in some embodiments of this specification.

[0102] In some embodiments, such as Figure 6 As shown, the gas passage 290 has an intake passage 310 at its inlet and an exhaust passage 320 at its outlet. The intake passage 310 is used to connect with the combustion section 120, and the exhaust passage 320 is used to connect with the exhaust section 160.

[0103] In some embodiments, the intake passage 310 and the exhaust passage 320 form an angle along their axes, and the through hole 420 is located at the angle.

[0104] In some embodiments, the included angle is determined based on the angle between the tangent at one end of the central arc line in the cross-section of the blade 280 under test and the tangent at the other end of the central arc line.

[0105] The intake passage 310 is connected to the blade thermo-mechanical coupling test section 110 via a flange, and the exhaust passage 320 is connected to the blade thermo-mechanical coupling test section 110 via a flange. By using the installation method of flange + blade thermo-mechanical coupling test section 110 + flange, the flow dimension of the blade thermo-mechanical coupling test section 110 can be made small enough to avoid wasting high-temperature alloy materials. The flow dimension of the blade thermo-mechanical coupling test section 110 only needs to be slightly larger than the chord length of the blade 280 under test.

[0106] like Figure 6 As shown, arrow F indicates the direction of high-temperature gas entry, arrow E indicates the direction of high-temperature gas exit, and angle G is the angle between the directions of arrow E and arrow F, which is also the angle formed by the axial directions of the intake channel 310 and the exhaust channel 320, and the deflection angle of the high-temperature gas after it has done work on the blade 280 under test. The extensions of arrows E and F can be considered as the tangents at both ends of the mid-arc line in the cross-section of the blade 280 under test.

[0107] In practical applications, the included angle G can be determined based on the specific structure and installation position of the test blade 280, and according to the design requirements of the above-mentioned scheme; that is, the included angle G is different for test blades 280 of different shapes and sizes, and the included angle G is also different for test blades 280 installed in different positions. An error of ±1° to 5° is allowed when determining the included angle. In some embodiments, the included angle G can range from 20° to 70°, and the specific angle can be 20°, 25°, 30°, 35°, 40°, 45°, 50°, 55°, 60°, 65°, or 70°. In some embodiments, the included angle G can range from 20° to 50°. In some embodiments, the included angle G can range from 25° to 55°. In some embodiments, the included angle G can range from 30° to 60°. In some embodiments, the included angle G can range from 35° to 65°. In some embodiments, the included angle G can range from 40° to 70°. In some embodiments, the included angle G can range from 25° to 65°. In some embodiments, the included angle G can range from 30° to 60°. In some embodiments, the included angle G can range from 35° to 55°. In some embodiments, the included angle G can range from 40° to 50°.

[0108] It is worth noting that the inventors discovered that in actual working environments, after the high-temperature gas enters the gas combustion channel 290, it does work on the blade under test 280. This work is converted into the kinetic energy of the blade's rotation. After the high-temperature gas does work, its flow direction will deflect. If there is no angle between the intake channel 310 and the exhaust channel 320 during the experiment, the high-temperature gas, after deflection, will directly impact the inner wall of the gas combustion channel 290, causing severe ablation. This significantly shortens the lifespan of the experimental equipment and introduces significant safety risks and increased experimental costs.

[0109] In the above embodiment, by setting the included angle G, the flow direction of the high-temperature gas after impacting the test blade 280 will be deflected towards the outlet direction of the gas passage 290 and discharged along the length of the exhaust passage 320. This effectively avoids the high-temperature gas impacting the inner wall of the gas passage 290, greatly alleviates the ablation of the inner wall of the gas passage 290, and can greatly improve the service life of the gas passage 290, effectively reducing experimental risks and costs. Moreover, it can be used in conjunction with the exhaust section 160 to reduce the residence time of the high-temperature gas in the exhaust passage 320, further alleviating the ablation of the inner wall of the gas passage 290.

[0110] like Figure 7 As shown, the middle part of the blade 280 under test refers to the region H formed by extending the centerline I between the two ends of the blade 280 in the length direction of the blade 280 for 5% of the length of the blade 280. In some embodiments, the middle part of the blade 280 under test may specifically refer to the 50% length position in the length direction of the blade 280 under test.

[0111] The cross section of the blade 280 under test refers to the cross section of the blade 280 under test taken within region H, in a direction parallel to the length direction of the centerline I.

[0112] The middle arc line in the cross-section of the blade 280 under test refers to the arc segment obtained by taking the midpoints of the two ends in the width direction of the blade 280 under test as the endpoints and the arc surface direction of the blade 280 under test as the arc line.

[0113] The tangents at both ends of the central arc line in the cross-section of the blade 280 under test refer to the rays obtained by extending the central arc line outward from both ends.

[0114] Figure 8 for Figure 3 A magnified view of a portion of point A in the middle. Figure 9 for Figure 3 A magnified view of a portion of point B in the middle.

[0115] In some embodiments, such as Figure 8 As shown, the first cover 210 is provided with a through hole 420.

[0116] In some embodiments, such as Figure 8 As shown, a cooling gas groove 410 is provided at the end where the blade 280 under test is connected to the tie rod 230. The cooling gas groove 410 communicates with the inner cavity of the blade 280 under test to discharge the cooling gas passing through the inner cavity of the blade 280 under test. The cooling gas groove 410 can cool the end of the tie rod 230.

[0117] In some embodiments, one end of the pull rod 230 is used to enter the gas passage 290 through the through hole 420 and connect with the blade crown of the blade to be tested, and the other end of the pull rod 230 is used to connect with the output end of the tensile testing machine, wherein the tenon of the blade to be tested is detachably installed in the tenon groove of the second cover 220.

[0118] In some embodiments, the sleeve 240 is disposed at the through hole 420 on the outside of the first cover 210 and is fitted and sealed to the pull rod 230.

[0119] In some embodiments, pneumatic sealing channels 260 are symmetrically provided on both sides of the sleeve 240. The outlet end of the pneumatic sealing channel 260 is connected to the through hole 420, and the inlet end of the pneumatic sealing channel 260 is connected to the cooling system in the cooling system 150, so as to introduce gas with a pressure slightly greater than the gas pressure at the point where the through hole 420 is connected to the gas passage 290, thereby achieving pneumatic sealing.

[0120] The pneumatic sealing channel 260 and the toothed sealing structure 241 work together to cool and seal the pull rod 230. Cooling reduces the temperature inside the sleeve 240, while sealing prevents high-temperature gas from leaking out through the sleeve 240.

[0121] The outlet of the pneumatic sealing channel 260 is positioned as close as possible to the connection point between the through hole 420 and the gas passage 290. "Slightly greater than" specifically means: if the gas pressure supplied from the pneumatic sealing channel 260 to the through hole 420 is p1, and the gas pressure at the connection point between the through hole 420 and the gas passage 290 is p2, then the value of p1 ranges from 1 to 1.05 times that of p2.

[0122] In other embodiments, the pneumatic sealing channel 260 is equipped with an air source that supplies room-temperature, high-pressure air to the pneumatic sealing channel 260. The room-temperature, high-pressure air mixes at the connection between the through-hole 420 and the gas passage 290, which serves as a seal and effectively prevents high-temperature gas from flowing out of the through-hole 420. Simultaneously, to ensure the effectiveness of the pneumatic seal, such as... Figure 8 As shown, the gap between the surface of the pull rod 230 and the through hole 420 can be 0.1mm to 0.5mm. The cross-sectional area of ​​the gap is much smaller than the cross-sectional area of ​​the pneumatic sealing channel 260. The design area ratio of the two is 1:S, where S≥10. According to the continuity equation of gas, the volumetric flow rate of the sealed gas will be more than 10 times that of the gas flow rate. This can control the gas leakage to a very small level (e.g., no more than 1% of the mainstream gas flow rate) and reduce the temperature of the leaked gas to less than half of the mainstream gas temperature (in degrees Celsius, for example, from 1000 degrees Celsius to below 500 degrees Celsius).

[0123] Normal temperature high pressure air specifically refers to air with a temperature between 20℃ and 25℃ and a pressure between 3MPa and 3.2MPa.

[0124] In some embodiments, such as Figure 9 As shown, there is a gap 430 between the lining blade 281 and the inner wall surface of the first cover 210, and the gap 430 communicates with the inner cavity of the lining blade 281.

[0125] Figure 10 This is a schematic diagram of the structure of the liquid cooling channel 510 involved in some embodiments of this specification.

[0126] In some embodiments, both the air intake channel 310 and the exhaust channel 320 are provided with liquid cooling channels 510 surrounding their respective internal cavities, and the bottom side of the liquid cooling channel 510 is provided with a liquid inlet pipe 330 (see Figure 5 The top side of the liquid cooling channel 510 is provided with a liquid outlet pipe 340 (see...). Figure 5 The liquid cooling channel 510 is connected to the water cooling system in the cooling system 150 through the liquid inlet pipe 330 and the liquid outlet pipe 340 to cool the intake channel 310 and the exhaust channel 320 and prevent the intake channel 310 and the exhaust channel 320 from overheating.

[0127] In some embodiments, such as Figure 10 As shown, the cooling structure of the liquid cooling channel 510 can be a honeycomb cooling structure 520.

[0128] The embodiments described above are for illustrative purposes only and are not intended to limit the invention. Therefore, any changes in numerical values ​​or substitutions of equivalent elements should still fall within the scope of this invention.

[0129] The above detailed description will enable those skilled in the art to understand that the present invention can indeed achieve the aforementioned objectives and has complied with the provisions of the Patent Law.

[0130] Although preferred embodiments of the invention have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of the invention. The above descriptions are merely preferred embodiments of the invention and are not intended to limit the invention. It should be noted that any modifications, equivalent substitutions, and improvements made within the spirit and principles of the invention should be included within the scope of protection of the invention.

[0131] It should be noted that the above description of the process is for illustrative purposes only and does not limit the scope of this specification. Those skilled in the art can make various modifications and changes to the process under the guidance of this specification. However, these modifications and changes remain within the scope of this specification.

[0132] The basic concepts have been described above. Obviously, for those skilled in the art who have read this application, the above disclosure is merely illustrative and does not constitute a limitation of this application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are suggested in this application, and therefore, such modifications, improvements, and corrections still fall within the spirit and scope of the exemplary embodiments of this application.

[0133] Furthermore, this application uses specific terms to describe its embodiments. For example, "an embodiment," "one embodiment," and / or "some embodiments" refer to a particular feature, structure, or characteristic related to at least one embodiment of this application. Therefore, it should be emphasized and noted that "an embodiment," "one embodiment," or "an alternative embodiment" mentioned twice or more in different positions in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of this application can be appropriately combined.

[0134] Similarly, it should be noted that, in order to simplify the description of the present application and thus aid in the understanding of one or more embodiments of the invention, the foregoing description of the embodiments of the present application sometimes combines multiple features into a single embodiment, drawing, or description thereof. However, this approach of the present application should not be construed as reflecting an intention that the claimed subject matter requires more features than expressly recited in each claim. Rather, the subject of the invention should possess fewer features than in any single embodiment described above.

Claims

1. A blade thermo-mechanical coupling test section, characterized in that, include: A first cover, wherein the first cover is provided with a through hole; The second cover is detachably connected to the first cover to form a gas passage with openings at both ends; A pull rod, one end of which is used to enter the gas passage through the through hole and connect with the blade crown of the blade to be tested, and the other end of which is used to connect with the output end of the tensile testing machine, wherein the tenon of the blade to be tested is detachably installed in the tenon groove of the second cover; A sleeve, which is disposed at the through hole on the outside of the first cover and fits and seals the pull rod; and a fixing mounting part, which is disposed on the outer wall surface of the first cover and is used to fix the position of the first cover. The fixed mounting part is a lug formed by extending outward from the outer wall of the first cover or a reinforcing rib with through holes; The first cover includes an upper cover plate and two side wall plates connected to the upper cover plate. The second cover includes a lower cover plate. One end of each side wall plate is connected to the upper cover plate, and the other end is detachably connected to the lower cover plate to form a gas passage. The fixed installation part is provided on the outer wall surface of the side wall plates. The thickness of the lower cover plate is greater than 1.5 times the height of the blade to be tested, and the thickness of the upper cover plate is greater than 0.5 times the height of the blade to be tested. The fixed mounting part is used to connect with the tensile testing machine so that the lower cover plate is suspended in the air; The inner side of the second cover is equipped with at least one liner blade with the same shape and structure as the blade under test in the transverse direction of the gas passage, so as to simulate the actual working environment of the blade under test. The second cover is provided with a cold air pipe, which is connected to the inner cavity of the blade to be tested and the inner cavity of each of the supporting blades.

2. The blade thermo-mechanical coupling test section as described in claim 1, characterized in that, The connecting surfaces between the side wall plate and the lower cover plate are respectively interlocking concave and convex surfaces.

3. The blade thermo-mechanical coupling test section as described in claim 1, characterized in that, The sleeve is provided with pneumatic sealing channels symmetrically on both sides. The air outlet of the pneumatic sealing channel is connected to the through hole. The cross-sectional area of ​​the gap between the surface of the pull rod and the through hole is smaller than the cross-sectional area of ​​the air outlet of the pneumatic sealing channel, and the area ratio of the two is 1:S, where S is greater than or equal to 10.

4. The blade thermo-mechanical coupling test section as described in claim 1, characterized in that, The end of the pull rod connected to the blade under test is provided with a cold air groove, which is connected to the inner cavity to discharge the cold air passing through the inner cavity of the blade under test.

5. The blade thermo-mechanical coupling test section as described in claim 1, characterized in that, There is a gap between the lining blade and the inner wall surface of the first cover, and the gap communicates with the inner cavity of the lining blade.

6. A blade thermo-mechanical coupling test system, characterized in that, include: The blade thermo-mechanical coupling test section according to any one of claims 1 to 5; The combustion section is connected to the blade thermo-mechanical coupling test section to provide high-temperature fuel gas; A fuel supply system, connected to the combustion section, provides fuel. An air supply system, connected to the combustion section, provides compressed air; as well as A cooling system, connected to the blade thermo-mechanical coupling test section, provides a cooling medium.

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