Turbine holding ring thermal deformation test device

Abstract

The invention discloses a turbine holding ring thermal deformation test device, and relates to the technical field of turbine holding ring deformation measurement, and the turbine holding ring thermal deformation test device comprises a thermal insulation shell, a heating system, a cooling system and a displacement measurement system, the heat preservation shell is divided into a heating cavity, a cooling cavity and a heat preservation cavity which are independently arranged from front to back in the axial direction of the turbine holding ring, the front end of the turbine holding ring is located in the heating cavity and the cooling cavity, the rear end of the turbine holding ring is located in the heat preservation cavity, a cooling flow channel is formed in a base body of the turbine holding ring, and the cooling flow channel is communicated with the heat preservation cavity. The cooling systems are respectively communicated with the cooling cavity and the cooling flow channel, a plurality of heating systems are uniformly arranged in the heating cavity, and the displacement measuring system is used for measuring the thermal deformation of the inner wall surface of the front end of the turbine holding ring in a plurality of directions. According to the invention, the real use environment of the turbine holding ring can be simulated, and the thermal deformation characteristics of the turbine holding ring at different temperatures can be reflected more accurately.

Description

Technical Field

[0001] This invention relates to the field of turbine ring deformation measurement technology, and in particular to a turbine ring thermal deformation testing device. Background Technology

[0002] During gas turbine operation, the turbine retainer, as a core component, is constantly exposed to high temperatures. The thermal deformation caused by the thermal expansion and contraction of the turbine retainer directly affects the tip clearance between the retainer and the rotor blades. If the tip clearance is too large, it will lead to airflow leakage and increased energy loss; if the clearance is too small, it may cause rotor-stationary rubbing and damage to the equipment. Current testing equipment primarily uses a heating and cooling measurement method, i.e., first heating and then cooling to a certain temperature before measurement, followed by proportional calculation using an algorithm. This method is mainly used because high-temperature environments are difficult to guarantee. However, the thermal deformation characteristics of the turbine retainer under actual high-temperature conditions differ from those after cooling. Using a proportional conversion method cannot accurately reflect the actual thermal deformation characteristics of the turbine retainer. Furthermore, under actual operating conditions, turbine bearings typically experience a high temperature at the front end and a low temperature at the rear end, with a temperature difference reaching up to 200°C. However, current testing devices employ overall measurement simulation, meaning the temperature at every point is the same before measurement. These devices cannot accurately simulate the temperature field of the turbine bearing under actual operating conditions and cannot precisely reflect the thermal deformation characteristics of the turbine bearing. Therefore, there is an urgent need for a turbine bearing thermal deformation testing device to address the aforementioned technical problems. Summary of the Invention

[0003] The purpose of this invention is to provide a turbine ring thermal deformation testing device to solve the problems existing in the prior art, which can simulate the real use environment of the turbine ring and more accurately reflect the thermal deformation characteristics of the turbine ring.

[0004] To achieve the above objectives, the present invention provides the following solution: This invention provides a turbine ring thermal deformation testing device, comprising an insulation shell, a heating system, a cooling system, and a displacement measuring system. The turbine ring is fixedly disposed within the insulation shell. The insulation shell is divided into a heating chamber, a cooling chamber, and an insulation chamber, which are independently disposed from front to back along the axial direction of the turbine ring. The front end of the turbine ring is located within the heating chamber and the cooling chamber, and the rear end of the turbine ring is located within the insulation chamber. A cooling channel is disposed within the base of the turbine ring. The cooling system is connected to the cooling chamber and the cooling channel respectively. Multiple heating systems are uniformly arranged within the heating chamber. The displacement measuring system is used to measure the thermal deformation at multiple positions on the inner wall surface of the front end of the turbine ring.

[0005] In some embodiments, the heating system includes a plurality of resistance wires evenly arranged within the heating chamber, and the resistance wires are electrically connected to a DC power supply.

[0006] In some embodiments, the resistance wire is wound in a spiral shape.

[0007] In some embodiments, the insulation shell includes an outer insulation shell and an inner insulation shell, both of which are double-layered structures. The turbine retaining ring is disposed between the outer insulation shell and the inner insulation shell, and insulation cotton is filled between the two inner insulation shells and between the two outer insulation shells.

[0008] In some embodiments, the displacement measurement system includes a support, displacement rods, a measuring block, and a displacement sensor. Two displacement rods, one measuring block, and the displacement sensor constitute a measurement module. The turbine ring thermal deformation testing device is equipped with multiple measurement modules, and the measurement modules are divided into two groups along the axial direction of the turbine ring. Each group is used to measure the thermal deformation at various circumferential positions on the inner wall surface of the turbine ring. One end of the displacement rod is fixedly connected to the inner wall surface of the front end of the turbine ring, and the other end is fixedly connected to the measuring block. The thermal deformation of the inner wall surface of the turbine ring is led out to the measuring block through the displacement rod and measured by the displacement sensor.

[0009] In some embodiments, a measuring block is fixed to two displacement rods by a threaded connection. Each displacement rod has a threaded end away from the measuring block for threaded connection with the inner wall of the turbine holding ring. The two displacement rods on each measuring block are evenly arranged circumferentially along the inner wall of the turbine holding ring.

[0010] In some embodiments, both the displacement rod and the measuring block are made of Invar steel.

[0011] In some embodiments, a support system is also included, the support system including a fixed leg, the top of the fixed leg being fixedly connected to the outer peripheral surface of the rear end of the turbine retaining ring, and a mica gasket is provided at the connection for heat insulation, and the bottom of the fixed leg being fixedly connected to the ground.

[0012] In some embodiments, the cooling channel is a serpentine channel.

[0013] In some embodiments, the cooling system includes a first cooling passage and a second cooling passage. The first cooling passage consists of a steam source, a first flow control valve, a first flow meter, a steam inlet located on the pseudo-flange on the outer wall of the turbine holding ring, a cooling channel, a steam outlet located on the pseudo-flange on the outer wall of the turbine holding ring, a back pressure valve, and a discharge port, which are connected in sequence. A temperature sensor and a pressure sensor are also installed on the pipeline between the first flow meter and the steam inlet located on the outer wall of the turbine holding ring. The second cooling passage consists of a steam source, a pressure reducing valve, a second flow control valve, a second flow meter, a steam cooling chamber, and a discharge port, which are connected in sequence.

[0014] The present invention achieves the following technical effects compared to the prior art: The turbine ring thermal deformation testing device provided by this invention utilizes multiple evenly distributed heating systems to heat the front end of the turbine ring, a cooling system to cool the cooling chamber of the turbine ring, and an insulation shell to prevent rapid heat dissipation. This device can approximately simulate the temperature field of the turbine ring under actual operating conditions and directly reflect the true thermal deformation performance of the turbine ring under that temperature field. The cooling system introduces cooling steam at different flow rates into the cooling channels of the turbine ring, enabling rapid and precise control of the temperature change at the front end of the ring, simulating the changes in ring thermal deformation and blade tip clearance during turbine start-up, shutdown, or adjustment. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram of the turbine ring heat deformation test device in some embodiments of the present invention; Figure 2 This is a schematic diagram of the turbine retaining ring structure in some embodiments of the present invention; Figure 3 This is a schematic diagram of the turbine ring heat deformation testing device without a displacement measurement system in some embodiments of the present invention; Figure 4 This is a schematic diagram illustrating the arrangement of mica gaskets in some embodiments of the present invention; Figure 5 This is a schematic diagram of the cooling system configuration in some embodiments of the present invention; Figure 6 This is a schematic diagram of the displacement measurement system in some embodiments of the present invention.

[0017] In the diagram: 1-Turbine holding ring; 101-Steam inlet; 102-Cooling flow channel; 103-Steam outlet; 104-Support positioning groove; 2-Heating chamber; 3-Cooling chamber; 4-Insulation chamber; 5-Displacement measurement system; 51-Bracket; 52-Displacement rod; 53-Measuring block; 531-Horizontal part; 532-Vertical part; 54-Displacement sensor; 55-Sensor mounting base; 6-Insulation cotton; 8-Fixed support leg; 9-Resistance wire; 10-Mica gasket; 11-Steam source; 12-First flow control valve; 13-First flow meter; 14-Temperature sensor; 15-Pressure sensor; 16-Back pressure valve; 17-Pressure reducing valve; 18-Second flow control valve; 19-Second flow meter. Detailed Implementation

[0018] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] The purpose of this invention is to provide a turbine bearing ring thermal deformation testing device to solve the problems existing in the prior art. It can simulate the real use environment of the turbine bearing ring and more accurately reflect the temperature field and thermal deformation characteristics of the turbine bearing ring under different working conditions.

[0020] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0021] like Figures 1-6As shown, this invention provides a turbine ring thermal deformation testing device, including an insulation shell, a heating system, a cooling system, and a displacement measuring system 5. The turbine ring 1 is fixedly disposed within the insulation shell. The insulation shell is divided into three independently arranged chambers along the axial direction of the turbine ring 1: a heating chamber 2, a cooling chamber 3, and an insulation chamber 4. The front end of the turbine ring 1 is located within the heating chamber 2 and the cooling chamber 3, while the rear end is located within the insulation chamber 4. A cooling channel 102 is provided within the base of the turbine ring 1. The cooling system is connected to both the cooling chamber 3 and the cooling channel 102. Multiple heating systems are evenly arranged within the heating chamber 2. The displacement rods of the displacement measuring system 5 are circumferentially distributed and fixed to the inner wall surface of the turbine ring 1. The insulation shell prevents rapid heat dissipation, providing a stable testing environment for the turbine ring 1. Multiple evenly distributed heating systems heat the front end of the turbine retainer ring 1, while a cooling system cools the cooling chamber 3 of the turbine retainer ring 1, which can very closely simulate the temperature field of the retainer ring under actual operating conditions. The displacement measurement system 5 directly measures the thermal deformation of the turbine retainer ring 1 under actual high-temperature conditions, which can directly reflect the true thermal deformation characteristics of the turbine retainer ring 1 under this temperature field. The second passage of the cooling system introduces steam with different parameters into the cooling channel inside the turbine retainer ring 1, which can quickly and accurately control the temperature change of the front end of the retainer ring, simulating the thermal deformation of the retainer ring and the change of blade tip clearance during turbine start-up, shutdown, or adjustment.

[0022] In some embodiments, the heating system includes multiple resistance wires 9, which are uniformly arranged within the heating chamber 2 and electrically connected to a DC power supply. The uniform arrangement of multiple resistance wires 9 forms a uniformly distributed heat source array within the heating chamber 2. Compared to single-point or few heat sources, this effectively avoids problems such as excessively high local temperatures (overheating) or insufficient heating (underheating) in certain areas of the turbine ring 1 due to heat concentration. This ensures that the temperature field at the front end of the turbine ring 1 closely approximates the actual operating conditions. The resistance wires 9, as heating elements, have low thermal inertia and rapid heating speed, and are directly controlled by DC power, maintaining a constant power output. Furthermore, the multiple resistance wires 9 can be controlled in groups or zones. For example, different power can be applied to resistance wires 9 at different locations based on the expected heat flux density in different areas of the front end of the turbine ring 1, thereby achieving a more refined temperature field simulation, rather than simply providing uniform overall heating. This allows the experimental setup to more realistically simulate the complex temperature field on the actual turbine ring, improving the realism of the experiment and the application value of the data.

[0023] In some embodiments, the resistance wire 9 is spirally wound and is made of nickel-chromium wire. At high temperatures, a dense chromium oxide protective film forms on the surface of the nickel-chromium wire, effectively preventing further oxidation of the internal alloy matrix and giving the material extremely high high-temperature stability. During repeated high-temperature heating and cooling cycles in the test apparatus, this type of resistance wire 9 is less prone to becoming brittle, pulverizing, or burning out, thus extending the service life and reliability of the entire heating system. The spiral structure concentrates the long resistance wire 9 into a smaller space, achieving a heat source concentration effect. This allows the heater to achieve high power density, rapidly heating the medium in the heating chamber 2, shortening test preparation time, and effectively simulating the rapid thermal shock during turbine start-up and shutdown. The spiral structure is similar to a spring, with significantly higher structural stiffness than a straight wire. It better resists its own high-temperature softening and deformation caused by gravity, ensuring that the resistance wire 9 maintains shape stability during long-term use. The coils will not short-circuit due to deformation, ensuring heating safety and long-term reliability. It should be noted that there are seven heating sections of resistance wire 9, and seven corresponding heating chambers 2 are also provided. Resistance wire 9 is set on the inner wall of heating chamber 2 and fixed to the heat preservation shell by a bracket.

[0024] In some embodiments, the insulation shell includes an outer insulation shell and an inner insulation shell, both of which are double-layered structures. A turbine retainer ring is disposed between the outer and inner insulation shells, and insulation cotton is filled between the two inner and outer insulation shells. The double-layered structure provides better insulation. In actual gas turbines, the temperature field of the turbine retainer ring 1 is formed by the heating or cooling of various regions inside and outside the front end of the retainer ring by the main gas flow and the compressor gas supply. In this invention, the temperature field of the retainer ring is simulated by multiple electric heating systems and steam cooling in the cooling chamber. The double-layered structure of the insulation shell with insulation cotton effectively prevents heat loss, making the simulation more accurate.

[0025] In some embodiments, the turbine ring heat deformation testing device further includes a thermocouple. Temperature measuring points are provided on the turbine ring 1, and the thermocouple passes through the insulation shell, insulation cotton 6, and insulation cavity 4 to measure the temperature at these measuring points. The thermocouple is directly positioned on the temperature measuring points of the turbine ring 1, which is a contact temperature measurement method. This allows for direct and rapid sensing of the true temperature of the ring's metal body, ensuring the accuracy and response speed of the temperature data from the source and avoiding conversion errors and delays caused by indirect measurements. Furthermore, multiple temperature measuring points are provided on the turbine ring 1.

[0026] In some embodiments, the displacement measurement system includes a bracket 51, displacement rods 52, a measuring block 53, and a displacement sensor 54. Two displacement rods 52, one measuring block 53, and the displacement sensor 54 form a measurement module. The turbine ring thermal deformation testing device is equipped with multiple measurement modules, and the measurement modules are divided into two groups along the axial direction of the turbine ring 1. Each group is used to measure the thermal deformation at each circumferential position of the inner wall surface of the turbine ring. One end of the displacement rod 52 is fixedly connected to the inner wall surface of the front end of the turbine ring 1, and the other end is fixedly connected to the measuring block 53. The thermal deformation of the inner wall surface of the turbine ring 1 is led out to the measuring block 53 through the displacement rod 52 and measured by the displacement sensor 54. Further, a sensor mounting base 55 is fixedly connected to the end of the bracket 51. The sensor mounting base 55 is horizontally arranged, and the displacement sensors 54 are all pen-type displacement sensors. The sensor mounting base 55 has a through hole. The pen-type displacement sensor used to measure radial displacement is inserted into the through hole and locked by a nut. The measuring head of the pen-type displacement sensor used to measure radial displacement contacts the base surface of the measuring block 53.

[0027] It should be noted that the measuring block 53 used to measure the inner wall surface of the front end of the turbine holding ring 1 is inverted L-shaped. The horizontal part 531 is set horizontally, and the top surface of the horizontal part 531 is fixedly connected to the displacement rod 52. The bottom surface of the horizontal part 531 contacts the measuring head of the displacement sensor used to measure radial displacement to provide a measuring surface. The vertical part 532 is fixedly connected to the edge of the horizontal part 531 and is set below the horizontal part 531. The side of the vertical part 532 away from the horizontal part 531 and close to the bracket 51 contacts the measuring head of the displacement sensor used to measure axial displacement. This displacement sensor is used to measure axial displacement.

[0028] The first end of the displacement rod 52 is directly fixed to the inner wall of the turbine holding ring 1. Any minute deformation of the turbine holding ring 1 will be transmitted directly to the measuring block at the far end through the rigid rod with almost no loss. The direct connection method has a short transmission chain and high rigidity, which effectively reduces the error and deformation delay in the intermediate links, ensuring that the measurement results can accurately and quickly reflect the actual deformation of the holding ring body. At the same time, the displacement rod draws the thermal deformation out of the high-temperature environment, so ordinary displacement sensors can be used instead of ultra-high temperature resistant displacement sensors. Moreover, the operating environment of the displacement sensor is close to the daily operating environment, avoiding damage and inaccurate detection caused by use in high-temperature environments.

[0029] In some embodiments, a measuring block 53 is fixed to two displacement rods 52 via a threaded connection. Each displacement rod 52 has a threaded end away from the measuring block 53 for connection to the inner wall of the turbine retaining ring 1. The two displacement rods 52 on each measuring block 53 are evenly arranged circumferentially along the inner wall of the turbine retaining ring 1. A single displacement rod can only reflect the radial displacement of a point on the inner ring of the retaining ring. If this point happens to have local micro-inhomogeneities (such as small material defects or temperature transients), the measurement data will produce noise or bias, failing to represent the overall deformation of the cross-section. Arranging two displacement rods 52 circumferentially on each measuring block 53 is equivalent to setting two measuring points within a small local area. The displacement of these two rods is transmitted to the same measuring block, and its output signal naturally contains information from both measuring points, enabling preliminary detection of local asymmetric deformation (such as ellipticity). More importantly, it produces an averaging effect, effectively smoothing out the random errors that may exist at a single measuring point, making the final displacement output by the measuring block 53 closer to the true average radial deformation at the circumferential position of the cross-section, significantly improving the representativeness and accuracy of the data. It should be noted that six displacement rods 52 are preferably arranged on the inner wall of the front end of the turbine holding ring 1, and six displacement rods 52 are also arranged on the inner wall of the rear end of the turbine holding ring 1.

[0030] In some embodiments, both the displacement rod 52 and the measuring block 53 are made of Invar steel. Invar steel is an iron-nickel alloy, whose most significant characteristic is its extremely low coefficient of thermal expansion over a considerable temperature range. During the hot deformation test, the ambient temperature of the displacement rod 52 itself also increases. If an ordinary steel rod is used, the rod will elongate significantly due to heat, and this elongation will be misread by the displacement sensor as thermal deformation of the ring, thus introducing a large measurement error. However, the Invar steel rod hardly undergoes thermal expansion and contraction under the same conditions, and its own length can be regarded as a stable scale. By using Invar steel to bring the deformation to the room temperature range, the true deformation of the ring can be transmitted to the measuring end with high fidelity and without distortion, ensuring the accuracy of the data from the source.

[0031] In some embodiments, the turbine ring heat deformation testing device further includes a support system, which includes a fixed leg 8. The top of the fixed leg 8 is fixedly connected to the outer peripheral surface of the rear end of the turbine ring 1. Preferably, a support positioning groove 104 is provided at the rear end of the turbine ring 1, and an insert block is provided at the top of the fixed leg 8 that can be inserted into the support positioning groove 104. This arrangement ensures that the fixed leg 8 has a small impact on the axial and radial movement of the turbine ring, allowing the turbine ring 1 to produce a small displacement relative to the fixed leg. A mica gasket 10 is provided at the connection between the turbine ring 1 and the fixed leg 8, and the bottom of the fixed leg 8 is fixedly connected to the ground. The fixed leg 8 provides a stable foundation through its rigid connection to the ground. Mica is an excellent high-temperature resistant insulating material with extremely low thermal conductivity. A mica gasket 10 is installed at the connection between the fixed leg 8 and the rear end of the retaining ring. This acts as a thermal barrier between the high-temperature retaining ring and the relatively low-temperature fixed leg 8, effectively preventing heat transfer from the retaining ring to the fixed leg 8. This prevents the fixed leg 8 from weakening due to overheating, oxidation, or even creep deformation, ensuring the long-term stability and safety of the support structure. Furthermore, the mica gasket 10 significantly reduces heat loss from the rear end of the retaining ring to the ground through the fixed leg 8, helping to maintain the preset temperature at the rear end of the retaining ring (located within the insulation cavity 4). This makes the axial temperature gradient of the entire retaining ring closer to the design state, improving the accuracy of the thermal environment simulation in the experiment.

[0032] In some embodiments, the cooling channel 102 is a serpentine channel. Compared to a simple straight channel, the serpentine channel significantly extends the total length of the channel, thereby multiplying the contact area between the cooling medium (such as steam or coolant) and the inner wall of the retaining metal, resulting in higher heat transfer efficiency. Moreover, when the cooling medium flows through the curved portion of the serpentine channel, the flow direction constantly changes, which disrupts the stable laminar boundary layer within the pipe, inducing and enhancing turbulence. This leads to stronger mixing within the cooling medium, continuously agitating the low-temperature fluid in the central region to the vicinity of the pipe wall, while simultaneously carrying away the high-temperature fluid that has absorbed heat from the pipe wall. This strengthens the convective heat transfer coefficient between the pipe wall and the fluid, resulting in a heat transfer effect far exceeding that of laminar flow, achieving active and enhanced heat transfer.

[0033] In some embodiments, the cooling system includes a first cooling passage and a second cooling passage. The first cooling passage consists of a steam source 11, a first flow control valve 12, a first flow meter 13, a steam inlet 101 located on the pseudo-flange on the outer wall of the turbine holding ring 1, a cooling channel 102, a steam outlet 103 located on the pseudo-flange on the outer wall of the turbine holding ring 1, a back pressure valve 16, and a discharge port, connected in sequence. A temperature sensor 14 and a pressure sensor 15 are also installed on the pipeline between the first flow meter 13 and the steam inlet 101 located on the outer ring of the turbine holding ring 1. The second cooling passage consists of a steam source 11, a pressure reducing valve 17, a second flow control valve 18, a second flow meter 19, a cooling chamber 3, and a discharge port, connected in sequence. The steam source 11 uses natural gas to heat a steam boiler, which then generates superheated steam at 1 MPa and a temperature range of 240°C after passing through a heat exchanger. The temperature of the turbine holding ring 1 is generally around 400°C, and steam below 240°C can be used for appropriate cooling. The first cooling path is equipped not only with a first flow meter 13, but also with a temperature sensor 14 and a pressure sensor 15. By measuring the temperature, pressure, and flow rate of the steam inlet 101 and outlet, the total heat carried away by the cooling steam from the inside of the retaining ring can be accurately calculated, aiding in the verification of the thermal model and cooling efficiency. Simultaneously, real-time data is fed back to the first flow control valve 12 and the back pressure valve 16, forming a high-precision closed-loop control system. This ensures that the internal cooling conditions strictly meet the requirements of the test outline and are unaffected by fluctuations in the steam source 11. The flow rate, pressure, and temperature of the steam in both paths can be independently adjusted. Researchers can accurately reproduce different engine operating conditions (such as cooling steam ratios at different power levels) or separately study the specific impact of internal or external cooling on the thermal deformation of the retaining ring, providing precise data support for optimized design. It should be noted that manual ball valves are also installed before the first flow control valve 12 in the first cooling pipeline and before the second flow control valve 18 in the second cooling pipeline for controlling the opening and closing of the pipelines. Furthermore, the cooling system uses a PLC closed-loop control system to manage the steam parameters.

[0034] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A turbine ring heat deformation testing device, characterized in that: The device includes an insulation shell, a heating system, a cooling system, and a displacement measuring system. A turbine holding ring is fixedly installed inside the insulation shell. The insulation shell is divided into a heating chamber, a cooling chamber, and an insulation chamber, which are independently arranged from front to back along the axial direction of the turbine holding ring. The front end of the turbine holding ring is located in the heating chamber and the cooling chamber, and the rear end of the turbine holding ring is located in the insulation chamber. A cooling channel is provided in the base of the turbine holding ring. The cooling system is connected to the cooling chamber and the cooling channel respectively. Multiple heating systems are evenly arranged in the heating chamber. The displacement measuring system is used to measure the thermal deformation of the inner wall surface of the front end of the turbine holding ring in multiple directions.

2. The turbine ring heat deformation testing device according to claim 1, characterized in that: The heating system includes multiple resistance wires, which are evenly arranged inside the heating chamber and are electrically connected to a DC power supply.

3. The turbine ring heat deformation test device according to claim 2, characterized in that: The resistance wire is wound in a spiral shape.

4. The turbine ring heat deformation test device according to claim 1, characterized in that: The insulation shell includes an outer insulation shell and an inner insulation shell. Both the inner insulation shell and the outer insulation shell are double-layered structures. The turbine retaining ring is disposed between the outer insulation shell and the inner insulation shell. Insulation cotton is filled between the two inner insulation shells and between the two outer insulation shells.

5. The turbine ring heat deformation test device according to claim 1, characterized in that: The displacement measurement system includes a support, displacement rods, a measuring block, and a displacement sensor. Two displacement rods, one measuring block, and the displacement sensor constitute a measurement module. The turbine ring thermal deformation testing device is equipped with multiple measurement modules, and the measurement modules are divided into two groups along the axial direction of the turbine ring. Each group is used to measure the thermal deformation at various circumferential positions on the inner wall surface of the turbine ring. One end of the displacement rod is fixedly connected to the inner wall surface of the front end of the turbine ring, and the other end is fixedly connected to the measuring block. The thermal deformation of the inner wall surface of the turbine ring is led out to the measuring block through the displacement rod and measured by the displacement sensor.

6. The turbine ring heat deformation testing device according to claim 5, characterized in that: A measuring block is fixed to two displacement rods by a threaded connection. Each displacement rod has a thread at the end away from the measuring block for threaded connection with the inner wall of the turbine holding ring. The two displacement rods on each measuring block are evenly arranged circumferentially along the inner wall of the turbine holding ring.

7. The turbine ring heat deformation testing device according to claim 5, characterized in that: Both the displacement rod and the measuring block are made of Invar steel.

8. The turbine ring heat deformation test device according to claim 1, characterized in that: It also includes a support system, which includes a fixed leg. The top of the fixed leg is fixedly connected to the outer peripheral surface of the rear end of the turbine holding ring, and a mica gasket is provided at the connection. The bottom of the fixed leg is fixedly connected to the ground.

9. The turbine ring heat deformation test apparatus according to claim 1, characterized in that: The cooling channel is a serpentine channel.

10. The turbine ring heat deformation testing device according to claim 1, characterized in that: The cooling system includes a first cooling passage and a second cooling passage. The first cooling passage consists of a steam source, a first flow control valve, a first flow meter, a steam inlet located on the pseudo-flange on the outer wall of the turbine holding ring, a cooling channel, a steam outlet located on the pseudo-flange on the outer wall of the turbine holding ring, a back pressure valve, and a discharge port, which are connected in sequence. A temperature sensor and a pressure sensor are also installed on the pipeline between the first flow meter and the steam inlet located on the outer wall of the turbine holding ring. The second cooling passage consists of a steam source, a pressure reducing valve, a second flow control valve, a second flow meter, a steam cooling chamber, and a discharge port, which are connected in sequence.

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