Design and testing method of gas turbine blade test piece with multi-site detachable passage

Abstract

The application discloses a test piece design and a test method of a gas turbine blade with a multi-part detachable and replaceable channel, the test piece comprising a blade body, a channel partition plate A and a channel partition plate B, a spoiler A, a spoiler B and a spoiler C, a guide vane plate A and a guide vane plate B, a suction surface cover plate, a blade platform, a connecting flange, a transition section A and a transition section B; the method splits the blade into multiple substructures for processing, and finally assembles the blade into a whole, thereby reducing the difficulty of blade processing and internal sensor arrangement, and expanding the research object from a basic heat exchange unit to a real gas turbine blade, so that the test data is more real and effective, wherein the cooling channel structure inside the blade is replaceable, thereby not only reducing the test cost of different structure models, but also reducing the processing difference between different blades and the influence of other variables of the test piece; and a test piece test process is established, so that the cooling characteristics of different cooling channel forms and internal spoiler structures in a static state / rotating state can be tested.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of gas turbine blade cooling technology, and particularly relates to a gas turbine blade test piece design with multiple detachable and replaceable channels and a testing method. BACKGROUND

[0002] As one of the core components of a gas turbine, a gas turbine turbine blade is directly impacted by gas for a long time, and has a very high thermal load. The development speed of high-temperature resistant materials is far slower than the speed of the increase of the gas turbine inlet temperature. Therefore, in order to ensure the safe and stable operation of the turbine blade, effective heat exchange technology must be taken to reduce the blade temperature.

[0003] At present, numerical simulation has become the main research method for the research on the rotating cooling characteristics of the gas turbine blade due to its high accuracy and low cost. However, experimental research, as an important means of evaluating the heat exchange characteristics of the blade, can provide direct, real and detailed experimental data for the actual blade cooling design, and is the most critical step for verifying and improving the blade cooling structure design. At present, there are still the following problems in the gas turbine blade cooling test: first, most of the tests are only carried out on the basis of the heat exchange unit structure, such as U-shaped channel and serpentine channel, without considering the structural characteristics of the internal cooling channel with variable cross-section under the actual blade profile, and without considering the influence of the blade solid on the test results; second, the integrated design and processing of the blade test piece with long and complex cooling channels are relatively complex, and the change of the internal channel structure parameters requires the replacement of the entire test piece, which not only has high test cost, but also makes it difficult to arrange the internal sensors of the blade; third, the current internal cooling test research of the blade is mostly for the channel cooling performance under the static state, and it is difficult to realize the rotating state test research which is closer to the actual operating condition. In order to obtain the test data of the internal channel cooling performance of the real blade under the rotating state, it is urgent to establish a complete gas turbine turbine blade design, processing and test method. SUMMARY

[0004] In view of the deficiencies of the prior art, the present application provides a gas turbine blade test piece design and testing method with multiple parts of detachable and replaceable channels. The method splits the gas turbine turbine blade into multiple substructures for processing, and finally assembles the blade as a whole, greatly reducing the difficulty of blade processing and internal sensor arrangement, and expanding the research object from the basic heat exchange unit to the real gas turbine blade, making the test data more real and effective. The cooling channel structure inside the blade can be replaced, which not only greatly reduces the test cost of different structure models, but also reduces the processing difference between different blades and the influence of other variables of the test piece. A complete blade simulation test process is established based on the model, which can test the cooling effect of different cooling channel forms and internal disturbance structures under different conditions such as static and rotation. The test simulation piece has a simple structure, the rotating connection of the test system is reliable, the test data is accurate, and it can provide guidance ideas and solutions for the design and processing of gas turbine turbine blade test pieces and the cooling performance research of the test pieces in the rotating state.

[0005] To achieve the above purpose, the technical scheme is adopted as follows:

[0006] The test piece includes a blade body, a channel partition plate A and a channel partition plate B for partitioning the internal cavity of the blade into a serpentine cooling channel, a disturbance plate A, a disturbance plate B and a disturbance plate C for arranging the surface disturbance structure of the serpentine channel, a guide vane plate A and a guide vane plate B for arranging the guide vane structure of the turning area of the serpentine channel, a suction surface cover plate for sealing the serpentine channel structure and forming an external profile together with the blade body, a blade platform, a connecting flange for connecting the blade test piece and the test platform, and a transition section A and a transition section B for connecting the blade platform and the connecting flange and forming a serpentine channel inside.

[0007] The method comprises the following steps:

[0008] Firstly, select the channel partition plate A, the channel partition plate B, the disturbance plate A, the disturbance plate B, the disturbance plate C, the guide vane plate A and the disturbance plate B corresponding to the test working condition;

[0009] Secondly, arrange sensors in the bottom area of the square groove at the back of the disturbance plate A, the disturbance plate B and the disturbance plate C, and lead the sensors out of the test simulation piece through the lead hole of the blade body and the blade platform. The sensor type is thermocouple and strain gauge;

[0010] Thirdly, evenly smear a layer of thin high-performance thermal conductive silicone grease on the interface between the disturbance plate A, the disturbance plate B and the disturbance plate C and the blade body, and fix the disturbance plate A, the disturbance plate B and the disturbance plate C on the blade body by using the filleting screw and the filleting threaded hole Q1.

[0011] Fourth step, evenly apply a thin layer of high-performance thermal conductive silicone grease on the interface between guide vane plate A and guide vane plate B and the blade body, and use bolts, threaded holes L7 and countersunk through holes C7 to fix the channel partition plate A and the channel partition plate B on the blade body;

[0012] Fifth step, evenly apply a thin layer of high-performance thermal conductive silicone grease on the interface between channel partition plate A and channel partition plate B and the blade body, and use bolts, threaded holes L6 and countersunk through holes C6 to fix the channel partition plate A and the channel partition plate B on the blade body;

[0013] Sixth step, use bolts, threaded holes L2 and countersunk through holes C2 to fix the suction surface cover plate on the blade body;

[0014] Seventh step, use bolts, threaded holes L3 and countersunk through holes C3 to assemble transition section A and transition section B;

[0015] Eighth step, use bolts, threaded holes L4 and countersunk through holes C4 to tightly connect transition section A and transition section B with the blade platform;

[0016] Ninth step, use bolts, threaded holes L1 and countersunk through holes C1 to tightly connect the blade body with the blade platform;

[0017] Tenth step, use bolts, threaded holes L5 and countersunk through holes C5 to tightly connect transition section A and transition section B with the connecting flange;

[0018] Eleventh step, use bolts and threaded holes L8 to tightly connect the assembled gas turbine blade test piece with the test section connecting flange of the gas turbine blade rotating thermal solid characteristic test bench;

[0019] Twelfth step, complete the test piece temperature load arrangement, sensor-collector ring-data acquisition instrument dynamic-static conversion connection and other test preparation work, and carry out multi-working condition heat transfer performance test of the gas turbine blade test piece under the selected structure;

[0020] Thirteenth step, after completing the test of the twelfth step, stop applying all loads, disconnect the sensor cable, and complete the disassembly of the gas turbine blade test piece in the order of the eleventh step to the second step.

[0021] Further improvement of the application is that threaded holes L1 are arranged on the bottom front edge and trailing edge area of the blade body, countersunk through holes C1 are arranged on the blade platform, and the blade body and the blade platform are tightly connected by bolts.

[0022] Further improvement of the application is that the bolts tightly connect the suction surface cover plate and the blade body through two rows of countersunk through holes C2 on both sides of the suction surface cover plate and threaded holes L2 on both sides of the blade body.

[0023] The further improvement of the application is that the transition section A and the transition section B are respectively provided with a plurality of countersunk through holes C3 and threaded holes L3, and the outside is cylindrical and the inside is a lofting channel and an inlet extension section after bolt connection; the middle of the blade platform is provided with a plurality of countersunk through holes C4, the upper end surfaces of the transition section A and the transition section B are provided with a plurality of threaded holes L4, and the upper ends of the blade body, the transition section A and the transition section B are connected respectively through bolts; the lower ends of the transition section A and the transition section B are provided with a plurality of threaded holes L5, the middle of the connecting flange is provided with a plurality of countersunk through holes C5, and the lower ends of the transition section A and the transition section B are connected with the connecting flange through bolts.

[0024] The further improvement of the application is that the outer surface of the suction surface cover plate and the profile surface of the blade body are combined to form the outer profile surface of the whole blade, and during the test, heating pieces are arranged on the outer profile surface to simulate the real high-temperature environment of the blade, and a heat preservation layer is arranged outside the heating pieces to reduce the heat transfer from the back of the heating pieces and the surface of the blade test simulation piece to the environment in the form of convection and radiation.

[0025] The further improvement of the application is that the inner surface of the blade body, the outer surface of the spoiler A, the outer surface of the spoiler B, the outer surface of the spoiler C, the outer surface of the channel partition A, the outer surface of the channel partition B, the outer surface of the guide vane plate A and the inner surface of the suction surface cover plate together constitute a chordal serpentine cooling channel of the blade, and during operation, the cooling medium flows inside the serpentine cooling channel, so as to achieve the purpose of cooling the blade and reducing the temperature of the blade.

[0026] During the test, the cooling medium flows into from the lower connecting flange, first passes through the lofting channel inside the transition section A and the transition section B to convert the through-flow area provided by the test platform into the through-flow area required by the inlet of the test piece, then improves the uniformity of the cooling gas through the inlet extension section inside the transition section A and the transition section B, then flows into the chordal serpentine cooling channel section of the blade to heat exchange and cool the blade, and finally flows out from the outflow hole at the top of the blade.

[0027] The further improvement of the application is that the back of the blade body corresponds to the positions of the channel partition A and the channel partition B, the back of the channel partition A and the channel partition B is respectively provided with a countersunk through hole C6 and a threaded hole L6, and the blade body is fastened and connected with the channel partition A and the channel partition B through long countersunk bolts.

[0028] The further improvement of the application is that in order to facilitate the arrangement of sensors and lead-out wires inside the blade, square grooves are designed on the backs of the spoiler A, the spoiler B and the spoiler C, lead-in holes are opened in the blade body and the blade platform, and the square grooves and the outside of the blade are connected; a plurality of sensors are arranged at the bottom end surface of the square groove, that is, the measurement point area inside the blade, the sensor wires pass through the lead-in holes along the square grooves and are led out of the test simulation piece, the led-out wires pass through the lead-in channel to connect the conductive slip ring and are transmitted to the collector, so as to realize the measurement of the rotating state of the test piece.

[0029] The relative width and the relative depth of the square groove satisfy d / D < 0.2 and l / L < 0.2 respectively, wherein l and L are the width of the square groove and the width of the spoiler respectively, and d and D are the depth of the square groove and the thickness of the spoiler respectively.

[0030] Further improvement of the present application is that the spoiler A, the spoiler B and the spoiler C are provided with corresponding riding seam threaded holes Q1 at the corner junctions with the blade body, and the riding seam screws are screwed into the riding seam threaded holes Q1 for fixing when the spoiler A, the spoiler B and the spoiler C are installed; the quick release threaded holes K1 are provided at both ends of the spoiler A, the spoiler B and the spoiler C, and after the riding seam screws between the spoiler A, the spoiler B and the spoiler C and the blade body are removed, the long studs are screwed into the quick release threaded holes K1, and the spoilers can be taken out by means of the long studs.

[0031] Further improvement of the present application is that the test piece can be freely disassembled and replaced with the guide vane plate A and the guide vane plate B with corresponding structures according to the content of the test research, and the guide vane shape includes arc guide vanes, flat plate guide vanes and airfoil guide vanes; the countersunk through holes C7 and the threaded holes L7 are respectively arranged at the corresponding positions of the turning areas of the internal cooling channels of the blade body, the back of the guide vane plate A and the back of the guide vane plate B, and the blade body is fastened and connected with the guide vane plate A and the guide vane plate B by means of long countersunk bolts.

[0032] Compared with the prior art, the present application has at least the following beneficial technical effects:

[0033] 1. The gas turbine blade test piece designed in the present application not only considers the variable cross-section characteristics of the internal cooling channels under the influence of the blade profile, but also introduces the influence of the blade solid, so that the test results are closer to the actual operating conditions, compared with the rectangular channel, U-shaped channel and other basic heat exchange unit test simulation pieces currently used in tests.

[0034] 2. The gas turbine blade is divided into multiple substructures in the present application, and each substructure is independently processed, so that the high requirements of the geometric machining precision and the surface roughness of each heat transfer surface of the internal long and complex cooling channel can be met, and in addition, a special structure is designed for facilitating the arrangement of internal sensors of the blade and the wiring leading out, so that the processing difficulties, high cost and the problem that internal sensors cannot be arranged of the traditional integrated blade test piece are solved.

[0035] 3、The key structure components (including spoiler, channel partition, guide vane plate) of the internal cooling channel of the test piece designed by the application have the advantages of quick and simple disassembly and replacement, when the influence of different channel structures on the blade cooling performance is studied, only the local structure components of the internal cooling channel need to be simply replaced, without replacing the entire blade test piece, the heat transfer test under various internal cooling structure combinations can be quickly carried out, so as to provide a local structure-combination structure blade cooling performance database for blade cooling design, not only the test speed is improved, but also the test cost is greatly reduced. In addition, since a set of blade body main body, suction surface cover plate, blade platform and other unchanged test components are shared by different cooling structure test pieces, the machining error influence between different blade test pieces is reduced, and the reliability of the test is improved;

[0036] 4、The test piece designed by the application can pass the sensor cable arranged in the square groove at the back of the spoiler through the blade body main body and the blade platform, fasten the bottom connecting flange and the flange on the shaft body of the test platform, pass the lead wire channel to connect the conductive slip ring, and transmit to the collector, so as to realize the measurement of the rotating state of the test piece, and solve the problem of difficult measurement of the rotating test piece. BRIEF DESCRIPTION OF DRAWINGS

[0037] Figure 1 The figure is a disassembly schematic diagram of the gas turbine blade test piece with arc guide vanes, single connecting bridge channel partition and ball socket spoiler for the embodiment of the application;

[0038] Figure 2 The figure is a schematic diagram of the blade body structure; wherein Figure 2 (a) is a suction surface side view, Figure 2 (b) is a pressure surface view, Figure 2 (c) is a bottom view;

[0039] Figure 3 The figure is a schematic diagram of the blade platform structure; wherein Figure 3 (a) is a lower inclined view, Figure 3 (b) is an upper inclined view;

[0040] Figure 4 The figure is a schematic diagram of the suction surface cover plate structure;

[0041] Figure 5 The figure is a schematic diagram of the transition section A structure; wherein Figure 5 (a) is an upper inclined view, Figure 5 (b) is a lower inclined view;

[0042] Figure 6 The figure is a schematic diagram of the transition section B structure; wherein Figure 6 (a) is an upper inclined view, Figure 6 (b) is a lower inclined view;

[0043] Figure 7Fig. 1 is a schematic diagram of the connecting flange structure;

[0044] Figure 8 Fig. 2 is a schematic diagram of the internal cooling working medium flow path of the gas turbine blade test piece;

[0045] Figure 9 Fig. 3 is a schematic diagram of the detachable and replaceable passage partition plate structure; Figure 9 (a) Fig. 4 is a schematic diagram of the bottom of the passage partition plate, Figure 9 (b) Fig. 5 is a single connecting bridge passage partition plate, Figure 9 (c) Fig. 6 is a double connecting bridge passage partition plate;

[0046] Figure 10 Fig. 7 is a schematic diagram of the detachable and replaceable spoiler structure;

[0047] Figure 11 Fig. 8 is a schematic diagram of the local enlarged structure of the contact area between the blade body and the spoiler;

[0048] Figure 12 Fig. 9 is a schematic diagram of the internal lead hole of the blade body and the blade platform;

[0049] Figure 13 Fig. 10 is a schematic diagram of the detachable and replaceable guide vane plate structure; Figure 13 (a) Fig. 11 is a schematic diagram of the bottom of the guide vane plate, Figure 13 (b) Fig. 12 is a flat plate guide vane plate, Figure 13 (c) Fig. 13 is an arc-shaped guide vane plate.

[0050] Explanation of reference signs:

[0051] 1 is a blade body, 2 is a passage partition plate A, 3 is a passage partition plate B, 4 is a spoiler A, 5 is a spoiler B, 6 is a spoiler C, 7 is a guide vane plate A, 8 is a guide vane plate B, 9 is a suction surface cover plate, 10 is a blade platform, 11 is a transition section A, 12 is a transition section B, 13 is a connecting flange, 14 is a square groove, 15 is a lead hole, L1-L8 are threaded holes, C1-C7 are countersunk through holes, Q1 is a fillet threaded hole, and K1 is a quick release threaded hole. DETAILED DESCRIPTION

[0052] The embodiments of the present application will be described in detail below with reference to the accompanying drawings. The embodiments are based on the technical solutions of the present application and give detailed implementation manners and specific operation processes, but the protection scope of the present application is not limited to the following embodiments.

[0053] For example, Figures 1 to 7As shown, the application provides a gas turbine blade test piece with multiple detachable and replaceable channels, which comprises a blade body 1, channel partition plates A2 and B3 for partitioning the internal cavity of the blade into serpentine cooling channels, spoiler plates A4, B5 and C6 for arranging surface spoiler structures of the serpentine channels, guide vane plates A7 and B8 for arranging guide vane structures of the turning areas of the serpentine channels, a suction surface cover plate 9 for sealing the serpentine channel structure and forming an external profile together with the blade body, a blade platform 10, a connecting flange 13 for connecting the blade test piece with a test platform, and transition sections A11 and B12 for connecting the blade platform 10 with the connecting flange 13 and internally forming the lofting channel and the inlet extension section of the serpentine channel. The bottom leading edge and trailing edge areas of the blade body 1 are respectively provided with threaded holes L1, and the blade platform 10 is correspondingly provided with countersunk through holes C1, and the blade body 1 and the blade platform 10 are connected by bolt fastening. This fastening structure avoids the heat transfer test area, has the advantage of small influence on the test, and also plays the role of positioning pin, reducing the assembly difficulty. The suction surface cover plate 9 and the blade body 1 are fastened and connected by bolts through two rows of countersunk through holes C2 on both sides of the suction surface cover plate 9 and threaded holes L2 on both sides of the blade body 1. The transition sections A11 and B12 are respectively provided with a plurality of countersunk through holes C3 and threaded holes L3, and after bolt connection, the outside is cylindrical, and the inside forms the lofting channel and the inlet extension section of the serpentine channel. The middle part of the blade platform 10 is provided with a plurality of countersunk through holes C4, the upper end surfaces of the transition sections A11 and B12 are provided with a plurality of threaded holes L4, and the upper ends of the blade body 1, the transition sections A11 and B12 are connected by bolts. The lower ends of the transition sections A11 and B12 are provided with a plurality of threaded holes L5, the middle part of the connecting flange 13 is provided with a plurality of countersunk through holes C5, and the lower ends of the transition sections A11 and B12 are connected with the connecting flange 13 by bolts. The bolt holes L8 on the connecting flange 13 are used to connect the connecting flange 13 with a rotating test platform, so as to realize the rotating test state of the whole test piece.

[0054] The outer surface of the suction surface cover plate 9 and the profile surface of the blade body 1 combine to form the external profile of the whole blade. During the test, heating strips are arranged on the external profile to simulate the real high temperature environment of the blade, and a heat preservation layer is arranged outside the heating strips to reduce the heat transfer from the back of the heating strips and the surface of the blade test simulation piece to the environment through convection, radiation and other forms, so as to ensure that the blade reaches the required heat flux density. The whole blade test piece can be made of high thermal conductivity alloy materials such as aluminum alloy and copper, or the material of the real turbine to be tested.

[0055] As Figure 8As shown, the inner surface of the blade body 1, the spoiler A4, the spoiler B5, the outer surface of the spoiler C6, the passage partition plate A2, the outer surface of the passage partition plate B3, the guide vane plate A7, the outer surface of the guide vane plate 8 and the inner surface of the suction surface cover plate 9 jointly constitute a mid-chord serpentine cooling channel of the blade, and the cooling medium flows inside the serpentine cooling channel during operation, so as to achieve the purpose of cooling the blade and reducing the temperature of the blade. During the test, the cooling medium flows in from the lower connecting flange 13, first passes through the lofting channel inside the transition section A11 and the transition section B12 to convert the through-flow area provided by the test platform into the required through-flow area at the inlet of the test piece, then passes through the inlet extension section inside the transition section A11 and the transition section B12 to improve the uniformity of the cooling gas, then flows into the mid-chord serpentine cooling channel section of the blade to heat exchange and cool the blade, and finally flows out from the outlet hole at the top of the blade.

[0056] As shown in Figure 2 and Figure 9 , the test piece designed by the present application can be freely disassembled and replaced with the passage partition plate A2 and the passage partition plate B3 having a corresponding structure according to the content of the test research, and any structure required for research can be arranged on the passage partition plate A2 and the passage partition plate B3, such as a single-connection-bridge passage partition plate and a double-connection-bridge passage partition plate. The passage partition plate A2 and the passage partition plate B3 are respectively provided with a countersunk through hole C6 and a threaded hole L6 on the back thereof, and a long countersunk bolt is passed through and tightly connected with the blade body 1 and the passage partition plate A2 and the passage partition plate B3. In this embodiment, a single-connection-bridge passage structure partition plate is used.

[0057] As shown in Figure 2 , Figure 10 and Figure 12 , the test piece designed by the present application can be freely disassembled and replaced with the passage partition plate A2 and the passage partition plate B3 having a corresponding structure according to the content of the test research, and any structure required for research can be arranged on the passage partition plate A2 and the passage partition plate B3, such as a single-connection-bridge passage partition plate and a double-connection-bridge passage partition plate. The passage partition plate A2 and the passage partition plate B3 are respectively provided with a countersunk through hole C6 and a threaded hole L6 on the back thereof, and a long countersunk bolt is passed through and tightly connected with the blade body 1 and the passage partition plate A2 and the passage partition plate B3. In this embodiment, a single-connection-bridge passage structure partition plate is used.

[0058] In particular, in order to reduce the influence of the square groove on the heat transfer characteristics, make the data closer to the actual situation, the size of the square groove needs to be within a reasonable range, the relative width and the relative depth meet d / D < 0.2 and l / L < 0.2 respectively, wherein l and L are the width of the square groove and the width of the spoiler respectively, and d and D are the depth of the square groove and the thickness of the spoiler respectively. Under this special design structure, the measuring elements behind the spoiler can be freely replaced according to the content of the test research, such as temperature sensors and strain sensors, and the gas-thermal characteristics and thermal-solid characteristics of the blade can be obtained at the same time, providing the most direct and detailed data for the cooling design and safety design of the blade.

[0059] In addition, as shown in Figure 10 and Figure 11 The corner junctions of the spoiler A4, the spoiler B5 and the spoiler C6 and the blade body 1 are provided with corresponding riding thread holes Q1, and the riding screws need to be screwed into the riding thread holes Q1 for fixing when the spoiler A4, the spoiler B5 and the spoiler C6 are installed. Since the size of the spoiler is small and the mass is light, only a small size thread hole can meet the fastening requirement, and the small size riding screw is basically flush with the surface of the spoiler A4, the spoiler B5 and the spoiler C6 after being screwed into the rear end face. Therefore, compared with the traditional fastening method, the riding cooperation structure can not damage the internal flow structure of the blade, is far away from the measurement point area, has little interference to the measurement point, and greatly improves the test precision. In particular, since the spoiler A4, the spoiler B5 and the spoiler C6 need to be closely embedded with the blade body 1 to reduce the thermal resistance and the expansion difference, it is difficult to take out when the spoiler A4, the spoiler B5 and the spoiler C6 are replaced. Therefore, quick release thread holes K1 are provided at both ends of the spoiler A4, the spoiler B5 and the spoiler C6, after the riding screws between the spoiler A4, the spoiler B5 and the spoiler C6 and the blade body 1 are removed, the long studs are screwed into the quick release thread holes K1, and the spoilers can be easily taken out with the help of the long studs.

[0060] As shown in Figure 2 and Figure 13 The test piece designed by the present application can freely replace the guide vane plates A7 and B8 with corresponding structures according to the content of the test research, and the guide vane shape includes arc guide vanes, flat plate guide vanes and airfoil guide vanes and any structure needed to be researched, and the guide vane plates A7 and B8 with arc guide vane structure are adopted in the embodiment. The back of the guide vane plates A7 and B8 is provided with a countersunk through hole C7 and a threaded hole L7 at the corresponding position of the turning area of the cooling channel in the blade body 1, and the long countersunk bolt is used to penetrate the blade body 1 and the guide vane plates A7 and B8 to realize fastening connection.

[0061] The gas turbine blade test piece with multiple detachable and replaceable channels can be applied to various gas turbine blade rotating thermal solid characteristic test benches by simply replacing the transition section A11, the transition section B12 and the connecting flange 13, and a detailed test process is formulated based on the design, and the specific steps are as follows:

[0062] Firstly, the channel partition plate A2, the channel partition plate B3, the spoiler A4, the spoiler B5, the spoiler C6, the guide vane plate A7 and the spoiler B8 corresponding to the test working condition are selected;

[0063] Secondly, the sensors are arranged at the bottom area of the square groove 14 at the back of the spoiler A4, the spoiler B5 and the spoiler C6, and the sensor leads are led out of the test simulation piece from the square groove 14 through the lead hole 15 of the blade body 1 and the blade platform 10, and the sensor types include but are not limited to thermocouples and strain gauges;

[0064] Thirdly, a layer of thin high-performance thermal conductive silicone grease is evenly smeared at the interface between the spoiler A4, the spoiler B5 and the spoiler C6 and the blade body 1, and the spoiler A4, the spoiler B5 and the spoiler C6 are fixed on the blade body 1 by using the caulking screws and the caulking threaded holes Q1;

[0065] Fourthly, a layer of thin high-performance thermal conductive silicone grease is evenly smeared at the interface between the guide vane plate A7 and the guide vane plate B8 and the blade body 1, and the channel partition plate A2 and the channel partition plate B3 are fixed on the blade body 1 by using the bolts, the threaded holes L7 and the countersunk through holes C7;

[0066] Fifthly, a layer of thin high-performance thermal conductive silicone grease is evenly smeared at the interface between the channel partition plate A2 and the channel partition plate B3 and the blade body 1, and the channel partition plate A2 and the channel partition plate B3 are fixed on the blade body 1 by using the bolts, the threaded holes L6 and the countersunk through holes C6;

[0067] Sixthly, the suction surface cover plate 9 is fixed on the blade body 1 by using the bolts, the threaded holes L2 and the countersunk through holes C2;

[0068] Seventhly, the transition section A11 and the transition section B12 are assembled by using the bolts, the threaded holes L3 and the countersunk through holes C3;

[0069] Eighthly, the transition section A11 and the transition section B12 are tightly connected with the blade platform 10 by using the bolts, the threaded holes L4 and the countersunk through holes C4;

[0070] Ninthly, the blade body 1 is tightly connected with the blade platform 10 by using the bolts, the threaded holes L1 and the countersunk through holes C1;

[0071] Tenthly, the transition section A11 and the transition section B12 are tightly connected with the connecting flange 13 by using the bolts, the threaded holes L5 and the countersunk through holes C5.

[0072] Tenth, the assembled gas turbine blade test piece is fastened to the test section flange of the gas turbine blade rotating thermal solid characteristic test bench by bolts and threaded holes L8;

[0073] Twelfth, the test piece temperature load arrangement, sensor-collector ring-data acquisition instrument static and dynamic conversion connection and other test preparation work are completed, and the multi-working condition heat transfer performance test of the gas turbine blade test piece under the selected structure is carried out.

[0074] Thirteenth, after the test of the twelfth step is completed, the application of all loads is stopped, the sensor wire harness connection is disconnected, and the disassembly of the gas turbine blade test piece is completed according to the order of the tenth step to the second step (i.e., the reverse order of the installation process), and the heat transfer performance test of the gas turbine blade test piece with another cooling channel structure can be completed by repeating the first step to the twelfth step.

[0075] In summary, the present application provides a gas turbine blade test piece design with multiple detachable and replaceable channels and a test method, which can expand the research object from a basic heat exchange unit to a real gas turbine blade, and the test results are more realistic and effective. The gas turbine turbine blade is divided into multiple substructures for processing, and finally assembled into a whole blade, which not only meets the demand for processing precision, but also greatly reduces the difficulty of blade processing. The test piece is provided with a special structure for facilitating sensor arrangement and wire harness extraction, and the sensor arrangement difficulty is low. The internal cooling channel key structure components of the test piece can be replaced, which not only improves the test speed and reduces the test cost, but also reduces the processing difference between different blades and improves the reliability of the test. A complete test test process is established according to the test piece design. The present application provides a new guiding idea and solution for the design and processing of the gas turbine turbine blade test piece and the cooling performance test thereof.

Claims

1. A design and test method for a gas turbine vane test article with multi- site removable passages, characterized in that, The test piece comprises a blade body, channel partition plates A and B for partitioning the internal cavity of the blade into serpentine cooling channels, spoiler plates A, B and C for arranging serpentine channel surface spoiler structures, guide vane plates A and B for arranging serpentine channel turning area guide vane structures, suction surface cover plates for sealing the serpentine channel structure and forming an external profile together with the blade body, a blade platform, a connecting flange for connecting the blade test piece with a test platform, and transition sections A and B for connecting the blade platform and the connecting flange and internally forming a serpentine channel and an inlet extension section; The method comprises the following steps: In the first step, channel partition plates A and B, spoiler plates A, B and C, guide vane plates A and B corresponding to the test conditions are selected; In the second step, sensors are arranged at the bottom of the square groove at the back of the spoiler plates A, B and C, and the sensor leads are led out of the gas turbine blade test piece through the lead holes of the blade body and the blade platform, and the sensors are thermocouples and strain gauges; In the third step, a thin layer of high-performance heat-conducting silicone grease is evenly applied to the interface between the spoiler plates A, B and C and the blade body, and the spoiler plates A, B and C are fixed to the blade body by using the riding screws and the riding threaded holes Q1; In the fourth step, a thin layer of high-performance heat-conducting silicone grease is evenly applied to the interface between the guide vane plates A and B and the blade body, and the guide vane plates A and B are fixed to the blade body by using the bolts, threaded holes L7 and countersunk through holes C7; In the fifth step, a thin layer of high-performance heat-conducting silicone grease is evenly applied to the interface between the channel partition plates A and B and the blade body, and the channel partition plates A and B are fixed to the blade body by using the bolts, threaded holes L6 and countersunk through holes C6; In the sixth step, the suction surface cover plates are fixed to the blade body by using the bolts, threaded holes L2 and countersunk through holes C2; In the seventh step, the transition sections A and B are assembled by using the bolts, threaded holes L3 and countersunk through holes C3; In the eighth step, the transition sections A and B are fastened to the blade platform by using the bolts, threaded holes L4 and countersunk through holes C4; In the ninth step, the blade body is fastened to the blade platform by using the bolts, threaded holes L1 and countersunk through holes C1; In the tenth step, the transition sections A and B are fastened to the connecting flange by using the bolts, threaded holes L5 and countersunk through holes C5; In the eleventh step, the assembled gas turbine blade test piece is fastened to the test section connecting flange of the gas turbine blade rotating thermal solid characteristic test bench by using the bolts and threaded holes L8; In the twelfth step, the temperature load arrangement of the test piece, the dynamic-static conversion connection test preparation work of the sensors-collecting rings-data acquisition instruments, and the multi-condition heat transfer performance test of the gas turbine blade test piece under the selected structure are completed; In the thirteenth step, after the test in the twelfth step is completed, the application of all loads is stopped, the sensor lead connection is disconnected, and the disassembly of the gas turbine blade test piece is completed in the order of the eleventh step to the twelfth step.

2. The design and testing method of a gas turbine vane test article with multi- site replaceable passages according to claim 1, characterized in that, Threaded holes L1 are arranged at the front and trailing edge regions of the bottom of the blade body, and counterbores C1 are arranged on the blade platform.

3. The design and testing method of a gas turbine vane test article with multi- site replaceable passages of claim 1, wherein, The suction surface cover plate and the blade body are fastened and connected by bolts through the two rows of counterbores C2 on the two sides of the suction surface cover plate and the threaded holes L2 on the two sides of the blade body.

4. The design and testing method of a gas turbine vane test article with multi- site replaceable passages of claim 1, wherein, The transition section A and the transition section B are respectively provided with counterbores C3 and threaded holes L3, and after being connected by bolts, the outside is a cylinder, the inside is a lofting channel and an inlet extension section in a serpentine shape; the middle of the blade platform is provided with counterbores C4, the upper end surfaces of the transition section A and the transition section B are provided with threaded holes L4, and the upper ends of the blade body, the transition section A and the transition section B are connected by bolts; the lower ends of the transition section A and the transition section B are provided with threaded holes L5, the middle of the connecting flange is provided with counterbores C5, and the lower ends of the transition section A and the transition section B are connected to the connecting flange by bolts.

5. The design and testing method of a gas turbine vane test article with multi- site replaceable passages of claim 1, wherein, The outer surface of the suction surface cover plate and the airfoil surface of the blade body combine to form the outer profile of the entire blade, and during the test, heating strips are arranged on the outer profile to simulate the actual high-temperature environment of the blade, and a heat preservation layer is arranged outside the heating strips to reduce the heat transfer from the back of the heating strips and the surface of the turbine blade test piece to the environment through convection and radiation.

6. The design and testing method of a gas turbine vane test article with multi- site replaceable passages of claim 1, wherein, The inner surface of the blade body, the outer surfaces of the spoiler A, the spoiler B and the spoiler C, the outer surfaces of the channel partition A and the channel partition B, the outer surfaces of the guide vane plate A and the guide vane plate B, and the inner surface of the suction surface cover plate together form a mid-chord serpentine cooling channel of the blade, and during operation, the cooling medium flows inside the serpentine cooling channel, thereby achieving the purpose of cooling the blade and reducing the temperature of the blade; During the test, the cooling medium flows from the lower connecting flange, first passes through the lofting channel inside the transition section A and the transition section B to convert the through-flow area provided by the test platform into the required through-flow area at the inlet of the test piece, then passes through the inlet extension section inside the transition section A and the transition section B to improve the uniformity of the cooling gas, then flows into the mid-chord serpentine cooling channel section to heat exchange and cool the blade, and finally flows out from the outflow hole at the top of the blade.

7. The design and testing method of a gas turbine vane test article with multi- site replaceable passages of claim 1, wherein, The back of the blade body corresponds to the positions of the channel partition A and the channel partition B, and the back of the channel partition A and the channel partition B is respectively provided with a counterbores C6 and a threaded hole L6, and the blade body is fastened and connected with the channel partition A and the channel partition B by penetrating and fastening with long counterbores.

8. The design and testing method of a gas turbine vane test article with multi- site replaceable passages of claim 1, wherein, In order to facilitate the arrangement of sensors and lead-out wires inside the blade, square grooves are designed on the back of the spoiler A, the spoiler B and the spoiler C, and lead-in holes are arranged inside the blade body and the blade platform to connect the square grooves on the back of the spoilers and the outside of the blade; the bottom end surface of the square groove, i.e. the measurement point area inside the blade, is arranged with multiple sensors, and the sensor wires pass through the lead-in holes along the square grooves and are led out of the turbine blade test piece, the led-out wires pass through the lead-in channel to connect the conductive slip ring and are transmitted to the collector, thereby realizing the measurement of the rotating state of the test piece. the relative width and the relative depth of the square groove satisfy d / D < 0.2, l / L < 0.2, wherein l 、 L are the width of the square groove and the width of the spoiler, respectively, d 、 D are the depth of the square groove and the thickness of the spoiler, respectively.

9. The design and testing method of a gas turbine vane test article with multi- site replaceable passages of claim 1, wherein, The spoiler A, the spoiler B and the spoiler C are provided with corresponding riding seam threaded holes Q1 at the corner junctions with the blade body, and the riding seam screws are screwed into the riding seam threaded holes Q1 to fix the spoiler A, the spoiler B and the spoiler C during installation; the quick release threaded holes K1 are provided at both ends of the spoiler A, the spoiler B and the spoiler C, and after the riding seam screws between the spoiler A, the spoiler B and the spoiler C and the blade body are removed, the long studs are screwed into the quick release threaded holes K1, and the spoilers can be taken out by means of the long studs.

10. The design and testing method of a gas turbine vane test article with multi- site replaceable passages of claim 1, wherein, The test piece can freely disassemble and replace the guide vane plate A and the guide vane plate B with corresponding structures according to the content of the test research, and the guide vane shape includes arc-shaped guide vanes, flat plate guide vanes and airfoil guide vanes; the inside cooling channel of the blade body is provided with a countersunk through hole C7 and a threaded hole L7 at the corresponding position of the turning area, respectively at the back of the guide vane plate A and the guide vane plate B, and the blade body is fastened and connected with the guide vane plate A and the guide vane plate B by means of long countersunk bolts.

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