Matrix type heating device for turbine case and non-uniform temperature field simulation method

Abstract

The invention discloses a matrix type heating device for a turbine case and a non-uniform temperature field simulation method, and the device comprises a supporting table top for fixing the turbine case, a lamp tube for heating the turbine case, a lamp tube support for installing the lamp tube, and a cooling layer partition plate. The lamp tube support comprises outer side supports, inner side supports and a clamp, the outer side supports and the supporting table face are arranged at an angle theta, the inner side supports are arranged in parallel with the axis direction of the turbine case, the clamp is used for installing the lamp tube, the outer side supports are annularly arranged on the outer side of the turbine case in a winding mode, and the inner side supports are annularly arranged on the inner side of the turbine case in a winding mode. The lamp tubes are respectively arranged on the outer side support and the inner side support through the clamps, and the cooling layer partition plate is arranged between the outer side support and the inner side support; the device is simple and reliable, is low in test cost, can simulate the temperature field of the turbine casing in the actual working state of the engine under the laboratory condition, and can improve the test efficiency.

Description

Technical Field

[0001] The present invention relates to the field of aircraft engine technology, and in particular, to a matrix heating device for a turbine casing. In addition, the present invention also relates to a non-uniform temperature field simulation method for a turbine casing. Background Art

[0002] The working environment of the turbine casing in the engine is very harsh. It not only bears the mechanical load of the engine components, but also bears the influence of gas expansion pressure and thermal load. Whenever the engine starts and stops and changes the working conditions, the temperature inside the casing changes drastically, which will generate great thermal stress, causing fatigue and damage to the internal components of the casing. The resulting thermal deformation will affect the radial clearance between the rotor blade tip and the casing, forming a more complex leakage flow, seriously affecting the reliability of the turbine efficiency, and thus affecting the performance, fuel consumption and reliability of the entire engine. Therefore, it is necessary to simulate the temperature distribution of the turbine casing of an aircraft engine under working conditions, master the thermal deformation law of the turbine casing, and provide data support for the design of the turbine casing.

[0003] At present, the main heating methods used for turbine casing deformation tests are flame heating, heating film and resistance wire heating. Traditional flame heating has a wide heating temperature range, but has high requirements for fuel nozzle design and jet gas velocity, is difficult to accurately control, and has high cost; heating film contact heating can achieve uniform heating and is low in cost, but the heating temperature is limited and it is difficult to meet the temperature requirements of aircraft engine turbine casings under working conditions; when using resistance wire heating, the heating efficiency is high, but the smaller test pieces cannot adapt to high-power resistance wires. Summary of the invention

[0004] The present invention provides a matrix heating device for a turbine casing, so as to solve the technical problem that the existing heating method for a turbine casing deformation test is difficult to meet the use requirements.

[0005] According to one aspect of the present invention, there is provided a matrix heating device for a turbine casing, comprising a support table for fixing the turbine casing, a lamp tube for heating the turbine casing, a lamp tube support for mounting the lamp tube, and a cooling layer partition, the lamp tube support comprising an outer support arranged at an angle θ with the support table, an inner support arranged parallel to the axial direction of the turbine casing, and a clamp for mounting the lamp tube, a plurality of the outer supports are arranged in a ring shape around the outer side of the turbine casing, a plurality of the inner supports are arranged in a ring shape around the inner side of the turbine casing, the lamp tubes are respectively arranged on the outer supports and the inner supports by the clamps, and the cooling layer partition is arranged between the outer supports and the inner supports.

[0006] Furthermore, two adjacent outer supports are connected to each other to form a conical surface, and two clamps are arranged at intervals on the inner wall surface of each outer support, and the clamps include a sliding seat, a slider slidably arranged on the sliding seat and capable of being fixed after sliding, and a mounting seat arranged on the slider for mounting the lamp tube, and the two ends of the lamp tube are respectively connected to the corresponding mounting seats, and the installation angle of the lamp tube on the outer support is adjusted by adjusting the position of the slider on the sliding seat.

[0007] Furthermore, two adjacent inner supports are interconnected to form a cylindrical surface, and two clamps are arranged at intervals on the outer wall surface of each inner support. The clamps on the inner supports have the same structure as the clamps on the outer supports, and the installation angle of the lamp tube on the inner support can be adjusted by adjusting the position of the slider on the slide seat.

[0008] Furthermore, the outer support is hinged to the support table, and the installation angle of the lamp tube on the outer support is adjusted by adjusting the angle θ between the outer support and the support table.

[0009] Furthermore, assuming that the installation angle of the lamp tube is 0° when it is parallel to the turbine casing, the adjustment range of the installation angle of the lamp tube is -20° to 20°.

[0010] Furthermore, it also includes a lifting mechanism, which includes a telescope that can be extended and retracted along the axial direction of the turbine casing and a lifting platform arranged on the telescope for driving the inner support to move.

[0011] Furthermore, the cooling layer partition is provided with an annular channel, an air inlet pipe for introducing external cold air into the annular channel, and an air outlet pipe connected to the annular channel.

[0012] Furthermore, the lamp tube includes an outer lamp tube arranged on the outer support and an inner lamp tube arranged on the inner support, the outer lamp tube has a power of 1.5kW to 2.5kW, a total length of 150 to 250mm, and a heating length of 80 to 140mm, and the inner lamp tube has a power of 2.5kW to 3.5kW, a total length of 200 to 300mm, and a heating length of 120 to 180mm.

[0013] According to another aspect of the present invention, a method for simulating a non-uniform temperature field of a turbine casing is provided, using the above-mentioned matrix heating device for a turbine casing, which comprises the following steps: S1. Establishing the corresponding relationship between the heating power of the lamp and the temperature of the local position of the turbine casing through calibration; S2. According to the uneven distribution of circumferential temperature on the outer side of the turbine casing, combined with the calibration result of step S1, the circumferential position layout of the outer lamp tubes is determined. In the local high temperature area, the outer lamp tubes around the position can be densely arranged, and in the local low temperature area, the outer lamp tubes around the position can be sparsely arranged. Then, by adjusting the heating power of the outer lamp tubes at different circumferential positions, the uneven distribution of circumferential temperature on the outer side of the turbine casing is simulated; S3. Adjust the height of the lifting mechanism so that the inner lamp tube is aligned with the outer ring of the turbine, ensuring that the heat radiated by the inner lamp tube evenly covers the entire inner surface of the outer ring of the turbine; S4, according to the uneven distribution of circumferential temperature of the inner side of the turbine casing and the outer ring of the turbine, combined with the calibration result of step S1, determine the circumferential position layout of the inner lamp tube, and simulate the uneven distribution of circumferential temperature of the inner side of the turbine casing and the outer ring of the turbine by adjusting the heating power of the inner lamp tube at different circumferential positions; S5, introducing cold air into the annular channel in the cooling layer partition through the air duct to prevent the outer lamp tube and the inner lamp tube from heating each other; S6. Turn on all the outer and inner lamps at the same time, and achieve uneven temperature distribution through uneven heating, so as to simulate the non-uniform temperature field of the turbine casing under the working state of the aircraft engine.

[0014] Furthermore, the step S1 specifically includes the following steps: S11. Take a casing sample made of the same material as the turbine casing, and ensure that the heating area of ​​the casing sample is 1 / 30 to 1 / 20 of the turbine casing model; S12, fixing the thermocouple on the inner and outer surfaces of the casing sample by spot welding, and arranging a plurality of measuring points on the inner and outer surfaces of the casing sample respectively; S13. Use a lamp to perform radiation heating on the casing sample. The installation angle and distance of the lamp to the turbine casing are consistent with those of the test device. After the temperature stabilizes, record the heating power and temperature, adjust the heating power, and obtain the temperatures of the inner and outer surfaces of the casing under different heating powers. S14, using two lamps to perform radiation heating on the casing sample, adjusting the heating power, and obtaining the temperatures of the inner and outer surfaces of the casing under different heating powers; S15, using three lamps to perform radiation heating on the casing sample, adjusting the heating power, and obtaining the temperatures of the inner and outer surfaces of the casing under different heating powers; S16. Arrange the test data and establish the corresponding relationship between the number of lamps, heating power and the temperature of the local position of the turbine casing.

[0015] The present invention has the following beneficial effects: The matrix heating device for the turbine casing of the present invention has a support table placed horizontally, and when the turbine casing is installed on the support table, its axial direction is arranged vertically, the lamp tubes on the outer support are arranged around the outer side of the turbine casing, and the lamp tubes on the inner support are arranged around the inner side of the turbine casing, which can simulate the temperature distribution law of the turbine casing of the aircraft engine under the working state, and has a wide heating temperature range, and the highest heating temperature can reach 1800K, which can meet the casing temperature variation range within the engine working envelope, and the heating power can be adjusted by adjusting the arrangement of the lamp tubes on the outer support and the inner support, and the heating power of the lamp tubes can be accurately controlled. Thermal temperature, thereby realizing the simulation of non-uniform or uniform temperature load on the turbine casing circumferentially; the cooling layer partition is placed between the outer support and the inner support, which can effectively prevent the lamps on the outer support and the inner support from heating each other, thereby ensuring the heating accuracy; compared with flame heating, heating film and resistance wire heating, the lamp heats the casing by thermal radiation heating with uniform circumferential temperature distribution, with high heating efficiency. It only takes 30 minutes to complete a state point test, which can improve the test efficiency. It is simple and reliable, with low test cost, and can simulate the turbine casing temperature field when the engine is actually working under laboratory conditions.

[0016] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings: Figure 1 It is a structural schematic diagram of a matrix heating device for a turbine casing according to a preferred embodiment of the present invention; Figure 2 It is a structural schematic diagram of a lifting mechanism of a preferred embodiment of the present invention; Figure 3 is a cross-sectional view of a matrix heating device for a turbine casing according to a preferred embodiment of the present invention; Figure 4 is a schematic structural diagram of an outer support of a preferred embodiment of the present invention; Figure 5 is a schematic structural diagram of a lamp tube according to a preferred embodiment of the present invention; Figure 6 is one of the structural schematic diagrams of the clamp of the preferred embodiment of the present invention; wherein, Figure 6 (a) is a schematic diagram of the structure when the lamp tube is parallel to the turbine casing; Figure 6 (b) is a schematic diagram of the structure for adjusting the installation angle of the lamp tube and the turbine casing; Figure 7This is the second structural schematic diagram of the clamp of the preferred embodiment of the present invention; Figure 8 It is a schematic structural diagram of a cooling layer baffle in a preferred embodiment of the present invention; Fig. 9 is a cross-sectional view of a cooling layer baffle according to a preferred embodiment of the present invention; Fig.10 Schematic diagram of the structure of the thermocouple groove of the preferred embodiment of the present invention; Fig.11 is a cross-sectional view of a casing pattern of a preferred embodiment of the present invention; Fig.12 It is a schematic structural diagram of a turbine casing according to a preferred embodiment of the present invention.

[0018] Legend: 100. Turbine casing; 101. Thermocouple groove; 102. Casing style; 1. Support table; 2. Lamp tube; 21. Outer lamp tube; 22. Inner lamp tube; 3. Lamp tube support; 31. Outer support; 331. Sliding seat; 332. Sliding block; 32. Inner support; 33. Clamp; 4. Cooling layer partition; 41. Annular channel; 42. Air duct; 43. Exhaust pipe; 44. Avoidance groove; 5. Lifting mechanism; 51. Telescopic device; 52. Lifting platform; 53. Connecting rod. DETAILED DESCRIPTION

[0019] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0020] Please also read Figures 1 to 12 The matrix heating device for the turbine casing of this embodiment includes a support table 1 for fixing the turbine casing 100, a lamp tube 2 for heating the turbine casing 100, a lamp tube support 3 for mounting the lamp tube 2, and a cooling layer partition 4. The lamp tube support 3 includes an outer support 31 arranged at an angle θ with the support table 1, an inner support 32 arranged parallel to the axial direction of the turbine casing 100, and a clamp 33 for mounting the lamp tube 2. The support 31 is arranged in a ring shape around the outer side of the turbine casing 100, and multiple inner supports 32 are arranged in a ring shape around the inner side of the turbine casing 100. The lamp tube 2 is respectively arranged on the outer support 31 and the inner support 32 through the clamp 33. The cooling layer partition 4 is arranged between the outer support 31 and the inner support 32. The outer side of the turbine casing 100 and the inner side of the turbine casing 100 are arranged at an angle, and a buckle for connecting the turbine outer ring is arranged on the inner side of the turbine casing 100.

[0021] In the matrix heating device for the turbine casing of the present embodiment, the support table 1 is placed horizontally, and the turbine casing 100 is arranged vertically in the axial direction when it is installed on the support table 1. The lamp tube 2 on the outer support 31 is arranged around the outer side of the turbine casing 100, and the lamp tube 2 on the inner support 32 is arranged around the inner side of the turbine casing 100. It can simulate the temperature distribution law of the turbine casing of the aircraft engine under the working state, and its heating temperature range is wide, and the maximum heating temperature can reach 1800K, which can meet the casing temperature variation range within the engine working envelope. By adjusting the arrangement of the lamp tube 2 on the outer support 31 and the inner support 32, the lamp tube 2 can be adjusted in coordination with the adjustment of the lamp tube 2. The heating power can accurately control the heating temperature, thereby realizing the simulation of non-uniform or uniform temperature load on the turbine casing; the cooling layer partition 4 is placed between the outer support 31 and the inner support 32, which can effectively prevent the lamp tubes 2 on the outer support 31 and the inner support 32 from heating each other, thereby ensuring the heating accuracy; compared with flame heating, heating film and resistance wire heating, the lamp tube 2 heats the casing by thermal radiation heating with uniform circumferential temperature distribution, with high heating efficiency, and it only takes 30 minutes to complete a state point test. It is simple and reliable, with low test cost, and can simulate the turbine casing temperature field when the engine is in actual working state under laboratory conditions. Optionally, 120°≤θ≤150° is adjusted according to the angle between the outer side of the turbine casing 100 and the inner side of the turbine casing 100 to ensure that the heat radiated by the lamp tube 2 on the outer support 31 can cover the entire outer side of the turbine casing 100.

[0022] like Figure 1 , Figure 2 , Figure 4 and Figure 6 As shown, in this embodiment, two adjacent outer supports 31 are connected to each other to form a conical surface, which can form a relatively closed heating space to avoid heat loss, and can improve the heating efficiency of the lamp tube 2 on the outer support 31 to the outer side of the turbine casing 100; two clamps 33 are arranged at intervals on the inner wall surface of each outer support 31, and the clamp 33 includes a sliding seat 331, a slider 332 slidably arranged on the sliding seat 331 and can be fixed after sliding, and a mounting seat arranged on the slider 332 for mounting the lamp tube 2, and the two ends of the lamp tube 2 are respectively connected to the corresponding mounting seats, and the installation angle of the lamp tube 2 on the outer support 31 can be adjusted by adjusting the position of the slider 332 on the sliding seat 331; as shown in FIG. Figure 6 As shown in (a), the distance between the upper end of the lamp tube 2 and the right end of the upper end slide 331 is d1, and the distance between the lower end of the lamp tube 2 and the right end of the lower end slide 331 is d2. When d1=d2, the lamp tube 2 on the outer support 31 is parallel to the outer side of the turbine casing 100. At this time, the installation angle of the lamp tube 2 on the outer support 31 relative to the outer side of the turbine casing 100 is 0°; Figure 6As shown in (b), when d1>d2, the installation angle of the lamp tube 2 on the outer support 31 relative to the outer side of the turbine casing 100 is>0°; when d1<d2, the installation angle of the lamp tube 2 on the outer support 31 relative to the outer side of the turbine casing 100 is<0°; by adjusting the installation angle of the lamp tube 2 on the outer support 31 relative to the outer side of the turbine casing 100, on the one hand, the heating requirements of different types of turbine casings 100 (different types of turbine casings 100 have different angles between the outer side and the inner side) can be met, and on the other hand, the distance between the two ends of the lamp tube 2 on the outer support 31 and the outer side of the turbine casing 100 can be adjusted, thereby realizing the simulation of the non-uniform temperature field on the outer side of the turbine casing 100.

[0023] like Figure 2 , Figure 4 and Figure 6 As shown, in this embodiment, two adjacent inner supports 32 are connected to each other to form a cylindrical surface, which can form a relatively closed heating space to avoid heat loss and improve the heating efficiency of the lamp tube 2 on the inner support 32 to the inner side of the turbine casing 100; two clamps 33 are arranged at intervals on the outer wall surface of each inner support 32, and the clamps 33 on the inner support 32 have the same structure as the clamps 33 on the outer support 31. The installation angle of the lamp tube 2 on the inner support 32 can be adjusted by adjusting the position of the slider 332 on the slide seat 331; Figure 6 As shown in (a), the distance between the upper end of the lamp tube 2 and the right end of the upper end slide 331 is d1, and the distance between the lower end of the lamp tube 2 and the right end of the lower end slide 331 is d2. When d1=d2, the lamp tube 2 on the inner support 32 is parallel to the inner support 32 of the turbine casing 100. At this time, the installation angle of the lamp tube 2 on the inner support 32 relative to the inner side of the turbine casing 100 is 0°; Figure 6 As shown in (b), when d1>d2, the installation angle of the lamp tube 2 on the inner support 32 relative to the inner side of the turbine casing 100 is>0°; when d1<d2, the installation angle of the lamp tube 2 on the inner support 32 relative to the inner side of the turbine casing 100 is<0°; by adjusting the installation angle of the lamp tube 2 on the inner support 32 relative to the inner side of the turbine casing 100, on the one hand, the heating requirements of turbine casings 100 of different models can be met, and on the other hand, the distance between the two ends of the lamp tube 2 on the inner support 32 and the inner support 32 of the turbine casing 100 can be adjusted, thereby realizing the simulation of the non-uniform temperature field inside the turbine casing 100.

[0024] like Figure 3As shown, in this embodiment, each outer support 31 is hinged to the support table 1, so that the outer support 31 can swing relative to the support table 1, and is fixed when the outer support 31 swings to a specified position. Since the clamp 33 is installed on the outer support 31 by bolts, the angle θ between the outer support 31 and the support table 1 is adjusted to achieve the installation angle adjustment of the lamp tube 2 on the outer support 31 relative to the outer side of the turbine casing 100. The structure is simple and can be applied to turbine casings 100 of different models. Optionally, as Figure 7 As shown, connectors are arranged at both ends of the lamp tube 2, and the connectors at both ends of the lamp tube 2 are connected to the corresponding clamps 33. The clamp 33 includes a front section, a middle section and a tail section. The front section is used to connect to the outer support 31. The width c of the front section of the clamp 33 is greater than the width of the connector of the lamp tube 2. An angle β is formed at the connection between the front section and the middle section. The angle range of the angle β is 45° to 65°. Within this angle range, the angle β makes it easy to place the connector of the lamp tube 2 into the clamp 33 and has good stability; the tail section of the clamp 33 is sharp, and the angle γ of the sharp angle ranges from 80° to 100°. Angle γ within this angle range enables the clamp to have good extensional stretchability. If the angle of sharp angle γ is too small, the sharp corner part of the tail section of the clamp 33 will be too long, which is not conducive to the overall size of the clamp 33. If the angle γ is too large, it will affect the extensional stretchability of the tail section of the clamp 33. The width b of the middle section of the clamp 33 is 0.1 to 0.2 mm smaller than the width of the connecting head of the lamp tube 2, so that the connecting head of the lamp tube 2 can be tightly clamped by the clamp 33, ensuring that the lamp tube 2 can be stably installed on the outer support 31, and the clamp 33 on the inner support 32 has the same structure as the clamp 33 on the outer support 31.

[0025] In this embodiment, the installation angle of the lamp tube 2 when it is parallel to the turbine casing 100 is 0°, and the adjustment range of the installation angle of the lamp tube 2 is -20° to 20°, which can meet the heating requirements of turbine casings 100 of different models.

[0026] like Figure 1 and Figure 2 As shown, in this embodiment, a lifting mechanism 5 is also included, and the lifting mechanism 5 includes a telescope 51 that is telescopic along the axis direction of the turbine casing 100 and a lifting platform 52 arranged on the telescope 51 for driving the inner support 32 to move; the telescope 51 drives the inner support 32 to move up and down through the lifting platform 52, which can ensure that the heating section of the lamp 2 on the inner support 32 is aligned with the turbine casing 100, thereby ensuring heating efficiency. Optionally, the lifting platform 52 is connected to the inner support 32 through a connecting rod 53, which can reduce the overall weight of the lifting mechanism 5 on the one hand, and shorten the travel requirement of the telescope 51 on the other hand, thereby reducing costs.

[0027] like Figure 8 and Fig. 9As shown, in this embodiment, the cooling layer partition 4 is provided with an annular channel 41, an air duct 42 for introducing external cold air into the annular channel 41, and an air outlet pipe 43 connected to the annular channel 41. When working, the external cold air enters the annular channel 41 through the air duct 42, cools the cooling layer partition 4, and is discharged from the air outlet pipe 43, which can ensure the heat insulation effect of the cooling layer partition 4, thereby ensuring the heating accuracy. Optionally, the cooling layer partition 4 is provided with an avoidance groove 44 for avoiding the lamp tube 2, which can effectively prevent the lamp tube 2 on the outer support 31 and the lamp tube 2 on the inner support 32 from heating each other while reducing the size of the cooling layer partition 4.

[0028] In the actual working state of the aircraft engine, there is a difference in the temperature distribution between the inner side of the turbine casing 100 (including the turbine outer ring arranged on the inner side of the turbine casing 100) and the outer side of the turbine casing 100, and the inner side of the turbine casing 100 and the turbine outer ring are in the high temperature area of ​​the gas side with high temperature, and the outer side of the turbine casing 100 is in the inflow area of ​​the air system, where there is cooling air and the temperature is lowered. Therefore, lamps 2 with different heating powers are used to heat the outer side of the turbine casing 100 and the inner side of the turbine casing 100. , which can reduce costs while meeting the needs; in this embodiment, the lamp tube 2 includes an outer lamp tube 21 arranged on the outer support 31 and an inner lamp tube 22 arranged on the inner support 32, the power of the outer lamp tube 21 is 1.5kW~2.5kW, the total length is 150~250mm, and the heating length is 80~140mm, the power of the inner lamp tube 22 is 2.5kW~3.5kW, the total length is 200~300mm, and the heating length is 120~180mm. Optionally, the lamp tube 2 is a quartz lamp tube; the connectors at both ends of the quartz lamp tube are power supply electrodes, the electrodes are wrapped in white high-temperature resistant porcelain heads, the wires at both ends of the electrodes pass through the top of the porcelain head, and the porcelain head of the quartz lamp tube is connected to the mounting seat to form a ring quartz lamp tube heating system. The quartz lamp tube is connected to the power supply end through the control cabinet, and the input voltage is adjusted through the control cabinet to change the input power of the quartz lamp tube, thereby achieving an adjustable heating rate to meet the heating requirements required for the test. Optionally, the back side of the heating filament of the quartz lamp tube is sprayed with a silver reflective coating, and the quartz lamp tubes are arranged in a ring to concentrate the radiant heat and reflect it onto the turbine casing 100 .

[0029] The matrix heating device for the turbine casing of the present invention can simulate the temperature distribution law of the turbine casing of an aircraft engine in the working state. It has a wide heating temperature range, and the highest heating temperature can reach 1800K, which meets the casing temperature variation range within the working envelope of the aircraft engine. The installation angles of the outer lamp tube 21 and the inner lamp tube 22 can be adjusted within the range of -20° to 20°. The heating temperature can be accurately controlled by adjusting the heating power of the outer lamp tube 21 and the inner lamp tube 22, thereby realizing the circumferential non-uniform or uniform temperature load simulation of the turbine casing. Compared with flame heating, heating film and resistance wire heating, the lamp tube 2 heats the casing by thermal radiation heating with uniform circumferential temperature distribution, and has high heating efficiency. It only takes 30 minutes to complete a state point test. It is simple and reliable, with low test cost, and can simulate the temperature field of the turbine casing when the engine is actually working under laboratory conditions, and can improve test efficiency.

[0030] like Figure 1 and Figure 5 As shown, a method for simulating a non-uniform temperature field of a turbine casing, using the above-mentioned matrix heating device for a turbine casing, comprises the following steps: S1, establishing a corresponding relationship between the heating power of the lamp tube 2 and the temperature of a local position of the turbine casing 100 through calibration; S2. According to the uneven distribution of circumferential temperature on the outer side of the turbine casing, combined with the calibration result of step S1, the circumferential position layout of the outer lamp tubes 21 is determined. In the local high temperature area, the outer lamp tubes 21 around the position can be densely arranged, and in the local low temperature area, the outer lamp tubes 21 around the position can be sparsely arranged. Then, by adjusting the heating power of the outer lamp tubes 21 at different circumferential positions, the uneven distribution of circumferential temperature on the outer side of the turbine casing is simulated; S3, adjusting the height of the lifting mechanism 5 so that the inner lamp tube 22 is aligned with the turbine outer ring, ensuring that the heat radiated by the inner lamp tube 22 evenly covers the inner surface of the entire turbine outer ring; S4, according to the uneven distribution of circumferential temperature of the inner side of the turbine casing 100 and the outer ring of the turbine, combined with the calibration result of step S1, the circumferential position layout of the inner lamp tube 22 is determined, and the uneven distribution of circumferential temperature of the inner side of the turbine casing and the outer ring of the turbine is simulated by adjusting the heating power of the inner lamp tube 22 at different circumferential positions of the inner lamp tube 22; S5, introducing cold air into the annular channel 41 in the cooling layer partition 4 through the air duct 42 to prevent the outer lamp tube 21 and the inner lamp tube 22 from heating each other; S6. Turn on all the outer lamp tubes 21 and the inner lamp tubes 22 at the same time, and achieve uneven temperature distribution through uneven heating, so as to simulate the non-uniform temperature field of the turbine casing 100 when the aircraft engine is in operation.

[0031] The non-uniform temperature field simulation method for the turbine casing of the present embodiment realizes the circumferential temperature difference of the outer side of the turbine casing 100 by the circumferential non-uniform distribution of the outer lamp tubes 21 and the adjustment of the heating power of the outer lamp tubes 21 at different positions. The non-uniform circumferential temperature distribution of the inner side and outer ring of the turbine casing is realized by the circumferential non-uniform distribution of the inner lamp tubes 22 and the adjustment of the heating power of the inner lamp tubes 22 at different positions. The uneven temperature distribution is realized by the uneven heating amount, so as to simulate the non-uniform temperature field of the turbine casing under the working state of the aircraft engine.

[0032] like Fig.10 and Fig.11 As shown, in this embodiment, step S1 specifically includes the following steps: S11, taking a casing sample 102 made of the same material as the turbine casing 100, and ensuring that the heating area of ​​the casing sample 102 is 1 / 30 to 1 / 20 of the turbine casing 100 model; S12, the thermocouple is fixed on the inner and outer surfaces of the casing pattern 102 by spot welding, a plurality of measuring points are arranged on the inner and outer surfaces of the casing pattern 102 respectively, a plurality of thermocouple grooves 101 are respectively provided on the inner and outer surfaces of the casing pattern 102, the thermocouple is fixed in the thermocouple groove 101 by spot welding, three thermocouple grooves 101 are provided on the outer surface of the casing pattern 102, and the thermocouple groove 101 provided on the inner surface of the casing pattern 102 is not shown. It can be understood that the number of the thermocouple grooves 101 can be increased or decreased according to the use requirements; S13, using a lamp tube 2 to perform radiation heating on the casing sample 102, the installation angle of the lamp tube 2 and the distance to the turbine casing 100 are consistent with those of the test device, after the temperature is stable, the heating power and temperature are recorded, the heating power is adjusted, and the temperatures of the inner and outer surfaces of the casing under different heating powers are obtained; S14, using two lamps 2 to perform radiation heating on the casing sample 102, adjusting the heating power, and obtaining the temperatures of the inner and outer surfaces of the casing under different heating powers; S15, using three lamps 2 to perform radiation heating on the casing sample 102, adjusting the heating power, and obtaining the temperatures of the inner and outer surfaces of the casing under different heating powers; S16. Organize the test data and establish the corresponding relationship between the number of lamp tubes 2, the heating power and the temperature of the local position of the turbine casing 100; determine the heating power and number of the outer lamp tubes 21 and the inner lamp tubes 22 according to the simulation requirements of the circumferential uniform temperature load of the turbine casing 100, and adjust the heating power of each lamp tube 2 so that the circumferential temperature load of the casing meets the simulation requirements.

[0033] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A matrix heating device for a turbine casing, characterized in that: The invention comprises a support table (1) for fixing a turbine casing, a lamp tube (2) for heating the turbine casing, a lamp tube support (3) for mounting the lamp tube (2), and a cooling layer baffle (4); the lamp tube support (3) comprises an outer support (31) arranged at an angle θ with the support table (1), an inner support (32) arranged parallel to the axial direction of the turbine casing, and a clamp (33) for mounting the lamp tube (2); a plurality of the outer supports (31) are arranged in a ring shape on the outer side of the turbine casing, a plurality of the inner supports (32) are arranged in a ring shape on the inner side of the turbine casing, the lamp tube (2) is arranged on the outer support (31) and the inner support (32) respectively through the clamp (33), and the cooling layer baffle (4) is arranged between the outer support (31) and the inner support (32).

2. The matrix heating device for a turbine casing according to claim 1, characterized in that: Two adjacent outer supports (31) are connected to each other to form a conical surface, and two clamps (33) are arranged at intervals on the inner wall surface of each outer support (31), and the clamp (33) comprises a sliding seat (331), a slider (332) slidably arranged on the sliding seat (331) and capable of being fixed after sliding, and a mounting seat arranged on the slider (332) for mounting the lamp tube (2), and the two ends of the lamp tube (2) are respectively connected to the corresponding mounting seats, and the mounting angle of the lamp tube (2) on the outer support (31) can be adjusted by adjusting the position of the slider (332) on the sliding seat (331).

3. The matrix heating device for a turbine casing according to claim 2, characterized in that: Two adjacent inner supports (32) are connected to each other to form a cylindrical surface, and two clamps (33) are arranged at intervals on the outer wall surface of each inner support (32). The clamps (33) on the inner support (32) have the same structure as the clamps (33) on the outer support (31), and the installation angle of the lamp tube (2) on the inner support (32) can be adjusted by adjusting the position of the slider (332) on the slider (331).

4. The matrix heating device for a turbine casing according to claim 1, characterized in that: The outer support (31) is hinged to the support table (1), and the installation angle of the lamp tube (2) on the outer support (31) can be adjusted by adjusting an angle θ between the outer support (31) and the support table (1).

5. The matrix heating device for a turbine casing according to any one of claims 2 to 4, characterized in that: Assuming that the installation angle of the lamp tube (2) is 0° when it is parallel to the turbine casing, the adjustment range of the installation angle of the lamp tube (2) is -20° to 20°.

6. The matrix heating device for a turbine casing according to claim 5, characterized in that: It also includes a lifting mechanism (5), the lifting mechanism (5) comprising a telescoping device (51) that is telescopic along the axial direction of the turbine casing, and a lifting platform (52) disposed on the telescoping device (51) and used for driving the inner support (32) to move.

7. The matrix heating device for a turbine casing according to claim 6, characterized in that: The cooling layer partition plate (4) is provided with an annular channel (41), an air inlet pipe (42) for introducing external cold air into the annular channel (41), and an air outlet pipe (43) in communication with the annular channel (41).

8. The matrix heating device for a turbine casing according to claim 7, characterized in that: The lamp tube (2) comprises an outer lamp tube (21) arranged on the outer support (31) and an inner lamp tube (22) arranged on the inner support (32); the outer lamp tube (21) has a power of 1.5 kW to 2.5 kW, a total length of 150 to 250 mm, and a heating length of 80 to 140 mm; the inner lamp tube (22) has a power of 2.5 kW to 3.5 kW, a total length of 200 to 300 mm, and a heating length of 120 to 180 mm.

9. A method for simulating a non-uniform temperature field of a turbine casing, characterized in that: The matrix heating device for a turbine casing according to claim 8 comprises the following steps: S1. establishing, by calibration, a corresponding relationship between the heating power of the lamp tube (2) and the temperature at a local position of the turbine casing; S2, according to the uneven distribution of circumferential temperature on the outer side of the turbine casing, combined with the calibration result of step S1, the circumferential position layout of the outer lamp tubes (21) is determined, the outer lamp tubes (21) around the local high temperature area can be densely arranged, and the outer lamp tubes (21) around the local low temperature area can be sparsely arranged, and then the heating power of the outer lamp tubes (21) at different circumferential positions is adjusted to simulate the uneven distribution of circumferential temperature on the outer side of the turbine casing; S3, adjusting the height of the lifting mechanism (5) so that the inner lamp tube (22) is aligned with the turbine outer ring, ensuring that the heat radiated by the inner lamp tube (22) evenly covers the entire inner surface of the turbine outer ring; S4, according to the uneven distribution of circumferential temperature of the inner side of the turbine casing and the outer ring of the turbine, combined with the calibration result of step S1, determining the circumferential position layout of the inner lamp tube (22), simulating the uneven distribution of circumferential temperature of the inner side of the turbine casing and the outer ring of the turbine by adjusting the heating power of the inner lamp tube (22) at different circumferential positions of the inner lamp tube (22); S5, introducing cold air into the annular channel (41) in the cooling layer partition (4) through the air duct (42) to prevent the outer lamp tube (21) and the inner lamp tube (22) from heating each other; S6. All the outer lamp tubes (21) and the inner lamp tubes (22) are turned on at the same time, and uneven temperature distribution is achieved through uneven heating, so as to simulate the non-uniform temperature field of the turbine casing when the aircraft engine is in operation.

10. The method for simulating a non-uniform temperature field of a turbine casing according to claim 9, characterized in that: The step S1 specifically includes the following steps: S11. Take a casing sample made of the same material as the turbine casing, and ensure that the heating area of ​​the casing sample is 1 / 30 to 1 / 20 of the turbine casing model; S12, fixing the thermocouple on the inner and outer surfaces of the casing sample by spot welding, and arranging a plurality of measuring points on the inner and outer surfaces of the casing sample respectively; S13, using a lamp tube (2) to perform radiation heating on the casing sample, the installation angle of the lamp tube (2) and the distance to the turbine casing are consistent with those of the test device, after the temperature is stable, recording the heating power and temperature, adjusting the heating power, and obtaining the temperatures of the inner and outer surfaces of the casing under different heating powers; S14, using two lamps (2) to perform radiation heating on the casing sample, adjusting the heating power, and obtaining the temperatures of the inner and outer surfaces of the casing under different heating powers; S15, using three lamps (2) to perform radiation heating on the casing sample, adjusting the heating power, and obtaining the temperatures of the inner and outer surfaces of the casing under different heating powers; S16. Arrange the test data and establish a corresponding relationship between the number of lamp tubes (2), the heating power and the temperature at a local position of the turbine casing.

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