A device and method for testing the noise reduction performance of an acoustic liner in an aeroengine

Abstract

The application belongs to the technical field of testing the performance of aero-engine acoustic liner noise reduction, and particularly relates to an aero-engine acoustic liner noise reduction performance testing device and method. The device is designed to adjust the connection sequence of each module section, and replace the light plate contrast part and the acoustic liner sample. The device has a downstream noise reduction performance comparison test state, a downstream noise reduction performance test state, an upstream noise reduction performance comparison test state, and an upstream noise reduction performance test state. The device can measure the downstream noise reduction performance and the upstream noise reduction performance of the acoustic liner. The device can further adjust the frequency and sound pressure level of the noise through two noise sources, and adjust the air flow speed through the fan. The device can calculate the corresponding downstream noise reduction performance and upstream noise reduction performance of the acoustic liner. The device can replace the acoustic liner sample with different structural parameters to calculate the corresponding downstream noise reduction performance and upstream noise reduction performance of the acoustic liner. The device can efficiently construct a database of acoustic liner structural parameters and corresponding noise reduction performance.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of testing the noise reduction performance of acoustic liners in an aero-engine, and particularly relates to a device and method for testing the noise reduction performance of acoustic liners in an aero-engine. BACKGROUND

[0002] In an aero-engine, acoustic liners are used for noise reduction, and acoustic liners are usually arranged before a fan, after the fan, and in a nacelle. Currently, the noise reduction performance of acoustic liners is verified by testing an entire engine or a component in an anechoic chamber, which has a long test cycle, high cost, time-consuming, and labor-intensive, and it is difficult to effectively build a database of acoustic liner structure parameters and corresponding noise reduction performance, and it is unable to provide database support for the design of acoustic liners.

[0003] The present application is proposed in view of the above technical defects.

[0004] It should be noted that the disclosure of the above background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present patent application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0005] The purpose of the present application is to provide a device and method for testing the noise reduction performance of acoustic liners in an aero-engine to overcome or alleviate at least one aspect of the known technical defects.

[0006] The technical solution of the present application is:

[0007] In one aspect, a device for testing the noise reduction performance of acoustic liners in an aero-engine is provided, comprising a high-Mach air source section, a front conventional muffler section, an intermediate expansion muffler section, a rear conventional muffler section, an upstream noise measurement section, a test installation section, a downstream noise measurement section, an exhaust section, a light plate comparison piece, and an acoustic liner sample.

[0008] Among them,

[0009] The high-Mach air source section has a built-in fan.

[0010] The upstream noise measurement section has two noise sources and two upstream noise monitors arranged thereon.

[0011] The test installation section has a plurality of flow rate measuring devices arranged thereon and a test installation opening.

[0012] The downstream noise measurement section has two downstream noise monitors arranged thereon.

[0013] The acoustic liner sample is in the form of a plate.

[0014] The device for testing the noise reduction performance of acoustic liners in an aero-engine has:

[0015] The upstream noise monitor is close to the test installation section compared with the noise source; the light plate comparison piece is connected to the test installation section and blocked in the test installation port;

[0016] The upstream noise monitor is close to the test installation section compared with the noise source; the light plate comparison piece is connected to the test installation section and blocked in the test installation port;

[0017] The upstream noise monitor is close to the test installation section compared with the noise source; the light plate comparison piece is connected to the test installation section and blocked in the test installation port;

[0018] The upstream noise monitor is close to the test installation section compared with the noise source; the light plate comparison piece is connected to the test installation section and blocked in the test installation port;

[0019] According to at least one embodiment of the present application, the above-mentioned acoustic lining noise reduction performance test device of the aero-engine, the cross sections of the high Mach air source section, the front conventional muffler section, the intermediate expansion muffler section, the rear conventional muffler section, the upstream noise measurement section, the test installation section, the downstream noise measurement section and the exhaust section are rectangular;

[0020] Each flow rate measurer is located on the side wall opposite to the test installation port on the test installation section;

[0021] The two noise sources and the two upstream noise monitors are located on the upstream noise measurement section corresponding to the direction side wall and the opposite direction side wall of the test installation port;

[0022] The two downstream noise monitors are located on the downstream noise measurement section corresponding to the direction side wall and the opposite direction side wall of the test installation port.

[0023] According to at least one embodiment of the present application, the abovementioned aircraft engine in-sound liner noise reduction performance testing device, the abutment between the high Mach air source section, the front conventional muffler section, the intermediate expansion muffler section, the rear conventional muffler section, the upstream noise measurement section, the test mounting section, the downstream noise measurement section, and the exhaust section is specifically bolted with the annular connecting edge.

[0024] According to at least one embodiment of the present application, the abovementioned aircraft engine in-sound liner noise reduction performance testing device, the light plate comparison piece is bolted on the test mounting section with the annular connecting edge and inserted into the test mounting port with the protruding part to block the test mounting port.

[0025] According to at least one embodiment of the present application, the abovementioned aircraft engine in-sound liner noise reduction performance testing device further comprises:

[0026] a shell with two open ends and an inner wall having two positioning holes; and

[0027] two clamping blocks arranged at the two positioning holes;

[0028] two screws threadedly connected to the shell to clamp the two clamping blocks and clamp the sound liner sample from both ends;

[0029] a cover plate bolted to the other end of the shell to block the end of the shell;

[0030] The sound liner sample is bolted on the test mounting section with the annular connecting edge of the shell and inserted into the test mounting port with the protruding part to block the test mounting port.

[0031] On the other hand, a method for testing the noise reduction performance of an in-sound liner of an aircraft engine is provided, comprising:

[0032] setting the aircraft engine in-sound liner noise reduction performance testing device in a downstream noise reduction performance comparison testing state, and calculating the noise reduction data when there is no sound liner in the downstream based on the measurement data of the upstream noise monitor and the downstream noise monitor;

[0033] setting the aircraft engine in-sound liner noise reduction performance testing device in a downstream noise reduction performance comparison testing state, and calculating the noise reduction data when there is a sound liner in the downstream based on the measurement data of the upstream noise monitor and the downstream noise monitor;

[0034] calculating the downstream noise reduction performance of the sound liner based on the noise reduction data when there is no sound liner in the downstream and the noise reduction data when there is a sound liner in the downstream;

[0035] The device for testing the noise reduction performance of the sound lining in the aero-engine is set in the counter-flow noise reduction performance comparison test state, the measurement data of the upstream noise monitor and the downstream noise monitor are used, and the noise reduction data of the counter-flow without sound lining is calculated;

[0036] The device for testing the noise reduction performance of the sound lining in the aero-engine is set in the counter-flow noise reduction performance comparison test state, the measurement data of the upstream noise monitor and the downstream noise monitor are used, and the noise reduction data of the counter-flow without sound lining is calculated;

[0037] The counter-flow noise reduction performance of the sound lining is calculated by using the noise reduction data of the counter-flow without sound lining and the noise reduction data of the counter-flow with sound lining.

[0038] The corresponding counter-flow noise reduction performance and counter-flow noise reduction performance of the sound lining are calculated by adjusting the frequency and sound pressure level of the noise through two noise sources.

[0039] The corresponding counter-flow noise reduction performance and counter-flow noise reduction performance of the sound lining are calculated by adjusting the airflow speed through the fan.

[0040] The counter-flow noise reduction performance and counter-flow noise reduction performance of the corresponding sound lining are calculated by replacing the sound lining samples with different structural parameters.

[0041] The application has at least the following beneficial technical effects:

[0042] The device and method for testing the noise reduction performance of the sound lining in the aero-engine are provided, the design adjusts the connection sequence of each module segment, and the light plate comparison piece and the sound lining sample are replaced, the device has the counter-flow noise reduction performance comparison test state, the counter-flow noise reduction performance test state, the counter-flow noise reduction performance comparison test state, and the counter-flow noise reduction performance test state, so as to realize the measurement of the counter-flow noise reduction performance and the counter-flow noise reduction performance of the sound lining, and further calculate the corresponding counter-flow noise reduction performance and counter-flow noise reduction performance of the sound lining by adjusting the frequency and sound pressure level of the noise through two noise sources, adjusting the airflow speed through the fan, and replacing the sound lining samples with different structural parameters, so as to efficiently construct the database of the sound lining structural parameters and the corresponding noise reduction performance, and provide the database support for the design of the sound lining. BRIEF DESCRIPTION OF DRAWINGS

[0043] Figure 1 is a schematic diagram of the device for testing the noise reduction performance of the sound lining in the aero-engine in the counter-flow noise reduction performance comparison test state provided by the embodiment of the application;

[0044] Figure 2 is a schematic diagram of the device for testing the noise reduction performance of the sound lining in the aero-engine in the counter-flow noise reduction performance test state provided by the embodiment of the application;

[0045] Figure 3is a schematic diagram of the aero-engine sound lining noise reduction performance testing device in a counter-flow noise reduction performance comparison testing state provided by the embodiment of the present application;

[0046] Figure 4 is a schematic diagram of the aero-engine sound lining noise reduction performance testing device in a counter-flow noise reduction performance testing state provided by the embodiment of the present application;

[0047] Figure 5 is an assembly schematic diagram of partial components of the aero-engine sound lining noise reduction performance testing device provided by the embodiment of the present application;

[0048] Figure 6 is a schematic diagram of frequency domain noise reduction performance comparison of sound lining patterns S1-S6 at 0.3Ma provided by the embodiment of the present application;

[0049] Figure 7 is a schematic diagram of frequency domain noise reduction performance comparison of sound lining pattern S2 at 0.3-0.8Ma provided by the embodiment of the present application;

[0050] wherein:

[0051] 1-high Mach air source section; 2-previous conventional muffler section; 3-intermediate expansion muffler section; 4-later conventional muffler section; 5-upstream noise measurement section; 6-test installation section; 7-downstream noise measurement section; 8-exhaust section; 9-light plate comparison piece; 10-sound lining sample; 11-fan; 12-noise source; 13-upstream noise monitor; 14-flow rate measurer; 15-downstream noise monitor; 16-housing; 17-clamp block; 18-rotary knob; 19-cover plate.

[0052] In order to better illustrate the embodiments, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual product size. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the patent. DETAILED DESCRIPTION

[0053] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further clearly and completely described in combination with the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, which are used to explain the present application, but not to limit the present application. It should be noted that, in order to facilitate description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0054] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the present application shall be understood as the general meaning understood by those of ordinary skill in the art to which the present application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like used in the description of the present application only indicate relative directions or positional relationships, and are not intended to imply that the device or element must have a particular orientation, be constructed and operated in a particular orientation, and the relative positional relationship thereof can also be changed accordingly when the absolute position of the described object is changed, therefore it cannot be understood as a limitation on the present application. The "first", "second", "third" and the like used in the description of the present application are only for the purpose of description, in order to distinguish different components, and cannot be understood as indicating or implying relative importance. The "one", "an" or "the" and the like used in the description of the present application should not be understood as an absolute limitation on the quantity, but should be understood as the presence of at least one. The "includes" or "contains" and the like used in the description of the present application means that the elements or objects appearing before the word are encompassed by the elements or objects listed after the word and their equivalents, without excluding other elements or objects.

[0055] In addition, it should be further pointed out that, unless otherwise explicitly specified and limited, the "installation", "connection", "connection" and the like used in the description of the present application should be understood in a broad sense, for example, the connection can be a fixed connection, or a detachable connection, or an integral connection; can be a mechanical connection, or an electrical connection; can be directly connected, or indirectly connected through an intermediate medium, or the internal communication of two elements, those skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0056] The test of acoustic liner noise reduction in the aero-engine mainly includes two steps, first, the noise reduction data without acoustic liner is tested, second, the noise reduction data with acoustic liner is measured, the difference between the two noise reduction data is calculated to obtain the noise reduction performance of acoustic liner. The structural parameters related to the noise reduction performance of acoustic liner mainly include perforation rate, hole diameter, honeycomb thickness and single or double degree of freedom, etc.

[0057] The factors affecting the noise reduction performance of acoustic liner in the aero-engine mainly include noise frequency, noise sound pressure level, airflow velocity, airflow direction. According to the airflow direction, the noise reduction performance of acoustic liner can be divided into "downstream noise reduction performance" and "upstream noise reduction performance". The downstream noise reduction performance is for the noise reduction performance of acoustic liner in the nacelle and acoustic liner behind the fan, that is, the noise reduction performance of acoustic liner under the condition that the noise propagation direction is the same as the airflow direction. The upstream noise reduction performance is for the noise reduction performance of acoustic liner in front of the fan, that is, the noise reduction performance of acoustic liner under the condition that the noise propagation direction is opposite to the airflow direction.

[0058] According to the above description, the following will be described in combination with the accompanying drawings Figures 1 to 7This application will be described in further detail.

[0059] On the one hand, a test device for the noise reduction performance of acoustic liner in aero-engine is provided, including a high Mach gas source section 1, a front conventional muffler section 2, an intermediate expansion muffler section 3, a rear conventional muffler section 4, an upstream noise measurement section 5, a test installation section 6, a downstream noise measurement section 7, an exhaust section 8, a bare plate comparison piece 9, and an acoustic liner sample 10.

[0060] in,

[0061] High Mach air source section 1, with built-in fan 11;

[0062] Upstream noise measurement section 5, on which two noise sources 12 and two upstream noise monitors 13 are installed;

[0063] The test installation section 6 is equipped with multiple flow velocity measuring devices 14 and has a test installation port.

[0064] Downstream noise measurement section 7, on which two downstream noise monitors 15 are installed;

[0065] The acoustic liner sample 10 is plate-shaped;

[0066] The aforementioned acoustic liner noise reduction performance testing device for aero-engines has the following features:

[0067] The performance comparison test of downstream noise reduction, such as... Figure 1 As shown, the high Mach gas source section 1, the front conventional muffler section 2, the intermediate expansion muffler section 3, the rear conventional muffler section 4, the upstream noise measurement section 5, the test installation section 6, the downstream noise measurement section 7, and the exhaust section 8 are connected in sequence; the upstream noise monitor 13 is closer to the test installation section 6 than the noise source 12; the light plate comparison piece 9 is connected to the test installation section 6 and sealed in the test installation port;

[0068] The downstream noise reduction performance test status, such as... Figure 2 As shown, the high Mach gas source section 1, the front conventional muffler section 2, the intermediate expansion muffler section 3, the rear conventional muffler section 4, the upstream noise measurement section 5, the test installation section 6, the downstream noise measurement section 7, and the exhaust section 8 are connected in sequence; the upstream noise monitor 13 is closer to the test installation section 6 than the noise source 12; the acoustic liner sample 10 is connected to the test installation section 6 and sealed in the test installation opening; the only difference between the downstream noise reduction performance test state and the downstream noise reduction performance comparison test state is that the bare plate comparison piece 9 is replaced with the acoustic liner sample 10;

[0069] The performance comparison test status of reverse flow noise reduction, such as... Figure 3As shown, the high Mach air source section 1, the front conventional muffler section 2, the intermediate expansion muffler section 3, the rear conventional muffler section 4, the downstream noise measurement section 7, the test installation section 6, the upstream noise measurement section 5, and the exhaust section 8 are sequentially connected; the upstream noise monitor 13 is closer to the test installation section 6 than the noise source 12; the light plate comparison piece 9 is connected to the test installation section 6 and blocked in the test installation opening; the counter-flow noise reduction performance comparison test state is only a change in the positions of the downstream noise measurement section 7 and the upstream noise measurement section 5 compared with the normal-flow noise reduction performance comparison test state;

[0070] The counter-flow noise reduction performance test state is as shown in FIG. 4. Figure 4 As shown, the high Mach air source section 1, the front conventional muffler section 2, the intermediate expansion muffler section 3, the rear conventional muffler section 4, the downstream noise measurement section 7, the test installation section 6, the upstream noise measurement section 5, and the exhaust section 8 are sequentially connected; the upstream noise monitor 13 is closer to the test installation section 6 than the noise source 12; the light plate comparison piece 9 is connected to the test installation section 6 and blocked in the test installation opening; the counter-flow noise reduction performance comparison test state is only a change in the positions of the downstream noise measurement section 7 and the upstream noise measurement section 5 compared with the normal-flow noise reduction performance comparison test state.

[0071] The above-mentioned embodiment discloses an aero-engine sound lining noise reduction performance testing device, which can be tested for sound lining noise reduction performance by referring to the following steps:

[0072] The aero-engine sound lining noise reduction performance testing device is set in the normal-flow noise reduction performance comparison test state, and the measured data of the upstream noise monitor 13 and the downstream noise monitor 15 are used to calculate the noise reduction data when there is no sound lining in the normal flow, which is the transmission loss, i.e., the attenuation amount of sound waves in the propagation process when there is no sound reduction measure in the sound wave propagation in the pipeline.

[0073] The aero-engine sound lining noise reduction performance testing device is set in the normal-flow noise reduction performance comparison test state, and the measured data of the upstream noise monitor 13 and the downstream noise monitor 15 are used to calculate the noise reduction data when there is sound lining in the normal flow, which is the insertion loss, i.e., the attenuation amount of sound waves in the propagation process when there is sound reduction measure in the sound wave propagation in the pipeline.

[0074] The normal-flow noise reduction performance of the sound lining is calculated based on the noise reduction data when there is no sound lining in the normal flow and the noise reduction data when there is sound lining in the normal flow.

[0075] The aero-engine sound lining noise reduction performance testing device is set in the counter-flow noise reduction performance comparison test state, and the measured data of the upstream noise monitor 13 and the downstream noise monitor 15 are used to calculate the noise reduction data when there is no sound lining in the counter flow.

[0076] The device for testing the noise reduction performance of the sound lining in the aero-engine is set in the reverse flow noise reduction performance test state, and the noise reduction data of the reverse flow with the sound lining is calculated by using the measurement data of the upstream noise monitor 13 and the downstream noise monitor 15.

[0077] The reverse flow noise reduction performance of the sound lining is calculated by using the noise reduction data of the reverse flow without the sound lining and the noise reduction data of the reverse flow with the sound lining.

[0078] The corresponding mufflers are arranged in the front conventional muffler section 2, the middle expansion muffler section 3 and the rear conventional muffler section 4, and the airflow generated by the high Mach air source section 1 can be effectively silenced by the coupling effect among the three sections in the sound lining noise reduction performance test process, so that the airflow only becomes the carrier of the noise generated by the noise source 12, and the accuracy of the test is ensured.

[0079] For the device for testing the noise reduction performance of the sound lining in the aero-engine disclosed in the above embodiment, those skilled in the art can understand that the design has the following states by adjusting the connection order of each module section and replacing the light plate comparison piece 9 and the sound lining sample 10: the parallel flow noise reduction performance comparison test state, the parallel flow noise reduction performance test state, the reverse flow noise reduction performance comparison test state and the reverse flow noise reduction performance test state. Thus, the parallel flow noise reduction performance and the reverse flow noise reduction performance of the sound lining can be measured, and the corresponding parallel flow noise reduction performance and reverse flow noise reduction performance of the sound lining can be calculated by adjusting the frequency and sound pressure level of the noise through the two noise sources 12 and adjusting the airflow speed through the fan 11. Furthermore, the parallel flow noise reduction performance and reverse flow noise reduction performance of the sound lining with different structural parameters can be calculated by replacing the sound lining sample 10, so that the database of the structural parameters of the sound lining and the corresponding noise reduction performance can be efficiently constructed, and the database support for the design of the sound lining can be provided.

[0080] In some optional embodiments, the cross sections of the high Mach air source section 1, the front conventional muffler section 2, the middle expansion muffler section 3, the rear conventional muffler section 4, the upstream noise measurement section 5, the test installation section 6, the downstream noise measurement section 7 and the exhaust section 8 are rectangular.

[0081] Each flow rate measurer 14 is located on the side wall opposite to the test installation port of the test installation section 6.

[0082] The two noise sources 12 and the two upstream noise monitors 13 are located on the upstream noise measurement section 5 corresponding to the direction side wall and the opposite direction side wall of the test installation port.

[0083] The two downstream noise monitors 15 are located on the downstream noise measurement section 7 corresponding to the direction side wall and the opposite direction side wall of the test installation port.

[0084] In some alternative embodiments, the above-mentioned aero-engine in-sound liner noise reduction performance test device, the high Mach number air source section 1, the front conventional muffler section 2, the intermediate expansion muffler section 3, the rear conventional muffler section 4, the upstream noise measurement section 5, the test installation section 6, the downstream noise measurement section 7, and the exhaust section 8 have the same radial size, and both ends are designed as standard interfaces to facilitate adjustment of the connection sequence, and the interfaces are connected, which can be connected by bolts using the annular connection edge and positioned by the stop.

[0085] In some alternative embodiments, the above-mentioned aero-engine in-sound liner noise reduction performance test device, the light plate comparison piece 9 is connected to the test installation section 6 and blocked in the test installation port, which is bolted to the test installation section 6 using the annular connection edge and blocked in the test installation port by extending the protruding part into the test installation port.

[0086] In some alternative embodiments, the above-mentioned aero-engine in-sound liner noise reduction performance test device further comprises:

[0087] The shell 16 is open at both ends, and the inner wall has two positioning holes; the sound liner sample 10 is arranged at one end of the shell 16;

[0088] Two clamping blocks 17 are arranged at the two positioning holes;

[0089] Two screws 18 are threadedly connected to the shell 16 and clamp the two clamping blocks 17, thereby clamping the sound liner sample 10 from both ends;

[0090] The cover plate 19 is connected to the other end of the shell 16 by screws to block the end of the shell 16;

[0091] The sound liner sample 10 is connected to the test installation section 6 and blocked in the test installation port, which is bolted to the test installation section 6 using the annular connection edge of the shell 16, and the end where the sound liner sample 10 is arranged is extended into the test installation port to block the test installation port, as shown in Figure 5 .

[0092] For the above-mentioned aero-engine in-sound liner noise reduction performance test device, those skilled in the art can understand that the sound liner sample 10 is fixed to one end of the shell 16 by the two screws 18 and the two clamping blocks 17, which does not damage the sound liner sample 10, and provides installation allowance for sound liner samples 10 of different thicknesses, which facilitates replacement of the sound liner sample 10, and the cover plate 19 is connected to the other end of the shell 16 by screws to block the shell 16, and the shell 16 is bolted to the test installation section 6 using the annular connection edge, and the end where the sound liner sample 10 is arranged is extended into the test installation port to block the test installation port, which can restore the working environment of the sound liner in the aero-engine and ensure the accuracy of the measurement results.

[0093] The method comprises the following steps:

[0094] The method comprises the following steps:

[0095] The method comprises the following steps:

[0096] The method comprises the following steps:

[0097] The method comprises the following steps:

[0098] The method comprises the following steps:

[0099] The method comprises the following steps:

[0100] The method comprises the following steps:

[0101] The method comprises the following steps:

[0102] The method comprises the following steps:

[0103] The method comprises the following steps:

[0104] In one specific embodiment, the sound lining patterns S1-S6 with different structural parameters are tested for the performance of downflow noise reduction at a 0.3 Mach airflow speed:

[0105] First, the noise reduction data measurement is performed for the downflow without sound lining at a 0.3 Mach airflow speed, and the noise reduction data P WS1, P WS2, P WS3, P WS4, P WS5, P WS6 for the downflow without sound lining are obtained.

[0106] Second, the noise reduction data measurement is performed for the downflow with sound lining at a 0.3 Mach airflow speed, and the noise reduction data P S1, P S2, P S3, P S4, P S5, P S6 for the downflow with sound lining are obtained.

[0107] The downflow noise reduction performance of the sound lining pattern S1 is calculated by P S1-P WS1, …, the downflow noise reduction performance of the sound lining pattern S6 is calculated by P S6-P WS6, and the downflow noise reduction performance of the sound lining patterns S1-S6 at 0.3 Ma is compared as shown in Figure 7 .

[0108] In another specific embodiment, the sound lining pattern S2 is tested for the performance of downflow noise reduction at 0.3, 0.4, 0.5, 0.6, 0.7, 0.8 Mach airflow speed:

[0109] First, the noise reduction data measurement is performed for the downflow without sound lining at 0.3-0.8 Mach airflow speed, and the noise reduction data P WM1, P WM2, P WM3, PWM4, P WM5, P WM6 for the downflow without sound lining are obtained.

[0110] Second, the noise reduction data measurement is performed for the downflow with sound lining at 0.3-0.8 Mach airflow speed, and the noise reduction data P M1, P M2, P M3, P M4, P M5, P M6 for the downflow with sound lining are obtained.

[0111] The downflow noise reduction performance of the sound lining pattern S2 at 0.3 Mach airflow speed is calculated by P M1- P WM1, …, the downflow noise reduction performance of the sound lining pattern S2 at 0.8 Mach airflow speed is calculated by P M6- P WM6, and the downflow noise reduction performance of the sound lining pattern S2 at 0.3-0.8 Ma is compared as shown in Figure 7 .

[0112] The embodiments in the specification are described in a progressive manner, and each embodiment focuses on the difference from other embodiments. The same or similar parts of each embodiment can be referred to each other.

[0113] The technical scheme of the present application has been described in combination with the preferred embodiments shown in the drawings, and it should be understood by those skilled in the art that the protection scope of the present application is obviously not limited to these specific embodiments, and those skilled in the art can make equivalent changes or replacements to the related technical features without departing from the principles of the present application, and the technical schemes after the changes or replacements will fall within the protection scope of the present application.

Claims

1. An apparatus for testing the acoustic liner noise reduction performance in an aeroengine, characterized in that, It comprises a high Mach air source section (1), a front conventional muffler section (2), an intermediate expansion muffler section (3), a rear conventional muffler section (4), an upstream noise measurement section (5), a test installation section (6), a downstream noise measurement section (7), an exhaust section (8), a light plate comparison piece (9), and an acoustic lining sample (10); Wherein, The high Mach air source section (1) is internally provided with a fan (11); The upstream noise measurement section (5) is provided with two noise sources (12) and two upstream noise monitors (13) thereon; The test installation section (6) is provided with a plurality of flow rate measuring devices (14) and a test installation opening; The downstream noise measurement section (7) is provided with two downstream noise monitors (15) thereon; The acoustic lining sample (10) is in the form of a plate; The aviation engine acoustic lining noise reduction performance testing device has: In the downstream noise reduction performance test state, the high Mach air source section (1), the front conventional muffler section (2), the intermediate expansion muffler section (3), the rear conventional muffler section (4), the downstream noise measurement section (7), the test installation section (6), the upstream noise measurement section (5), and the exhaust section (8) are sequentially connected; the upstream noise monitor (13) is closer to the test installation section (6) than the noise source (12); the light plate comparison piece (9) is connected to the test installation section (6) and blocked in the test installation opening; In the downstream noise reduction performance test state, the high Mach air source section (1), the front conventional muffler section (2), the intermediate expansion muffler section (3), the rear conventional muffler section (4), the downstream noise measurement section (7), the test installation section (6), the upstream noise measurement section (5), and the exhaust section (8) are sequentially connected; the upstream noise monitor (13) is closer to the test installation section (6) than the noise source (12); the light plate comparison piece (9) is connected to the test installation section (6) and blocked in the test installation opening; In the downstream noise reduction performance test state, the high Mach air source section (1), the front conventional muffler section (2), the intermediate expansion muffler section (3), the rear conventional muffler section (4), the downstream noise measurement section (7), the test installation section (6), the upstream noise measurement section (5), and the exhaust section (8) are sequentially connected; the upstream noise monitor (13) is closer to the test installation section (6) than the noise source (12); the light plate comparison piece (9) is connected to the test installation section (6) and blocked in the test installation opening; In the downstream noise reduction performance test state, the high Mach air source section (1), the front conventional muffler section (2), the intermediate expansion muffler section (3), the rear conventional muffler section (4), the downstream noise measurement section (7), the test installation section (6), the upstream noise measurement section (5), and the exhaust section (8) are sequentially connected; the upstream noise monitor (13) is closer to the test installation section (6) than the noise source (12); the light plate comparison piece (9) is connected to the test installation section (6) and blocked in the test installation opening.

2. The aviation engine acoustic lining noise reduction performance testing device according to claim 1, characterized in that, The cross sections of the high Mach air source section (1), the front conventional muffler section (2), the intermediate expansion muffler section (3), the rear conventional muffler section (4), the upstream noise measurement section (5), the test installation section (6), the downstream noise measurement section (7) and the exhaust section (8) are rectangular; Each flow rate measurer (14) is located on the side wall opposite to the test installation port on the test installation section (6); The two noise sources (12) and the two upstream noise monitors (13) are located on the upstream noise measurement section (5) on the side wall corresponding to the direction of the test installation port and the opposite side wall thereof; The two downstream noise monitors (15) are located on the downstream noise measurement section (7) on the side wall corresponding to the direction of the test installation port and the opposite side wall thereof.

3. The device for testing the noise reduction performance of an aeroengine mid-frequency sound liner according to claim 2, wherein the high Mach air source section (1), the front conventional muffler section (2), the intermediate expansion muffler section (3), the rear conventional muffler section (4), the upstream noise measurement section (5), the test installation section (6), the downstream noise measurement section (7) and the exhaust section (8) are connected through annular connecting edges by bolts.

4. The device for testing the noise reduction performance of an aeroengine mid-frequency sound liner according to claim 3, wherein the light plate contrast piece (9) is connected to the test installation section (6) by bolts through the annular connecting edges and extends into the test installation port through the protruding part to block the test installation port.

5. The device for testing the noise reduction performance of an aeroengine mid-frequency sound liner according to claim 4, further comprising: a shell (16) with two ends open and two positioning holes in the inner wall, and the sound liner sample (10) is arranged in one end of the shell (16); two clamping blocks (17) arranged at the two positioning holes; two knobs (18) threadedly connected to the shell (16) to clamp the two clamping blocks (17) and clamp the sound liner sample (10) from both ends; a cover plate (19) connected to the other end of the shell (16) by a screw to block the end of the shell (16); the sound liner sample (10) is connected to the test installation section (6) by bolts through the annular connecting edges of the shell (16) and extends into the test installation port to block the test installation port. comprising: setting the device for testing the noise reduction performance of an aeroengine mid-frequency sound liner in a downstream noise reduction performance comparison test state, and calculating the downstream noise reduction data without a sound liner by using the measurement data of the upstream noise monitor (13) and the downstream noise monitor (15); setting the device for testing the noise reduction performance of an aeroengine mid-frequency sound liner in a downstream noise reduction performance comparison test state, and calculating the downstream noise reduction data with a sound liner by using the measurement data of the upstream noise monitor (13) and the downstream noise monitor (15); 6. A method for testing the noise reduction performance of an acoustic liner in an aeroengine, implemented on the basis of the device for testing the noise reduction performance of an acoustic liner in an aeroengine according to claim 5, characterized in that, calculating the downstream noise reduction performance of the sound liner by using the downstream noise reduction data without a sound liner and the downstream noise reduction data with a sound liner. ​ ​ ​ Setting the aero-engine mid-frequency sound liner noise reduction performance test device in the counter-flow noise reduction performance comparison test state, using the measurement data of the upstream noise monitor (13) and the downstream noise monitor (15), the noise reduction data of the counter-flow without sound liner is calculated; Setting the aero-engine mid-frequency sound liner noise reduction performance test device in the counter-flow noise reduction performance comparison test state, using the measurement data of the upstream noise monitor (13) and the downstream noise monitor (15), the noise reduction data of the counter-flow with sound liner is calculated; With the noise reduction data of the counter-flow without sound liner and the noise reduction data of the counter-flow with sound liner, the counter-flow noise reduction performance of the sound liner is calculated; Through the two noise sources (12), the frequency and sound pressure level of the noise are adjusted, and the corresponding counter-flow noise reduction performance and counter-flow noise reduction performance of the sound liner are calculated; Through the fan (11), the air flow speed is adjusted, and the corresponding counter-flow noise reduction performance and counter-flow noise reduction performance of the sound liner are calculated; By replacing the sound liner sample (10) with different structural parameters, the corresponding counter-flow noise reduction performance and counter-flow noise reduction performance of the sound liner are calculated.

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