Turbine blade double-layer wall air cooling structure simulation piece, test fixture and test system

Abstract

The invention discloses a turbine blade double-layer wall air cooling structure simulation piece, a test fixture and a test system, and belongs to the technical field of test. The turbine blade double-layer wall air cooling structure simulation part is designed for a turbine blade based on a double-layer wall air cooling structure, an inner-layer and outer-layer double-wall structural arrangement is adopted, cooling airflow enters an overflowing clamping cavity from an impact hole and then firstly impacts on the inner wall face of an outer-layer wall, jet flow impact cooling is formed, and the cooling effect is achieved. Then the cooling airflow bypasses the turbulent flow columns and then flows out from air film holes distributed in the outer layer wall, and a thin air film is formed on the outer surface of the outer layer wall; the air cooling flow mode is combined with external fuel gas impact, so that a simulation test of the double-wall air cooling structure under an approximate service condition can be realized. The test fixture and the test system are matched with the turbine blade double-layer wall air cooling structure simulation piece, and can meet the service test requirement of the turbine blade double-layer wall air cooling structure simulation piece close to the actual working condition on the basis of stably clamping the simulation piece.

Description

Technical Field

[0001] The present invention belongs to the field of testing technology, and relates to a service behavior test of a double-walled air-cooled structure simulation part of an aircraft engine turbine blade, and in particular to a double-walled air-cooled structure simulation part of a turbine blade and a test fixture and a test system adapted therefor. Background Art

[0002] With the continuous development of advanced aircraft engines, the temperature before the turbine continues to increase, and higher requirements are also placed on the cooling design of the core hot end component, the turbine blade. The turbine blade adopts a double-wall air-cooled structure, coupled with multiple cooling methods such as impact and air film, giving full play to the role of internal impact jet enhanced heat exchange and air film hole overflow enhanced heat exchange. Compared with traditional cooling methods, the cooling efficiency of the turbine blade is significantly improved.

[0003] Testing and analyzing the near-operating service behavior of materials through characteristic cooling structure simulation parts has become an important direction for the integrated development of multidisciplinary disciplines such as turbine blade design and materials. However, the cooling structure of turbine blades based on double-wall air-cooling structures is complex. It is difficult to reproduce the actual service state by evaluating the blade and material performance through well-known standard performance specimens, which reduces the test accuracy. Therefore, it is necessary to specially propose a double-wall air-cooling structure simulation part that is compatible with turbine blades based on double-wall air-cooling structures to meet the near-operating service behavior test requirements of turbine blades based on double-wall air-cooling structures.

[0004] In addition, due to design limitations, the current testing and clamping system is unable to adapt to the above-mentioned double-walled air-cooled structure simulation parts and realize the service test of the double-walled air-cooled structure simulation parts under conditions close to the actual working conditions. Based on this, the present invention also proposes a test fixture and a test system adapted to the above-mentioned double-walled air-cooled structure simulation parts of the turbine blades to overcome the above-mentioned difficulties. Summary of the invention

[0005] The purpose of the present invention is to provide a double-wall air-cooled structure simulation part of a turbine blade and a test fixture and a test system adapted thereto, which can meet the requirements of testing the near-operating condition service behavior of the double-wall cooling structure, and realize the service test of the double-wall air-cooled structure simulation part under conditions close to the actual operating conditions, so as to solve the problems existing in the above-mentioned prior art.

[0006] To achieve the above object, the present invention provides the following solutions:

[0007] The present invention provides a double-walled air-cooled structure simulation part of a turbine blade, comprising an inner wall, an outer wall, an impact hole, an air film hole and a spoiler column, wherein the inner wall and the outer wall are parallel and spaced apart to form a flow cavity between the inner wall and the outer wall, the inner wall is provided with a plurality of impact holes connected to the flow cavity, the outer wall is provided with a plurality of air film holes connected to the flow cavity, and any of the air film holes is staggered with any of the impact holes; the inner wall and the outer wall are connected by a plurality of spoiler columns, and any of the spoiler columns is staggered with any of the air film holes and any of the impact holes; the peripheries of the inner wall and the outer wall are provided with a sealing structure that can keep the periphery of the flow cavity closed during a test, so that the fluid entering the flow cavity through the impact hole during the test can only be discharged from the air film hole.

[0008] In one embodiment, the sealing structure 1 is a side wall structure disposed at a peripheral position between the inner wall and the outer wall;

[0009] Alternatively, the sealing structure 1 is a groove or a protrusion located on the periphery of the inner wall and the outer wall, and the specimen clamping position of the test fixture is provided with a sealing structure 2 that is seal-matched with the groove or the protrusion, and the sealing structure 2 can be sealed with the sealing structure 1 during the test to keep the periphery of the flow-through cavity closed during the test.

[0010] In one embodiment, the inner wall and the outer wall are of the same shape and size, and are rectangular or circular; at least one of the impact hole and the air film hole is a circular hole, a square hole or a fan-shaped hole; and the spoiler column is cylindrical or prismatic.

[0011] The present invention provides a test fixture adapted to the above-mentioned turbine blade double-wall air-cooled structure simulation part, which can be adapted to clamp the turbine blade double-wall air-cooled structure simulation part described in claim 1, and the test fixture comprises a first clamping part and a second clamping part assembled relatively, and the first clamping part and the second clamping part are detachably connected through a clamp locking part; wherein:

[0012] The first clamping member and the second clamping member are each provided with a half cavity, and after the first clamping member and the second clamping member are assembled, the half cavities of the two are connected to each other to form a clamp cavity, and the side walls of the first clamping member and / or the second clamping member are provided with a fluid passage connected to the clamp cavity;

[0013] A mounting notch communicating with the half cavity is provided on one side wall of the first clamping member and the second clamping member. After the first clamping member and the second clamping member are assembled, the mounting notches of the two are butted to form a clamping notch adapted to the outer contour of the turbine blade double-wall air-cooling structure simulation member. After the turbine blade double-wall air-cooling structure simulation member is installed in the clamping notch, the impact hole of the turbine blade double-wall air-cooling structure simulation member is communicated with the fixture cavity.

[0014] The fluid port is used for externally connecting the test fluid so as to introduce the test fluid into the double-walled air-cooled structure simulation part of the turbine blade installed on the clamping slot through the fixture cavity.

[0015] In one embodiment, the sealing structure 1 is a groove or a protrusion located on the periphery of the inner wall and the outer wall, and the inner ring of the clamping groove is provided with a sealing structure 2 that is seal-matched with the groove or the protrusion. The sealing structure 2 can be sealed with the sealing structure 1 during the test to keep the periphery of the flow clamp cavity closed during the test.

[0016] In one embodiment, the first sealing structure is a groove located at the periphery of the inner wall and the outer wall, and the second sealing structure is a protrusion arranged on the inner circle of the clamping groove, and the top of the protrusion is a sharp edge.

[0017] In one embodiment, the other side walls of the first clamping member and the second clamping member are each provided with a detection notch connected to the half cavity. After the first clamping member and the second clamping member are assembled, the detection notches of the two are butted together to form a detection window, and a quartz plate is embedded in the detection window.

[0018] In one embodiment, an annular convex ridge is provided in the middle of the outer circumference of the quartz plate, and an annular mounting groove which is inserted and matched with the annular convex ridge is provided in the inner circle of the detection window.

[0019] The present invention provides a test system, comprising the above-mentioned turbine blade double-wall air-cooled structure simulation component and the above-mentioned test fixture.

[0020] In one embodiment, the test system further includes a fixture connecting plate and a fluid delivery tube, wherein a fluid flow channel is opened in the fixture connecting plate, a plug-in boss is provided at one end of the fluid flow channel, the test fixture is provided on the plug-in boss and is detachably connected to the plug-in boss through the fixture locking piece, and the fluid port is interconnected with the fluid flow channel; the fluid delivery tube is connected to the other end of the fluid flow channel, and the fluid delivery tube is used to introduce the test fluid into the fixture cavity.

[0021] Compared with the prior art, the present invention has achieved the following technical effects:

[0022] The double-wall air-cooled structure simulation part of the turbine blade proposed in the present invention is designed for the turbine blade based on the double-wall air-cooled structure. Its structural design is reasonable and adopts the structural arrangement of inner and outer double walls. After the cooling airflow enters the flow cavity from the impact hole, it first hits the inner wall surface of the outer wall to form jet impact cooling. Then the cooling airflow bypasses the spoiler column and flows out from the air film holes distributed on the outer wall to form a thin air film on the outer surface of the outer wall. This air-cooling flow mode is combined with external combustion gas impact to realize simulation tests of the double-wall air-cooled structure under approximate service conditions, which overcomes the problem that the existing known standard performance samples cannot be used to evaluate the actual service status of the double-wall turbine blade material performance.

[0023] The test fixture and test system proposed in the present invention are adapted to the double-wall air-cooled structure simulation part of the turbine blade, and can meet the service test requirements of the double-wall air-cooled structure simulation part of the turbine blade under conditions close to the actual working conditions on the basis of stably clamping the simulation part. This overcomes the problem that the current testing and clamping system cannot be adapted to the above-mentioned double-wall air-cooled structure simulation part due to design limitations, and realizes the service test of the double-wall air-cooled structure simulation part under conditions close to the actual working conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0025] Figure 1 It is an overall structural diagram of a double-walled air-cooled structure simulation part of a turbine blade disclosed in an embodiment;

[0026] Figure 2 is an overall structural diagram of a test fixture disclosed in an embodiment at a first viewing angle;

[0027] Figure 3 is an overall structural diagram of a test fixture disclosed in an embodiment at a second viewing angle;

[0028] Figure 4 A test fixture disclosed in an embodiment is shown in an exploded structural diagram;

[0029] Figure 5 for Figure 4 A schematic diagram of the enlarged structure at A in the middle;

[0030] Figure 6 is an overall structural diagram of a test system disclosed in an embodiment;

[0031] Figure 7 is a cross-sectional structural diagram of a test system disclosed in an embodiment;

[0032] Figure 8 A structural diagram of a fixture connecting plate and a fluid delivery pipe in a test system disclosed in an embodiment.

[0033] In the figure, the reference numerals are:

[0034] 1. Turbine blade double-wall air-cooled structure simulation part; 11. Inner wall; 12. Outer wall; 13. Spoiler column; 14. Impact hole; 15. Air film hole; 16. Groove;

[0035] 2. Test fixture; 21. First clamping piece; 22. Second clamping piece; 23. Clamp sleeve; 24. Clamp locking bolt; 25. Clamp cavity; 26. Fluid passage; 27. Clamping notch; 28. Protrusion; 29. ​​Sharp edge; 210. Platform; 211. Detection window; 212. Quartz plate; 213. Annular convex edge; 214. Annular mounting groove;

[0036] 3. Test system; 31. Fixture connecting plate; 32. Fluid delivery pipe; 33. Fluid flow channel; 34. Plug-in boss; 35. Tooling positioning bolt; 36. Tooling plate; 37. Tooling nut; 38. Tooling rod. DETAILED DESCRIPTION

[0037] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0038] One of the purposes of the present invention is to provide a double-wall air-cooled structure simulation part of a turbine blade, which can meet the requirements of near-operating condition service behavior testing of the double-wall cooling structure, and realize service testing of the double-wall air-cooled structure simulation part under conditions close to the actual operating conditions, so as to solve the problems existing in the prior art.

[0039] Another object of the present invention is to provide a test fixture adapted to the above-mentioned turbine blade double-wall air-cooled structure simulation part.

[0040] Another object of the present invention is to provide a testing system, comprising the above-mentioned turbine blade double-wall air-cooled structure simulation part and the above-mentioned testing fixture.

[0041] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0042] Example 1

[0043] like Figure 1 As shown, the present embodiment provides a double-walled air-cooled structure simulation part 1 of a turbine blade, which includes an inner wall 11, an outer wall 12 and a spoiler column 13, wherein the inner wall 11 and the outer wall 12 are parallel and spaced apart to form a flow cavity between the inner wall 11 and the outer wall 12, a plurality of impact holes 14 connected to the flow cavity are opened on the inner wall 11, a plurality of air film holes 15 connected to the flow cavity are opened on the outer wall 12, and any air film hole 15 and any impact hole 14 are staggered, and preferably completely staggered, that is, the hole opening of any air film hole 15 on the surface of the outer wall 12 on one side of the flow cavity and the hole opening of any impact hole 14 on the surface of the inner wall 11 on the other side of the flow cavity, have no overlap in projection along the normal direction of the inner and outer wall surfaces. The inner wall 11 and the outer wall 12 are connected by a plurality of spoiler columns 13, and any spoiler column 13 is staggered with any air film hole 15 and any impact hole 14, that is, the spoiler column 13 is arranged at a non-porous position of the inner wall 11 and the outer wall 12; the periphery of the inner wall 11 and the outer wall 12 is provided with a sealing structure 1 that can keep the periphery of the flow cavity closed during the test, so that the fluid entering the flow cavity through the impact hole 14 during the test can only be discharged from the air film hole 15. The double-walled air-cooled structure simulator 1 of the turbine blade can be used to simulate the cold air circulation state of the double-walled air-cooled structure in the working state of the aircraft engine turbine blade, generally combined with a high-temperature gas impact flame, to simulate the large temperature gradient state of the external high-temperature flame flow coupled with the internal cooling airflow during the service process of the real blade, and can realize the thermal-fluid-solid multidisciplinary coupling test research of the double-walled air-cooled structure under the simulated service environment. During the test, after the cold air enters the flow cavity through the impact hole 14, it first impacts the wall surface of the outer wall 12 to achieve jet impact cooling; then, the cold air flows in the flow cavity, and the turbulence effect of the turbulent column 13 can enhance the convective heat exchange effect in the cavity; finally, all the cold air flows out from the air film holes 15 distributed on the outer wall 12, and forms a thin air film on the outer surface of the outer wall 12, thereby effectively isolating the direct contact between the high-temperature combustion gas and the blade simulation in the test, and reducing the surface temperature of the blade simulation. The structural design of the double-walled air-cooled structure simulation part 1 of the turbine blade can accurately guide the flow direction of the cooling airflow, thereby realizing the service test of the double-walled blade simulation part under conditions close to the actual working conditions.

[0044] In one embodiment, the preferred sealing structure 1 is a groove or a protrusion located at the periphery of the inner wall 11 and the outer wall 12. Accordingly, the specimen clamping position of the test fixture is provided with a sealing structure 2 that is seal-matched with the groove or the protrusion. The sealing structure 2 can be seal-matched with the sealing structure 1 during the test process to keep the outer periphery of the flow-through cavity closed during the test process. The preferred sealing structure 1 of this embodiment is a groove located at the periphery of the inner wall 11 and the outer wall 12, and the groove is preferably a groove 16. The groove 16 is formed in the interval between the inner wall 11 and the outer wall 12 and is arranged close to the outer periphery of the inner wall 11 and the outer wall 12. Based on this, the sealing structure 2 can be a protrusion that is seal-plugged with the groove 16 to ensure that after the double-walled air-cooled structure simulation part 1 of the turbine blade is clamped at the specimen clamping position of the test fixture, the outer periphery of the flow-through cavity is closed by the sealing structure 2.

[0045] In one embodiment, the inner wall 11 and the outer wall 12 are preferably of the same shape and size, specifically, rectangular or circular.

[0046] In one embodiment, the turbine blade double-wall air-cooled structure simulation part 1 is preferably a rectangular block as a whole, and accordingly, the inner wall 11 and the outer wall 12 are both as follows Figure 1 To ensure uniform heating, the length and width of the inner wall 11 and the outer wall 12 are preferably less than 20 mm, preferably 15 mm to 20 mm, and the thickness of the inner wall 11 and the outer wall 12 is preferably 0.8 mm.

[0047] In one embodiment, the spoiler column 13 can be a cylindrical, prismatic, elliptical column or other spoiler column shape, preferably the spoiler column 13 is cylindrical. As a further preferred embodiment, the diameter of the spoiler column 13 is 1 mm, and the axial length (column height, i.e., the interval between the inner and outer walls) is 1 mm; the array arrangement of the spoiler columns 13 is in a sequential arrangement, with the number of rows and columns being 5 and 6 respectively, and the row and column spacing of the spoiler column 13 array (i.e., the row and column spacing between the center points of the spoiler columns) is 3 mm.

[0048] In one embodiment, at least one of the impact hole 14 and the air film hole 15 is a circular hole, a square hole or a fan-shaped hole. At least one of the impact hole 14 and the air film hole 15 is set as a straight hole or an inclined hole. As a preferred embodiment, the impact hole 14 preferably adopts a circular straight hole, and the air film hole 15 preferably adopts a circular straight hole or a circular inclined hole. Any cross-section of the circular straight hole and the circular inclined hole is circular. The only difference between the two is that the axis of the circular straight hole is perpendicular to the inner and outer walls, and the axis of the circular inclined hole is arranged at an angle to the inner and outer walls. As a further preferred embodiment, the impact hole 14 is set as a circular straight hole with a hole diameter of 1 mm, and the air film hole 15 is set as a circular inclined hole with a hole diameter of 0.5 mm. The inclination direction and angle are rotated 45° with the overall length direction of the double-walled air-cooled structure simulator 1 as the axis (that is, the axis of the air film hole 15 is arranged at a 45-degree angle to the wall thickness direction of the inner and outer walls). The impact hole 14 is opened on the inner wall 11, and the center position of the opening is located in the middle of the column center line of two adjacent (including row-facing and column-facing) spoiler columns 13 in the array of spoiler columns in the row; the air film hole 15 is opened on the outer wall 12, and the center of the opening of the air film hole 15 on the surface of the outer wall 12 on one side of the flow cavity is located in the middle of the column center line of two adjacent oblique spoiler columns 13 in the array of spoiler columns in the row.

[0049] The above-mentioned turbine blade double-wall air-cooled structure simulation part 1 is designed for turbine blades based on a double-wall air-cooled structure. It adopts an inner and outer double-wall structural arrangement. After the cooling airflow enters the flow cavity from the impact hole 14, it first hits the inner wall surface of the outer wall 12 to form jet impact cooling. Then the cooling airflow bypasses the spoiler column 13 and flows out from the air film holes 15 distributed on the outer wall 12, and forms a thin air film on the outer surface of the outer wall 12. This air-cooling flow mode is combined with external combustion gas impact to realize a simulation test of the double-wall air-cooled structure under approximate service conditions, which overcomes the problem that the existing known standard performance samples cannot be used to evaluate the actual service status of the double-wall turbine blade material performance.

[0050] Example 2

[0051] The present embodiment provides a turbine blade double-wall air-cooled structure simulation part 1, which differs from the embodiment 1 only in that the sealing structure 1 does not need to cooperate with the sealing structure 2 to achieve sealing. The sealing structure 1 is a side wall structure arranged at the peripheral position between the inner wall 11 and the outer wall 12, that is, the turbine blade double-wall air-cooled structure simulation part 1 has its own outer side wall. No matter where the clamping position of the turbine blade double-wall air-cooled structure simulation part 1 is, as long as the impact hole 14 of the turbine blade double-wall air-cooled structure simulation part 1 can introduce the test fluid, the turbine blade double-wall air-cooled structure simulation part 1 can ensure that the periphery of the flow clamping cavity is always in a closed state through the sealing structure 1, which is the side wall structure.

[0052] Example 3

[0053] like Figure 2 to Figure 5 As shown, this embodiment proposes a test fixture 2, which can be adapted to clamp the turbine blade double-wall air-cooled structure simulation part 1 of embodiment 1. The test fixture 2 mainly includes a first clamping member 21 and a second clamping member 22 that are assembled relatively, and the first clamping member 21 and the second clamping member 22 are detachably connected through a clamp locking member; wherein, a half cavity is opened in each of the first clamping member 21 and the second clamping member 22, and after the first clamping member 21 and the second clamping member 22 are assembled, the half cavities of the two are connected to each other to form a fixture cavity 25, and a fluid passage 26 connected to the fixture cavity 25 is opened on the side wall of the first clamping member 21 and / or the second clamping member 22, as shown in FIG. Figure 4 and Figure 7 As shown, the bottom of the half cavity of the first clamp 21 and the second clamp 22 are both provided with a half opening. After the first clamp 21 and the second clamp 22 are assembled, the half openings of the two are butted to form a closed annular fluid opening 26. One side wall of the first clamp 21 and the second clamp 22 is provided with a mounting notch connected to the half cavity. After the first clamp 21 and the second clamp 22 are assembled, the mounting notches of the two are butted to form a clamping notch 27 adapted to the outer contour of the turbine blade double-wall air-cooled structure simulation part 1. After the turbine blade double-wall air-cooled structure simulation part 1 is installed and clamped in the clamping notch 27, the impact hole 14 of the turbine blade double-wall air-cooled structure simulation part 1 is connected to the fixture cavity 25; the fluid opening 26 is used for external test fluid, so as to introduce the test fluid into the turbine blade double-wall air-cooled structure simulation part 1 installed on the clamping notch 27 through the fixture cavity 25. The above-mentioned test fluid is mostly cooling gas.

[0054] In one embodiment, the double-walled air-cooled structure simulation part 1 of the turbine blade is assembled on the clamping slot 27 on the side wall of one side of the test fixture 2. In order to prevent the cold air from directly flowing out from the assembly gap between the edge of the blade simulation part and the clamping slot 27, the inner ring of the clamping slot 27 is provided with a sealing structure 2 that is sealed and adapted to the groove 16 (i.e., the sealing structure 1). The sealing structure 2 is a protrusion 28 arranged on the inner ring of the clamping slot 27.

[0055] In one embodiment, the groove 16 is preferably an annular groove, and the protrusion 28 is set as an annular protrusion that matches the annular groove. Among them, the protrusion 28 is preferably a sharp-edged protrusion with a sharp edge 29 on the top, and the cross-section of the entire protrusion 28 is preferably an isosceles triangle with an acute apex angle. The maximum width of the protrusion 28 (i.e., the width of the base) is preferably smaller than the groove width of the groove 16, for example, the maximum width of the protrusion 28 is set to 0.8 to 0.9 times the length of the groove width of the groove 16; the height of the protrusion 28 is preferably 0.8 mm to 1.2 mm, and the groove depth of the groove 16 is preferably the same as the height of the protrusion 28, so that after the protrusion 28 is assembled in the groove 16, the protrusion 28 can fix the position of the blade simulation part from the periphery and seal the groove 16 at the same time. It should be noted that the depth of the above-mentioned groove 16 is determined by the setting position of the spoiler column 13. The outermost side wall of the spoiler column 13 located in the outermost circle between the inner and outer walls determines the groove depth position of the groove 16. Generally, the spoiler columns 13 located in the outermost circle between the inner and outer walls are evenly arranged along the axial direction. The outer contour formed by all the spoiler columns 13 in the outermost circle is the shape of the groove 16. The groove 16 can be a circular ring or a rectangular ring.

[0056] In one embodiment, both ends of the bottom edge of the protrusion 28 extend horizontally to both sides to form a platform 210, such as Figure 4 and Figure 5 As shown, the platform 210 is a planar structure. After the protrusion 28 and the groove 16 are inserted into place (that is, after the top edge of the protrusion 28 contacts the spoiler column 13 at the bottom of the groove 16), the outer wall surfaces of the inner wall 11 and the outer wall 12 are respectively matched with the gaps of the platforms 210 on both sides, and the gap tolerance is preferably +0.05; at the same time, the width of the platform 210 is preferably slightly larger than the thickness of the inner wall 11 and the outer wall 12.

[0057] Based on the assembly form of the above-mentioned turbine blade double-wall air-cooled structure simulation part 1 and the clamping groove 27, it can be ensured that after the turbine blade double-wall air-cooled structure simulation part 1 is assembled, the entire outer surface of its inner wall 11 is exposed to the flow clamp cavity.

[0058] In one embodiment, the other side walls of the first clamping member 21 and the second clamping member 22 are both provided with a detection notch connected to the half cavity. After the first clamping member 21 and the second clamping member 22 are assembled, the detection notches of the two are butted to form a detection window 211, and a quartz plate 212 is embedded in the detection window 211. The main function of the quartz plate 212 is to transmit infrared heat signals, so that the infrared probe can be used to detect the temperature of the blade simulation member away from the flame surface (i.e., the outer surface of the inner wall 11).

[0059] In one embodiment, in order to realize the installation of the quartz plate 212 and prevent the cold air from leaking from the gap between the edge of the quartz plate 212 and the detection window 211, it is preferred that an annular convex ridge 213 is provided in the middle of the outer periphery of the quartz plate 212, and an annular installation groove 214 is provided in the inner circle of the detection window 211 to be inserted and adapted to the annular convex ridge 213. Specifically, the quartz plate 212 as a whole needs to be designed as a three-stage cylinder with a protruding part in the middle, such as Figure 4 As shown, the quartz plate 212 is in the shape of a thin sheet, and the partially protruding cylinder in the middle is the aforementioned annular ridge 213 . The diameters of the cylinders at both ends of the annular ridge 213 are the same and are both smaller than the outer diameter of the annular ridge 213 .

[0060] In one embodiment, the detection window 211 is preferably arranged coaxially with the clamping notch 27. Taking the clamping notch 27 as a rectangular notch as an example, the inner diameter of the detection window 211 (i.e., the outer diameter of the quartz plate 212) is preferably larger than the diagonal length of the clamping notch 27 (i.e., the turbine blade double-wall air-cooled structure simulation part 1) to ensure that the observation field of the simulation part is large enough. The annular convex ridge 213 of the quartz plate 212 is generally matched with the annular mounting groove 214. Considering that the size of the quartz plate 212 is not easy to process, the clearance tolerance of the annular mounting groove 214 is preferably the design size of the quartz plate 212 + 0.5.

[0061] In one embodiment, the quartz plate 212 and the turbine blade double-wall air-cooled structure simulation part 1 are respectively embedded in the middle of the two side walls of the test fixture 2, and the overall width of the test fixture 2 is greater than the major diameter of the quartz plate 212. The overall height of the test fixture 2 should ensure that the distance from the double-wall simulation part on both sides of the fixture in the height direction is at least 20 mm to facilitate the assembly of the fixture sleeve 23. The overall thickness of the test fixture 2 is determined by the wall thickness of the double-wall clamping port, the wall thickness of the quartz plate installation port, and the fixture cavity spacing. There is no specific size requirement except the cavity spacing.

[0062] In one embodiment, the overall height of the test fixture 2 is preferably 60 mm. The cavity spacing of the test fixture 2 should be greater than 2 mm, preferably 3 mm, and the overall thickness of the test fixture 2 is determined by the wall thickness of the first clamping member 21 and the second clamping member 22 and the thickness of the flow-through clamping cavity.

[0063] In one embodiment, in the preferred test fixture 2, the fixture cavity 25 is arranged toward the lower end of the test fixture 2, and the upper end of the test fixture 2 is a solid structure, and this design can ensure the structural strength of the test fixture 2. The fluid passage 26 is opened on the bottom wall of the first clamping member 21 and the second clamping member 22.

[0064] In one embodiment, the clamp locking member includes a clamp sleeve 23, a clamp locking bolt 24 and a clamp locking nut. Figure 2 to Figure 4As shown, a pair of clamp sleeves 23 are provided, which are detachably sleeved on the outer sides of the first clamp member 21 and the second clamp member 22. After the first clamp member 21 and the second clamp member 22 are docked in place, the two clamp sleeves 23 are docked, and the two clamp sleeves 23 are locked and connected by the clamp locking bolts 24 and the clamp locking nuts, so that the first clamp member 21 and the second clamp member 22 are clamped by the two clamp sleeves 23, so as to achieve the purpose of locking the first clamp member 21 and the second clamp member 22.

[0065] The above-mentioned test fixture 2, through the design of the clamping slot 27, can ensure that the cooling gas entering the fixture cavity 25 can flow in the turbine blade double-wall air-cooled structure simulation part 1 according to the airflow flow mode of Example 1 while achieving a firm clamping of the simulation part.

[0066] After assembling the double-walled air-cooled structure simulation part 1 of the turbine blade and the quartz plate 212, the fluid port 26 at the lower end of the test fixture 2 is connected to the cooling airflow. After the cooling airflow enters the flow cavity from the impact hole 14 of the double-walled air-cooled structure simulation part 1 of the turbine blade, it first hits the inner wall surface of the outer wall 12 to form jet impact cooling, and then the cooling airflow bypasses the spoiler column 13 and flows out from the air film holes 15 distributed on the outer wall 12, and forms a thin air film on the outer surface of the outer wall 12; this air-cooling flow mode combined with external gas impact can realize the simulation test of the double-walled air-cooled structure under the approximate service condition. The above-mentioned test fixture 2 is adapted to the double-walled air-cooled structure simulation part 1 of the turbine blade, and can meet the service test requirements of the double-walled air-cooled structure simulation part 1 of the turbine blade under conditions close to the actual working conditions on the basis of stably clamping the simulation part. It overcomes the problem that the current testing and clamping system cannot be adapted to the above-mentioned double-walled air-cooled structure simulation part due to design limitations, and realizes the service test of the double-walled air-cooled structure simulation part under conditions close to the actual working conditions.

[0067] Example 4

[0068] like Figure 6 to Figure 8As shown, this embodiment proposes a test system 3, including the turbine blade double-wall air-cooled structure simulation part 1 of embodiment 1 and the test fixture 2 of embodiment 3. Remove the clamp locking bolts 24, separate the first clamp 21 and the second clamp 22 from each other, then embed the turbine blade double-wall air-cooled structure simulation part 1 with matching size specifications into the installation notch of the first clamp 21, and embed the quartz plate 212 into the detection notch of the first clamp 21, then align the second clamp 22 with the first clamp 21, and use the clamping groove 27 and the detection window 211 formed by assembly to respectively wrap the turbine blade double-wall air-cooled structure simulation part 1 and the quartz plate 212, and then after the clamp sleeve 23 is used to cover the first clamp 21 and the second clamp 22, use the clamp locking bolts 24 to lock the first clamp 21 and the second clamp 22, so as to achieve the sealing clamping of the turbine blade double-wall air-cooled structure simulation part 1 and the quartz plate 212 by the first clamp 21 and the second clamp 22.

[0069] In one embodiment, the test system 3 also includes a fixture connecting plate 31 and a fluid delivery tube 32. A fluid flow channel 33 is opened in the fixture connecting plate 31. A plug-in boss 34 is provided at one end of the fluid flow channel 33. The test fixture 2 is set on the plug-in boss 34 and is detachably connected to the plug-in boss 34 through a fixture locking piece. The fluid port 26 is interconnected with the fluid flow channel 33. The fluid delivery tube 32 is connected to the other end of the fluid flow channel 33, and the fluid delivery tube 32 is used to introduce the test fluid into the fixture cavity 25.

[0070] In one embodiment, the outer contour of the lower end of the test fixture 2 is the same as the outer contour of the plug-in boss 34. After assembling the turbine blade double-wall air-cooled structure simulation part 1 and the quartz plate 212, align and dock the fluid port 26 at the lower end of the test fixture 2 with the plug-in boss 34 of the fixture connecting plate 31, and Figure 6-7 As shown, the fixture sleeve 23 is simultaneously sleeved on the test fixture 2 and the outer periphery of the plug-in boss 34 , and the connection and fixation of the test fixture 2 and the fixture connecting plate 31 are also achieved while the first clamping member 21 and the second clamping member 22 are fastened.

[0071] The fixture sleeve 23 is installed with interference fit on the periphery of the test fixture 2 and the plug-in boss 34, and the interference tolerance is preferably -0.05 of the design width of the test fixture 2. The fastening height of the fixture sleeve 23 is higher than the height of the plug-in boss 34, and is preferably 10mm higher than the height of the plug-in boss 34, to ensure that the fixture sleeve 23 fixes the relative position of the test fixture 2 and the fixture connecting plate 31. Below the plug-in boss 34 of the fixture connecting plate 31 is a circular through hole, the depth of which is greater than 15mm, preferably 15mm to 20mm, and the circular through hole is connected to the fluid delivery pipe 32 by threads. Figure 6 to Figure 8 As shown, the fluid delivery pipe 32 is preferably a 90° air-cooled elbow.

[0072] A square through hole is preferably provided in the plug boss 34 to communicate with the fluid port 26. A transition through hole is designed between the circular through hole of the fixture connecting plate 31 and the square through hole in the plug boss 34 to ensure that after the cold air flows from the fluid delivery pipe 32 into the circular through hole, it can flow out from the square through hole of the plug boss 34 evenly into the fixture cavity 25 of the test fixture 2, thereby realizing the cold air supply to the double-wall air-cooled structure simulation part 1 of the turbine blade.

[0073] The above-mentioned 90° air-cooled elbow can be made of standard parts, and the size of the circular through hole of the fixture connecting plate 31 should correspond to the size of the 90° elbow standard part. The cold air of the test fixture 2 of the present invention can be supplied by an air compressor, and the cold air supply described above can be achieved by connecting the air compressor airflow to the fluid delivery pipe 32. In practical applications, a vortex flowmeter and a pressure reducing valve can be installed on the fluid delivery pipe 32 or on the pipeline connected to the fluid delivery pipe 32 to control the mass flow of the cold air.

[0074] Example 5

[0075] This embodiment provides a test system 3, which, based on the embodiment 4, further provides a tooling rod 38 and a tooling plate 36 to provide positioning and fixation for the entire test system 3. Figure 6 and Figure 7As shown, the small diameter end of the tooling rod 38 is threaded, and the large diameter end is fixed relative to the ground coordinate system. A through hole with a diameter slightly larger than the outer diameter of the thread of the tooling rod 38 is opened at the center position of the tooling plate 36, so that the tooling plate 36 can be sleeved on the outer periphery of the thread of the small diameter end of the tooling rod 38 and placed on the platform between the large diameter and the small diameter; the tooling nut 37 cooperates with the tooling rod 38 to fix the relative position of the tooling plate 36 and the tooling rod 38. The fixture connecting plate 31 is fixed to the fixture plate 36 by the fixture positioning bolts 35 and the fixture positioning nuts. Through holes of the same size are symmetrically provided on both sides of the fixture connecting plate 31 and the fixture plate 36 for inserting the fixture positioning bolts 35. The diameter of the through holes should be slightly larger than the diameter of the fixture positioning bolts 35 to facilitate loading and unloading. The horizontality of the fixture connecting plate 31 and the relative distance between the fixture connecting plate 31 and the fixture plate 36 can be achieved by adjusting the fixture positioning nuts. After the adjustment is completed, the fixture positioning nuts on the upper and lower sides of the fixture plate 36 and the upper and lower sides of the fixture connecting plate 31 are tightened to achieve tightening. After the installation is completed, no obvious shaking should be generated when the entire clamping device is forced to be bent. This is considered a good tightening standard. After the fixture positioning bolts 35 are tightened, the fixture connecting plate 31 and the fixture plate 36 should maintain a parallel relationship in all dimensional directions. If it is necessary to achieve thermal shock at different angles to the jet flame, it is only necessary to adjust the installation angle of the tooling plate 36, and then after the tooling plate 36 is fixed, the fixture connecting plate 31, the test fixture 2 and the turbine blade double-wall air-cooled structure simulation part 1 can be linked to achieve the adjustment of the impact angle. The tooling positioning bolts 35, the tooling plate 36, the tooling nuts 37 and the tooling rods 38 can all be standard parts with appropriate sizes to reduce costs.

[0076] In the test system 3 of the present invention, the test fixture 2 is directly affected by the impact of high-temperature combustion gas, so the material is preferably a high-temperature alloy, such as GH4169 (i.e., a nickel-based high-temperature alloy); the fixture sleeve 23 and the fixture locking bolt 24 are greatly affected by the high-temperature combustion gas, so 45 steel (also called "oil steel") is preferably used; in the test system 3, the materials of the remaining components are preferably 304 stainless steel.

[0077] In actual testing, the above-mentioned test system 3 can be adaptably installed on a test platform of a thermal coupling test device simulating the high-temperature service environment of an aircraft engine, such as the "Thermal Coupling Test Device Simulating the High-Temperature Service Environment of an Aircraft Engine" disclosed in the Chinese invention patent with application number 202110766353.2.

[0078] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core ideas of the present invention. At the same time, for those skilled in the art, according to the ideas of the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. A double-walled air-cooled structure simulation part of a turbine blade, characterized in that: The invention comprises an inner wall (11), an outer wall (12) and a spoiler column (13), wherein the inner wall (11) and the outer wall (12) are arranged in parallel and at intervals to form a flow-through cavity between the inner wall (11) and the outer wall (12), the inner wall (11) is provided with a plurality of impact holes (14) connected to the flow-through cavity, the outer wall (12) is provided with a plurality of air film holes (15) connected to the flow-through cavity, and any one of the air film holes (15) and any one of the impact holes (14) are arranged in a staggered manner. The inner wall (11) and the outer wall (12) are connected via a plurality of spoiler columns (13), and any spoiler column (13) is staggered with any air film hole (15) and any impact hole (14); the periphery of the inner wall (11) and the outer wall (12) is provided with a sealing structure capable of keeping the periphery of the flow-through cavity closed during the test, so that the fluid entering the flow-through cavity through the impact hole (14) during the test can only be discharged from the air film hole (15).

2. The double-walled air-cooled structure simulation component of a turbine blade according to claim 1, characterized in that: The sealing structure 1 is a side wall structure arranged at the outer peripheral position between the inner wall (11) and the outer wall (12); Alternatively, the sealing structure 1 is a groove or a protrusion located on the periphery of the inner wall (11) and the outer wall (12), and a sealing structure 2 is provided at the specimen clamping position of the test fixture, which is seal-matched with the groove or the protrusion. The sealing structure 2 can be seal-matched with the sealing structure 1 during the test process to keep the periphery of the flow-through clamp cavity closed during the test process.

3. The double-walled air-cooled structure simulation component of a turbine blade according to claim 1 or 2, characterized in that: The inner wall (11) and the outer wall (12) are of the same shape and size, and are rectangular or circular; at least one of the impact hole (14) and the air film hole (15) is a circular hole, a square hole or a fan-shaped hole; and the spoiler column (13) is cylindrical or prismatic.

4. A test fixture, characterized in that: A test fixture capable of being adapted to clamp the double-walled air-cooled structure simulation part (1) of a turbine blade according to claim 1, the test fixture comprising a first clamping part (21) and a second clamping part (22) assembled relatively to each other, the first clamping part (21) and the second clamping part (22) being detachably connected via a clamp locking part; wherein: The first clamping member (21) and the second clamping member (22) are both provided with a half cavity. After the first clamping member (21) and the second clamping member (22) are assembled, the half cavities of the two are connected to each other to form a clamp cavity (25). The side walls of the first clamping member (21) and / or the second clamping member (22) are provided with a fluid passage (26) connected to the clamp cavity (25). A mounting notch communicating with the half cavity is provided on one side wall of the first clamping member (21) and the second clamping member (22); after the first clamping member (21) and the second clamping member (22) are assembled, the mounting notches of the two are butted together to form a clamping notch (27) adapted to the outer contour of the turbine blade double-wall air-cooling structure simulation member; and after the turbine blade double-wall air-cooling structure simulation member is installed in the clamping notch (27), the impact hole (14) of the turbine blade double-wall air-cooling structure simulation member is communicated with the fixture cavity (25); The fluid passage (26) is used for externally connecting the test fluid so as to introduce the test fluid into the double-walled air-cooled structure simulation part of the turbine blade installed on the clamping slot (27) through the fixture cavity (25).

5. The test fixture according to claim 4, characterized in that: The sealing structure 1 is a groove or a protrusion located on the periphery of the inner wall (11) and the outer wall (12), and the inner ring of the clamping groove (27) is provided with a sealing structure 2 that is seal-matched with the groove or the protrusion. The sealing structure 2 can be sealed with the sealing structure 1 during the test to keep the periphery of the flow-through clamp cavity closed during the test.

6. The test fixture according to claim 5, characterized in that: The first sealing structure is a groove (16) located on the outer periphery of the inner wall (11) and the outer wall (12), and the second sealing structure is a protrusion (28) arranged on the inner circle of the clamping groove (27), and the top of the protrusion (28) is a sharp edge (29).

7. The test fixture according to any one of claims 4 to 6, characterized in that: The other side walls of the first clamping member (21) and the second clamping member (22) are each provided with a detection notch communicating with the half cavity; after the first clamping member (21) and the second clamping member (22) are assembled, the detection notches of the two are butted together to form a detection window (211), and a quartz plate (212) is embedded in the detection window (211).

8. The test fixture according to claim 7, characterized in that: An annular convex ridge (213) is provided in the middle of the outer periphery of the quartz plate (212), and an annular mounting groove (214) adapted to be inserted into and fitted with the annular convex ridge (213) is provided in the inner ring of the detection window (211).

9. A testing system, characterized in that: It comprises the double-walled air-cooled structure simulation part (1) of a turbine blade as claimed in claim 1 and the test fixture (2) as claimed in any one of claims 4 to 8.

10. The test system according to claim 9, characterized in that: Also includes: A fixture connecting plate (31), wherein a fluid flow channel (33) is provided in the fixture connecting plate (31), an inserting boss (34) is provided at one end of the fluid flow channel (33), the test fixture (2) is provided on the inserting boss (34), and is detachably connected to the inserting boss (34) via the fixture locking member, and the fluid port (26) is in communication with the fluid flow channel (33); A fluid delivery tube (32) is connected to the other end of the fluid flow channel (33), and the fluid delivery tube (32) is used to introduce the test fluid into the fixture cavity (25).

Images