Gas turbine interstage specific pulsation frequency generation simulation device

Abstract

The invention provides a gas turbine interstage specific pulsation frequency generation simulation device, and belongs to the field of gas turbine tests.The gas turbine interstage specific pulsation frequency generation simulation device comprises an acoustic excitation assembly, an air entraining assembly and a gas compressor test piece, and the gas compressor test piece is provided with an air entraining cavity and a plurality of air entraining openings communicating with the air entraining cavity; the sound excitation assembly comprises a sound excitation gas supply main pipeline, a sound excitation gas inlet pressure regulating valve, a sound excitation gas supply branch pipeline, a sound horn, a sound excitation gas exhaust branch pipeline, a sound excitation gas exhaust main pipeline and a gas insulation and sound transmission diaphragm, the front end and the rear end of the sound horn are connected with the sound excitation gas supply branch pipeline and the sound excitation gas exhaust branch pipeline respectively, and high-pressure gas is introduced into the sound excitation gas supply main pipeline; high-pressure gas flows to the sound loudspeaker, the sound loudspeaker is adjusted to generate the sound pressure level of the preset pulse frequency through the sound excitation air inlet pressure adjusting valve, the sound loudspeaker is connected with the air entraining opening, and the air isolation and sound transmission diaphragm is arranged on the air entraining opening corresponding to the sound loudspeaker; the air entraining assembly comprises a plurality of air entraining pipes, and the air entraining pipes are arranged on the air entraining ports without the sound horns.

Description

Technical Field

[0001] This application belongs to the field of gas turbine tests, and particularly relates to a simulation device for generating specific pulsation frequencies between stages of a gas turbine. Background Art

[0002] Compressor surge failure is a typical aerodynamic failure of aero-engines and gas turbines, and the harm of compressor surge failure is extremely great. A certain type of gas turbine once exposed the problem of high-pressure compressor surge failure during the test. After evaluation, abnormal pulsation characteristic frequency disturbance is one of the main reasons for triggering the high-pressure compressor surge failure. Compressor surge failure often first shows instability characteristics in a certain stage of blades, and then induces the compressor to have a surge failure. Under the conditions of compressor component tests or the whole machine, there is currently no relevant test simulation scheme for applying abnormal disturbance to a certain stage of blades of the compressor.

[0003] The simulation of the pulsation frequency of the compressor test piece mainly includes the following two technical solutions: 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 pulsation frequency, amplitude and the propagation characteristics of the pulsation frequency inside the pipeline by controlling the sounding frequency, amplitude and sounding phase of the electric horn; however, the electric excitation pipeline pulsation frequency simulation method is mostly applied to the flow control or acoustic vibration mechanism research of cascades or compressor test pieces, and the sound pressure level generated by the electric horn is less than 140 dB. For low-frequency high-intensity pulsation frequency simulation, a larger size of the electric horn is required, and 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 the engineering environment.

[0004] Solution 2: Based on the pneumatic horn pulsation frequency simulation method, in this method, when the pneumatic horn works, the air flow enters from the inlet, passes through the filter and reaches the moving and static coil working unit. The driving current passes through the induction of the moving coil and the magnetic field, causing relative movement between the moving coil and the static coil, and then changing the gap between the moving coil and the static coil through which the air flow passes. As a result, the gap between the moving coil and the static coil through which the air flow passes changes accordingly, and finally high-intensity sound waves corresponding to the driving signal are generated, and the adjustable frequency range is 20 Hz to 500 Hz. However, this solution requires the introduction of high-pressure air flow. For the compressor test piece, the introduction of high-pressure air flow may cause changes in the internal flow field of the compressor, thus affecting the stability of the compressor. Therefore, it is mainly applied to acoustic excitation and acoustic fatigue test research.

[0005] Therefore, it can be seen that the simulation of high-signal-to-noise ratio pulsation frequency under the conditions of the compressor or the whole machine cannot be well achieved. Summary of the Invention

[0006] 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.

[0007] 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: The compressor test piece has an air bleed cavity and a plurality of air bleed ports connected to the air bleed cavity; 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. 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.

[0008] 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; 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. The outer casing is provided with a plurality of air inlets, and the air inlets are connected to the air inlet cavity.

[0009] 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.

[0010] In at least one embodiment of the present application, the acoustic horn is an air horn.

[0011] 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.

[0012] In at least one embodiment of the present application, the air extraction assembly further includes an air extraction branch pipe, the air extraction pipe is connected to the air extraction branch pipe, and the high-temperature and high-pressure gas in the air extraction cavity is discharged after flowing into the air extraction main pipe through the air extraction pipe and the air extraction branch pipe.

[0013] In at least one embodiment of the present application, the air isolation and sound transmission diaphragm is a polytetrafluoroethylene film, a polyurethane film or a composite film.

[0014] In at least one embodiment of the present application, it further includes a pressure measurement point, the pressure measurement point is arranged at the rear end of the sound horn and in the air extraction cavity, and the pressure at the rear end of the sound horn is made the same as that in the air extraction cavity through the pressure measurement point.

[0015] The simulation device for generating a specific pulse frequency between stages of a gas turbine provided by the present application isolates the sound horn from the test environment, ensuring that the operating environment temperature of the sound horn does not exceed 100 °C even under a relatively high temperature environment or even higher temperature conditions in the test environment. Therefore, high-precision simulation of abnormal pulse frequency disturbances under complex environments (high temperature and high pressure) can be achieved, the simulation excitation of the target sound pressure level of the compressor component can be realized, and the engineering simulation of the inter-stage characteristic frequency of the gas turbine under complex test conditions such as high temperature, high pressure, and strong background noise interference can be realized. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions provided by the present application, the drawings will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application.

[0017] Figure 1 It is a general schematic diagram of the simulation device for generating a specific pulse frequency between stages of a gas turbine of the present application.

[0018] Figure 2 It is a structural schematic diagram of the compressor test piece of the present application.

[0019] Reference Signs: 10 - Sound excitation assembly 11 - Main air supply pipeline for sound excitation 12 - Air intake pressure regulating valve for sound excitation 13 - Branch air supply pipeline for sound excitation 14 - Sound horn 15 - Branch exhaust pipeline for sound excitation 16 - Main exhaust pipeline for sound excitation 17 - Air isolation and sound transmission diaphragm 20 - Air extraction assembly 21 - Air extraction pipe 22 - Air extraction branch pipe 23 - Air extraction main pipe 30 - Compressor test piece 31 - Inner casing 32 - Outer casing 33 - Bleed air ring 34 - Bleed air cavity 35 - Bleed air port Specific implementation manner

[0020] To make the purpose, technical solution and advantages of the implementation of this application clearer, the technical solution in the embodiments of this application will be described in more detail below in conjunction with the accompanying drawings in the embodiments of this application.

[0021] Regarding the problem of simulating the high - signal - to - noise characteristic frequency in complex test conditions such as high temperature, high pressure, and strong background noise interference for compressor components, this application provides a simulation device for generating specific pulse frequencies between stages of a gas turbine, which is used to achieve the test simulation of abnormal characteristic frequency disturbances under all test conditions of the compressor, and solve the technical problem that it is difficult to achieve the test simulation of abnormal characteristic frequencies on compressor components for compressor surge faults.

[0022] As Figure 1 and Figure 2 shown, the simulation device for generating specific pulse frequencies between stages of the gas turbine of this application includes: a sound excitation component 10, a bleed air component 20, and a compressor test piece 30.

[0023] The compressor test piece 30 includes an inner casing 31, an outer casing 32, and a bleed air ring 33. An internal flow path of the compressor is formed between the inner casing 31, the outer casing 32, and the bleed air ring 33. High - temperature and high - pressure gas is introduced into the internal flow path of the compressor, and the temperature of this high - temperature and high - pressure gas can usually reach 350 °C or above. The bleed air ring 33 is fixedly connected to the rear end of the outer casing 32, so as to form a bleed air cavity 34 between the bleed air ring 33 and the outer casing 32. There is a certain gap between the front end of the bleed air ring 33 and the outer casing 32, and this gap forms an annular groove. The gas in the internal flow path of the compressor can enter the bleed air cavity 34 along the annular groove. A plurality of circumferentially distributed bleed air ports 35 are provided on the outer casing 32, and the bleed air ports 35 communicate with the bleed air cavity 34.

[0024] The sound excitation component 10 includes a main sound excitation gas supply pipeline 11, a sound excitation intake pressure regulating valve 12, a sound excitation gas supply branch pipeline 13, a sound horn 14, a sound excitation exhaust branch pipeline 15, a sound excitation exhaust main pipeline 16, and a gas - isolating sound - permeable diaphragm 17.

[0025] In some embodiments of the present application, the sound horn 14 is an air horn. The front end of each sound horn 14 is connected to a sound excitation air supply branch pipe 13, and the rear end is connected to a sound excitation exhaust branch pipe 15. The sound excitation air supply branch pipe 13 is connected to the sound excitation air supply main pipe 11, and the sound excitation exhaust branch pipe 15 is connected to the sound excitation exhaust main pipe 16. The high-pressure air source supplies air to one or more sound excitation exhaust branch pipes 15 through the sound excitation air supply main pipe 11, thereby driving the sound horn 14 to work. Then, the high-pressure gas flows into the sound excitation exhaust main pipe 16 along the sound excitation exhaust branch pipe 15 and is discharged. The sound frequency of the sound horn 14 on the corresponding sound excitation air supply branch pipe 13 can be adjusted through the sound excitation intake pressure regulating valve 12, so as to simulate the sound pressure level of a specific frequency.

[0026] The air isolation and sound transmission diaphragm 17 is arranged on one or more air extraction ports 35 of the compressor test piece 30 corresponding to the sound horn 14. The sound pressure level of a specific frequency emitted by the sound horn 14 can be transmitted into the air extraction cavity 34 of the compressor test piece 30 through the air isolation and sound transmission diaphragm 17, so as to apply a specific pulse characteristic frequency disturbance to the air extraction cavity 34 of the compressor test piece 30. In some embodiments of the present application, the air isolation and sound transmission diaphragm 17 can be a polytetrafluoroethylene membrane, a polyurethane membrane or a composite membrane.

[0027] The air extraction assembly 20 includes an air extraction main pipe 23, an air extraction pipe 21 and an air extraction branch pipe 22. The air extraction pipe 21 is connected to the air extraction port 35 of the compressor test piece 30, and the other end is connected to the air extraction main pipe 23 or is connected to the air extraction main pipe 23 through the air extraction branch pipe 22, so as to discharge the gas introduced from the internal flow path of the compressor into the air extraction cavity 34.

[0028] In the present application, the gas turbine inter-stage specific pulse frequency generation simulation device of the present application is described by taking two sound horns 14 and six air extraction pipes 21 in the figure as an example.

[0029] There are 8 air extraction ports 35 on the compressor test piece 30. The 8 air extraction ports 35 can be evenly distributed circumferentially or non-uniformly distributed circumferentially. Two sound horns 14 are arranged symmetrically on both sides of the compressor test piece 30 and are connected to the air extraction ports 35 through the air isolation and sound transmission diaphragms 17, and the remaining air extraction ports 35 are connected to the air extraction pipes 21.

[0030] A high-pressure gas source (not shown) provides high-pressure gas, which is connected to the main acoustic excitation gas supply pipeline 11. The high-pressure gas flows through the main acoustic excitation gas supply pipeline 11 and the branch acoustic excitation gas supply pipeline 13 to the acoustic horn 14. The high-pressure gas flow in the pipeline is adjusted by the acoustic excitation intake pressure regulating valve 12, 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 branch acoustic excitation exhaust pipeline 15 and the main acoustic excitation exhaust pipeline 16. Among them, an air isolation sound transmission diaphragm 17 is provided at the air intake port 35 corresponding to the acoustic horn 14. The branch acoustic excitation exhaust pipeline 15 is located at the front end of the air isolation sound transmission diaphragm 17 in the air flow path. The high-pressure gas passing through the acoustic horn 14 is discharged through the branch acoustic excitation exhaust pipeline 15 and the main acoustic excitation exhaust pipeline 16, while the sound pressure level generated by the acoustic horn 14 is transmitted through the air isolation sound transmission diaphragm 17 into the air intake cavity 34 of the compressor test piece 30, thereby realizing the simulation of the pulsation frequency in the engineering environment of the compressor air intake cavity.

[0031] In this application, pressure measurement points may be provided at the rear end of the acoustic horn 14 and in the air intake cavity 34 of the compressor test piece 30. The pressure in the acoustic excitation pipeline is measured through the pressure measurement point at the rear end of the acoustic horn 14, and the pressure of the air intake port 35 or the air intake cavity 34 is measured through the pressure measurement point in the air intake cavity 34, ensuring that the pressure of the air intake port 35 or the air intake cavity 34 is the same as the outlet pressure of the acoustic horn 14. In some embodiments of this application, pressure measurement can be achieved by setting pressure sensors at the positions of these pressure measurement points.

[0032] Furthermore, temperature measurement points may be provided in the air intake cavity 34 of the compressor test piece 30. The gas temperature in the air intake cavity 34 is monitored through the temperature measurement points, realizing no air flow transmission at the connection interface between the air intake cavity 34 and the acoustic excitation pipeline. In some embodiments of this application, temperature measurement can be achieved by setting thermocouples at the positions of these temperature measurement points.

[0033] The gas turbine inter-stage specific pulse frequency generation simulation device provided by this application isolates the acoustic horn 14 from the test environment, ensuring that the operating environment temperature of the acoustic horn 14 does not exceed 100°C under the condition of a relatively high test environment temperature (close to 350°C) or even higher temperature conditions. Thus, high-precision simulation of abnormal pulse frequency disturbances under complex environments (high temperature and high pressure) can be achieved, the simulation excitation of the target sound pressure level of the compressor components can be realized, and the engineering simulation of the inter-stage characteristic frequency of the gas turbine under complex test conditions such as high temperature, high pressure, and strong background noise interference can be realized.

[0034] The above is only the specific implementation manner of this application, but the protection scope of this application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in this application should be covered by the protection scope of this application. Therefore, the protection scope of this application should be subject to the protection scope of the claimed rights.

Claims

1. A simulation device for generating a specific pulsation frequency between stages of a gas turbine, characterized in that, Comprising: A sound excitation component (10), an air extraction component (20), and a compressor test piece (30), wherein: The compressor test piece (30) has an air extraction cavity (34) and a plurality of air extraction ports (35) communicating with the air extraction cavity (34); The sound excitation component (10) includes a main sound excitation air supply pipeline (11), a sound excitation air intake pressure regulating valve (12), a sound excitation air supply branch pipeline (13), a sound horn (14), a sound excitation exhaust branch pipeline (15), a sound excitation exhaust main pipeline (16), and an air isolation and sound transmission diaphragm (17). The front end and the rear end of the sound horn (14) are respectively connected to the sound excitation air supply branch pipeline (13) and the sound excitation exhaust branch pipeline (15). The sound excitation air supply branch pipeline (13) is connected to the main sound excitation air supply pipeline (11), and the sound excitation exhaust branch pipeline (15) is connected to the sound excitation exhaust main pipeline (16). The sound excitation air intake pressure regulating valve (12) is arranged on the sound excitation air supply branch pipeline (13). High-pressure gas is introduced through the main sound excitation air supply pipeline (11). The high-pressure gas flows along the sound excitation air supply branch pipeline (13) towards the sound horn (14). The sound pressure level of a predetermined pulse frequency is generated by the sound horn (14) through the adjustment of the sound excitation air intake pressure regulating valve (12). Then, the high-pressure gas is discharged along the sound excitation exhaust branch pipeline (15) and the sound excitation exhaust main pipeline (16). The sound horn (14) is connected to the air extraction port (35), and the air isolation and sound transmission diaphragm (17) is arranged on the air extraction port (35) corresponding to the sound horn (14); The air extraction component (20) includes a plurality of air extraction pipes (21), and the air extraction pipes (21) are arranged on the air extraction ports (35) where the sound horn (14) is not installed.

2. The simulation device for generating a specific pulsation frequency between stages of a gas turbine according to claim 1, wherein, The compressor test piece (30) includes an inner casing (31), an outer casing (32), and an air extraction ring (33). A compressor internal flow path is formed between the inner casing (31), the outer casing (32), and the air extraction ring (33). High-temperature and high-pressure gas is introduced into the compressor internal flow path; One end of the air extraction ring (33) is fixedly connected to the outer casing (32), so as to form an air extraction cavity (34) between the air extraction ring (33) and the outer casing (32). A gap is provided between the other end of the air extraction ring (33) and the outer casing (32), and the gap forms an annular groove. The gas in the compressor internal flow path can enter the air extraction cavity (34) along the annular groove; A plurality of air extraction ports (35) are provided on the outer casing (32), and the air extraction ports (35) communicate with the air extraction cavity (34).

3. The simulation device for generating a specific pulsation frequency between stages of a gas turbine according to claim 2, characterized in that, The temperature of the high-temperature and high-pressure gas is not lower than 350 °C.

4. The simulation device for generating specific pulsation frequencies between stages of a gas turbine according to claim 3, characterized in that, The sound horn (14) is an air horn.

5. The simulation device for generating a specific pulsation frequency between stages of a gas turbine as claimed in claim 4, characterized in that, The air extraction component (20) further includes an air extraction main pipe (23). The air extraction pipes (21) are connected to the air extraction main pipe (23). The high-temperature and high-pressure gas in the air extraction cavity (34) is discharged after converging into the air extraction main pipe (23) through the air extraction pipes (21).

6. The simulation device for generating a specific pulsation frequency between stages of a gas turbine as claimed in claim 5, wherein, The air extraction assembly (20) further includes an air extraction branch pipe (22), the air extraction pipe (21) is connected to the air extraction branch pipe (22), and the high-temperature and high-pressure gas in the air extraction cavity (34) is discharged after converging into the main air extraction pipe (23) through the air extraction pipe (21) and the air extraction branch pipe (22).

7. The simulation device for generating a specific pulsation frequency between stages of a gas turbine as described in claim 1, wherein, The air isolation and sound transmission diaphragm (17) is a polytetrafluoroethylene film, a polyurethane film or a composite film.

8. The simulation device for generating specific pulsation frequencies between stages of a gas turbine according to claim 1, wherein It further includes a pressure measurement point, and the pressure measurement point is arranged at the rear end of the sound horn (14) and the air extraction cavity (34), so that the pressure at the rear end of the sound horn (14) is the same as that of the air extraction cavity (34) through the pressure measurement point.

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