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

Abstract

The present invention discloses a matrix heating device for a turbine casing and a non-uniform temperature field simulation method, which includes a support table for fixing the turbine casing, a lamp tube for heating the turbine casing, a lamp tube support for installing the lamp tube, and a cooling layer partition. The lamp tube support includes an outer support arranged at an angle θ with the support table, an inner support arranged parallel to the axis direction of the turbine casing, and a fixture for installing the lamp tube. A plurality of the outer supports are arranged in a ring around the outside of the turbine casing, a plurality of the inner supports are arranged in a ring around the inside of the turbine casing, the lamp tubes are respectively arranged on the outer support and the inner support through the fixture, and the cooling layer partition is arranged between the outer support and the inner support; it is simple and reliable, with low test costs, and can simulate the temperature field of the turbine casing under the actual working conditions of the engine in the laboratory, improving the test efficiency.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, 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 including the above. Background Art

[0002] The working environment of the turbine casing in the engine is very harsh. It not only bears the mechanical loads of the engine components, but also withstands the gas expansion pressure and heat load and other influences. Whenever the engine starts, stops, and changes operating conditions, the temperature change inside the casing is very drastic. At this time, a large thermal stress will be generated, which will cause fatigue and damage to the internal components of the casing. The thermal deformation generated will affect the radial clearance between the rotor tip and the casing, forming a more complex leakage flow, seriously affecting the reliability of the turbine efficiency, and further affecting the performance, fuel consumption rate, and reliability of the entire engine. Therefore, it is necessary to simulate the temperature distribution of the aero-engine turbine casing under the working state, master the thermal deformation law of the turbine casing, and provide data support for the design of the turbine casing.

[0003] At present, when conducting turbine casing deformation tests, heating methods such as flame heating, heating film pasting, and resistance wire heating are mainly used. The traditional flame heating has a wide heating temperature range, but has high requirements for the fuel nozzle design and the jet gas velocity, is difficult to accurately control, and has a high use cost; the heating film contact heating can achieve uniform heating and low cost, but the heating temperature is limited and it is difficult to meet the temperature requirements of the aero-engine turbine casing under the working state; when using resistance wire heating, the heating efficiency is high, but small-sized 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 to solve the technical problem that the heating methods of the existing turbine casing deformation tests are 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, including a support table for fixing the turbine casing, a lamp tube for heating the turbine casing, a lamp tube support for installing the lamp tube, and a cooling layer partition. The lamp tube support includes an outer support disposed at an angle θ with the support table, an inner support disposed parallel to the axis direction of the turbine casing, and a fixture for installing the lamp tube. A plurality of the outer supports are arranged in a ring around the outside of the turbine casing, a plurality of the inner supports are arranged in a ring around the inside of the turbine casing, the lamp tubes are respectively disposed on the outer supports and the inner supports through the fixtures, and the cooling layer partition is disposed between the outer support and the inner support.

[0006] Further, two adjacent outer supports are connected to form a conical surface. Two clamps are arranged at intervals on the inner wall surface of each outer support. The clamp includes 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. Both ends of the lamp tube are respectively connected to the corresponding mounting seats. 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] Further, two adjacent inner supports are connected to form a cylindrical surface. Two clamps are arranged at intervals on the outer wall surface of each inner support. The clamps on the inner support have the same structure as the clamps on the outer support. The installation angle of the lamp tube on the inner support is adjusted by adjusting the position of the slider on the sliding seat.

[0008] Further, the outer support is hinged to the support tabletop. 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 tabletop.

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

[0010] Further, a lifting mechanism is further included. The lifting mechanism includes a telescopic device that telescopically moves along the axis direction of the turbine casing and a lifting platform arranged on the telescopic device for driving the inner support to move.

[0011] Further, an annular channel, an air inlet pipe for introducing external cold air into the annular channel, and an air outlet pipe communicated with the annular channel are arranged on the cooling layer partition plate.

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

[0013] According to another aspect of the present invention, a method for simulating a non-uniform temperature field for a turbine casing is further provided. Using the above matrix heating device for a turbine casing, it includes the following steps:

[0014] S1. Establish the corresponding relationship between the heating power of the lamp tube and the temperature of the local position of the turbine casing through calibration;

[0015] S2. Based on the circumferential non-uniform temperature distribution on the outer side of the turbine casing, and combining with the calibration results in step S1, determine the circumferential position layout of the outer lamps. In the local high-temperature area, the outer lamps around this position can be densely arranged, and in the local low-temperature area, the outer lamps around this position can be sparsely arranged. Then, by adjusting the heating power of the outer lamps at different circumferential positions, simulate the circumferential non-uniform temperature distribution on the outer side of the turbine casing;

[0016] S3. Adjust the height of the lifting mechanism so that the inner lamps are aligned with the turbine outer ring, ensuring that the heat radiated by the inner lamps evenly covers the inner surface of the entire turbine outer ring;

[0017] S4. Based on the circumferential non-uniform temperature distribution on the inner side of the turbine casing and the turbine outer ring, and combining with the calibration results in step S1, determine the circumferential position layout of the inner lamps. By making the circumferential position distribution of the inner lamps uneven and adjusting the heating power of the inner lamps at different circumferential positions, simulate the circumferential non-uniform temperature distribution on the inner side of the turbine casing and the turbine outer ring;

[0018] S5. Introduce cold air into the annular channel in the cooling layer partition through the air inlet pipe to prevent the outer lamps and the inner lamps from heating each other;

[0019] S6. Turn on all the outer lamps and inner lamps simultaneously. Achieve uneven temperature distribution through uneven heating amounts, thereby simulating the non-uniform temperature field of the turbine casing under the working conditions of an aero-engine.

[0020] Further, step S1 specifically includes the following steps:

[0021] S11. Take a casing sample of the same material as the turbine casing, ensuring that the heating area of the casing sample is 1 / 30 to 1 / 20 of the turbine casing model;

[0022] S12. Fix the thermocouples on the inner and outer surfaces of the casing sample by spot welding, and arrange multiple measurement points on the inner and outer surfaces of the casing sample respectively;

[0023] S13. Use a single lamp to radiatively heat the casing sample. The installation angle of the lamp and the distance to the turbine casing are consistent with the test device. After the temperature stabilizes, record the heating power and temperature, and adjust the heating power to obtain the temperatures of the inner and outer surfaces of the casing at different heating powers;

[0024] S14. Use two lamps to radiatively heat the casing sample, and adjust the heating power to obtain the temperatures of the inner and outer surfaces of the casing at different heating powers;

[0025] S15. Use three lamps to radiatively heat the casing sample, and adjust the heating power to obtain the temperatures of the inner and outer surfaces of the casing at different heating powers;

[0026] S16. Organize the test data and establish the corresponding relationship between the number of lamp tubes, the heating power, and the temperature at the local position of the turbine casing.

[0027] The present invention has the following beneficial effects:

[0028] For the matrix heating device for a turbine casing of the present invention, the support tabletop is placed horizontally. When the turbine casing is installed on the support tabletop, its axis direction is vertically arranged. The lamp tubes on the outer support are arranged around the outside of the turbine casing, and the lamp tubes on the inner support are arranged around the inside of the turbine casing. It can simulate the temperature distribution law under the working state of the turbine casing of an aero-engine. Its heating temperature range is wide, and the maximum heating temperature can reach 1800K, which can meet the temperature change range of the casing within the engine operating envelope. By adjusting the arrangement of the lamp tubes on the outer support and the inner support, and coordinating with the adjustment of the heating power of the lamp tubes, the heating temperature can be accurately controlled, so as to realize the simulation of non-uniform or uniform circumferential temperature loads of the turbine casing; the cooling layer partition is placed between the outer support and the inner support, which can effectively prevent the lamp tubes on the outer support and the inner support from heating each other, thus ensuring the heating accuracy; compared with flame heating, heating film pasting, and resistance wire heating, the lamp tubes heat the casing by means of thermal radiation with uniform circumferential temperature distribution, with high heating efficiency. It only takes 30 minutes to complete a test at one state point, which can improve the test efficiency. It is simple and reliable, with low test costs, and can simulate the temperature field of the turbine casing under the actual working state of the engine under laboratory conditions.

[0029] In addition to the purposes, features, and advantages described above, the present invention has other purposes, features, and advantages. The following will refer to the drawings to further elaborate on the present invention in detail. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The drawings forming a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0031] Figure 1 is a schematic structural diagram of the matrix heating device for a turbine casing according to a preferred embodiment of the present invention;

[0032] Figure 2 is a schematic structural diagram of the lifting mechanism according to a preferred embodiment of the present invention;

[0033] Figure 3 is a cross-sectional view of the matrix heating device for a turbine casing according to a preferred embodiment of the present invention;

[0034] Figure 4 is a schematic structural diagram of the outer support according to a preferred embodiment of the present invention;

[0035] Figure 5It is a schematic structural diagram of the lamp tube according to a preferred embodiment of the present invention;

[0036] Figure 6 It is one of the schematic structural diagrams of the fixture according to a preferred embodiment of the present invention; wherein, Figure 6 (a) is a schematic structural diagram when the lamp tube is parallel to the turbine casing; Figure 6 (b) is a schematic structural diagram for adjusting the installation angle between the lamp tube and the turbine casing;

[0037] Figure 7 It is the second schematic structural diagram of the fixture according to a preferred embodiment of the present invention;

[0038] Figure 8 It is a schematic structural diagram of the cooling layer partition according to a preferred embodiment of the present invention;

[0039] Figure 9 It is a cross-sectional view of the cooling layer partition according to a preferred embodiment of the present invention;

[0040] Figure 10 It is a schematic structural diagram of the thermocouple groove according to a preferred embodiment of the present invention;

[0041] Figure 11 It is a cross-sectional view of the casing style according to a preferred embodiment of the present invention;

[0042] Figure 12 It is a schematic structural diagram of the turbine casing according to a preferred embodiment of the present invention.

[0043] Legend:

[0044] 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, slider; 32, inner support; 33, fixture; 4, cooling layer partition; 41, annular channel; 42, air inlet pipe; 43, air outlet pipe; 44, avoidance groove; 5, lifting mechanism; 51, telescopic device; 52, lifting platform; 53, connecting rod. Detailed implementation manners

[0045] The following will describe the embodiments of the present invention in detail with reference to the accompanying drawings. However, the present invention can be implemented in many different ways defined and covered by the following.

[0046] Please refer to together Figures 1 to 12, the matrix heating device for a turbine casing in 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 installing 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 axis direction of the turbine casing 100, and a fixture 33 for installing the lamp tube 2. A plurality of outer supports 31 are arranged in a ring around the outside of the turbine casing 100, and a plurality of inner supports 32 are arranged in a ring around the inside of the turbine casing 100. The lamp tubes 2 are respectively arranged on the outer support 31 and the inner support 32 through the fixtures 33. The cooling layer partition 4 is arranged between the outer support 31 and the inner support 32. The outside of the turbine casing 100 and the inside of the turbine casing 100 are arranged at an angle, and a buckle for connecting the turbine outer ring is arranged on the inside of the turbine casing 100.

[0047] In the matrix heating device for a turbine casing in this embodiment, the support table 1 is placed horizontally. When the turbine casing 100 is installed on the support table 1, its axis direction is arranged vertically. The lamp tubes 2 on the outer support 31 are arranged around the outside of the turbine casing 100, and the lamp tubes 2 on the inner support 32 are arranged around the inside of the turbine casing 100. It can simulate the temperature distribution law under the working state of the turbine casing of an aero-engine. Its heating temperature range is wide, and the maximum heating temperature can reach 1800K, which can meet the range of casing temperature changes within the engine operating envelope. By adjusting the arrangement of the lamp tubes 2 on the outer support 31 and the inner support 32 and coordinating the adjustment of the heating power of the lamp tubes 2, the heating temperature can be accurately controlled, so as to realize the simulation of circumferentially non-uniform or uniform temperature loads 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, thus ensuring the heating accuracy; compared with flame heating, heating film pasting, and resistance wire heating, the lamp tubes 2 heat the casing by means of thermal radiation with uniform circumferential temperature distribution, with high heating efficiency. It only takes 30 minutes to complete a state point test. It is simple and reliable, with low test costs, and can simulate the temperature field of the turbine casing under the actual working state of the engine under laboratory conditions. Optionally, 120°≤θ≤150°, which is adjusted according to the angle between the outside of the turbine casing 100 and the inside of the turbine casing 100 to ensure that the heat radiated by the lamp tubes 2 on the outer support 31 can cover the entire outside of the turbine casing 100.

[0048] As Figure 1 , Figure 2 , Figure 4 and Figure 6As shown in the figure, in this embodiment, two adjacent outer supports 31 are connected to each other to form a conical surface. The conical surface can form a relatively enclosed heating space, avoiding heat dissipation, and improving the heating efficiency of the lamp tube 2 on the outer support 31 for the outside of the turbine casing 100. On the inner wall surface of each outer support 31, two clamps 33 are arranged at intervals. The clamp 33 includes 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 for mounting the lamp tube 2 arranged on the slider 332. Both ends of the lamp tube 2 are connected to the corresponding mounting seats. By adjusting the position of the slider 332 on the sliding seat 331, the installation angle of the lamp tube 2 on the outer support 31 can be adjusted. As Figure 6 shown in (a), the distance between the upper end of the lamp tube 2 and the right end of the upper sliding seat 331 is d1, and the distance between the lower end of the lamp tube 2 and the right end of the lower sliding seat 331 is d2. When d1 = d2, the lamp tube 2 on the outer support 31 is parallel to the outside of the turbine casing 100. At this time, the installation angle of the lamp tube 2 on the outer support 31 relative to the outside of the turbine casing 100 is 0°. As Figure 6 shown in (b), when d1 > d2, the installation angle of the lamp tube 2 on the outer support 31 relative to the outside of the turbine casing 100 > 0°. When d1 < d2, the installation angle of the lamp tube 2 on the outer support 31 relative to the outside of the turbine casing 100 < 0°. By adjusting the installation angle of the lamp tube 2 on the outer support 31 relative to the outside of the turbine casing 100, on the one hand, the heating requirements of different models of turbine casings 100 (the included angles between the outside and the inside of different models of turbine casings 100 are different) can be met. On the other hand, the distance between both ends of the lamp tube 2 on the outer support 31 and the outside of the turbine casing 100 can be adjusted, so as to realize the simulation of the non-uniform temperature field on the outside of the turbine casing 100.

[0049] As Figure 2 、 Figure 4 and Figure 6 shown in the figure, in this embodiment, two adjacent inner supports 32 are connected to each other to form a cylindrical surface. The cylindrical surface can form a relatively enclosed heating space, avoiding heat dissipation, and improving the heating efficiency of the lamp tube 2 on the inner support 32 for the inside of the turbine casing 100. On the outer wall surface of each inner support 32, two clamps 33 are arranged at intervals. The clamps 33 on the inner support 32 have the same structure as the clamps 33 on the outer support 31. By adjusting the position of the slider 332 on the sliding seat 331, the installation angle of the lamp tube 2 on the inner support 32 can be adjusted. As Figure 6 shown in (a), the distance between the upper end of the lamp tube 2 and the right end of the upper sliding seat 331 is d1, and the distance between the lower end of the lamp tube 2 and the right end of the lower sliding seat 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 inside of the turbine casing 100 is 0°. As Figure 6As 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 > 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 < 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, it can meet the heating requirements of different models of turbine casings 100, and on the other hand, it can adjust the distance between both ends of the lamp tube 2 on the inner support 32 and the inner support 32 of the turbine casing 100, so as to simulate the non-uniform temperature field inside the turbine casing 100.

[0050] As Figure 3 shown, in this embodiment, each outer support 31 is respectively hinged to the support table 1, so that the outer support 31 can swing relative to the support table 1 and be fixed when the outer support 31 swings to a specified position. Since the fixture 33 is installed on the outer support 31 through bolts, by adjusting the angle θ between the outer support 31 and the support table 1, the installation angle of the lamp tube 2 on the outer support 31 relative to the outer side of the turbine casing 100 can be adjusted. Its structure is simple and it can be applied to different models of turbine casings 100. Optionally, as Figure 7 shown, connection heads are respectively arranged at both ends of the lamp tube 2, and the connection heads at both ends of the lamp tube 2 are connected to the corresponding fixtures 33. The fixture 33 includes a front section, a middle section and a tail section. The front section is used to connect the outer support 31. The width c of the front section of the fixture 33 is greater than the width of the connection head of the lamp tube 2. An included angle β is formed at the connection between the front section and the middle section. The angle range of the included angle β is 45° - 65°. The included angle β within this angle range makes it easy for the connection head of the lamp tube 2 to be placed into the fixture 33 and has good stability; the tail section of the fixture 33 is in a sharp angle, and the angle range of the sharp angle γ is 80° - 100°. The sharp angle γ within this angle range makes the fixture have good circumferential telescopicity. If the angle of the sharp angle γ is too small, the sharp angle part of the tail section of the fixture 33 is too long, which is not conducive to the overall size of the fixture 33. If the angle of the included angle γ is too large, it will affect the circumferential telescopicity of the tail section of the fixture 33; the width b of the middle section of the fixture 33 is 0.1 - 0.2 mm smaller than the width of the connection head of the lamp tube 2, so that the connection head of the lamp tube 2 can be tightly clamped by the fixture 33, ensuring that the lamp tube 2 can be stably installed on the outer support 31. The fixture 33 on the inner support 32 has the same structure as the fixture 33 on the outer support 31.

[0051] In this embodiment, it is assumed that the installation angle is 0° when the lamp tube 2 is parallel to the turbine casing 100, and the adjustment range of the installation angle of the lamp tube 2 is -20° - 20°, which can meet the heating requirements of different models of turbine casings 100.

[0052] As Figure 1 and Figure 2As shown, in this embodiment, a lifting mechanism 5 is further included. The lifting mechanism 5 includes a telescopic device 51 that telescopically moves along the axis direction of the turbine casing 100 and a lifting platform 52 disposed on the telescopic device 51 for driving the inner support 32 to move. The telescopic device 51 drives the inner support 32 to lift through the lifting platform 52, which can ensure that the heating section of the lamp tube 2 on the inner support 32 is aligned with the turbine casing 100 and guarantee the heating efficiency. Optionally, the lifting platform 52 is connected to the inner support 32 through a connecting rod 53. On the one hand, it can reduce the overall weight of the lifting mechanism 5, and on the other hand, it can shorten the stroke requirement of the telescopic device 51, thereby reducing costs.

[0053] As Figure 8 and Figure 9 As shown, in this embodiment, 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 communicating with the annular channel 41 are arranged on the cooling layer partition 4. During operation, the external cold air enters the annular channel 41 through the air inlet pipe 42, cools the cooling layer partition 4, and then is discharged from the air outlet pipe 43, which can ensure the heat insulation effect of the cooling layer partition 4 and thus guarantee the heating accuracy. Optionally, an avoidance groove 44 for avoiding the lamp tube 2 is formed on the cooling layer partition 4, which can effectively prevent the lamp tube 2 on the outer support 31 from heating the lamp tube 2 on the inner support 32 while reducing the size of the cooling layer partition 4.

[0054] Due to the temperature distribution difference between the inner side of the turbine casing 100 (including the outer turbine ring disposed on the inner side of the turbine casing 100) and the outer side of the turbine casing 100 under the actual working conditions of the aero-engine, and the inner side of the turbine casing 100 and the outer turbine ring are in the high-temperature gas side area with high temperature, while the outer side of the turbine casing 100 is in the internal flow area of the air system and is cooled by cold air with a reduced temperature. Therefore, using the lamp tubes 2 with different heating powers to heat the outer side and the inner side of the turbine casing 100 can reduce the cost while meeting the requirements. In this embodiment, the lamp tubes 2 include the outer lamp tubes 21 disposed on the outer support 31 and the inner lamp tubes 22 disposed on the inner support 32. The power of the outer lamp tubes 21 is 1.5 kW to 2.5 kW, the total length is 150 to 250 mm, and the heating length is 80 to 140 mm. The power of the inner lamp tubes 22 is 2.5 kW to 3.5 kW, the total length is 200 to 300 mm, and the heating length is 120 to 180 mm. Optionally, the lamp tubes 2 are quartz lamp tubes. The connection heads at both ends of the quartz lamp tubes are power supply electrodes, and the electrodes are wrapped in white high-temperature resistant porcelain heads. The wires at both ends of the electrodes pass through above the porcelain heads to connect the porcelain heads of the quartz lamp tubes to the mounting seat, thus forming a ring-shaped quartz lamp tube heating system. The quartz lamp tubes are connected to the power supply end through a control cabinet, and the input voltage is adjusted through the control cabinet to change the input power of the quartz lamp tubes, thereby realizing an adjustable heating rate to meet the heating requirements for the test. Optionally, a silver reflective coating is sprayed on the back of the heating filaments of the quartz lamp tubes. By arranging the quartz lamp tubes in a ring shape, the radiant heat is concentrated and reflected onto the turbine casing 100.

[0055] The matrix heating device for the turbine casing of the present invention can simulate the temperature distribution law under the working state of the turbine casing of the aero-engine. Its heating temperature range is wide, and the maximum heating temperature can reach 1800 K, meeting the range of casing temperature changes within the working envelope of the aero-engine. The installation angles of the outer lamp tubes 21 and the inner lamp tubes 22 can both be adjusted within the range of -20° to 20°. By coordinating and adjusting the heating powers of the outer lamp tubes 21 and the inner lamp tubes 22, the heating temperature can be precisely controlled, thereby realizing the simulation of non-uniform or uniform temperature loads in the circumferential direction of the turbine casing. Compared with flame heating, heating film pasting, and resistance wire heating, the lamp tubes 2 heat the casing by means of thermal radiation with a uniform circumferential temperature distribution, with high heating efficiency. It only takes 30 minutes to complete a state point test. It is simple and reliable, with low test costs, and can simulate the temperature field of the turbine casing under the actual working state of the engine under laboratory conditions, and can improve the test efficiency.

[0056] As Figure 1 and Figure 5 shown, a method for simulating a non-uniform temperature field for a turbine casing uses the above-mentioned matrix heating device for the turbine casing, and it includes the following steps:

[0057] S1. Establish the corresponding relationship between the heating power of the lamp tube 2 and the temperature at the local position of the turbine casing 100 through calibration;

[0058] S2. According to the circumferential temperature non-uniform distribution on the outer side of the turbine casing, combined with the calibration result of step S1, determine the circumferential position layout of the outer lamp tubes 21. In the local high-temperature area, the outer lamp tubes 21 around this position can be densely arranged, and in the local low-temperature area, the outer lamp tubes 21 around this position can be sparsely arranged. Then, by adjusting the heating power of the outer lamp tubes 21 at different circumferential positions, simulate the circumferential temperature non-uniform distribution on the outer side of the turbine casing;

[0059] S3. Adjust 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;

[0060] S4. According to the circumferential temperature non-uniform distribution on the inner side of the turbine casing 100 and the turbine outer ring, combined with the calibration result of step S1, determine the circumferential position layout of the inner lamp tubes 22. By making the circumferential position distribution of the inner lamp tubes 22 non-uniform and adjusting the heating power of the inner lamp tubes 22 at different circumferential positions, simulate the circumferential temperature non-uniform distribution on the inner side of the turbine casing and the turbine outer ring;

[0061] S5. Introduce cold air into the annular channel 41 in the cooling layer partition 4 through the air inlet pipe 42 to prevent the outer lamp tubes 21 and the inner lamp tubes 22 from heating each other;

[0062] S6. Turn on all the outer lamp tubes 21 and the inner lamp tubes 22 simultaneously, and achieve non-uniform temperature distribution through uneven heating quantity, simulating the non-uniform temperature field of the turbine casing 100 under the working condition of the aero-engine.

[0063] In the non-uniform temperature field simulation method for the turbine casing of this embodiment, through the circumferential non-uniform distribution of the outer lamp tubes 21 and adjusting the heating power of the outer lamp tubes 21 at different positions, the circumferential temperature difference on the outer side of the turbine casing 100 is achieved. Through the circumferential non-uniform distribution of the inner lamp tubes 22 and adjusting the heating power of the inner lamp tubes 22 at different positions, the circumferential temperature non-uniform distribution on the inner side of the turbine casing and the outer ring is achieved. Through uneven heating quantity, non-uniform temperature distribution is achieved, simulating the non-uniform temperature field of the turbine casing under the working condition of the aero-engine.

[0064] As Figure 10 and Figure 11 shown, in this embodiment, step S1 specifically includes the following steps:

[0065] S11. Take a casing sample 102 made of the same material as the turbine casing 100, and ensure that the heating area of the casing sample 102 is 1 / 30 - 1 / 20 of the turbine casing 100 model;

[0066] S12. Fix the thermocouples on the inner and outer surfaces of the casing specimen 102 by spot welding. A plurality of measuring points are arranged on the inner and outer surfaces of the casing specimen 102 respectively. A plurality of thermocouple grooves 101 are respectively formed on the inner and outer surfaces of the casing specimen 102. The thermocouples are fixed in the thermocouple grooves 101 by spot welding. Three thermocouple grooves 101 are formed on the outer surface of the casing specimen 102, and the thermocouple grooves 101 formed on the inner surface of the casing specimen 102 are not shown. It can be understood that the number of the thermocouple grooves 101 can be increased or decreased according to the use requirements;

[0067] S13. Radiatively heat the casing specimen 102 with a lamp tube 2. The installation angle of the lamp tube 2 and the distance to the turbine casing 100 are kept consistent with the test device. After the temperature is stable, record the heating power and the temperature, and adjust the heating power to obtain the temperatures of the inner and outer surfaces of the casing under different heating powers;

[0068] S14. Radiatively heat the casing specimen 102 with two lamp tubes 2, and adjust the heating power to obtain the temperatures of the inner and outer surfaces of the casing under different heating powers;

[0069] S15. Radiatively heat the casing specimen 102 with three lamp tubes 2, and adjust the heating power to obtain the temperatures of the inner and outer surfaces of the casing under different heating powers;

[0070] S16. Sort out the test data, and establish the corresponding relationship between the number of the lamp tubes 2, the heating power and the temperature of the local position of the turbine casing 100; According to the simulation requirements of the circumferentially uniform temperature load of the turbine casing 100, determine the heating powers and the numbers of the outer lamp tube 21 and the inner lamp tube 22, and adjust the heating powers of each lamp tube 2 to make the circumferential temperature load of the casing reach the simulation requirements.

[0071] The above are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. 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 it includes a support tabletop (1) for fixing the turbine casing, a lamp tube (2) for heating the turbine casing, a lamp tube support (3) for installing 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 tabletop (1), an inner support (32) arranged parallel to the axis direction of the turbine casing, and a fixture (33) for installing the lamp tube (2). A plurality of the outer supports (31) are arranged in a ring around the outside of the turbine casing, a plurality of the inner supports (32) are arranged in a ring around the inside of the turbine casing, the lamp tube (2) is respectively arranged on the outer support (31) and the inner support (32) through the fixture (33), and the cooling layer partition (4) is arranged between the outer support (31) and the inner support (32). Two adjacent outer supports (31) are connected to form a conical surface. Two fixtures (33) are arranged at intervals on the inner wall surface of each outer support (31). The fixture (33) includes 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 for installing the lamp tube (2) arranged on the slider (332). Both ends of the lamp tube (2) are respectively connected to the corresponding mounting seats. By adjusting the position of the slider (332) on the sliding seat (331), the installation angle adjustment of the lamp tube (2) on the outer support (31) is realized.

2. The matrix heating device for a turbine casing according to claim 1, characterized in that Two adjacent inner supports (32) are connected to form a cylindrical surface. Two fixtures (33) are arranged at intervals on the outer wall surface of each inner support (32). The fixture (33) on the inner support (32) has the same structure as the fixture (33) on the outer support (31). By adjusting the position of the slider (332) on the sliding seat (331), the installation angle adjustment of the lamp tube (2) on the inner support (32) is realized.

3. The matrix heating device for a turbine casing according to claim 1, characterized in that the outer support (31) is hinged to the support tabletop (1). By adjusting the angle θ between the outer support (31) and the support tabletop (1), the installation angle adjustment of the lamp tube (2) on the outer support (31) is realized.

4. The matrix heating device for a turbine casing according to any one of claims 1 to 3, characterized in that assuming that the installation angle is 0° when the lamp tube (2) is parallel to the turbine casing, the adjustment range of the installation angle of the lamp tube (2) is -20° to 20°.

5. The matrix heating device for a turbine casing according to claim 4, characterized in that It further includes a lifting mechanism (5), and the lifting mechanism (5) includes a telescopic device (51) that telescopically moves along the axis direction of the turbine casing and a lifting platform (52) disposed on the telescopic device (51) for driving the inner support (32) to move.

6. The matrix heating device for a turbine casing according to claim 5, wherein 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) communicated with the annular channel (41) are disposed on the cooling layer partition plate (4).

7. The matrix heating device for a turbine casing according to claim 6, wherein the lamp tube (2) includes an outer lamp tube (21) disposed on the outer support (31) and an inner lamp tube (22) disposed on the inner support (32). The power of the outer lamp tube (21) is 1.5 kW to 2.5 kW, the total length is 150 to 250 mm, and the heating length is 80 to 140 mm. The power of the inner lamp tube (22) is 2.5 kW to 3.5 kW, the total length is 200 to 300 mm, and the heating length is 120 to 180 mm.

8. A method for simulating a non-uniform temperature field of a turbine casing, characterized in that, Using the matrix heating device for a turbine casing according to claim 7, it includes the following steps: S1. Establish the corresponding relationship between the heating power of the lamp tube (2) and the temperature of the local position of the turbine casing through calibration; S2. According to the circumferential temperature non-uniform distribution on the outer side of the turbine casing, combined with the calibration result of step S1, determine the circumferential position layout of the outer lamp tube (21). In the local high-temperature area, the outer lamp tubes (21) around this position can be densely arranged, and in the local low-temperature area, the outer lamp tubes (21) around this position can be sparsely arranged. Then, by adjusting the heating power of the outer lamp tubes (21) at different circumferential positions, simulate the circumferential temperature non-uniform distribution on the outer side of the turbine casing; S3. Adjust the height of the lifting mechanism (5) so that the inner lamp tube (22) is aligned with the turbine outer ring, and ensure 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 circumferential temperature non-uniform distribution on the inner side of the turbine casing and the turbine outer ring, combined with the calibration result of step S1, determine the circumferential position layout of the inner lamp tube (22). Through the non-uniform circumferential position distribution of the inner lamp tube (22) and adjusting the heating power of the inner lamp tubes (22) at different circumferential positions, simulate the circumferential temperature non-uniform distribution on the inner side of the turbine casing and the turbine outer ring; S5. Introduce cold air into the annular channel (41) in the cooling layer partition plate (4) through the air inlet pipe (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 inner lamp tubes (22) simultaneously, and realize the non-uniform temperature distribution through the uneven heating quantity to simulate the non-uniform temperature field of the turbine casing under the working condition of the aeroengine.

9. The non-uniform temperature field simulation method for a turbine casing according to claim 8, characterized in that, The specific steps of step S1 include the following steps: S11. Take a casing sample 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. Fix the thermocouple on the inner and outer surfaces of the casing sample by spot welding, and arrange multiple measuring points on the inner and outer surfaces of the casing sample respectively; S13. Radiatively heat the casing sample with a lamp tube (2). The installation angle of the lamp tube (2) and the distance to the turbine casing are consistent with the test device. After the temperature stabilizes, record the heating power and temperature, and adjust the heating power to obtain the temperatures of the inner and outer surfaces of the casing at different heating powers; S14. Radiatively heat the casing sample with two lamp tubes (2), and adjust the heating power to obtain the temperatures of the inner and outer surfaces of the casing at different heating powers; S15. Radiatively heat the casing sample with three lamp tubes (2), and adjust the heating power to obtain the temperatures of the inner and outer surfaces of the casing at 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 at the local position of the turbine casing.

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