Gas quenching test device and test method for simulating thermal inertia of blade tip

Abstract

The invention relates to the technical field of engine turbine blades, in particular to an air quenching test device and method for simulating thermal inertia of a blade tip, and the device comprises a test device body which comprises a temperature measurement mechanism, a profiling induction heating mechanism, an annular heat dissipation mechanism and an electric feeding and discharging mechanism. The temperature measuring mechanism is used for closed-loop control of the blade temperature, the profiling induction heating mechanism is used for heating the blade, the annular heat dissipation mechanism is used for cooling the blade, and the electric feeding and discharging mechanism is used for controlling loading and unloading of the blade, so that the thermal fatigue performance of the blade tip of the engine turbine blade can be checked.

Description

Technical Field

[0001] The invention relates to the technical field of engine turbine blades, and in particular to a gas quenching test device and a test method for simulating blade tip thermal inertia. Background Art

[0002] Turbine blades are key components of aircraft engines. They are used in harsh environments and are prone to cracks at the blade tips under the effects of thermomechanical fatigue stress, high-temperature corrosion, high-temperature oxidation, centrifugal force, etc., affecting the reliability of blade use.

[0003] Existing test and evaluation technologies mainly focus on the overall test and evaluation of turbine blades, but there are few reports on the test and verification of blade tip parts. However, in actual practice, blade tip failures account for more than 95% of blade failures. For example, the gas impact tester uses high-temperature gas generated by fuel to impact the turbine blades to simulate the thermal shock of the turbine blades when the engine is working. The equipment required is huge, the test and evaluation cycle is long, the fuel combustion cost is high, and the exhaust gas will pollute the environment.

[0004] However, this method is for the assessment and testing of the entire turbine blade, especially the area below the blade tip. It is difficult to accurately control the temperature of the blade tip, and it is basically difficult to assess the thermal fatigue performance of the blade tip. Summary of the invention

[0005] In view of the above problems, the present invention provides a gas quenching test device and a test method for simulating the thermal inertia of a blade tip.

[0006] The adopted technical scheme is a gas quenching test device simulating thermal inertia of blade tip, comprising a test device body, wherein the test device body comprises a temperature measuring mechanism, a contour induction heating mechanism, an annular heat dissipation mechanism and an electric loading and unloading mechanism; The electric loading and unloading mechanism is used to fix the turbine blades and can pass through the annular heat dissipation mechanism; The annular heat dissipation mechanism is used to cool the blade tips of the turbine blades; The temperature measuring mechanism is used to collect the tip temperature of the turbine blade and control the temperature rise and fall process; The contoured induction heating mechanism can be sleeved on the outer periphery of the blade tip of the turbine blade and heat the blade tip of the turbine blade.

[0007] Optionally, the temperature measuring mechanism includes a controller and a temperature measuring instrument, wherein the temperature measuring instrument can monitor the tip temperature of the turbine blade and feed back the temperature to the controller in real time; The controller can control the contour induction heating mechanism to heat up and the annular heat dissipation mechanism to spray cooling medium.

[0008] Optionally, the annular heat dissipation mechanism includes a base, a cooling medium input pipe, a guide seat, a cooling medium conduit and an annular fixing seat; The guide seat is arranged on the base; The cooling medium input pipe is inserted into the guide seat and communicated with one end of the cooling medium conduit through the inner cavity of the guide seat; The other end of the cooling medium conduit is connected to the annular fixing seat; The annular fixing seat is provided with a cooling medium nozzle, and the cooling medium nozzle faces the blade tip of the turbine blade.

[0009] Optionally, an opening is provided in the middle of the base, and the electric loading and unloading mechanism can pass through the opening, the opening is located below the annular fixing seat, and the projection of the annular fixing seat on the base is located on both sides of the opening.

[0010] Optionally, the contoured induction heating mechanism includes a connecting tube and a heating ring tube, both ends of the heating ring tube are connected to the connecting tube, the heating ring tube surrounds to form a heating cavity adapted to the tip of the turbine blade, and the tip of the turbine blade can pass through the heating cavity.

[0011] Optionally, the electric loading and unloading mechanism includes a support rod, a movable rod, a movable table, a telescopic mechanism and a mounting fixed seat; The movable rod is arranged on the upper surface of the support rod; The movable platform can slide along the support rod; The telescopic mechanism is arranged on the movable platform; The mounting and fixing seat is arranged at the end of the telescopic mechanism, and a mounting groove for fixing the turbine blade is arranged on the mounting and fixing seat.

[0012] Optionally, the telescopic mechanism includes a telescopic seat and a telescopic rod, the telescopic seat is connected to the upper surface of the movable table, one end of the telescopic rod is inserted into the telescopic seat, the other end of the telescopic rod is connected to the mounting fixed seat, and the telescopic rod can be telescoped in the telescopic seat.

[0013] Optionally, a protective cover is further provided on the base, and the annular fixing seat and the contoured induction heating mechanism are both arranged inside the protective cover.

[0014] The present application also provides a gas quenching test method for simulating the thermal inertia of a blade tip based on a gas quenching test device for simulating the thermal inertia of a blade tip, comprising the following steps: S1. Write the turbine blade test information into the controller in the temperature measuring mechanism; S2. Install the turbine blade to be tested into the electric loading and unloading mechanism; S3. The controller in the temperature measuring mechanism controls the electric loading and unloading mechanism to drive the turbine blades into a predetermined position; S4. The controller in the temperature measuring mechanism controls the profiling induction heating mechanism to heat and keep the tip of the turbine blade warm; S5. The controller in the temperature measuring mechanism controls the annular heat dissipation mechanism to cool the tip of the turbine blade; S6. After completing one thermal cycle, proceed to the next thermal cycle until the test cycle number is completed; S7. The controller in the temperature measuring mechanism controls the electric loading and unloading mechanism to drive the turbine blades into a predetermined position and remove the blades.

[0015] The beneficial effects of the present invention are: 1. The temperature of the tip of the turbine blade is precisely controlled, with an error within ±5°C. The present invention heats and cools the tip of the turbine blade, has a small control range, temperature closed-loop feedback, and precise temperature control.

[0016] 2. High degree of automation and simple operation. The present invention only needs to write information into the controller to automatically complete different numbers of thermal cycles.

[0017] 3. Energy saving and environmental protection. The present invention targets the tip of the turbine blade, has a small heating range, uses electric heating, and has little pollution. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the structure of a gas quenching test device simulating the thermal inertia of blade tip; Figure 2 It is a schematic diagram of the temperature measurement mechanism structure; Figure 3 It is a structural schematic diagram of the contour induction heating mechanism; Figure 4 It is a schematic diagram of the structure of the annular heat dissipation mechanism; Figure 5 This is a schematic diagram of the structure of the electric loading and unloading mechanism; Figure 6 Schematic diagram of turbine blade structure.

[0019] The accompanying drawings are marked as follows: 1 is a temperature measuring mechanism, 2 is a contoured induction heating mechanism, 3 is an annular heat dissipation mechanism, 4 is an electric loading and unloading mechanism, 5 is a protective cover, 6 is a connecting pipe, 7 is a heating ring pipe, 8 is a heating chamber, 9 is a cooling medium input pipe, 10 is a base, 11 is an opening, 12 is a guide seat, 13 is a cooling medium conduit, 14 is an annular fixed seat, 15 is a cooling medium nozzle, 16 is a support rod, 17 is a chain belt, 18 is a movable rod, 19 is a movable table, 20 is a telescopic seat, 21 is a telescopic rod, 22 is a mounting fixed seat, 23 is a mounting groove, and 24 is a turbine blade. DETAILED DESCRIPTION

[0020] The following describes the implementation of the present invention through specific examples. Those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific implementations, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict.

[0021] It should be noted that the illustrations provided in the following embodiments are only used to schematically illustrate the basic concept of the present invention, and thus the drawings only show components related to the present invention rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0022] like Figure 1 As shown, a gas quenching test device simulating thermal inertia of a blade tip comprises a test device body, wherein the test device body comprises a temperature measuring mechanism 1, a contour induction heating mechanism 2, an annular heat dissipation mechanism 3 and an electric loading and unloading mechanism 4; The electric loading and unloading mechanism 4 is used to fix the turbine blades 24 and can pass through the annular heat dissipation mechanism 3; The annular heat dissipation mechanism 3 is used to cool the blade tips of the turbine blades 24; The temperature measuring mechanism 1 is used to collect the tip temperature of the turbine blade 24 and control the temperature rise and fall process; The contoured induction heating mechanism 2 can be sleeved on the outer periphery of the blade tip of the turbine blade 24 to heat the blade tip of the turbine blade 24 .

[0023] The purpose of this design is to accurately control the temperature of the turbine blade tip, with an error of less than ±5°C. This embodiment heats and cools the turbine blade tip, with a small control range, closed-loop temperature feedback, and accurate temperature control. It has a high degree of automation and is easy to operate. This embodiment only needs to write information into the controller to automatically complete different numbers of thermal cycles. It is energy-saving and environmentally friendly. This embodiment targets the turbine blade tip, has a small heating range, uses electric heating, and has low pollution.

[0024] like Figure 2 As shown, in this embodiment, a specific structure of a temperature measuring mechanism is provided. The temperature measuring mechanism 1 includes a controller and a temperature measuring instrument. The temperature measuring instrument can monitor the tip temperature of the turbine blade 24 and feed back the temperature to the controller in real time. The controller can control the contour induction heating mechanism 2 to increase the temperature and the annular heat dissipation mechanism 3 to spray the cooling medium.

[0025] The purpose of this design is that the controller can write specific heating programs, process temperature feedback information, and control the spraying of cooling medium as needed; the temperature meter can accurately monitor the tip temperature of the blade and feed back the temperature to the controller in real time, thereby realizing closed-loop control of the temperature rise and fall process.

[0026] like Figure 4 As shown, in this embodiment, a specific structure of an annular heat dissipation mechanism is provided, and the annular heat dissipation mechanism 3 includes a base 10, a cooling medium input pipe 9, a guide seat 12, a cooling medium conduit 13 and an annular fixing seat 14; The guide seat 12 is arranged on the base 10; The cooling medium input pipe 9 is inserted into the guide seat 12 and communicates with one end of the cooling medium conduit 13 through the inner cavity of the guide seat 12; The other end of the cooling medium conduit 13 is connected to the annular fixing seat 14; A cooling medium nozzle 15 is provided on the annular fixing seat 14, and the cooling medium nozzle 15 is directed toward the tip of the turbine blade 24. An opening 11 is provided in the middle of the base 10, and the electric loading and unloading mechanism 4 can pass through the opening 11. The opening 11 is located below the annular fixing seat 14, and the projection of the annular fixing seat 14 on the base 10 is located on both sides of the opening 11.

[0027] The purpose of this design is to be able to cool the tip of the turbine blade by spraying cooling gas according to the cooling requirements.

[0028] like Figure 3 As shown, in this embodiment, a specific structure of a contoured induction heating mechanism is provided, wherein the contoured induction heating mechanism 2 includes a connecting tube 6 and a heating ring tube 7, both ends of the heating ring tube 7 are connected to the connecting tube 6, the heating ring tube 7 surrounds a heating cavity 8 adapted to the tip of the turbine blade 24, and the tip of the turbine blade 24 can pass through the heating cavity 8.

[0029] The purpose of this design is to be able to heat the turbine blade tip according to its temperature distribution and heating requirements.

[0030] like Figure 4 As shown, in this embodiment, a specific structure of an electric loading and unloading mechanism is provided, wherein the electric loading and unloading mechanism 4 includes a support rod 16, a movable rod 18, a movable platform 19, a telescopic mechanism and a mounting fixed seat 22; The movable rod 18 is disposed on the upper surface of the support rod 16; The movable platform 19 can slide along the support rod 16; The telescopic mechanism is arranged on the movable platform 19; The mounting and fixing seat 22 is arranged at the end of the telescopic mechanism, and a mounting groove 23 for fixing the turbine blade 24 is arranged on the mounting and fixing seat 22; The telescopic mechanism includes a telescopic seat 20 and a telescopic rod 21. The telescopic seat 20 is connected to the upper surface of the movable platform 19. One end of the telescopic rod 21 is inserted into the telescopic seat 20, and the other end of the telescopic rod 21 is connected to the mounting fixed seat 22. The telescopic rod 21 can be telescoped in the telescopic seat 20. A chain belt 17 is also provided on the support rod 16, and the direction of the chain belt 17 is consistent with the direction of the movable rod 18. The movable platform 19 can move on the chain belt 17.

[0031] The purpose of this design is to fix the turbine blades on it, design the movement trajectory, and perform loading, unloading, movement and other operations as required.

[0032] In this embodiment, a protective cover 5 is further provided on the base 10 , and the annular fixing seat 14 and the contoured induction heating mechanism 2 are both provided in the protective cover 5 .

[0033] like Figure 5 As shown, this embodiment provides a gas quenching test method for simulating the thermal inertia of a blade tip based on a gas quenching test device for simulating the thermal inertia of a blade tip, comprising the following steps: S1. The turbine blade 24 test information is written into the controller in the temperature measuring mechanism 1; S2. The turbine blade 24 to be tested is loaded into the electric loading and unloading mechanism 4; S3. The controller in the temperature measuring mechanism 1 controls the electric loading and unloading mechanism 4 to drive the turbine blade 24 into a predetermined position; S4. The temperature measuring mechanism 1 controller controls the profiling induction heating mechanism 2 to heat and keep the tip of the turbine blade 24 warm; S5. The controller in the temperature measuring mechanism 1 controls the annular heat dissipation mechanism 3 to cool the tip of the turbine blade 24; S6. After completing one thermal cycle, proceed to the next thermal cycle until the test cycle number is completed; S7. The controller in the temperature measuring mechanism 1 controls the electric loading and unloading mechanism 4 to drive the turbine blade 24 into a predetermined position and remove the blade.

[0034] In this way, the shortcomings of the existing technology such as high price, long cycle, high pollution and difficulty in accurately measuring the tip temperature of the blade are overcome. At the same time, it should be pointed out that in actual use, the entire cycle process takes about 6 minutes. At the same time, the annular heat dissipation mechanism immediately sprays the cooling medium after each cycle is completed. Finally, the specific blade conditions are photographed manually on site or with a remote camera. After the number of cycles is completed, the test results are judged based on the absence of cracking as the assessment standard.

[0035] Finally, it should be noted that the above are only preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A gas quenching test device for simulating blade tip thermal inertia, comprising a test device body, characterized in that: The test device body comprises a temperature measuring mechanism (1), a contour induction heating mechanism (2), an annular heat dissipation mechanism (3) and an electric loading and unloading mechanism (4); The electric loading and unloading mechanism (4) is used to fix the turbine blades (24) and can pass through the annular heat dissipation mechanism (3); The annular heat dissipation mechanism (3) is used to cool the blade tips of the turbine blades (24); The temperature measuring mechanism (1) is used to collect the tip temperature of the turbine blade (24) and control the temperature rise and fall process; The contoured induction heating mechanism (2) can be sleeved on the outer periphery of the blade tip of the turbine blade (24) and heat the blade tip of the turbine blade (24).

2. The gas quenching test device for simulating blade tip thermal inertia according to claim 1, characterized in that: The temperature measuring mechanism (1) comprises a controller and a temperature measuring instrument, wherein the temperature measuring instrument can monitor the tip temperature of the turbine blade (24) and feed back the temperature to the controller in real time; The controller can control the contoured induction heating mechanism (2) to increase the temperature and the annular heat dissipation mechanism (3) to spray the cooling medium.

3. The gas quenching test device for simulating blade tip thermal inertia according to claim 2, characterized in that: The annular heat dissipation mechanism (3) comprises a base (10), a cooling medium input pipe (9), a flow guide seat (12), a cooling medium conduit (13) and an annular fixing seat (14); The flow guide seat (12) is arranged on the base (10); The cooling medium input pipe (9) is inserted into the flow guide seat (12) and communicates with one end of the cooling medium conduit (13) via the inner cavity of the flow guide seat (12); The other end of the cooling medium conduit (13) is connected to the annular fixing seat (14); The annular fixing seat (14) is provided with a cooling medium nozzle (15), and the cooling medium nozzle (15) faces the blade tip of the turbine blade (24).

4. The gas quenching test device for simulating blade tip thermal inertia according to claim 3, characterized in that: An opening (11) is provided in the middle of the base (10), and the electric loading and unloading mechanism (4) can pass through the opening (11); the opening (11) is located below the annular fixing seat (14), and the projection of the annular fixing seat (14) on the base (10) is located on both sides of the opening (11).

5. The gas quenching test device for simulating blade tip thermal inertia according to claim 4, characterized in that: The contoured induction heating mechanism (2) comprises a connecting pipe (6) and a heating ring pipe (7), both ends of the heating ring pipe (7) are connected to the connecting pipe (6), the heating ring pipe (7) surrounds to form a heating cavity (8) adapted to the tip of a turbine blade (24), and the tip of the turbine blade (24) can pass through the heating cavity (8).

6. The gas quenching test device for simulating blade tip thermal inertia according to claim 5, characterized in that: The electric loading and unloading mechanism (4) comprises a support rod (16), a movable rod (18), a movable platform (19), a telescopic mechanism and a mounting base (22); The movable rod (18) is arranged on the upper surface of the support rod (16); The movable platform (19) can slide along the support rod (16); The telescopic mechanism is arranged on the movable platform (19); The mounting and fixing seat (22) is arranged at the end of the telescopic mechanism, and a mounting groove (23) for fixing the turbine blade (24) is provided on the mounting and fixing seat (22).

7. The gas quenching test device for simulating blade tip thermal inertia according to claim 6, characterized in that: The telescopic mechanism comprises a telescopic seat (20) and a telescopic rod (21); the telescopic seat (20) is connected to the upper surface of the movable platform (19); one end of the telescopic rod (21) is inserted into the telescopic seat (20); the other end of the telescopic rod (21) is connected to the mounting fixed seat (22); and the telescopic rod (21) can be telescoped in the telescopic seat (20).

8. The gas quenching test device for simulating blade tip thermal inertia according to claim 7, characterized in that: The support rod (16) is also provided with a chain belt (17), and the direction of the chain belt (17) is consistent with the direction of the movable rod (18), and the movable platform (19) can move on the chain belt (17).

9. A gas quenching test device for simulating blade tip thermal inertia according to any one of claims 3 to 8, characterized in that: A protective cover (5) is also provided on the base (10), and the annular fixing seat (14) and the contoured induction heating mechanism (2) are both provided inside the protective cover (5).

10. A gas quenching test method for simulating blade tip thermal inertia, implemented based on the gas quenching test device for simulating blade tip thermal inertia according to claim 9, characterized in that: The following steps are involved: S1. Writing the test information of the turbine blade (24) into the controller in the temperature measuring mechanism (1); S2. The turbine blade to be tested (24) is loaded into the electric loading and unloading mechanism (4); S3. The controller in the temperature measuring mechanism (1) controls the electric loading and unloading mechanism (4) to drive the turbine blade (24) into a predetermined position; S4. The controller in the temperature measuring mechanism (1) controls the contour induction heating mechanism (2) to heat and keep the tip of the turbine blade (24); S5. The controller in the temperature measuring mechanism (1) controls the annular heat dissipation mechanism (3) to cool the tip of the turbine blade (24); S6. After completing one thermal cycle, proceed to the next thermal cycle until the test cycle number is completed; S7. The controller in the temperature measuring mechanism (1) controls the electric loading and unloading mechanism (4) to drive the turbine blade (24) into a predetermined position and remove the blade.

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