A gas turbine interstage specific pulsation frequency generation simulation device

Abstract

The present application provides a simulation device for generating a specific pulsation frequency between stages of a gas turbine, which belongs to the field of gas turbine testing. The device includes: an acoustic excitation component, an air bleed component and a compressor test piece, the compressor test piece has an air bleed cavity and multiple air bleed ports connected to the air bleed cavity; the acoustic excitation component includes an acoustic excitation air supply main pipe, an acoustic excitation air intake pressure regulating valve, an acoustic excitation air supply branch pipe, an acoustic horn, an acoustic excitation exhaust branch pipe, an acoustic excitation exhaust main pipe and an air-isolating and sound-permeable diaphragm, the front and rear ends of the acoustic horn are respectively connected to the acoustic excitation air supply branch pipe and the acoustic excitation exhaust branch pipe, high-pressure gas is introduced into the acoustic excitation air supply main pipe, and the high-pressure gas flows to the acoustic horn, and the acoustic horn is adjusted by the acoustic excitation air intake pressure regulating valve to generate a sound pressure level of a predetermined pulse frequency, the acoustic horn is connected to the air bleed port, and the air-isolating and sound-permeable diaphragm is arranged on the air bleed port corresponding to the acoustic horn; the air bleed component includes multiple air bleed pipes, and the air bleed pipes are arranged on the air bleed port where the acoustic horn is not installed.

Description

Technical Field

[0001] The present application belongs to the field of gas turbine testing, and in particular relates to a device for simulating the generation of specific pulsation frequencies between gas turbine stages. Background Art

[0002] Compressor surge is a typical aerodynamic failure in aircraft engines and gas turbines, and it carries significant risks. During testing on a certain gas turbine, a high-pressure compressor surge failure was exposed. Evaluation revealed that abnormal pulsation characteristic frequency disturbances were one of the primary causes of this high-pressure compressor surge. Compressor surge failures often begin with the instability of a single stage of blades, which in turn triggers compressor surge. Currently, there are no test simulations for applying abnormal disturbances to a single stage of compressor blades during compressor component testing or complete unit testing.

[0003] There are two main technical solutions for pulsation frequency simulation of compressor test pieces:

[0004] Solution 1: Based on the electric excitation pipeline pulsation frequency simulation method, this method arranges one or more electric horns at the pipeline inlet, and controls the sound frequency and amplitude of the electric horns as well as the sound phase of the electric horns, thereby controlling the pulsation frequency, amplitude and propagation characteristics of the pulsation frequency inside the pipeline. However, the electric excitation pipeline pulsation frequency simulation method is mostly used in the flow control or acoustic vibration mechanism research of blade or compressor test pieces, and the sound pressure level of the electric horn is less than 140dB. The low-frequency and high-sound-intensity pulsation frequency simulation requires a larger electric horn size. In addition, considering the high sound pressure background noise inside the real compressor, the traditional electric horn pulsation frequency simulation method cannot achieve high signal-to-noise ratio low-frequency pulsation frequency simulation in an engineering environment.

[0005] Scheme 2: Based on the pneumatic horn pulsation frequency simulation method, in this method, when the pneumatic horn is working, the air flow enters from the inlet, is filtered by the filter and reaches the dynamic and static coil working unit. The driving current passes through the dynamic coil and the magnetic field is induced, causing the dynamic and static coils to produce relative movement, thereby changing the gap between the dynamic and static coils through which the air flow flows. As a result, the gap between the dynamic and static coils through which the air flow flows changes accordingly, and finally generates a high-intensity sound wave corresponding to the driving signal, which can achieve an adjustable frequency of 20Hz~500Hz. However, this scheme requires the introduction of high-pressure airflow. For compressor test pieces, the introduction of high-pressure airflow may cause changes in the internal flow field of the compressor, thereby affecting the stability of the compressor. Therefore, it is mainly used in acoustic excitation and acoustic fatigue test research.

[0006] It can be seen from this that the simulation of high signal-to-noise ratio pulsation frequency under compressor or whole machine conditions cannot be achieved well. Summary of the Invention

[0007] The purpose of the present application is to provide a device for simulating the generation of a specific pulsation frequency between stages of a gas turbine, so as to solve or alleviate at least one problem in the background technology.

[0008] The technical solution of the present application is: a gas turbine interstage specific pulsation frequency generation simulation device, comprising: an acoustic excitation component, an air bleed component and a compressor test piece, wherein:

[0009] The compressor test piece has an air bleed cavity and a plurality of air bleed ports connected to the air bleed cavity;

[0010] The acoustic excitation component includes an acoustic excitation air supply main pipeline, an acoustic excitation air intake pressure regulating valve, an acoustic excitation air supply branch pipeline, an acoustic horn, an acoustic excitation exhaust branch pipeline, an acoustic excitation exhaust main pipeline and an air-isolating and sound-permeable diaphragm. The front end and the rear end of the acoustic horn are respectively connected to the acoustic excitation air supply branch pipeline and the acoustic excitation exhaust branch pipeline. The acoustic excitation air supply branch pipeline is connected to the acoustic excitation air supply main pipeline, and the acoustic excitation exhaust branch pipeline is connected to the acoustic excitation exhaust main pipeline. The acoustic excitation air intake pressure regulating valve is arranged on the acoustic excitation air supply branch pipeline, and high-pressure gas is introduced through the acoustic excitation air supply main pipeline. The high-pressure gas flows along the acoustic excitation air supply branch pipeline to the acoustic horn. The acoustic horn is adjusted by the acoustic excitation air intake pressure regulating valve to generate a sound pressure level with a predetermined pulse frequency. After that, the high-pressure gas is discharged along the acoustic excitation exhaust branch pipeline and the acoustic excitation exhaust main pipeline. The acoustic horn is connected to the air inlet, and the air-isolating and sound-permeable diaphragm is arranged on the air inlet corresponding to the acoustic horn.

[0011] The air bleed assembly includes a plurality of air bleed pipes, and the air bleed pipes are arranged on an air bleed port where no acoustic horn is installed.

[0012] In at least one embodiment of the present application, the compressor test piece includes an inner casing, an outer casing, and an air bleed ring, wherein a compressor inner flow passage is formed between the inner casing, the outer casing, and the air bleed ring, and high-temperature and high-pressure gas is introduced into the compressor inner flow passage;

[0013] One end of the air bleed ring is fixedly connected to the outer casing, thereby forming an air bleed cavity between the air bleed ring and the outer casing. A gap is provided between the other end of the air bleed ring and the outer casing, and the gap forms an annular groove. Gas in the compressor flow channel can enter the air bleed cavity along the annular groove.

[0014] The outer casing is provided with a plurality of air inlets, and the air inlets are connected to the air inlet cavity.

[0015] In at least one embodiment of the present application, the temperature of the high-temperature and high-pressure gas is not less than 350°C.

[0016] In at least one embodiment of the present application, the acoustic horn is an air horn.

[0017] In at least one embodiment of the present application, the air bleed assembly further includes an air bleed main pipe, the air bleed pipe is connected to the air bleed main pipe, and the high-temperature and high-pressure gas in the air bleed cavity is discharged after being discharged into the air bleed main pipe through the air bleed pipe.

[0018] In at least one embodiment of the present application, the air bleed assembly further includes an air bleed branch pipe, the air bleed pipe is connected to the air bleed branch pipe, and the high-temperature and high-pressure gas in the air bleed cavity is discharged after being discharged into the air bleed main pipe through the air bleed pipe and the air bleed branch pipe.

[0019] In at least one embodiment of the present application, the air-isolating and sound-permeable diaphragm is a polytetrafluoroethylene film, a polyurethane film or a composite film.

[0020] In at least one embodiment of the present application, a pressure measuring point is further included. The pressure measuring point is arranged at the rear end of the acoustic horn and the air induction cavity. The pressure at the rear end of the acoustic horn is made the same as that in the air induction cavity through the pressure measuring point.

[0021] The gas turbine interstage specific pulse frequency generation simulation device provided in the present application isolates the acoustic horn from the test environment, ensuring that the working environment temperature of the acoustic horn does not exceed 100°C under conditions of high test environment temperature or even higher temperature conditions. This can achieve high-precision simulation of abnormal pulse frequency disturbances in complex environments (high temperature and high pressure), realize simulated excitation of the target sound pressure level of the compressor components, and realize engineering simulation of the characteristic frequency of the gas turbine interstage under complex test conditions such as high temperature, high pressure, and strong background noise interference. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions provided by this application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of this application.

[0023] Figure 1 This is an overall schematic diagram of the gas turbine inter-stage specific pulse frequency generation simulation device of the present application.

[0024] Figure 2 This is a schematic diagram of the structure of the compressor test piece of this application.

[0025] Reference numerals:

[0026] 10-Acoustic excitation component

[0027] 11-Acoustically excited gas supply main pipeline

[0028] 12-Acoustically activated intake pressure regulating valve

[0029] 13-Acoustically excited gas supply branch pipe

[0030] 14-sound horn

[0031] 15-Acoustically excited exhaust branch pipe

[0032] 16-Acoustically excited exhaust main duct

[0033] 17-Air-insulating and sound-permeable diaphragm

[0034] 20-Bleed air assembly

[0035] 21-Airway

[0036] 22-air bleed pipe

[0037] 23-Bleed air main

[0038] 30-Compressor test piece

[0039] 31-Internal Receiver

[0040] 32-External casing

[0041] 33-Air bleed ring

[0042] 34-air bleed cavity

[0043] 35-air inlet DETAILED DESCRIPTION

[0044] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0045] In order to solve the problem of high signal-to-noise ratio characteristic frequency simulation of compressor components under complex test conditions such as high temperature, high pressure, and strong background noise interference, the present application provides a gas turbine inter-stage specific pulse frequency generation simulation device, which is used to realize the test simulation of abnormal characteristic frequency disturbance under all test conditions of the compressor, and solve the technical difficulty of realizing the test simulation of compressor surge failure due to abnormal characteristic frequency on compressor components.

[0046] like Figure 1 and Figure 2 As shown, the gas turbine inter-stage specific pulse frequency generation simulation device of the present application includes: an acoustic excitation component 10, an air bleed component 20 and a compressor test piece 30.

[0047] The compressor test piece 30 includes an inner casing 31, an outer casing 32, and an air bleed ring 33. The inner casing 31, the outer casing 32, and the air bleed ring 33 form the compressor's internal flow path, through which high-temperature, high-pressure gas flows. The temperature of this high-temperature, high-pressure gas can typically reach 350°C or above. The air bleed ring 33 is fixedly connected to the rear end of the outer casing 32, thereby forming an air bleed cavity 34 between the air bleed ring 33 and the outer casing 32. A certain gap exists between the front end of the air bleed ring 33 and the outer casing 32, forming an annular groove. Gas in the compressor's internal flow path can enter the air bleed cavity 34 along the annular groove. A plurality of circumferentially distributed air bleed ports 35 are provided on the outer casing 32, and these air bleed ports 35 are connected to the air bleed cavity 34.

[0048] The acoustic excitation component 10 includes an acoustic excitation air supply main pipe 11, an acoustic excitation air intake pressure regulating valve 12, an acoustic excitation air supply branch pipe 13, an acoustic horn 14, an acoustic excitation exhaust branch pipe 15, an acoustic excitation exhaust main pipe 16 and an air-isolating and sound-permeable diaphragm 17.

[0049] In some embodiments of the present application, the acoustic horn 14 is an air horn. The front end of each acoustic horn 14 is connected to an acoustically excited air supply branch pipe 13, and the rear end is connected to an acoustically excited exhaust branch pipe 15. The acoustically excited air supply branch pipe 13 is connected to the acoustically excited air supply main pipe 11, and the acoustically excited exhaust branch pipe 15 is connected to the acoustically excited exhaust main pipe 16. The high-pressure air source supplies air to one or more acoustically excited exhaust branch pipes 15 through the acoustically excited air supply main pipe 11, thereby driving the acoustic horn 14 to work. After that, the high-pressure gas flows along the acoustically excited exhaust branch pipe 15 into the acoustically excited exhaust main pipe 16, and is then discharged. The sound frequency of the acoustic horn 14 on the corresponding acoustically excited air supply branch pipe 13 can be adjusted by the acoustically excited air intake pressure regulating valve 12, thereby realizing the simulation of the sound pressure level of a specific frequency.

[0050] The air-isolating, acoustically permeable diaphragm 17 is disposed on one or more air bleed ports 35 of the compressor test specimen 30 corresponding to the acoustic horn 14. The specific frequency sound pressure level emitted by the acoustic horn 14 is transmitted through the air-isolating, acoustically permeable diaphragm 17 to the air bleed cavity 34 of the compressor test specimen 30, thereby applying a specific pulse characteristic frequency disturbance to the air bleed cavity 34 of the compressor test specimen 30. In some embodiments of the present application, the air-isolating, acoustically permeable diaphragm 17 may be a polytetrafluoroethylene membrane, a polyurethane membrane, or a composite membrane.

[0051] The bleed air assembly 20 includes a main bleed air pipe 23, a bleed air pipe 21, and a bleed air branch pipe 22. The bleed air pipe 21 is connected to the bleed air port 35 of the compressor test piece 30. Its other end is connected to the main bleed air pipe 23 or to the main bleed air pipe 23 via a bleed air branch pipe 22, thereby discharging gas introduced into the bleed air cavity 34 through the compressor's internal flow path.

[0052] This application uses the two acoustic horns 14 and six bleed air pipes 21 shown in the figure as an example to illustrate the gas turbine inter-stage specific pulse frequency generation simulation device of this application.

[0053] The compressor test specimen 30 is equipped with eight air bleed ports 35, which can be evenly or unevenly distributed around the circumference. Two acoustic horns 14 are roughly symmetrically positioned on either side of the compressor test specimen 30 and connected to the air bleed ports 35 via an air-isolating, acoustically transparent diaphragm 17. The remaining air bleed ports 35 are connected to the air bleed pipe 21.

[0054] A high-pressure gas source (not shown) provides high-pressure gas, which is connected to the acoustically excited gas supply main pipe 11. The high-pressure gas flows through the acoustically excited gas supply main pipe 11 and the acoustically excited gas supply branch pipe 13 to the acoustic horn 14. The acoustically excited air intake pressure regulating valve 12 regulates the high-pressure gas flow rate within the pipe, thereby controlling the sound pressure level of the characteristic frequency generated by the acoustic horn 14. After passing through the acoustic horn 14, the high-pressure gas is discharged through the acoustically excited exhaust branch pipe 15 and the acoustically excited exhaust main pipe 16. An air-isolating, acoustically permeable diaphragm 17 is installed at the air bleed port 35 corresponding to the acoustic horn 14. The acoustically excited exhaust branch pipe 15 is located at the front end of the air-isolating, acoustically permeable diaphragm 17 in the air flow path. The high-pressure gas passing through the acoustic horn 14 is discharged through the acoustically excited exhaust branch pipe 15 and the acoustically excited exhaust main pipe 16. The sound pressure level generated by the acoustic horn 14 is transmitted through the air-isolating, acoustically permeable diaphragm 17 to the bleed air cavity 34 of the compressor test piece 30, thereby simulating the pulsation frequency of the compressor bleed air cavity under engineering conditions.

[0055] In the present application, pressure measuring points may be provided at the rear end of the acoustic horn 14 and in the bleed air cavity 34 of the compressor test piece 30. The pressure in the acoustic excitation pipe is measured at the pressure measuring point at the rear end of the acoustic horn 14, and the pressure at the bleed air port 35 or the bleed air cavity 34 is measured at the pressure measuring point in the bleed air cavity 34, ensuring that the pressure at the bleed air port 35 or the bleed air cavity 34 is the same as the outlet pressure of the acoustic horn 14. In some embodiments of the present application, pressure measurement can be achieved by providing a pressure sensor at the pressure measuring point.

[0056] Furthermore, a temperature measuring point can be provided within the bleed air cavity 34 of the compressor test piece 30 to monitor the gas temperature within the bleed air cavity 34 and ensure that no airflow is transmitted at the interface between the bleed air cavity 34 and the acoustic excitation pipe. In some embodiments of the present application, a thermocouple can be provided at the temperature measuring point to achieve temperature measurement.

[0057] The gas turbine interstage specific pulse frequency generation simulation device provided in the present application isolates the acoustic horn 14 from the test environment, ensuring that the working environment temperature of the acoustic horn 14 does not exceed 100°C under conditions of high test environment temperature (close to 350°C) or even higher temperature conditions. This can achieve high-precision simulation of abnormal pulse frequency disturbances under complex environments (high temperature and high pressure), realize simulated excitation of the target sound pressure level of the compressor components, and realize engineering simulation of the characteristic frequency of the gas turbine interstage under complex test conditions such as high temperature, high pressure, and strong background noise interference.

[0058] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A gas turbine interstage specific pulsation frequency generation simulation device, characterized in that: include: An acoustic excitation assembly (10), a bleed air assembly (20), and a compressor test piece (30), wherein: The compressor test piece (30) has an air bleed cavity (34) and a plurality of air bleed ports (35) communicating with the air bleed cavity (34); The acoustic excitation component (10) comprises an acoustic excitation air supply main pipe (11), an acoustic excitation air intake pressure regulating valve (12), an acoustic excitation air supply branch pipe (13), an acoustic horn (14), an acoustic excitation exhaust branch pipe (15), an acoustic excitation exhaust main pipe (16) and an air-isolating sound-permeable membrane (17). The front end and the rear end of the acoustic horn (14) are respectively connected to the acoustic excitation air supply branch pipe (13) and the acoustic excitation exhaust branch pipe (15). The acoustic excitation air supply branch pipe (13) is connected to the acoustic excitation air supply main pipe (11), the acoustic excitation exhaust branch pipe (15) is connected to the acoustic excitation exhaust main pipe (16), and the acoustic excitation An air intake pressure regulating valve (12) is arranged on the acoustically excited air supply branch pipe (13), and high-pressure gas is introduced through the acoustically excited air supply main pipe (11). The high-pressure gas flows along the acoustically excited air supply branch pipe (13) to the acoustic horn (14). The acoustically excited air intake pressure regulating valve (12) adjusts the sound pressure level of the acoustic horn (14) to generate a predetermined pulse frequency. Thereafter, the high-pressure gas is discharged along the acoustically excited exhaust branch pipe (15) and the acoustically excited exhaust main pipe (16). The acoustic horn (14) is connected to the air inlet (35), and the air-isolating sound-permeable diaphragm (17) is arranged on the air inlet (35) corresponding to the acoustic horn (14); The air bleed assembly (20) comprises a plurality of air bleed pipes (21), wherein the air bleed pipes (21) are arranged on an air bleed port (35) where no acoustic horn (14) is installed.

2. The gas turbine inter-stage specific pulsation frequency generation simulation device according to claim 1, characterized in that: The compressor test piece (30) includes an inner casing (31), an outer casing (32) and an air bleed ring (33), wherein a compressor inner flow passage is formed between the inner casing (31), the outer casing (32) and the air bleed ring (33), and high-temperature and high-pressure gas is introduced into the compressor inner flow passage; One end of the air bleed ring (33) is fixedly connected to the outer casing (32), thereby forming an air bleed cavity (34) between the air bleed ring (33) and the outer casing (32), and a gap is provided between the other end of the air bleed ring (33) and the outer casing (32), the gap forming an annular groove, and the gas in the flow channel of the compressor can enter the air bleed cavity (34) along the annular groove; The outer casing (32) is provided with a plurality of air inlets (35), and the air inlets (35) are connected to the air inlet cavity (34).

3. The gas turbine inter-stage specific pulsation frequency generation simulation device according to claim 2, characterized in that: The temperature of the high-temperature and high-pressure gas is not less than 350°C.

4. The gas turbine inter-stage specific pulsation frequency generation simulation device according to claim 3, characterized in that: The acoustic horn (14) is an air horn.

5. The gas turbine inter-stage specific pulsation frequency generation simulation device according to claim 4, characterized in that: The air bleed assembly (20) further includes an air bleed main pipe (23), the air bleed pipe (21) is connected to the air bleed main pipe (23), and the high-temperature and high-pressure gas in the air bleed cavity (34) flows through the air bleed pipe (21) into the air bleed main pipe (23) and is then discharged.

6. The gas turbine inter-stage specific pulsation frequency generation simulation device according to claim 5, characterized in that: The air bleed assembly (20) further includes an air bleed branch pipe (22), the air bleed pipe (21) is connected to the air bleed branch pipe (22), and the high-temperature and high-pressure gas in the air bleed cavity (34) is discharged after being merged into the air bleed main pipe (23) through the air bleed pipe (21) and the air bleed branch pipe (22).

7. The gas turbine inter-stage specific pulsation frequency generation simulation device according to claim 1, characterized in that: The air-isolating and sound-permeable diaphragm (17) is a polytetrafluoroethylene film, a polyurethane film or a composite film.

8. The gas turbine inter-stage specific pulsation frequency generation simulation device according to claim 1, characterized in that: It also includes a pressure measuring point, which is arranged at the rear end of the sound horn (14) and the air induction cavity (34). The pressure at the rear end of the sound horn (14) is made equal to the pressure in the air induction cavity (34) through the pressure measuring point.

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