Casing thermal deformation test device and transient deformation simulation method

Abstract

The invention discloses a casing thermal deformation test device and a transient deformation simulation method, and the device comprises a test bench which is used for supporting and positioning a casing; the thermal environment simulation mechanism comprises an inner heating piece used for heating the inner surface of the casing and an outer heating piece used for heating the outer surface of the casing, and the heating temperature of the inner heating piece and the heating temperature of the outer heating piece are independently controlled so as to simulate the inner surface heating process and the outer surface heating process of the casing in actual work respectively; the cooling gas simulation mechanism is mounted on the test bed, is used for communicating with the inner cavity of the casing and is used for introducing cooling gas into the casing to simulate the heat transfer process of the cold air side of the casing in the actual working process; the measuring mechanism is used for monitoring the temperature of the inner and outer surfaces of the casing and measuring the thermal deformation of the casing. According to the invention, the simulation of the radial transient deformation process of the case in the working envelope of the aero-engine can be realized under laboratory conditions, the radial deformation of the case in different states can be accurately obtained, and the measurement precision of the thermal deformation of the case is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of active clearance control of aircraft engine turbines, and in particular to a casing thermal deformation test device and a casing transient deformation simulation method using the casing thermal deformation test device. Background Art

[0002] As an important connecting part of the engine turbine stator, the turbine casing of an aircraft engine bears mechanical loads, gas loads, and thermal loads. It is an important load-bearing component and a key high-temperature component in the engine. The turbine casing and the turbine moving blades directly or indirectly form a gas channel to form a tip clearance. Under long-term high-temperature working conditions, the casing will deform, affecting the tip clearance and forming a more complex leakage flow, which will in turn affect the performance, fuel consumption, and reliability of the entire engine. Therefore, understanding the thermal deformation law of the turbine casing, rationally designing the tip clearance, and reducing rotor-stator friction are of great significance to improving the performance of the entire engine.

[0003] In the existing turbine casing design process, the thermal deformation law of the turbine casing under the engine working state is often obtained by the finite element analysis method, and the change trend of the turbine casing under different engine working states is obtained, which has a certain reference value for the structural design of the turbine casing and the value of the tip clearance. However, this method cannot accurately obtain the deformation of the turbine casing under different states, the accuracy is not enough, and there is a lack of test data to support the refined design of the turbine casing. In order to accurately grasp the relationship between the change of casing thermal deformation and temperature, a mounting seat is usually arranged on the engine casing, and the engine tip clearance value under different states is tested by a gap probe, and the relationship between the change of casing thermal deformation and temperature is indirectly obtained. However, when measuring the turbine tip clearance in the whole machine, only the change value of the clearance can be obtained, but the deformation data of the casing cannot be obtained. Moreover, it is time-consuming and laborious to perform a whole machine tip clearance measurement test, and often only the clearance values ​​of several key states are measured, which is inefficient and costly, and it is impossible to achieve efficient and reliable design of the turbine casing.

[0004] The Chinese patent with publication number CN104713731B discloses a model verification test bench for active clearance control of an aircraft engine turbine casing, which includes an air supply module, a thermal environment simulation module, a measurement module, and a controllable thermal deformation casing model test piece. A heating mechanism and a cooling channel are arranged inside and outside the casing to simulate the thermal deformation process of the turbine casing under the working state of the engine. However, the temperature of the turbine casing simulated by the test bench does not exceed 200°C, and the temperature difference between the inner and outer surfaces of the casing is within 10°C. During the actual operation of the engine, the maximum temperature of the turbine casing wall under the design state can reach 650°C, and the minimum temperature is also 350°C. The temperature difference of the turbine casing wall is about 300°C. The test bench cannot simulate the temperature field of the turbine casing under real working conditions, and cannot realize the transient deformation simulation of the turbine casing within the working envelope under real engine working conditions, resulting in insufficient measurement accuracy of the casing thermal deformation. Summary of the invention

[0005] The present invention provides a casing thermal deformation test device and a transient deformation simulation method to solve the technical problem in the prior art that the temperature field of a turbine casing under real engine working conditions cannot be simulated, resulting in low measurement accuracy of casing thermal deformation.

[0006] According to one aspect of the present invention, there is provided a casing thermal deformation test device, comprising: a test bench for supporting and positioning the casing; A thermal environment simulation mechanism, comprising an inner heating element for heating the inner surface of the casing and an outer heating element for heating the outer surface of the casing, wherein the heating temperatures of the inner heating element and the outer heating element are independently controlled to respectively simulate the inner surface heating process and the outer surface heating process of the casing in actual operation; A cooling air simulation mechanism is installed on the test bench and communicated with the inner cavity of the casing, and is used to introduce cooling air into the casing to simulate the heat transfer process of the cooling air side of the casing during actual working process; A measuring mechanism is used to monitor the temperature of the inner and outer surfaces of the casing and to measure the radial thermal deformation of the casing.

[0007] Furthermore, the test bench includes a test base and a support plate fixed on the test base, and a mounting hole for the casing to pass through is opened in the support plate; An expansion cavity is opened in the radial direction of the mounting hole in the support plate, and an expansion block is movably installed in the expansion cavity along the radial direction. The expansion block is used to be connected with the flange edge of the casing.

[0008] Further, the inner heating element comprises an inner mounting seat for being arranged in the inner cavity of the casing and fixed on the test bench, an inner supporting seat fixed on the inner mounting seat, and an inner heating tube arranged around the outer surface of the inner supporting seat, and the outer heating element comprises an outer supporting seat for being arranged around the outside of the casing and fixed on the test bench, and an outer heating tube arranged around the inner surface of the outer supporting seat; The inner heating tube and the outer heating tube are both electrically connected to the electric controller.

[0009] Furthermore, the maximum heating power of the inner heating tube is set to 4KW.

[0010] Furthermore, the maximum heating power of the external heating tube is set to 2KW.

[0011] Furthermore, the inner heating tubes are used to be arranged at intervals along the radial direction relative to the inner surface of the casing, and the outer heating tubes are used to be arranged at intervals along the radial direction relative to the outer surface of the casing.

[0012] Furthermore, the cooling gas simulation mechanism includes an air supply pipe for conveying cooling gas, a heater for heating the cooling gas in the air supply pipe, and an air guide ring arranged outside the casing, wherein a cooling channel for surrounding the casing and communicating with the inner cavity of the casing is arranged in the air guide ring, and an outlet end of the air supply pipe is arranged along a tangent direction of the cooling channel and communicated with the bottom end of the cooling channel; The heater is connected to the inlet end of the gas supply pipe.

[0013] Furthermore, a rectifying baffle is provided in the middle of the cooling channel along the axial direction thereof, and the rectifying baffle is used to make the cooling gas evenly fill the cooling channel.

[0014] Furthermore, the measuring mechanism includes a temperature measuring member arranged on the inner and outer surfaces of the casing, a temperature inspection meter electrically connected to the temperature measuring member, and a displacement measuring member arranged around the outside of the outer support seat. The measuring end of the displacement measuring member extends into the outer support seat and is used to maintain unconstrained free contact with the outer surface of the casing in the radial direction to measure the radial displacement of the outer surface of the casing.

[0015] In addition, according to another aspect of the present invention, a casing transient deformation simulation method is also provided, using the casing thermal deformation test device, the casing transient deformation simulation method comprises the following steps: S1: According to the circumferential temperature load simulation requirement of the casing of the aircraft engine in one of the working states, the heating power of the thermal environment simulation mechanism is determined to be adapted thereto, that is, the heating powers of the inner heating element and the outer heating element can respectively heat the inner surface and the outer surface of the casing to the corresponding maximum temperature in the working state; S2: turning on the inner heating element and the outer heating element to heat the inner surface and the outer surface of the casing respectively and adjusting the inner heating element and the outer heating element so that the heating rate is consistent with the heat transfer rate of the casing in the current working state of the aircraft engine to simulate the heat transfer process on the gas side of the casing; S3: Turn on the cooling air simulation mechanism to introduce cooling air into the casing, so that the temperature of the cooling air is consistent with the actual bleed air temperature of the aircraft engine in this working state, so as to simulate the heat transfer process on the cooling air side of the casing; S4: Turn on the measuring mechanism to monitor the inner surface temperature and the outer surface temperature of the casing in real time, and adjust the thermal environment simulation mechanism and the cooling gas simulation mechanism according to the temperature data monitored by the measuring mechanism, so as to ensure that the inner surface and the outer surface of the casing respectively reach the corresponding stable temperature under the condition of introducing cooling gas, and keep the temperature stable for a preset time, and measure and collect the radial thermal deformation of the casing in real time through the measuring mechanism; S5: The above steps are used to simulate the transient deformation of the casing of the aircraft engine in other working states to obtain the radial thermal deformation of the casing in different working states.

[0016] The present invention has the following beneficial effects: The casing thermal deformation test device of the present invention can heat the inner surface of the casing by the inner heating element of the thermal environment simulation mechanism and heat the outer surface of the casing by the outer heating element, so as to respectively simulate the heating process of the inner surface and the outer surface of the casing in the actual process, and can simulate the large temperature difference between the inner surface and the outer surface of the casing, so as to make the heat transfer process of the casing consistent with that under the actual working conditions; cooling air is introduced into the interior of the casing by the cooling air simulation mechanism to simulate the heat transfer process of the cold air side of the casing in the actual working process; during the operation of the thermal environment simulation mechanism and the cooling air simulation mechanism, the temperature of the inner surface and the outer surface of the casing is monitored in real time by the measuring mechanism to ensure that the temperature of the inner surface and the outer surface of the casing is consistent with the temperature under the actual working conditions, and the deformation of the casing at different circumferential positions is measured in real time to record the thermal deformation of the casing under different working conditions, thereby realizing the measurement of the thermal deformation of the casing when the aircraft engine is in different working conditions. The device can heat the casing under the condition of cooling air passing through the casing, keep the casing temperature field consistent with the casing temperature field under the laboratory conditions and the actual working conditions, and highly match the test state with the working state of the aircraft engine. It can simulate the conversion of the aircraft engine from the working state of slow speed, take-off, climb, cruise and descent, effectively simulate the transient deformation process of the casing under the actual working conditions of the aircraft engine, accurately obtain the radial deformation of the casing under different conditions of the aircraft engine, and have high test accuracy for the thermal deformation of the casing, which can provide data support for the refined design of the casing. In addition, the device is simple and reliable, with low test cost, reduced test cycle and high test efficiency.

[0017] 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

[0018] 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 is a cross-sectional view of a casing thermal deformation test device according to a preferred embodiment of the present invention; Figure 2 It is a test flow chart of a casing thermal deformation test device according to a preferred embodiment of the present invention; Figure 3 sectional view of the cooling gas simulation mechanism of the preferred embodiment of the present invention Figure 1 ; Figure 4 sectional view of the cooling gas simulation mechanism of the preferred embodiment of the present invention Figure 2 ; Figure 5 It is a schematic plan view of a support plate according to a preferred embodiment of the present invention.

[0019] Legend: 100, casing; 200, test bench; 201, test base; 202, support plate; 2021, mounting hole; 2022, expansion chamber; 2023, expansion block; 2024, accommodation hole; 300, thermal environment simulation mechanism; 301, inner heating element; 3011, inner mounting seat; 3012, inner support seat; 3013, inner heating tube; 302, outer heating element; 3021, outer support seat; 3022, External heating tube; 400, cooling air simulation mechanism; 401, air supply pipe; 4011, cooling channel; 402, heater; 403, rectifying baffle; 404, compressor; 405, flow control valve; 406, flow meter; 407, thermocouple; 500, measuring mechanism; 501, temperature measuring part; 502, temperature patrol meter; 503, displacement measuring part; 504, data acquisition system; 600, sealing part. DETAILED DESCRIPTION

[0020] 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.

[0021] like Figure 1 and Figure 2As shown, the casing 100 thermal deformation test device of the present embodiment includes a test bench 200 for supporting and positioning the casing 100, and a thermal environment simulation mechanism 300, a cooling gas simulation mechanism 400 and a measuring mechanism 500 installed on the test bench 200. The thermal environment simulation mechanism 300 includes an inner heating element 301 and an outer heating element 302. The inner heating element 301 is arranged in the inner cavity of the casing 100, and is used to heat the inner surface of the casing 100 to simulate the gas temperature of the inner surface of the casing 100 under actual working conditions. The outer heating element 302 is arranged on the outside of the casing 100, and is used to heat the outer surface of the casing 100 to simulate the gas temperature of the inner surface of the casing 100 under actual working conditions, so that the heat transfer process of the casing 100 on the gas side in the actual working process is simulated by the inner heating element 301 and the outer heating element 302. The cooling air simulation mechanism 400 is arranged on the test bench 200 and communicated with the inner cavity of the casing 100, and is used to introduce cooling air into the casing 100, and make the introduced cooling air consistent with the actual bleed air temperature of the aircraft engine, so as to simulate the heat transfer process of the cold air side of the casing 100 during the actual working process. The measuring mechanism 500 is used to monitor the temperature of the inner and outer surfaces of the casing 100 during the working process of the thermal environment simulation mechanism 300 and the cooling air simulation mechanism 400, so as to ensure that the temperature of the inner and outer surfaces of the casing 100 is consistent with the temperature under the actual working condition, and to measure the deformation of the casing 100 at different circumferential positions in real time, so as to record the thermal deformation of the casing 100 under different working conditions. Therefore, by heating the casing 100 under the condition that cooling air is passed into the casing 100, the temperature field of the casing 100 under laboratory conditions can be kept consistent with the temperature field of the casing 100 under actual working conditions. The test state is highly matched with the working state of the aircraft engine, and the conversion of the aircraft engine from working states such as slow speed, take-off, climb, cruise and descent can be simulated to simulate the radial transient deformation process of the casing 100 under actual working conditions, truly reflecting the transient deformation of the casing under different working states of the aircraft engine, and the test accuracy of the thermal deformation of the casing 100 is high and the test efficiency is high.

[0022] Specifically, since the operation of an aircraft engine is a transient process, switching between various operating states such as slow speed, take-off, climbing, cruising and descending, the maximum temperature of the inner surface of the casing 100 in different states is between 300°C and 700°C, and the minimum temperature of the outer surface is between 150°C and 400°C. Therefore, the maximum surface temperature of the casing 100 in different states can be determined according to the simulation requirements of the circumferential temperature load of the casing 100 in different operating states. For example, when the aircraft engine is in the slow speed state on the ground, the maximum surface temperature of the casing 100 is about 300°C; when the aircraft engine is in the take-off, climbing and other states, the maximum surface temperature of the casing 100 is about 650°C. According to the maximum temperature that can be reached on the inner and outer surfaces of the casing 100 in one of the instantaneous working states of the aircraft engine, the heating powers of the inner heating element 301 and the outer heating element 302 are adjusted to match them respectively, and the inner surface of the casing 100 and the outer surface of the casing 100 are independently heated by the inner heating element 301 and the outer heating element 302 respectively to simulate the heating process of the fuel gas side of the casing 100 in this working state, and the cooling gas simulation mechanism 400 is started to pass cooling gas into the inner cavity of the casing 100, and the passed cooling gas is made consistent with the actual bleed air temperature of the aircraft engine to simulate The heat transfer process of the cold air side of the simulated casing 100 under this working condition is performed, and the measuring mechanism 500 is started to monitor the temperatures of the inner and outer surfaces of the casing 100, and the inner heating element 301 and the outer heating element 302 are adjusted according to the temperature data monitored by the measuring mechanism 500 to ensure that the temperatures of the inner and outer surfaces of the casing 100 reach the corresponding stable temperatures under the actual working conditions, and keep the temperature stable for about 3 minutes. The radial thermal deformation of the casing 100 is collected in real time by the measuring mechanism 500 to realize the transient deformation simulation and measurement of the casing 100 within the working envelope of the aircraft engine.

[0023] like Figure 1 and Figure 5 As shown, the test bench 200 includes a test base 201 for support and a support plate 202 for positioning. The support plate 202 is arranged at the upper end of the test base 201 and fixed on the test base 201. A mounting hole 2021 adapted to the outer surface of the casing 100 is opened in the support plate 202. A mounting groove corresponding to the mounting hole 2021 is opened in the test base 201. The casing 100 is inserted into the mounting hole 2021 and the mounting groove, and is placed on the support plate 202 through the flange edge of the casing 100.

[0024] Specifically, an expansion cavity 2022 is provided in the radial direction of the mounting hole 2021 in the support plate 202, and an expansion block 2023 is movably installed in the radial direction in the expansion cavity 2022. The flange edge cover of the casing 100 is provided at the upper end of the support plate 202 and connected and fixed with the expansion block 2023, so that the casing 100 is stably supported by the support plate 202, and the axial positioning of the casing 100 is achieved. Preferably, four expansion cavities 2022 are symmetrically provided along the circumference of the mounting hole 2021, and the number of the expansion blocks 2023 corresponds to the expansion cavities 2022. Preferably, the thickness of the expansion block 2023 is adapted to the thickness of the expansion cavity 2022, so that the upper end of the expansion block 2023 and the lower end of the flange edge of the casing 100 are in the same plane, ensuring that the flange edge of the casing 100 is stably placed on the support plate 202.

[0025] A certain length of radial distance is left between the outer ring of the expansion chamber 2022 and the expansion block 2023, leaving a deformation space for free expansion for the casing 100 fixed on the expansion block 2023, avoiding constraints on the free expansion of the casing 100 in the radial direction, so that the casing 100 can drive the expansion block 2023 to move radially in the expansion chamber 2022 when it expands due to heat. At the same time, the expansion chamber 2022 can constrain the casing 100 in the radial direction to center the casing 100 and ensure the stability of the casing 100 during the test. Preferably, the radial distance between the outer ring of the expansion chamber 2022 and the expansion block 2023 is reserved to be 5 mm to 10 mm.

[0026] like Figure 1 As shown, the inner heating element 301 is arranged in the inner cavity of the casing 100, and the inner heating element 301 includes an inner mounting seat 3011, an inner support seat 3012 and an inner heating tube 3013. The inner mounting seat 3011 is placed in the mounting groove of the test base 201, and the inner support seat 3012 is arranged above the inner mounting seat 3011 and fixed to the inner mounting seat 3011. The outer surface shape of the inner support seat 3012 is adapted to the inner surface shape of the casing 100. The inner heating tube 3013 is arranged around the outer surface of the inner support seat 3012 and fixed to the inner support seat 3012 to heat the inner surface of the casing 100. Preferably, a plurality of inner heating tubes 3013 are evenly distributed along the circumferential direction on the outer surface of the inner support seat 3012. Optionally, the inner mounting seat 3011 adopts a liftable structure, which can drive the inner heating tube 3013 to move along the axial direction of the casing 100, flexibly adjust the heating position, and simulate the heating conditions of the casing 100 under different working conditions.

[0027] like Figure 1As shown, the external heating element 302 is arranged outside the casing 100, and the external heating element 302 includes an external support seat 3021 and an external heating tube 3022. The external support seat 3021 is sleeved on the outside of the casing 100, and its bottom is fixed on the test bench 200. The inner surface shape of the external support seat 3021 is adapted to the outer surface shape of the casing 100. The external heating tube 3022 is annularly arranged on the inner surface of the external support seat 3021 and fixed to the external support seat 3021 to heat the outer surface of the casing 100. Preferably, a plurality of external heating tubes 3022 are evenly distributed along the circumferential direction on the inner surface of the external support seat 3021. Preferably, both the internal heating tube 3013 and the external heating tube 3022 are quartz electric heating tubes.

[0028] like Figure 1 and Figure 5 As shown, a receiving hole 2024 is also provided in the support plate 202. The receiving hole 2024 is provided on the outer ring of the expansion cavity 2022 and is evenly distributed along the circumference of the mounting hole 2021. The receiving hole 2024 is used for connecting and positioning with the outer support seat 3021 and for inserting the external heating tube 3022. Specifically, the flange cover of the outer support seat 3021 is arranged on the receiving hole 2024, and is inserted into the receiving hole 2024 by screws to form a connection with the support plate 202. The number of the receiving holes 2024 corresponds to the number of the external heating tubes 3022, and the inner wall shape of the receiving hole 2024 near the mounting hole 2021 is adapted to the outer wall shape of the external heating tube 3022. The external heating tube 3022 can be inserted into the receiving hole along the inner wall surface of the outer support seat 3021, so that the external heating tube 3022 can extend to the bottom end of the casing 100 to adapt to casings 100 of different sizes, so that the outer surface of the casing 100 can be heated from top to bottom, effectively expanding the heating range. In addition, the setting of the receiving hole 2024 can reduce the thermal stress of the support plate 202, and avoid the influence of excessive thermal stress of the support plate 202 on the thermal deformation of the casing 100 during the heating process of the casing 100.

[0029] The inner heating tube 3013 and the outer heating tube 3022 are both electrically connected to the electric controller, so that the input voltages of the inner heating tube 3013 and the outer heating tube 3022 can be adjusted by the electric controller to adjust the heating power, so as to achieve the temperature and heating rate required by the test requirements, and then achieve the result of simulating the heat transfer process on the gas side of the casing 100. There is a difference in the temperature distribution of the inner surface of the casing 100 and the outer surface of the casing 100 when the aircraft engine is in working state. Under the design state, the temperature of the inner surface of the casing 100 can reach 650°C, and the lowest temperature of the outer surface of the casing 100 is also around 350°C. The temperature difference inside the casing 100 is as high as 300°C, and the cooling air bleed temperature is also above 200°C. Therefore, according to the simulation requirements of the circumferential temperature load of the casing 100, the heating power and number of the inner heating tube 3013 and the outer heating tube 3022 are determined. Preferably, the maximum heating power of the inner heating tube 3013 is set to 4kW, and the maximum heating power of the outer heating tube 3022 is set to 2kW, so that the temperature of the inner surface of the casing 100 can be heated to above 1000°C, thereby meeting the heating requirements of the difference in temperature distribution between the inner surface and the outer surface of the casing 100, and realizing the simulation of the large temperature difference between the inner surface and the outer surface under the actual working conditions of the casing 100. Optionally, the maximum heating power of the inner heating tube 3013 can also be above 4kW, and the maximum heating power of the outer heating tube 3022 can also be above 2kW.

[0030] like Figure 1 As shown, the inner heating tube 3013 is arranged at intervals along the radial direction relative to the inner surface of the casing 100, and the outer heating tube 3022 is arranged at intervals along the radial direction relative to the outer surface of the casing 100. On the one hand, it can avoid the inner heating tube 3013 and the outer heating tube 3022 from directly contacting the surface of the casing 100, and prevent the casing 100 from being damaged due to local overheating of the casing 100 caused by excessive heat conduction efficiency, so that the heat of the inner heating tube 3013 and the outer heating tube 3022 can be evenly transferred to the casing 100 by means of thermal radiation and convection, more accurately simulating the temperature field distribution of the casing 100 in the working state, and improving the overall heat transfer efficiency. On the other hand, during the heating process, the inner heating tube 3013, the outer heating tube 3022 and the casing 100 will all experience a certain degree of thermal expansion, and the radial gap between the inner heating tube 3013, the outer heating tube 3022 and the casing 100 can accommodate this expansion, prevent friction caused by excessive mechanical stress caused by expansion, avoid damage to the inner heating tube 3013, the outer heating tube 3022 and the casing 100, and improve the service life of the device. In addition, the radial gap between the inner heating tube 3013, the outer heating tube 3022 and the casing 100 also leaves free thermal expansion space for the casing 100 in the radial direction, ensures the accuracy of the measurement of the thermal deformation of the casing 100, and can ensure the flexibility and maintainability of the installation of the thermal environment simulation mechanism 300.

[0031] like Figure 1 , Figure 2, Figure 3 and Figure 4 As shown, the cooling gas simulation mechanism 400 includes an air supply pipe 401 for introducing cooling gas into the casing 100, a heater 402 for heating the cooling gas in the air supply pipe 401, and an air guide ring arranged outside the casing 100, the air guide ring is provided with a cooling channel 4011 for surrounding the casing 100 and communicating with the inner cavity of the casing 100, the outlet end of the air supply pipe 401 is arranged along the tangential direction of the cooling channel 4011 and communicates with the bottom end of the cooling channel 4011, the heater 402 is connected to the inlet end of the air supply pipe 401, and the cooling gas simulation mechanism 400 also includes a compressor 404 for compressing and outputting cooling gas. Specifically, the compressor 404 is arranged outside the casing 100, and the two ends of the air supply pipe 401 are respectively connected to the compressor 404 and the casing 100. The heater 402 is installed on the air supply pipe 401 between the compressor 404 and the casing 100 and is connected to the air supply pipe 401 to heat the cooling air output from the compressor 404 to the air supply pipe 401. The heater 402 can heat the cooling air to a maximum temperature of 350°C to achieve the bleed air temperature of the aircraft engine in the working state. The heated cooling air spirally rises from the bottom of the air guide ring along the tangential direction of the cooling channel 4011 and fills the entire cooling channel 4011, so that the cooling air entering the casing 100 meets the temperature variation range of the casing 100 within the working envelope of the aircraft engine.

[0032] Preferably, a flow control valve 405 is provided between the compressor 404 and the heater 402. The flow control valve 405 is connected to the air supply pipe 401 and is used to adjust the amount of cold air output from the compressor 404 to the air supply pipe 401 and the cooling air flow rate by changing the valve size. Preferably, a flow meter 406 and a thermocouple 407 are also provided on the air supply pipe 401 between the heater 402 and the casing 100. The flow meter 406 is electrically connected to the flow control valve 405, so that the flow of cooling air in the air supply pipe 401 can be monitored by the flow meter 406, and the monitoring result is fed back to the flow control valve 405 for adjusting the valve size to ensure that the cooling air flow entering the casing 100 is equivalent to the cooling air flow under the actual working condition of the casing 100; the thermocouple 407 is electrically connected to the heater 402, so that the temperature of the cooling air in the air supply pipe 401 after being heated by the heater 402 is monitored by the thermocouple 407, and the monitoring result is fed back to the heater 402 for power adjustment to ensure that the cooling air temperature entering the casing 100 is consistent with the bleed air temperature under the actual working condition of the casing 100. Therefore, by changing the valve size of the flow control valve 405 and the power of the heater 402 to adjust the flow and temperature of the cooling air entering the casing 100, the surface temperature distribution of the casing 100 in the actual working state of the engine can be simulated.

[0033] like Figure 1As shown, the cooling channel 4011 is provided with a rectifying baffle 403 in the middle of its axial direction to adjust the airflow direction and speed of the cooling air entering the cooling channel 4011, effectively reduce the impact and vortex generated when the cooling air enters the cooling channel 4011, make the cooling air evenly fill the entire cooling channel 4011, ensure that the cooling air evenly enters the interior of the turbine casing 100 in the entire circumferential direction, and thus achieve the effect of simulating the heat transfer process on the cold air side of the casing 100. Preferably, the rectifying baffle 403 is a plate-shaped structure or a flat plate with an arc. Preferably, the rectifying baffle 403 is set in the middle of the cooling channel 4011. For a longer cooling channel 4011, the airflow distribution can be adjusted and optimized to ensure that the cooling airflow over the entire length of the cooling channel 4011 can remain uniform and stable. Optionally, a rectifying baffle 403 may be provided at the outlet section of the cooling channel 4011 to adjust the outlet velocity and direction of the airflow to ensure that the cooling air can flow out evenly and act on the casing 100, thereby simulating the temperature field of the casing 100 under real working conditions and improving the accuracy of the test.

[0034] like Figure 1 and Figure 2 As shown, the measuring mechanism 500 includes a temperature measuring piece 501, a temperature patrol meter 502 and a displacement measuring piece 503. A plurality of temperature measuring pieces 501 are evenly distributed on the inner surface and the outer surface of the casing 100, respectively, for measuring the temperature of the inner surface and the outer surface of the casing 100, respectively. The temperature measuring piece 501 is electrically connected to the temperature patrol meter 502 to feed back the measurement result to the temperature patrol meter 502, to monitor the surface temperature of the casing 100 in real time, to simulate the temperature field of the turbine casing 100 under the actual working condition, and to improve the detection accuracy of the thermal deformation of the casing 100. Several displacement measuring parts 503 are evenly arranged along the outer periphery of the casing 100. Specifically, the fixed end of the displacement measuring part 503 is arranged outside the outer support seat 3021 and fixed to the test bench 200, and the measuring end extends into the outer support seat 3021 to maintain unconstrained free contact with the outer surface of the casing 100 in the radial direction, so as to measure the radial displacement of each part of the outer surface of the casing 100, and obtain the thermal deformation data of the casing 100, and the test accuracy is high. The temperature measuring part 501 is electrically connected to the electric controller, so that the electric controller can adjust the heating power of the inner heating part 301 and the outer heating part 302 according to the detection result of the temperature measuring part 501. Preferably, the temperature measuring part 501 adopts a K-type patch thermocouple, and the displacement measuring part 503 adopts a self-collecting digital display dial indicator, which is connected to the data acquisition system 504. The data acquisition system 504 transmits the data measured by the dial indicator to the computer in real time, thereby realizing automatic data acquisition by the computer, and can realize real-time synchronous display of data, real-time data acquisition and export.

[0035] like Figure 1As shown, a seal 600 is provided between the casing 100 and the test bench 200 and / or the cooling gas simulation mechanism 400. The seal 600 is used to abut the casing 100 to prevent cooling gas from leaking from between the casing 100 and the air supply pipe 401 or the air guide ring, thereby ensuring the cooling effect and cooling efficiency of the cooling gas.

[0036] In addition, according to another aspect of the present invention, a casing transient deformation simulation method is also provided, using the casing thermal deformation test device, the casing transient deformation simulation method comprises the following steps: S1: According to the circumferential temperature load simulation requirement of the casing of the aircraft engine in one of the working states, the heating power of the thermal environment simulation mechanism is determined to be adapted thereto, that is, the heating powers of the inner heating element and the outer heating element can respectively heat the inner surface and the outer surface of the casing to the highest temperature in the working state; S2: turning on the inner heating element and the outer heating element to heat the inner surface and the outer surface of the casing respectively and adjusting the inner heating element and the outer heating element so that the heating rate is consistent with the heat transfer rate of the casing in the current working state of the aircraft engine to simulate the heat transfer process on the gas side of the casing; S3: Turn on the cooling air simulation mechanism to introduce cooling air into the casing, so that the temperature of the cooling air is consistent with the actual bleed air temperature of the aircraft engine in this working state, so as to simulate the heat transfer process on the cooling air side of the casing; S4: Turn on the measuring mechanism to monitor the inner surface temperature and the outer surface temperature of the casing in real time, and adjust the thermal environment simulation mechanism and the cooling gas simulation mechanism according to the temperature data monitored by the measuring mechanism, so as to ensure that the inner surface and the outer surface of the casing respectively reach the corresponding stable temperature under the condition of introducing cooling gas, and keep the temperature stable for a preset time, and measure and collect the radial thermal deformation of the casing in real time through the measuring mechanism; S5: The above steps are used to simulate the transient deformation of the casing of the aircraft engine in other working states to obtain the radial thermal deformation of the casing in different working states.

[0037] 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 casing thermal deformation test device, characterized in that: include: A test bench (200) for supporting and positioning the casing (100); A thermal environment simulation mechanism (300) comprises an inner heating element (301) for heating the inner surface of the casing (100) and an outer heating element (302) for heating the outer surface of the casing (100), wherein the heating temperatures of the inner heating element (301) and the outer heating element (302) are independently controlled to respectively simulate the inner surface heating process and the outer surface heating process of the casing (100) in actual operation; a cooling air simulation mechanism (400) installed on the test bench (200) and used to communicate with the inner cavity of the casing (100); the cooling air simulation mechanism (400) is used to pass cooling air into the casing (100) to simulate the heat transfer process on the cooling air side of the casing (100) during actual operation; The measuring mechanism (500) is used to monitor the temperature of the inner surface and the outer surface of the casing (100) and measure the radial thermal deformation of the casing (100).

2. The casing thermal deformation testing device according to claim 1, characterized in that: The test bench (200) comprises a test base (201) and a support plate (202) fixed on the test base (201); a mounting hole (2021) for the casing (100) to pass through is provided in the support plate (202); an expansion cavity (2022) is provided in the support plate (202) along the radial direction of the mounting hole (2021); an expansion block (2023) is movably installed in the expansion cavity (2022) along the radial direction; the expansion block (2023) is used to be connected to the flange edge of the casing (100).

3. The casing thermal deformation testing device according to claim 2, characterized in that: The internal heating element (301) comprises an internal mounting seat (3011) which is arranged in the inner cavity of the casing (100) and fixed on the test base (201), an internal support seat (3012) which is fixed on the internal mounting seat (3011), and an internal heating tube (3013) which is arranged around the outer surface of the internal support seat (3012); the external heating element (302) comprises an external support seat (3021) which is arranged around the outside of the casing (100) and fixed on the test base (201), and an external heating tube (3022) which is arranged around the inner surface of the external support seat (3021); the internal heating tube (3013) and the external heating tube (3022) are both electrically connected to an electric controller.

4. The casing thermal deformation testing device according to claim 3, characterized in that: The maximum heating power of the internal heating tube (3013) is set to 4KW.

5. The casing thermal deformation testing device according to claim 3, characterized in that: The maximum heating power of the external heating tube (3022) is set to 2KW.

6. The casing thermal deformation testing device according to claim 3, characterized in that: The inner heating tube (3013) is used to be arranged at intervals along the radial direction relative to the inner surface of the casing (100), and the outer heating tube (3022) is used to be arranged at intervals along the radial direction relative to the outer surface of the casing (100).

7. The casing thermal deformation testing device according to claim 1, characterized in that: The cooling air simulation mechanism (400) comprises an air supply pipe (401) for conveying cooling air, a heater (402) for heating the cooling air in the air supply pipe (401), and an air guide ring arranged outside the casing (100), wherein the air guide ring is provided with a cooling channel (4011) for surrounding the casing (100) and communicating with the inner cavity of the casing (100), the outlet end of the air supply pipe (401) is arranged along the tangent direction of the cooling channel (4011) and communicates with the bottom end of the cooling channel (4011); the heater (402) is connected to the inlet end of the air supply pipe (401).

8. The casing thermal deformation testing device according to claim 7, characterized in that: The cooling channel (4011) is provided with a rectifying baffle (403) in the middle of its axial direction, and the rectifying baffle (403) is used to make the cooling air evenly fill the cooling channel (4011).

9. The casing thermal deformation testing device according to claim 3, characterized in that: The measuring mechanism (500) comprises a temperature measuring member (501) for being arranged on the inner surface and the outer surface of the casing (100), a temperature inspection instrument (502) electrically connected to the temperature measuring member (501), and a displacement measuring member (503) arranged in a ring outside the outer support seat (3021); the measuring end of the displacement measuring member (503) extends into the outer support seat (3021) and is used to maintain unconstrained free contact with the outer surface of the casing (100) in the radial direction, so as to measure the radial displacement of the outer surface of the casing (100).

10. A method for simulating transient deformation of a casing, characterized in that: Using the casing thermal deformation test device described in any one of claims 1 to 9, the casing transient deformation simulation method comprises the following steps: S1: According to the circumferential temperature load simulation requirement of the casing (100) of the aircraft engine in one of the working states, the heating power of the thermal environment simulation mechanism (300) is determined to be adapted thereto, that is, the heating powers of the inner heating element (301) and the outer heating element (302) are respectively capable of heating the inner surface and the outer surface of the casing (100) to the corresponding maximum temperature in the working state; S2: turning on the inner heating element (301) and the outer heating element (302) to heat the inner surface and the outer surface of the casing (100) respectively and independently, and adjusting the inner heating element (301) and the outer heating element (302) so that their heating rates are consistent with the heat transfer rate of the casing (100) in the current working state of the aircraft engine, so as to simulate the heat transfer process on the gas side of the casing (100); S3: starting the cooling air simulation mechanism (400) to introduce cooling air into the casing (100), so that the temperature of the cooling air is consistent with the actual bleed air temperature of the aircraft engine in this working state, so as to simulate the heat transfer process on the cold air side of the casing (100); S4: turning on the measuring mechanism (500) to monitor the inner surface temperature and the outer surface temperature of the casing (100) in real time, and adjusting the thermal environment simulation mechanism (300) and the cooling gas simulation mechanism (400) according to the temperature data monitored by the measuring mechanism (500) to ensure that the inner surface and the outer surface of the casing (100) respectively reach the corresponding stable temperature under the condition of introducing cooling gas, and keep the temperature stable for a preset time, and measure and collect the radial thermal deformation of the casing (100) in real time through the measuring mechanism (500); S5: The above steps are used to simulate the transient deformation of the casing (100) of the aircraft engine in other working states, so as to obtain the radial thermal deformation amount of the casing (100) in different working states.

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