Housing Thermal Deformation Test Device and Transient Deformation Simulation Method

Abstract

The present invention discloses a casing thermal deformation test device and a transient deformation simulation method. The device includes: a test bench for supporting and positioning the casing; a thermal environment simulation mechanism including an inner heating member for heating the inner surface of the casing and an outer heating member for heating the outer surface of the casing, and the heating temperatures of the inner heating member and the outer heating member are independently controlled to respectively simulate the heat receiving processes of the inner surface and the outer surface of the casing during actual operation; a cooling air simulation mechanism installed on the test bench and used for communicating with the inner cavity of the casing, and used for introducing cooling air into the casing to simulate the heat transfer process on the cold air side during actual operation of the casing; a measuring mechanism for monitoring the temperatures of the inner and outer surfaces of the casing and measuring the thermal deformation amount of the casing. The present invention can simulate the radial transient deformation process of the casing within the working envelope of an aeroengine under laboratory conditions, can accurately obtain the radial deformation amounts of the casing under different conditions, and improves the measurement accuracy of the thermal deformation amount of the casing.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine turbine active clearance control, and in particular, to a casing thermal deformation test device. In addition, it also relates to 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 aero-engine turbine casing bears mechanical loads, gas loads, thermal loads, etc., and is an important load-bearing component and a key high-temperature component in the engine. The turbine casing directly or indirectly forms a gas passage with the turbine rotor blades, forming a tip clearance. Under long-term high-temperature working conditions, the casing will deform, affecting the tip clearance, forming a more complex leakage flow, and further affecting the performance, fuel consumption rate, and reliability of the entire engine. Therefore, mastering the thermal deformation law of the turbine casing, reasonably designing the tip clearance, and reducing the rubbing between the rotating and stationary parts are of great significance for improving the performance of the entire engine.

[0003] In the existing design process of the turbine casing, the thermal deformation law of the turbine casing under the engine working conditions is often obtained through finite element analysis, and the change trend of the turbine casing under different engine working conditions is obtained, which has 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 amount of the turbine casing under different states, with insufficient accuracy and lack of test data to support the refined design of the turbine casing. In order to accurately master the relationship between the casing thermal deformation and temperature, mounting seats are usually arranged on the engine casing, and the tip clearance values of the engine under different states are measured through clearance probes to indirectly obtain the relationship between the casing thermal deformation and temperature. However, when measuring the turbine tip clearance in the whole machine, only the change value of the clearance can be obtained, and the deformation data of the casing cannot be obtained. Moreover, conducting a whole-machine tip clearance measurement test is time-consuming and laborious. Usually, only the clearance values of several key states are measured, with low efficiency and high cost, and the efficient and reliable design of the turbine casing cannot be achieved.

[0004] The Chinese patent with the publication number CN104713731B discloses an experimental bench for validating the model of an aero-engine turbine active clearance control casing, which includes a gas supply module, a thermal environment simulation module, a measurement module, and a controllable thermal deformation casing model experimental piece. Heating mechanisms and cooling channels are arranged inside and outside the casing to simulate the thermal deformation process of the turbine casing under the working conditions of the engine. However, the temperature of the turbine casing simulated by this experimental bench does not exceed 200 °C, and the temperature difference between the inner surface and the outer surface of the casing is within 10 °C. In the actual working process of the engine, the maximum temperature of the turbine casing wall under the design condition can reach 650 °C, and the minimum temperature is also 350 °C. The temperature difference of the turbine casing wall is about 300 °C. This experimental 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 the real working conditions of the engine, resulting in insufficient measurement accuracy of the thermal deformation of the casing. 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 the turbine casing under the real working conditions of the engine cannot be simulated, resulting in low measurement accuracy of the thermal deformation of the casing.

[0006] According to one aspect of the present invention, a casing thermal deformation test device is provided, including: a test bench for supporting and positioning the casing;

[0007] A thermal environment simulation mechanism including 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, and the heating temperatures of the inner heating element and the outer heating element are independently controlled to respectively simulate the heat receiving processes of the inner surface and the outer surface of the casing during actual operation;

[0008] A cooling gas simulation mechanism installed on the test bench and communicating with the inner cavity of the casing, and the cooling gas simulation mechanism is used to introduce cooling gas into the casing to simulate the heat transfer process on the cold gas side during the actual operation of the casing;

[0009] A measurement mechanism for monitoring the temperatures of the inner surface and the outer surface of the casing and measuring the radial thermal deformation of the casing.

[0010] Further, the test bench includes a test base and a support plate fixed on the test base. An installation hole for the casing to pass through is provided inside the support plate;

[0011] An expansion cavity is provided radially along the installation hole inside the support plate. An expansion block is installed radially movably in the expansion cavity, and the expansion block is used to connect with the flange of the casing.

[0012] Further, the internal heating member includes an internal mounting seat for being disposed in the inner cavity of the casing and fixed to the test bench, an internal support seat fixed to the internal mounting seat, and an internal heating pipe disposed around the outer surface of the internal support seat. The external heating member includes an external support seat for being disposed around the outside of the casing and fixed to the test bench, and an external heating pipe disposed around the inner surface of the external support seat;

[0013] Both the internal heating pipe and the external heating pipe are electrically connected to the electric controller.

[0014] Further, the maximum heating power of the internal heating pipe is set to 4KW.

[0015] Further, the maximum heating power of the external heating pipe is set to 2KW.

[0016] Further, the internal heating pipe is used to be arranged at intervals along the radial direction relative to the inner surface of the casing, and the external heating pipe is used to be arranged at intervals along the radial direction relative to the outer surface of the casing.

[0017] Further, 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 a gas guide ring arranged around the outside of the casing. A cooling channel for surrounding the casing and communicating with the inner cavity of the casing is arranged in the gas guide ring. The outlet end of the air supply pipe is arranged along the tangential direction of the cooling channel and communicated with the bottom end of the cooling channel;

[0018] The heater is connected to the inlet end of the air supply pipe.

[0019] Further, a rectifying partition is arranged in the middle of the cooling channel along its axial direction, and the rectifying partition is used to evenly fill the cooling gas in the cooling channel.

[0020] Further, the measuring mechanism includes a temperature measuring member for being arranged on the inner surface and the outer surface of the casing, a temperature inspection instrument electrically connected to the temperature measuring member, and a displacement measuring member arranged around the outside of the external support seat. The measuring end of the displacement measuring member extends into the external support seat and is used to keep free contact with the outer surface of the casing along the radial direction to measure the radial displacement of the outer surface of the casing.

[0021] In addition, according to another aspect of the present invention, a method for simulating the transient deformation of the casing is further provided. By using the above-mentioned casing thermal deformation test device, the method for simulating the transient deformation of the casing includes the following steps:

[0022] S1: According to the circumferential temperature load simulation requirement of the casing in one of the working states of the aero-engine, determine the heating power of the thermal environment simulation mechanism to be adapted thereto, that is, make the heating powers of the internal heating member and the external heating member can respectively heat the inner surface and the outer surface of the casing to the corresponding maximum temperature in this working state;

[0023] S2: Turn on the internal heating element and the external heating element to independently heat the inner surface and the outer surface of the casing respectively, and adjust the internal heating element and the external heating element so that their heating rates are consistent with the heat transfer rate of the casing in this operating state of the aero-engine, so as to simulate the heat transfer process on the gas side of the casing;

[0024] S3: Turn on the cooling gas simulation mechanism to introduce cooling gas into the casing, so that the temperature of the cooling gas is consistent with the actual bleed air temperature of the aero-engine in this operating state, so as to simulate the heat transfer process on the cold gas side of the casing;

[0025] 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 heat 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 reach the corresponding stable temperatures in this operating state respectively under the condition of introducing cooling gas, and maintain this temperature stable for a preset time, and measure and collect the radial thermal deformation of the casing in real time through the measuring mechanism;

[0026] S5: Simulate the transient deformation of the casing of the aero-engine in other operating states by using the above steps, so as to obtain the radial thermal deformation of the casing in different operating states.

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

[0028] The casing thermal deformation test device of the present invention can heat the inner surface of the casing through the inner heating element of the thermal environment simulation mechanism and heat the outer surface of the casing through the outer heating element, so as to respectively simulate the heating processes 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, making the heat transfer process of the casing consistent with that under the real working conditions; cool air is introduced into the casing through the cool air simulation mechanism to simulate the heat transfer process on the cool air side of the casing in the actual working process. During the working processes of the thermal environment simulation mechanism and the cool air simulation mechanism, the temperature of the inner surface and the outer surface of the casing is monitored in real time through the measuring mechanism to ensure that the temperature of the inner surface and the outer surface of the casing is consistent with that under the real working conditions, and the deformation amount at different circumferential positions of the casing is measured in real time to record the thermal deformation amount of the casing under different working states, thereby realizing the measurement of the thermal deformation amount of the casing of the aeroengine under different working states. This device can heat the casing under the condition of introducing cool air into it, make the temperature field of the casing consistent with that of the casing under the real working conditions under laboratory conditions, the test state is highly matched with the working state of the aeroengine, can simulate the conversion of the working states of the aeroengine such as idle, takeoff, climb, cruise and descent, effectively simulate the transient deformation process of the casing of the aeroengine under the real working conditions, accurately obtain the radial deformation amount of the casing of the aeroengine under different states, has a high test accuracy for the thermal deformation amount of the casing, and can provide data support for the refined design of the casing. Moreover, this device is simple and reliable, has a low test cost, reduces the test cycle, and has a high test efficiency.

[0029] In addition to the purposes, features and advantages described above, the present invention has other purposes, features and advantages. The present invention will be further described in detail below with reference to the drawings. 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 cross-sectional view of the casing thermal deformation test device of the preferred embodiment of the present invention;

[0032] Figure 2 is the test flow chart of the casing thermal deformation test device of the preferred embodiment of the present invention;

[0033] Figure 3 is the cross-section of the cool air simulation mechanism of the preferred embodiment of the present invention Figure 1 ;

[0034] Figure 4 is the cross-section of the cool air simulation mechanism of the preferred embodiment of the present invention Figure 2 ;

[0035] Figure 5 It is a schematic plan view of the support plate of the preferred embodiment of the present invention.

[0036] Legend:

[0037] 100, casing; 200, test bench; 201, test base; 202, support plate; 2021, mounting hole; 2022, expansion cavity; 2023, expansion block; 2024, accommodation hole; 300, thermal environment simulation mechanism; 301, internal heating element; 3011, internal mounting seat; 3012, internal support seat; 3013, internal heating pipe; 302, external heating element; 3021, external support seat; 3022, external heating pipe; 400, cooling gas simulation mechanism; 401, air supply pipe; 4011, cooling channel; 402, heater; 403, rectifying partition; 404, compressor; 405, flow control valve; 406, flowmeter; 407, thermocouple; 500, measuring mechanism; 501, temperature measuring element; 502, temperature data logger; 503, displacement measuring element; 504, data acquisition system; 600, seal. Detailed implementation manners

[0038] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways defined and covered by the following.

[0039] As Figure 1 and Figure 2As shown in the figure, the casing 100 thermal deformation test device of this embodiment includes a test bench 200 for supporting and positioning the casing 100, and a thermal environment simulation mechanism 300, a cooling air simulation mechanism 400, and a measurement mechanism 500 installed on the test bench 200. The thermal environment simulation mechanism 300 includes an internal heating element 301 and an external heating element 302. The internal 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 on the inner surface of the casing 100 under actual working conditions. The external heating element 302 is arranged outside the casing 100 and is used to heat the outer surface of the casing 100 to simulate the gas temperature on the inner surface of the casing 100 under actual working conditions. Thus, the heat transfer process on the gas side of the casing 100 during actual operation can be simulated by the internal heating element 301 and the external heating element 302 respectively. The cooling air simulation mechanism 400 is arranged on the test bench 200 and is in communication with the inner cavity of the casing 100. It 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 aeroengine, so as to simulate the heat transfer process on the cold air side of the casing 100 during actual operation. The measurement mechanism 500 is used to monitor the temperatures of the inner surface and the outer surface of the casing 100 during the operation of the thermal environment simulation mechanism 300 and the cooling air simulation mechanism 400, so as to ensure that the temperatures of the inner surface and the outer surface of the casing 100 are consistent with the temperatures under actual working conditions, and to measure the deformation amounts at different circumferential positions of the casing 100 in real time to record the thermal deformation amounts of the casing 100 under different working states. Thus, by heating the casing 100 under the condition of introducing cooling air into the casing 100, the temperature field of the casing 100 under laboratory conditions can be made 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 aeroengine, and it can simulate the conversion of working states of the aeroengine such as idle, takeoff, climb, cruise, and descent, so as to simulate the transient deformation process in the radial direction of the casing 100 under actual working conditions, truly reflect the transient deformation conditions of the casing of the aeroengine under different working states, with high test accuracy for the thermal deformation amount of the casing 100 and high test efficiency.

[0040] Specifically, since the operation process of an aero-engine is a transient process, which involves various working state conversions such as idle, takeoff, climb, cruise, and descent, the highest temperature on the inner surface of the casing 100 ranges from 300°C to 700°C, and the lowest temperature on the outer surface ranges from 150°C to 400°C under different states. Thus, according to the simulation requirements of the circumferential temperature load of the casing 100 under different working states, the highest surface temperature of the casing 100 under different states can be determined. For example, when the aero-engine is in the ground idle state, the highest surface temperature of the casing 100 is about 300°C; when the aero-engine is in states such as takeoff and climb, the highest surface temperature of the casing 100 is about 650°C. According to the highest temperatures that can be reached on the inner surface and the outer surface of the casing 100 in one instantaneous working state of the aero-engine, the heating powers of the inner heating element 301 and the outer heating element 302 are respectively adjusted to match them. The inner surface and the outer surface of the casing 100 are respectively heated independently by the inner heating element 301 and the outer heating element 302 to simulate the heating process on the gas side of the casing 100 under this working condition. The cooling gas simulation mechanism 400 is started to introduce cooling gas into the inner cavity of the casing 100, and the introduced cooling gas is made to be consistent with the actual bleed air temperature of the aero-engine to simulate the heat transfer process on the cold gas side of the casing 100 under this working condition. The measuring mechanism 500 is started to monitor the temperatures of the inner surface and the outer surface 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 surface and the outer surface of the casing 100 respectively reach the corresponding stable temperatures under the real working conditions, and maintain this temperature stable for about 3 minutes. The radial thermal deformation amount of the casing 100 is collected in real time by the measuring mechanism 500 to achieve the simulation and measurement of the transient deformation of the casing 100 within the working envelope of the aero-engine.

[0041] As Figure 1 and Figure 5 As shown in the figure, the test bench 200 includes a test base 201 for support and a support plate 202 for positioning. The support plate 202 is provided at the upper end of the test base 201 and fixed to the test base 201. An installation hole 2021 adapted to the outer surface of the casing 100 is opened in the support plate 202. A mounting groove corresponding to the installation hole 2021 is opened in the test base 201. The casing 100 is passed through the installation hole 2021 and the mounting groove, and is placed on the support plate 202 through the flange of the casing 100.

[0042] Specifically, an expansion cavity 2022 is radially formed in the support plate 202 along the radial direction of the mounting hole 2021. An expansion block 2023 is movably mounted in the expansion cavity 2022 along the radial direction. The flange of the casing 100 is covered on the upper end of the support plate 202 and is fixedly connected to the expansion block 2023, so that the casing 100 is stably supported by the support plate 202, realizing the axial positioning of the casing 100. Preferably, four expansion cavities 2022 are symmetrically arranged along the circumferential direction of the mounting hole 2021, and the number of expansion blocks 2023 corresponds to that of 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 of the casing 100 are on the same plane, ensuring that the flange of the casing 100 is stably placed on the support plate 202.

[0043] A certain length of radial distance is left between the outer circle of the expansion cavity 2022 and the expansion block 2023, leaving a deformation space for free expansion for the casing 100 fixed on the expansion block 2023, avoiding the constraint on the free expansion of the casing 100 along the radial direction. Thus, the casing 100 can drive the expansion block 2023 to move radially in the expansion cavity 2022 when heated and expanded. At the same time, the expansion cavity 2022 can radially restrain the casing 100 to center the casing 100 and ensure the stability of the casing 100 during the test process. Preferably, the radial distance between the outer circle of the expansion cavity 2022 and the expansion block 2023 is reserved as 5 mm to 10 mm.

[0044] As Figure 1 shown, the inner heating element 301 is arranged in the inner cavity of the casing 100. 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. The inner support seat 3012 is arranged above the inner mounting seat 3011 and is 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 is 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 axially along the casing 100, flexibly adjusting the heating position to simulate the heating conditions of the casing 100 under different working conditions.

[0045] As Figure 1As shown, the external heating element 302 is arranged outside the casing 100. The external heating element 302 includes an external support base 3021 and an external heating tube 3022. The external support base 3021 is sleeved outside the casing 100, and its bottom is fixed on the test bench 200. The inner surface shape of the external support base 3021 is adapted to the outer surface shape of the casing 100. The external heating tube 3022 is arranged in a ring on the inner surface of the external support base 3021 and is fixed to the external support base 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 base 3021. Preferably, both the internal heating tube 3013 and the external heating tube 3022 are made of quartz electric heating tubes.

[0046] As Figure 1 and Figure 5 As shown, a receiving hole 2024 is further formed in the support plate 202. The receiving hole 2024 is arranged outside the expansion cavity 2022 and a plurality of receiving holes 2024 are evenly distributed along the circumferential direction of the mounting hole 2021. The receiving hole 2024 is used for connecting and positioning with the external support base 3021 and for inserting the external heating tube 3022. Specifically, the flange edge of the external support base 3021 is covered on the receiving hole 2024, and is connected to the support plate 202 by inserting a screw into the receiving hole 2024. The number of receiving holes 2024 corresponds to the number of external heating tubes 3022, and the inner wall shape of the receiving hole 2024 close to the mounting hole 2021 side 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 external support base 3021, so that the external heating tube 3022 can extend to the bottom end of the casing 100 to adapt to different size specifications of the casing 100, 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 affecting the thermal deformation amount of the casing 100 due to excessive thermal stress of the support plate 202 during the heating process of the casing 100.

[0047] 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 respectively adjusted through the electric controller to adjust the heating power, so as to achieve the temperature and heating rate required by the test requirements, and further achieve the result of simulating the heat transfer process on the gas side of the casing 100. There are differences in the temperature distributions on the inner surface and the outer surface of the casing 100 under the working conditions of the aero-engine. Under the design conditions, the temperature of the inner surface of the casing 100 can reach 650 °C, and the lowest temperature on the outer surface of the casing 100 is also about 350 °C. The temperature difference inside the casing 100 is as high as 300 °C, and the temperature of the cooling air bleed is also above 200 °C. Therefore, according to the simulation requirements of the circumferential temperature load of the casing 100, the heating powers and quantities 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 4 kW, and the maximum heating power of the outer heating tube 3022 is set to 2 kW, so that the temperature of the inner surface of the casing 100 can be heated to above 1000 °C, thereby meeting the heating requirements for the different temperature distributions on 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 4 kW, and the maximum heating power of the outer heating tube 3022 can also be above 2 kW.

[0048] As Figure 1 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 prevent the inner heating tube 3013 and the outer heating tube 3022 from directly contacting the surface of the casing 100, and prevent the local overheating of the casing 100 caused by too high 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 through the ways of heat radiation and convection, more accurately simulating the temperature field distribution of the casing 100 under the working conditions, 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 undergo a certain degree of thermal expansion. The radial clearance between the inner heating tube 3013 and the outer heating tube 3022 and the casing 100 can accommodate this expansion, prevent friction caused by too large mechanical stress due to 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 clearance between the inner heating tube 3013 and the outer heating tube 3022 and the casing 100 also leaves a free thermal expansion space for the casing 100 along the radial direction, ensuring the accuracy of the measurement of the thermal deformation of the casing 100, and ensuring the flexibility and maintainability of the installation of the thermal environment simulation mechanism 300.

[0049] As Figure 1 、 Figure 2, Figure 3 and Figure 4 As shown in Figure 3 and Figure 4 , the cooling gas simulation mechanism 400 includes a gas supply pipe 401 for introducing cooling gas into the casing 100, a heater 402 for heating the cooling gas in the gas supply pipe 401, and a gas guide ring arranged around the outside of the casing 100. A cooling channel 4011 for surrounding the casing 100 and communicating with the inner cavity of the casing 100 is provided in the gas guide ring. The outlet end of the gas 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 gas supply pipe 401. The cooling gas simulation mechanism 400 further includes a compressor 404 for compressing and outputting cooling gas. Specifically, the compressor 404 is arranged outside the casing 100. Both ends of the gas supply pipe 401 are respectively communicated with the compressor 404 and the casing 100. The heater 402 is installed on the gas supply pipe 401 between the compressor 404 and the casing 100 and communicates with the gas supply pipe 401 to heat the cooling gas output from the compressor 404 into the gas supply pipe 401. Through the heater 402, the maximum temperature of the cooling gas can be heated to 350 °C to reach the bleed air temperature in the operating state of the aeroengine. The heated cooling gas spirally rises along the tangent direction of the cooling channel 4011 from the bottom of the gas guide ring and fills the entire cooling channel 4011, so that the cooling gas introduced into the casing 100 meets the temperature change range of the casing 100 within the operating envelope of the aeroengine.

[0050] 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 gas supply pipe 401 and is used to adjust the amount of cold gas and the cooling gas flow rate output from the compressor 404 into the gas supply pipe 401 by changing the valve size. Preferably, a flow meter 406 and a thermocouple 407 are further provided on the gas 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 rate of the cooling gas in the gas supply pipe 401 can be monitored through the flow meter 406, and the monitoring result is fed back to the flow control valve 405 to adjust the valve size, ensuring that the flow rate of the cooling gas introduced into the casing 100 is equivalent to the flow rate of the cooling gas under the actual working conditions of the casing 100; the thermocouple 407 is electrically connected to the heater 402, so that the temperature of the cooling gas heated by the heater 402 in the gas supply pipe 401 can be monitored through the thermocouple 407, and the monitoring result is fed back to the heater 402 to adjust its power, ensuring that the temperature of the cooling gas introduced into the casing 100 is consistent with the bleed air temperature under the actual working conditions of the casing 100. Thus, by changing the valve size of the flow control valve 405 and the power of the heater 402, the flow rate and temperature of the cooling gas introduced into the casing 100 are adjusted to simulate the surface temperature distribution of the casing 100 in the actual working state of the engine.

[0051] As Figure 1As shown in the figure, a flow straightening partition 403 is provided in the middle of the cooling channel 4011 along its axial direction to adjust the flow direction and velocity of the cooling air entering the cooling channel 4011, effectively reducing the impact and eddy current generated when the cooling air enters the cooling channel 4011, making the cooling air evenly fill the entire cooling channel 4011, ensuring that the cooling air enters the inside of the turbine casing 100 evenly in the entire circumferential direction, and thus achieving the effect of simulating the heat transfer process on the cold air side of the casing 100. Preferably, the flow straightening partition 403 is a plate-shaped structure with a curvature or a flat plate. Preferably, the flow straightening partition 403 is arranged in the middle of the cooling channel 4011. For a longer cooling channel 4011, the adjustment and optimization of the air flow distribution can be realized, ensuring that the cooling air flow remains uniform and stable throughout the length of the entire cooling channel 4011. Optionally, a flow straightening partition 403 can also be provided at the outlet section of the cooling channel 4011 to adjust the outlet velocity and direction of the air flow, ensuring that the cooling air can flow out evenly and act on the casing 100, facilitating the simulation of the temperature field of the casing 100 under actual working conditions and improving the accuracy of the test.

[0052] As Figure 1 and Figure 2 shown in the figure, the measuring mechanism 500 includes a temperature measuring element 501, a temperature inspection instrument 502, and a displacement measuring element 503. A number of temperature measuring elements 501 are evenly distributed on the inner surface and the outer surface of the casing 100 respectively, used to measure the temperatures of the inner surface and the outer surface of the casing 100 respectively, and the temperature measuring element 501 is electrically connected to the temperature inspection instrument 502 to feedback the measurement results to the temperature inspection instrument 502, for real-time monitoring of the surface temperature of the casing 100, realizing the simulation of the temperature field of the turbine casing 100 under actual working conditions, and improving the detection accuracy of the thermal deformation amount of the casing 100. A number of displacement measuring elements 503 are evenly distributed along the outer circumference of the casing 100. Specifically, the fixed end of the displacement measuring element 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 and keeps free contact with the outer surface of the casing 100 in the radial direction to measure the radial displacements of various parts of the outer surface of the casing 100, obtaining the thermal deformation amount data of the casing 100, with high test accuracy. The temperature measuring element 501 is electrically connected to the electric controller so that the electric controller can adjust the heating powers of the inner heating element 301 and the outer heating element 302 according to the detection results of the temperature measuring element 501. Preferably, the temperature measuring element 501 adopts a K-type patch thermocouple, and the displacement measuring element 503 adopts a self-sampling digital display dial indicator. The dial indicator is connected to the data acquisition system 504, and the data acquisition system 504 transmits the data measured by the dial indicator to the computer terminal 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.

[0053] As Figure 1As shown, a seal 600 is provided between the casing 100 and the test bench 200 and / or the cooling air simulation mechanism 400. The seal 600 is used to abut against the casing 100 to prevent the cooling air from leaking between the casing 100 and the air supply pipe 401 or the air guide ring, ensuring the cooling effect and efficiency of the cooling air.

[0054] In addition, according to another aspect of the present invention, a method for simulating the transient deformation of the casing is also provided. Using the above-mentioned casing thermal deformation test device, the method for simulating the transient deformation of the casing includes the following steps:

[0055] S1: According to the circumferential temperature load simulation requirements of the casing of the aero-engine in one of the working states, determine the heating power of the thermal environment simulation mechanism to be adapted thereto, that is, make the heating powers of the internal heating element and the external heating element capable of heating the inner surface and the outer surface of the casing to the highest temperature in this working state respectively;

[0056] S2: Turn on the internal heating element and the external heating element to independently heat the inner surface and the outer surface of the casing respectively, and adjust the internal heating element and the external heating element so that their heating rates are consistent with the heat transfer rate of the casing in this working state of the aero-engine, to simulate the heat transfer process on the gas side of the casing;

[0057] 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 aero-engine in this working state, to simulate the heat transfer process on the cold air side of the casing;

[0058] 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 air simulation mechanism according to the temperature data monitored by the measuring mechanism, to ensure that the inner surface and the outer surface of the casing reach the corresponding stable temperatures in this working state respectively under the condition of introducing cooling air, and maintain this temperature stable for a preset time, and measure and collect the radial thermal deformation amount of the casing in real time through the measuring mechanism;

[0059] S5: Use the above steps to simulate the transient deformation of the casing of the aero-engine in other working states, so as to obtain the radial thermal deformation amounts of the casing in different working states.

[0060] 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 within the protection scope of the present invention.

Claims

1. A casing thermal deformation test device, characterized in that, Comprising: A test bench (200) for supporting and positioning the casing (100), the test bench (200) including a test base (201); A thermal environment simulation mechanism (300), including an internal heating element (301) for heating the inner surface of the casing (100) and an external heating element (302) for heating the outer surface of the casing (100), the heating temperatures of the internal heating element (301) and the external heating element (302) being independently controlled to respectively simulate the heat receiving processes of the inner surface and the outer surface of the casing (100) during actual operation; A cooling gas simulation mechanism (400), installed on the test bench (200) and used for communicating with the inner cavity of the casing (100), the cooling gas simulation mechanism (400) being used for introducing cooling gas into the casing (100) to simulate the heat transfer process on the cold gas side of the casing (100) during actual operation, the highest temperature on the inner surface of the casing (100) in different states being between 300°C and 700°C, and the lowest temperature on the outer surface being between 150°C and 400°C; A measuring mechanism (500) for monitoring the temperatures of the inner surface and the outer surface of the casing (100) and measuring the radial thermal deformation amount of the casing (100); The external heating element (302) includes an external support base (3021) disposed around the outside of the casing (100) and fixed to the test base (201), and an external heating tube (3022) disposed around the inner surface of the external support base (3021), the external heating tube (3022) being electrically connected to an electric controller, and the external heating tube (3022) being disposed at a radial interval relative to the outer surface of the casing (100); The cooling gas simulation mechanism (400) includes an air supply pipe (401) for conveying cooling gas, a heater (402) for heating the cooling gas in the air supply pipe (401), and a gas guide ring disposed around the outside of the casing (100), a cooling channel (4011) for surrounding the casing (100) and communicating with the inner cavity of the casing (100) being provided in the gas guide ring, the outlet end of the air supply pipe (401) being disposed along the tangent direction of the cooling channel (4011) and communicating with the bottom end of the cooling channel (4011); the heater (402) is connected to the inlet end of the air supply pipe (401).

2. The casing thermal deformation test device according to claim 1, characterized in that The test bench (200) includes a support plate (202) fixed to the test base (201), and an installation 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 installation hole (2021), an expansion block (2023) is movably installed in the expansion cavity (2022) along the radial direction, and the expansion block (2023) is used for connecting with the flange of the casing (100).

3. The casing thermal deformation test device according to claim 2, characterized in that The inner heating member (301) includes an inner mounting seat (3011) disposed in the inner cavity of the casing (100) and fixed to the test base (201), an inner support seat (3012) fixed to the inner mounting seat (3011), and an inner heating tube (3013) disposed around the outer surface of the inner support seat (3012); The inner heating tube (3013) is electrically connected to an electric controller.

4. The casing thermal deformation test device according to claim 3, wherein The maximum heating power of the inner heating tube (3013) is set to 4KW.

5. The casing thermal deformation test device according to claim 3, wherein The maximum heating power of the outer heating tube (3022) is set to 2KW.

6. The casing thermal deformation test device according to claim 3, wherein The inner heating tube (3013) is arranged at intervals along the radial direction relative to the inner surface of the casing (100).

7. The casing thermal deformation test device according to claim 1, wherein A rectifying partition (403) is provided in the middle of the cooling channel (4011) along its axial direction, and the rectifying partition (403) is used to evenly fill the cooling channel (4011) with cooling air.

8. The casing thermal deformation test device according to claim 1, wherein The measuring mechanism (500) includes a temperature measuring member (501) disposed on the inner and outer surfaces of the casing (100), a temperature inspection instrument (502) electrically connected to the temperature measuring member (501), and a displacement measuring member (503) disposed around the outside of 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 a freely unconstrained contact with the outer surface of the casing (100) along the radial direction to measure the radial displacement of the outer surface of the casing (100).

9. A method for simulating the transient deformation of a casing, characterized in that, Using the casing thermal deformation test device according to any one of claims 1 to 8, the casing transient deformation simulation method includes the following steps: S1: According to the circumferential temperature load simulation requirement of the casing (100) in one of the working states of the aero-engine, determine that the heating power of the thermal environment simulation mechanism (300) is adapted thereto, that is, the heating powers of the inner heating member (301) and the outer heating member (302) can respectively heat the inner surface and the outer surface of the casing (100) to the corresponding maximum temperature in this working state; S2: Turn on the inner heating member (301) and the outer heating member (302) to independently heat the inner surface and the outer surface of the casing (100) respectively, and adjust the inner heating member (301) and the outer heating member (302) so that their heating rates are consistent with the heat transfer rate of the casing (100) in this working state of the aero-engine to simulate the heat transfer process on the gas side of the casing (100); S3: Activate the cooling gas simulation mechanism (400) to introduce cooling gas into the casing (100), so that the temperature of the cooling gas is consistent with the actual bleed air temperature of the aero-engine in this operating state, to simulate the heat transfer process on the cold gas side of the casing (100); S4: Activate the measuring mechanism (500) to monitor the inner surface temperature and outer surface temperature of the casing (100) in real time, and adjust the heat environment simulation mechanism (300) and the cooling gas simulation mechanism (400) according to the temperature data monitored by the measuring mechanism (500), so as to ensure that the inner surface and outer surface of the casing (100) reach the corresponding stable temperatures in this operating state respectively under the condition of introducing cooling gas, and maintain this 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: Simulate the transient deformation of the casing (100) of the aero-engine in other operating states by using the above steps, so as to obtain the radial thermal deformation of the casing (100) in different operating states.

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