CN214748872U - Fan pipeline sound mode simulation device under incoming flow condition - Google Patents
Fan pipeline sound mode simulation device under incoming flow condition Download PDFInfo
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- CN214748872U CN214748872U CN202120982077.9U CN202120982077U CN214748872U CN 214748872 U CN214748872 U CN 214748872U CN 202120982077 U CN202120982077 U CN 202120982077U CN 214748872 U CN214748872 U CN 214748872U
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Abstract
A fan pipeline sound mode simulation device under the condition of incoming flow comprises an engine simplified model, loudspeakers, a sound lining installation area, a fairing, microphones, a nacelle shell, a wing section support sheet, a sound production control system and a PXi acquisition system, wherein the engine simplified model is connected with the nacelle shell through the wing section support sheet; the invention simulates the fan noise by using the electroacoustic source signal, thereby meeting the measurement requirement of fan forward noise under the current-carrying condition and measuring the noise reduction performance of the acoustic liner under different wind speeds. Compared with the traditional flow tube testing method, the method is closer to practical application, and the testing efficiency is improved.
Description
Technical Field
The utility model belongs to the technical field of the noise measurement, concretely relates to there is fan pipeline sound modal simulation device under the incoming flow condition.
Background
When the noise reduction of the fan noise of the aircraft engine is researched, it is important to research how to measure the mode of the fan noise transmitted from the front of the engine. At present, most of common measurement pipeline acoustic modal devices at home and abroad are under the acoustic theoretical research in a no-incoming-flow state, and mostly adopt a cylindrical pipeline structure, so that the comprehensive consideration of pneumatics and acoustics is lacked.
In the prior art, a method for measuring the acoustic mode of an engine pipeline generally adopts that an annular pipeline device is arranged at an inlet and an outlet of the engine pipeline, and an anechoic chamber test is performed on the center of an engine, or a motor-driven engine model is used for scanning rake sensor measurement in an anechoic chamber. For the above methods, there are interference flow effects or unnecessary noise sources added when testing under the condition of incoming flow. Therefore, a technical scheme is needed to be suitable for wind tunnel tests and measure the acoustic modal parameters of the pipeline of the nacelle structure.
SUMMERY OF THE UTILITY MODEL
Give above weak point, the utility model provides a there is fan pipeline sound mode analogue means under the incoming flow condition, utilize electroacoustic source signal simulation fan noise to satisfy and bring fan foreward pass noise measurement demand under the condition of flowing, measure the performance of making an uproar of falling of sound lining under the different wind speeds.
The utility model discloses the technical scheme who adopts: a fan pipeline sound mode simulation device under the condition of incoming flow comprises an engine simplified model, a loudspeaker, a sound lining installation area, a fairing, a microphone, a nacelle shell, a wing type support sheet, a sound production control system and a PXi acquisition system, wherein the PXi acquisition system is in electric signal connection with a plurality of microphones, the sound production control system is in electric signal connection with the loudspeaker,
the engine simplified model is connected with a nacelle shell through a wing type supporting sheet, the nacelle shell is connected with an acoustic wind tunnel wing type supporting device through a wing type support, the wing type support is used for supporting and fixing the whole nacelle model and reducing the pneumatic noise influence caused by interference on incoming flow, the wing type support is vertically and fixedly connected to a wind tunnel test stand, so that the nacelle model is stable in strength during a wind tunnel test, and the wing type supporting sheet adopts a wing type structure to reduce the pneumatic noise influence on air flow interference in the nacelle model;
a plurality of loudspeakers are arranged in front of the wing section supporting sheet on the nacelle shell at certain intervals along the circumference and are used for synthesizing and simulating circumferential acoustic modes generated by the fan so as to realize the simulation of the acoustic modes of the pipeline;
in front of the loudspeaker, a sound lining installation area is arranged in the nacelle shell and used for installing a sound-deadening sound lining test sample piece, a sound-absorbing hole of the sound lining is flush with the inner wall surface of the nacelle shell, the sound-deadening sound lining test sample piece is sealed by a cover plate when the sound lining is measured, and the sound-absorbing hole of the sound-deadening sound lining test sample piece is flush with the inner wall surface of the nacelle shell;
a plurality of microphones are fixedly arranged in front of the sound lining mounting area and near the lip of the nacelle shell at equal intervals along the inner wall surface of the nacelle shell;
a fairing is arranged outside the nacelle shell and comprises a loudspeaker and a projecting part of a microphone to prevent the loudspeaker and the sensor from being exposed in a flow field, and connecting cables are converged in the fairing and penetrate through the wing-shaped support to be respectively connected with an external sound production control system and a PXi acquisition system through electric signals;
in order to enable the sound pressure level to meet the test standard, through holes are designed on the surface of the nacelle shell to form the equal-section wave guide pipes. Since the speaker's ability to emit sound is concentrated in the throat, the waveguide size is consistent with the speaker's throat diameter.
The utility model has the advantages of: the utility model discloses utilize electroacoustic source signal simulation fan noise to satisfy and bring fan foreward pass noise measurement demand under the stream condition, measure the performance of making an uproar of falling of sound lining under the different wind speeds. The problem of low testing efficiency of the sound liner for mounting the real engine is solved, and the testing efficiency is improved.
Drawings
Fig. 1 is a cross-sectional view of a fan duct acoustic mode simulation apparatus according to an embodiment of the present invention.
Fig. 2 is a cross-sectional view of the speaker position of section a in fig. 1.
Fig. 3 is a schematic diagram of the sound source simulation apparatus controlling the speaker to sound.
FIG. 4 is a flowchart of an acoustic simulation control process for a fan duct.
Detailed Description
The invention is further described by way of example in the following description with reference to the accompanying drawings:
example 1
As shown in fig. 1-2, a fan duct acoustic modal simulation apparatus under an incoming flow condition includes an engine simplified model 1, a speaker 2, an acoustic liner installation region 3, a fairing 4, a microphone 5, a nacelle housing 6, a wing support 7, a wing support sheet 8, a sound production control system and a PXi acquisition system, wherein the engine simplified model 1 is connected with the nacelle housing 6 through the wing support sheet 8, and the nacelle housing 6 is connected with an acoustic wind tunnel wing support apparatus through the wing support 7; in front of the wing section supporting sheet 8, a plurality of loudspeakers 2 are arranged on the nacelle shell 6 at certain intervals along the circumference, and the phases and amplitudes of the loudspeakers are controlled by a sounding control system, so that circumferential acoustic modes generated by a fan are synthesized and simulated, and the simulation of the pipeline acoustic modes is realized;
the sound liner installation area 3 is arranged in front of the loudspeaker 2 along the axial direction and in the nacelle shell 6 and used for installing a sound-absorbing sound liner test sample piece and measuring the noise reduction performance of the sound liner at different wind speeds; when the anechoic lining test sample piece is measured, the anechoic lining test sample piece is sealed by a cover plate;
the nacelle housing is divided into two sections at the acoustic liner mounting section for ease of mounting the acoustic liner, connected by rivets. The nacelle shell is in threaded connection with the fairing.
A plurality of microphones 5 are fixedly arranged in front of the acoustic liner mounting area along the axial direction and near the lip of the nacelle shell 6 at equal intervals along the inner wall surface of the nacelle shell 6;
a fairing 4 is arranged outside the nacelle shell 6 and comprises a part where the loudspeaker 2 and the microphone 5 protrude, and connecting cables are converged in the fairing 4 and penetrate through a wing-shaped support 7 to be respectively connected with an external sound production control system and a PXi acquisition system through electric signals;
an acoustic mode simulation control program is installed in the sounding control system and used for setting the amplitude and phase of each loudspeaker 2, finally, the loudspeakers 2 emit high-sound-intensity plane waves, the fan acoustic modes are axially synthesized in the nacelle shell and transmitted to the downstream of the flow field; the PXi acquisition system acquires time domain signals through a plurality of microphones and respectively measures the sound pressure fluctuation quantity of a measurement point in a non-acoustic-lining state and an acoustic-lining state.
The surface of the nacelle shell 6 is provided with a plurality of through holes which are used as equal-section wave guide pipes 10, and the size of each wave guide pipe is consistent with the throat diameter 9 of the loudspeaker 2.
The sound absorption hole of the sound attenuation lining test sample piece is flush with the inner wall surface of the nacelle shell 6.
The fairing is annular and slightly larger than the outer diameter of the nacelle housing so that the speaker and the sensor can be enclosed therein. By arranging the loudspeaker near the wing section supporting sheet and utilizing the fan pipeline acoustic mode synthesis principle, a sound source emitted by forward noise of the analog fan can be controlled; by arranging the sensor near the lip and utilizing the space Fourier decomposition principle, the circumferential sound modal order and the sound pressure level of the fan front-transmitted noise subjected to sound liner sound absorption can be detected.
Fig. 3 is a schematic diagram of controlling speaker sounding. The sound production control system adopts an industrial personal computer to control a sound card 13 to output voltage signals to a driver audio processor 12, the driver audio processor controls 4 power amplifiers 11, and each power amplifier 11 controls 4 loudspeakers 2 to produce sound. The sound wave emitted by each loudspeaker 2 is regarded as plane wave, and each loudspeaker 2 is provided with two frequency dividing lines for controlling sound production and can emit medium and low frequency sound wave. The whole cabinet is placed outside the wind tunnel flow field.
Example 2
The utility model discloses measure fan pipeline sound modal's main test step in the wind-tunnel includes following:
the method comprises the following steps: and opening the cover plate of the acoustic liner mounting section, and mounting the tested acoustic liner test piece. The sound liner test piece is of an annular structure, and the nacelle shell can be divided into two sections in the sound liner mounting area. And (3) splitting the nacelle shell, clamping the sound lining test piece into the groove, and finally connecting the two sections of nacelle shells by using rivets.
Step two: and connecting the nacelle shell with a fairing, a wing section support sheet, an engine simplified model and a wing section support, and moving the nacelle shell to a wind tunnel test platform, wherein the engine simplified model corresponds to the center of a wind tunnel collector.
Step three: and the fan pipeline acoustic simulation device is connected, the cabinet is connected with the loudspeaker cable, and the cabinet is placed outside the wind tunnel. 16 loudspeakers are controlled to sound through a main control system, the sound emission amplitude of each loudspeaker is consistent, and the phase difference of adjacent loudspeakers is increased progressively. Thus, the sound source mode with the circumferential modal order of 8 can be synthesized.
Step four: and the synthesized sound source is transmitted to the downstream of the nacelle model along the incoming flow direction, and the sensor receives the time domain signal and obtains the main mode amplitude and the circumferential mode order after spatial Fourier decomposition.
Step five: and (4) under the state of a soundless lining (mounting a cover plate), repeating the test measurement according to the steps from two to four, measuring the sound pressure amplitude of the measurement point under the state of the soundless lining, and comparing the measured sound pressure amplitude with the sound lining under the test condition to obtain the sound lining sound absorption effect.
The steps are 8-order circumferential modal synthesis and acoustic liner testing schemes, and the steps can be correspondingly modified according to the steps if the order of the tested sound source and the acoustic liner sample piece need to be replaced.
Claims (3)
1. The utility model provides a there is fan pipeline sound mode analogue means under incoming flow condition, simplifies model (1), speaker (2), sound lining installing zone (3), radome fairing (4), microphone (5), nacelle shell (6), wing section support (7), wing section support piece (8) including the engine, sound production control system and PXi collection system, PXi collection system and a plurality of microphone (5) signal of telecommunication connection, sound production control system and speaker (2) signal of telecommunication connection, its characterized in that:
the simplified engine model (1) is connected with a nacelle shell (6) through a wing section support sheet (8), and the nacelle shell (6) is connected with an acoustic wind tunnel wing section support device through a wing section support (7);
a plurality of loudspeakers (2) are arranged in front of the wing section supporting sheet (8) on the nacelle shell (6) at certain intervals along the circumference, and the phases and amplitudes of the loudspeakers are controlled by a sounding control system, so that circumferential acoustic modes generated by the fan are synthesized and simulated, and the simulation of the pipeline acoustic modes is realized;
in front of the loudspeaker (2), a sound liner mounting area (3) is arranged in the nacelle shell (6) and used for mounting a sound-deadening liner test sample piece, and the sound-deadening liner test sample piece is sealed by a cover plate when measuring is carried out on the sound-deadening liner test sample piece;
a plurality of microphones (5) are fixedly arranged in front of the sound lining mounting area and near the lip of the nacelle shell (6) at equal intervals along the inner wall surface of the nacelle shell (6);
a fairing (4) is arranged outside the nacelle shell (6) and comprises parts of the loudspeaker (2) and the microphone (5) which protrude, and connecting cables are converged in the fairing (4) and penetrate through the inside of the wing-shaped support (7).
2. The device according to claim 1, wherein the simulation device comprises: a plurality of through holes are formed in the surface of the nacelle shell (6), the through holes are used as uniform-section wave guide tubes (10), and the size of each wave guide tube is consistent with the throat diameter (9) of the loudspeaker (2).
3. The device according to claim 1, wherein the simulation device comprises: and the sound absorption hole of the sound attenuation lining test sample piece is flush with the inner wall surface of the nacelle shell (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120982077.9U CN214748872U (en) | 2021-05-10 | 2021-05-10 | Fan pipeline sound mode simulation device under incoming flow condition |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120982077.9U CN214748872U (en) | 2021-05-10 | 2021-05-10 | Fan pipeline sound mode simulation device under incoming flow condition |
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| Publication Number | Publication Date |
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| CN214748872U true CN214748872U (en) | 2021-11-16 |
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| CN202120982077.9U Active CN214748872U (en) | 2021-05-10 | 2021-05-10 | Fan pipeline sound mode simulation device under incoming flow condition |
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2021
- 2021-05-10 CN CN202120982077.9U patent/CN214748872U/en active Active
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