A simulator for simulating the operation of a gas turbine turbine blade

Abstract

The application discloses a simulator for simulating the work of a gas turbine turbine blade, relates to the technical field of gas turbine turbine blade simulation, and specifically relates to the following: in the background art, when a multi-leaf high-radiation pyrometer is researched and designed, there is no corresponding auxiliary simulator for detecting and testing the performance and rationality of the mechanical structure, the application provides a simulator for simulating the work of a gas turbine turbine blade, the core part lies in the design of a driving motor, a slip ring and a blade simulation assembly and other structures, the corresponding control signal can be acquired while the blade simulation assembly rotates at a high speed, the correctness of the light path of the multi-leaf high-radiation pyrometer is verified, the correctness of the software temperature field reconstruction algorithm of the multi-leaf high-radiation pyrometer is verified, and the rationality of the design of the telescopic mechanism and other mechanical structures of the multi-leaf high-radiation pyrometer is verified.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of gas turbine turbine blade simulation, and particularly relates to a simulator for simulating the working of a gas turbine turbine blade. BACKGROUND

[0002] As a new type of power device, gas turbines play an extremely important role in many fields of national economy and national defense construction. In the field of land power generation, the installed capacity of gas turbine power generation equipment is increasing, in the field of ship power, the development of high-power gas turbines has become the mainstream, and in the field of modern aviation, gas turbines are the preferred power device for various military and civilian aircraft. As one of the key components of gas turbines, the turbine is an important heat end component that converts the available heat energy of the gas into mechanical energy, and the turbine blade includes a guide vane and a turbine blade. The guide vane is static and the turbine blade is rotating in actual operation. Based on the urgent need to improve the power performance, the turbine inlet temperature is continuously increased and is much higher than the melting point of the material. In order to ensure that the turbine blade can work safely and reliably in a high-temperature environment higher than the melting point of the material, it must be efficiently cooled, and accurate measurement and control of the turbine blade surface temperature distribution is an important basis for turbine blade profile and cooling structure design. At present, there are many studies on the measurement of the surface temperature of the turbine blade, but for the turbine blade, it is very difficult to measure the surface temperature due to its high-speed rotation and high-temperature harsh environment, and higher requirements are put forward for the performance of the measuring instrument.

[0003] The temperature measurement of the turbine blade of the gas turbine has always been a key research and development project in the detection technology of the gas turbine. At present, the products that can assist in the performance test of the multi-leaf high-radiation temperature measuring device in the world all depend on foreign imports, among which the Rotadata of the United Kingdom is the most representative, and the multi-leaf high-radiation temperature measurement technology has not been broken through in China, and the key reason is the lack of experimental environment. The internal environment of the gas turbine is in a high-temperature and high-pressure state, and the on-board test requirements of the gas turbine are harsh. Therefore, a special device that can assist in the research and development test of the multi-leaf high-radiation temperature measuring equipment is urgently needed to assist in the research and development of the multi-leaf high-radiation temperature measuring device.

[0004] Therefore, it is urgent to design a simulator for simulating the working of a gas turbine turbine blade to solve the above problems. SUMMARY

[0005] In view of the defects in the prior art, the present application aims to provide a simulator for simulating the working of a gas turbine turbine blade, which mainly combines mechanical and electrical equipment, and the core part is the design of the driving motor, slip ring and blade simulation assembly structure, to ensure that the corresponding control signal can be obtained while the blade simulation assembly is rotating at high speed. It is used to assist in verifying the correctness of the multi-leaf high-radiation pyrometer light path, the correctness of the software temperature field reconstruction algorithm and the rationality of the related mechanical settings, greatly promoting the development of domestic gas turbine turbine blade multi-leaf high-radiation temperature measuring equipment, and greatly shortening the time from the prototype machine to the actual test of the multi-leaf high-radiation temperature measuring equipment. Better promote the development of China's gas turbine industry.

[0006] In order to achieve the above-mentioned purpose, the technical scheme adopted by the present application is as follows:

[0007] A simulator for simulating the working of a gas turbine turbine blade, comprising a shell, further comprising:

[0008] A blade simulation device is arranged in the shell and connected to the upper and lower ends of the shell cavity;

[0009] A blade speed determination device is used in cooperation with the blade simulation device to determine the current blade speed;

[0010] A blade temperature determination device is used in cooperation with the blade simulation device to determine the temperature represented by the current blade.

[0011] Preferably, the blade simulation device comprises:

[0012] A slip ring is rotatably arranged at the top of the shell through a support, and the other end is connected to the blade simulation device and externally connected to a power supply;

[0013] A blade simulation assembly is arranged between the slip ring and the driving motor and coaxially connected with the driving motor;

[0014] A driving motor is arranged at the bottom of the shell through a support and electrically connected with the slip ring.

[0015] Preferably, the blade simulation assembly comprises:

[0016] A blade simulation piece is sleeved on the middle piece, and a threaded mounting hole is formed in the blade simulation piece;

[0017] A pressing plate is sleeved on the middle piece and located at the upper end of the blade simulation piece, and a threaded mounting hole is also formed in the pressing plate;

[0018] A middle piece is provided with a threaded mounting hole, an upper threaded hole and a lower threaded hole; the threaded mounting holes on the blade simulation piece, the pressing plate and the middle piece are used in cooperation with the bolts, the slip ring is connected with the middle piece through the upper threaded hole, and the driving motor is connected with the middle piece through the lower threaded hole.

[0019] Preferably, the blade simulation piece comprises:

[0020] a printed circuit board,

[0021] a plurality of blade simulation tubes, evenly welded on the printed circuit board, for simulating the state of the turbine blade radiating infrared light outwardly;

[0022] a plurality of current-limiting control resistors, welded on the printed circuit board, and electrically connected with the corresponding blade simulation tubes, for controlling the radiation intensity of the corresponding blade simulation tubes.

[0023] Preferably, the upper and lower ends of the shell are provided with holes communicating with the inner cavity thereof, and the side edges are provided with vertical holes communicating with the inner cavity thereof.

[0024] Preferably, the blade rotation speed determining device comprises:

[0025] a strong magnet, arranged on the blade simulation device, for emitting an electromagnetic pulse signal;

[0026] a Hall sensor, arranged on the inner wall of the shell, for receiving the electromagnetic pulse signal emitted by the strong magnet;

[0027] a code table, arranged on the upper end of the shell, and electrically connected with the Hall sensor, for receiving the electromagnetic pulse signal transmitted by the Hall sensor, and calculating and displaying the current rotation speed of the blade simulation device.

[0028] Preferably, the blade temperature determining device comprises a photoelectric sensor, which is used for collecting the radiated infrared light emitted by the blade simulation device, and converting it into an electric signal, for determining the current temperature of the blade simulation device.

[0029] The present application has the beneficial effects that: the present application discloses a simulator for simulating the working of the turbine blade of the gas turbine, compared with the prior art, the improvement of the present application lies in that:

[0030] (1) by using the simulator of the present application, it can be directly verified whether the structure of the multi-leaf high-radiation temperature measuring device is reasonable, and the defects in the structure can be adjusted and improved in time.

[0031] (2) the simulator of the present application can test the multi-leaf high-radiation temperature measuring device in an offline environment, and verify whether its performance meets the requirements.

[0032] (3) by adjusting the infrared light source and the rotation speed of the turbine disc in the simulator of the present application, the working state of the gas turbine in different working conditions can be simulated, so that the effectiveness of the multi-leaf high-radiation temperature measuring device can be more comprehensively analyzed.

[0033] (4) The infrared radiation light of the experimental device is collected by the developed multi-leaf high-radiation high-thermometer, so as to obtain the temperature distribution of the blade simulation assembly of the experimental device, and the temperature distribution data is utilized, so as to realize the verification of the turbine blade temperature field reconstruction algorithm and provide support for the turbine blade temperature field reconstruction. BRIEF DESCRIPTION OF DRAWINGS

[0034] Figure 1 It is a simulator sectional view of the application;

[0035] Figure 2 It is a simulator perspective view of the application;

[0036] Figure 3 It is a shell side view of the application;

[0037] Figure 4 It is a blade simulation assembly top view of the application;

[0038] Figure 5 It is a pressing plate structure schematic view of the application;

[0039] Figure 6 It is a middle piece structure schematic view of the application;

[0040] Figure 7 It is a middle piece sectional view of the application;

[0041] Figure 8 It is a blade simulation device side view of the application;

[0042] Figure 9 It is an electrical connection schematic view of the application;

[0043] Figure 10 It is a simulator working state actuality view of the application;

[0044] Figure 11 It is a simulator static state actuality view of the application;

[0045] Figure 12 It is a simulator working state view of the application;

[0046] Figure 13 It is a simulator internal structure actuality view of the application;

[0047] Wherein: 1. shell; 101. hole; 102. square hole; 103. vertical hole; 2. support; 3. slip ring; 4. blade simulation assembly; 401. printed circuit board; 401-1. threaded mounting hole; 402. blade simulation tube; 403. current limiting control resistance; 5. driving motor; 6. middle piece; 601. upper threaded hole; 602. lower threaded hole; 7. pressing plate; 8. bolt. DETAILED DESCRIPTION

[0048] In order to make ordinary skilled in the art better understand the technical solutions of the present application, the technical solutions of the present application are further described below in combination with the drawings and examples.

[0049] Embodiment:

[0050] Referring to the drawings Figures 1-9 The simulator for simulating the working of a gas turbine turbine blade comprises a housing 1, a blade simulation device, a blade rotating speed determining device and a blade temperature determining device, the blade simulation device is arranged in the housing 1 and connected with the upper and lower ends of the inner cavity of the housing 1; the blade rotating speed determining device is used in cooperation with the blade simulation device to determine the rotating speed of the current blade; the blade temperature determining device is used in cooperation with the blade simulation device to determine the temperature of the current blade;

[0051] Specifically, the blade simulation device comprises a slip ring 3, a blade simulation assembly and a driving motor 5, the slip ring 3 in this embodiment is selected as an A2H type mercury slip ring, the slip ring 3 is rotatably arranged at the top of the housing 1 through a support 2 and electrically connected with the driving motor 5 for supplying power to the driving motor 5; the blade simulation assembly is arranged between the slip ring 3 and the driving motor 5 and coaxially connected with the driving motor 5; in use, the driving motor 5 rotates to drive the blade simulation assembly to rotate synchronously, the driving motor 5 is arranged at the bottom of the housing 1 through the support 2, and the driving motor is a 775 type direct current motor;

[0052] Further referring to the drawings Figures 5-8 As shown in the drawings, considering the connection problem of the printed circuit board 401 in the blade simulation assembly and the driving motor 5, since the printed circuit board 401 is a relatively soft organic material and cannot be directly and stably connected with the driving motor 5, the intermediate piece 6 and the pressing plate 7 are designed, the printed circuit board 401 and the pressing plate 7 are sleeved on the intermediate piece 6, and the printed circuit board 401 is arranged at the lower end of the pressing plate 7, threaded mounting holes 401-1 are arranged on the pressing plate 7, the printed circuit board 401 and the intermediate piece 6, the threaded mounting holes 401-1 are used in cooperation with the bolts 8 to fix the pressing plate 7, the printed circuit board 401 and the intermediate piece 6 into an integral whole, and the stability of the connection between the printed circuit board 401 and the driving motor 5 is ensured; wherein the diameter of the bolt is 2.5 mm;

[0053] Referring to the drawings Figure 6As shown, a plurality of upper threaded holes 601 and lower threaded holes 602 are arranged on the middle piece 6, the upper threaded holes are matched with the first bolts to fix the middle piece 601 with the slip ring 3, and the lower threaded holes 602 are matched with the second bolts to fix the middle piece 601 with the output shaft of the driving motor 5; the driving motor 5 drives the middle piece 601 to rotate synchronously, the middle piece 601 drives the pressing plate 7 and the printed circuit board 401 to rotate synchronously, and the middle piece 601 also drives the slip ring 3 to rotate synchronously, and the rotation of the slip ring 3 does not affect the power supply; the purpose of the pressing plate 7 is to better make the printed circuit board 401 adhere to the middle piece 6, to ensure that the plane of the printed circuit board 401 is perpendicular to the axial direction of the driving motor 5, so as to reduce the vibration in the rotation process as much as possible.

[0054] Specifically, refer to the accompanying drawings Figures 2-3 As shown, the upper and lower ends of the shell 1 are provided with holes 101 which are communicated with the inner cavities of the shell 1, the holes 101 can reduce the weight of the shell 1, and the hole 101 at the upper end facilitates the observation of the running state inside the shell 1; a vertical hole 103 which is communicated with the inner cavity of the shell 1 is also arranged on the side of the shell 1, and the vertical hole 103 facilitates the multi-leaf high-radiation temperature measurement probe to enter the shell 1 to measure the temperature of the blade simulation assembly 4.

[0055] Specifically, refer to the accompanying drawings Figure 4 As shown, the blade simulation assembly 4 includes a printed circuit board 401, a plurality of blade simulation tubes 402, and a plurality of current-limiting control resistors 403, in this embodiment, the blade simulation tubes 402 are 50, and the current-limiting control resistors 403 are 50; each current-limiting control resistor 403 corresponds to one blade simulation tube 402 and is used to control the corresponding blade simulation tube 402, the blade simulation tube 402 in this embodiment is a full-spectrum light source tungsten lamp tube which is welded on the printed circuit board 401 and radiates infrared light outward after being electrified, to realize the simulation of the state that the turbine blade radiates infrared light outward, as shown in Figure 9 As shown, the printed circuit board 401 is electrified;

[0056] Further, the blade simulation tubes 402 and the current-limiting control resistors 403 are symmetrically arranged on the printed circuit board 401, the blade simulation tubes 402 are uniformly arranged on the outermost side of the surface of the printed circuit board 401, and the included angle between any two adjacent blade simulation tubes 402 is 7.2°; the current-limiting control resistors 403 are uniformly arranged on the inner side of the surface of the printed circuit board 401, and the current-limiting control resistors 403 are electrically connected with the blade simulation tubes 402, the radiation intensity of the blade simulation tubes 402 is controlled by the size of the current-limiting control resistors 403, so that different blade temperatures can be simulated;

[0057] The radiation light intensity of the blade simulation tube 402 is directly related to the current, and the resistance value of the current-limiting control resistor 403 is increased, so that the radiation light of the blade simulation tube 402 is reduced, and vice versa. Therefore, the radiation light intensity of the blade simulation tube 402 can be adjusted through the current, and during use, the blade simulation tubes 402 that are mutually symmetrical can be removed, and the blade simulation tubes 402 removed each time are double, so that the number of the blade simulation tubes 402 is changed to meet the temperature test of different numbers of blade simulation tubes 402;

[0058] The blade temperature determination device is an optical sensor, which is used in cooperation with the blade simulation device to determine the temperature of the current blade simulation device. The specific principle is that after the blade simulation device is started, the driving motor 5 drives the printed circuit board 401 to rotate, and the blade simulation tube 402 emits radiation light, which is collected by the optical sensor and converted into an electrical signal. Then, the experimenter determines the current temperature value of the simulation blade 402 through the corresponding relationship between the voltage value of the electrical signal and the temperature. Specifically, the 12V power supply is supplied by the slip ring 3, the input end of the slip ring 3 is connected with a cable, the cable is connected with the 12V power supply on the terminal, and is connected with the GND (grounding point);

[0059] Specifically, the blade rotation speed determination device includes a strong magnet, a Hall sensor, and a code table. The strong magnet is arranged on the blade simulation device. The Hall sensor is arranged on the inner wall of the shell 1 and is used to receive the electromagnetic pulse signal emitted by the strong magnet arranged on the printed circuit board 401. That is, the number of strong magnet signals received by the Hall sensor per second is the rotation speed of the printed circuit board 401. The code table is clamped on the upper end of the shell 1 through the square hole 102 on the shell 1 and is electrically connected with the Hall sensor, which is used to receive the electromagnetic pulse signal emitted by the Hall sensor and calculate and display the current rotation speed of the blade simulation device. The code table is electrically connected with the Hall element sensor, the +12V power supply, and the GND, respectively. The strong magnet is arranged in a slot formed at the edge of the circuit board 401, and a part of the strong magnet is fixedly arranged in the slot. The Hall sensor is electrically connected with the 12V power supply and the GND on the terminal, and the 12V power supply is used to supply power to the Hall sensor.

[0060] The principle of determining the current rotation speed of the blade simulation tube 402 is that the Hall sensor transmits the electromagnetic pulse signal received per second to the code table through wired connection, and the code table calculates and displays the rotation speed of the blade simulation tube 402 for the staff to check the current rotation speed of the blade simulation tube 402. Wherein, the strong magnet passes through the Hall sensor once, and the Hall sensor receives a signal once.

[0061] Specifically, a speed regulator is arranged on the outer wall of the shell 1 and electrically connected with the driving motor 5, and is externally connected with 12V power supply and GND on the terminal, respectively, and the speed regulator is used for controlling the rotating speed of the driving motor 5, so as to facilitate the research on the temperature of the blade simulation tube 402 under different rotating speeds; wherein, the speed regulator adjusts the rotating speed of the driving motor 5 by adjusting the PWM (pulse width).

[0062] The device can assist in the design and development of a multi-leaf high-radiation temperature meter. Specifically, the probe of a high-radiation pyrometer is inserted into the shell 1 through the vertical hole 103 and cooperates with the blade simulation device to realize the development of a multi-leaf high-radiation temperature meter. The specific function is that,

[0063] 1. Verify the correctness of the light path of the multi-leaf high-radiation pyrometer. After the light path of the multi-leaf high-radiation pyrometer is designed, the probe of the multi-leaf high-radiation pyrometer directly detects the radiation light of the blade simulation tube 402. Through the reverse light experiment, the position of the light spot is compared to verify the correctness of the light path of the multi-leaf high-radiation pyrometer.

[0064] 2. Verify the correctness of the software temperature field reconstruction algorithm of the multi-leaf high-radiation pyrometer. By controlling the resistance value of each current limiting resistor 403, the radiation light intensity of the corresponding blade simulation tube 402 can be controlled, and the temperature corresponding to the radiation light intensity is changed. Through the different temperatures of each blade simulation tube 402, the software temperature field reconstruction of the multi-leaf high-radiation pyrometer is verified. By comparing the image after temperature field reconstruction with the infrared camera image, the correctness of the algorithm is verified.

[0065] 3. Assist in verifying the rationality of the expansion mechanism and other mechanical structure design of the multi-leaf high-radiation pyrometer. By using the multi-leaf high-radiation pyrometer in the shell 1, the rationality of the expansion mechanism and other mechanical structure design of the multi-leaf high-radiation pyrometer is tested.

[0066] The above shows and describes the basic principles, main features and advantages of the present application. Those skilled in the art should understand that the present application is not limited to the above examples, and the above examples and descriptions in the specification are only to illustrate the principles of the present application. Without departing from the spirit and scope of the present application, various changes and improvements can be made to the present application, and these changes and improvements all fall within the scope of the claimed present application. The scope of protection of the present application is defined by the appended claims and their equivalents.

Claims

1. A simulator for simulating the operation of gas turbine blades, comprising a housing (1), characterized in that, Also includes: The blade simulation device is installed inside the outer casing (1) and connected to the upper and lower ends of the outer casing (1); The blade rotation speed determination device, used in conjunction with the blade simulation device, is used to determine the current blade rotation speed; The blade temperature determination device, used in conjunction with the blade simulation device, is used to determine the temperature of the current blade. The blade simulation device includes: The slip ring (3) is rotatably mounted on the top of the housing (1) via the support member (2), and the other end is connected to the blade simulation device and an external power supply; The blade simulation assembly is set between the slip ring (3) and the drive motor (5) and is coaxially connected to the drive motor (5); The drive motor (5) is mounted on the bottom of the housing (1) via the support member (2) and is electrically connected to the slip ring (3); The blade simulation components include: The blade simulation component (4) is fitted onto the intermediate component (6) and has a threaded mounting hole (401-1) on it. The pressure plate (7) is fitted on the intermediate part (6) and located at the upper end of the blade simulation part (4). The pressure plate (7) is also provided with threaded mounting holes (401-1). The intermediate part (6) is also provided with a threaded mounting hole (401-1), an upper threaded hole (601) and a lower threaded hole (602); the threaded mounting holes (401-1) on the blade simulation part (4), the pressure plate (7) and the intermediate part (6) are used in conjunction with the bolt (8), the slip ring (3) is connected to the intermediate part (6) through the upper threaded hole (601), and the drive motor (5) is connected to the intermediate part (6) through the lower threaded hole (602); The blade simulation component (4) includes: Printed circuit board (401). Several blade simulation tubes (402) are uniformly soldered on a printed circuit board (401) to simulate the state of turbine blades radiating infrared light outward; Several current-limiting control resistors (403) are soldered on a printed circuit board (401) and electrically connected to their corresponding blade simulation tubes (402) to control the radiation intensity of the corresponding blade simulation tubes (402).

2. A simulator for simulating the operation of gas turbine blades according to claim 1, characterized in that: The outer shell (1) has holes (101) at the top and bottom ends that communicate with its inner cavity, and vertical holes (103) on the side that communicate with its inner cavity.

3. A simulator for simulating the operation of gas turbine blades according to claim 1, characterized in that, The blade speed determination device includes: A strong magnet is installed on the blade simulation device to emit electromagnetic pulse signals; A Hall sensor is installed on the inner wall of the housing (1) to receive electromagnetic pulse signals emitted by a strong magnet. The speedometer is set on the upper end of the housing (1) and electrically connected to the Hall sensor. It is used to receive the electromagnetic pulse signal transmitted by the Hall sensor and to calculate and display the current rotation speed of the blade simulation device.

4. A simulator for simulating the operation of gas turbine blades according to claim 1, characterized in that: The blade temperature determination device includes a photoelectric sensor, which collects the infrared radiation emitted by the blade simulation device and converts it into an electrical signal to determine the current temperature of the blade simulation device.

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