CN114515683A - Hartmann sound source sounder and aero-engine component strength test device thereof - Google Patents

Hartmann sound source sounder and aero-engine component strength test device thereof Download PDF

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Publication number
CN114515683A
CN114515683A CN202111442930.9A CN202111442930A CN114515683A CN 114515683 A CN114515683 A CN 114515683A CN 202111442930 A CN202111442930 A CN 202111442930A CN 114515683 A CN114515683 A CN 114515683A
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China
Prior art keywords
hartmann
sound source
cavity tube
nozzle
tube
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Pending
Application number
CN202111442930.9A
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Chinese (zh)
Inventor
王琰
郭定文
许绯
刘洋
燕群
刘兴强
张彬
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AVIC Aircraft Strength Research Institute
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AVIC Aircraft Strength Research Institute
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Priority to CN202111442930.9A priority Critical patent/CN114515683A/en
Publication of CN114515683A publication Critical patent/CN114515683A/en
Pending legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B06—GENERATING OR TRANSMITTING MECHANICAL VIBRATIONS IN GENERAL
    • B06B—METHODS OR APPARATUS FOR GENERATING OR TRANSMITTING MECHANICAL VIBRATIONS OF INFRASONIC, SONIC, OR ULTRASONIC FREQUENCY, e.g. FOR PERFORMING MECHANICAL WORK IN GENERAL
    • B06B1/00—Methods or apparatus for generating mechanical vibrations of infrasonic, sonic, or ultrasonic frequency
    • B06B1/18—Methods or apparatus for generating mechanical vibrations of infrasonic, sonic, or ultrasonic frequency wherein the vibrator is actuated by pressure fluid
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M13/00—Testing of machine parts
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)

Abstract

The application relates to a hartmann sound source sounder, include: a breather pipe; the flow regulating valve is arranged on the vent pipe; the nozzle is connected to the outlet part of the vent pipe; a support; the resonance cavity tube is connected to the bracket, the inlet of the resonance cavity tube is opposite to the outlet of the nozzle, and the resonance cavity tube can move towards the direction close to or far away from the nozzle; and the piston is arranged in the resonant cavity tube and can axially slide along the resonant cavity tube. Furthermore, it relates to an aircraft engine component strength test device, comprising: a reverberation chamber having perforations thereon; the Hartmann sound source sounder has the structure that the outlet of the vent pipe and the nozzle thereof extend into the reverberation chamber from the perforation, and the bracket, the resonance cavity pipe and the piston thereof are arranged in the reverberation chamber.

Description

Hartmann sound source sounder and aero-engine component strength test device thereof
Technical Field
The application belongs to the technical field of aero-engine component strength tests, and particularly relates to a Hartmann sound source sounder and an aero-engine component strength test device thereof.
Background
The aeroengine part component is in a high-frequency noise environment in actual operation, and the high-frequency noise environment needs to be restored when the aeroengine part is subjected to an intensity test, for this reason, the aeroengine part intensity test is carried out in a reverberation room, and the required high-frequency noise is generated through an electric air flow loudspeaker, and the technical scheme has the following defects:
the controllable range of sinusoidal sound frequency of the existing electric air flow loudspeaker is less than or equal to 1250Hz, and the sound capability is obviously reduced above 1000Hz, so that the requirement of high-frequency noise environment of an aeroengine component strength test cannot be met.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
The present application aims to provide a hartmann sound source sounder and an aircraft engine component strength testing apparatus therefor, which overcome or mitigate at least one of the known disadvantages.
The technical scheme of the application is as follows:
in one aspect, there is provided a hartmann sound source sounder comprising:
a breather pipe;
the flow regulating valve is arranged on the vent pipe;
the nozzle is connected to the outlet part of the vent pipe;
a support;
the resonance cavity tube is connected to the bracket, the inlet of the resonance cavity tube is opposite to the outlet of the nozzle, and the resonance cavity tube can move towards the direction close to or far away from the nozzle;
and the piston is arranged in the resonant cavity tube and can axially slide along the resonant cavity tube.
According to at least one embodiment of the present application, in the hartmann sound source sounder, the support is provided with a support hole;
the resonant cavity pipe is screwed in the support hole.
According to at least one embodiment of the present application, in the hartmann sound source sounder described above, the radial dimension of the nozzle is smaller than the radial dimension of the resonant cavity tube.
According to at least one embodiment of the present application, in the hartmann sound source sounder described above, the resonance chamber tube is a circular tube.
According to at least one embodiment of the present application, in the hartmann sound source sounder described above, further comprising:
and the electric cylinder is arranged in the resonant cavity tube and is connected with the piston so as to drive the piston to axially slide along the resonant cavity tube.
In another aspect, an aircraft engine component strength testing apparatus is provided, comprising:
a reverberation chamber having perforations thereon;
in any of the above hartmann sound source sounders, the outlet of the vent pipe and the nozzle thereof extend into the reverberation chamber from the through hole, and the support, the resonance chamber pipe and the piston thereof are disposed in the reverberation chamber.
According to at least one embodiment of the present application, the aircraft engine component strength testing apparatus further includes:
and the microphone is arranged in the reverberation room.
Drawings
FIG. 1 is a schematic diagram of a Hartmann sound source sounder and an aircraft engine component strength testing device thereof provided by an embodiment of the application;
wherein:
1-a breather pipe; 2-a flow regulating valve; 3-a nozzle; 4-a scaffold; 5-a resonant lumen tube; 6-a piston; 7-an electric cylinder; 8-a reverberation chamber; 9-a microphone.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that devices or elements must have specific orientations, be constructed and operated in specific orientations, and that when the absolute position of an object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of any other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in the present application according to their specific situation.
The present application is described in further detail below with reference to fig. 1.
In one aspect, there is provided a hartmann sound source sounder comprising:
a breather pipe 1;
a flow regulating valve 2 arranged on the vent pipe 1;
a nozzle 3 connected to an outlet of the vent pipe 1;
a bracket 4;
the resonance cavity tube 5 is connected on the bracket 4, the inlet of the resonance cavity tube is opposite to the outlet of the nozzle 3, and the resonance cavity tube can move towards the direction close to or far away from the nozzle 3;
and the piston 6 is arranged in the resonant cavity tube 5 and can slide along the axial direction of the resonant cavity tube 5.
The Hartmann sound source sounder disclosed by the embodiment can be applied to strength tests of parts of an aircraft engine, and the specific application can refer to the following steps:
a through hole is arranged on the side wall of the reverberation chamber 8;
the outlet of a vent pipe 1 of a Hartmann sound source sounder and a nozzle 3 thereof extend into a reverberation chamber 8 through a perforation, and a bracket 4, a resonance cavity pipe 5 and a piston 6 thereof are arranged in the reverberation chamber 8;
air flow is introduced into the air pipe 1, is sprayed out through the nozzle 3 and enters the resonance cavity pipe 5, high-frequency noise is generated, the high-frequency noise environment where the aircraft engine component works is restored, and the strength test of the aircraft engine component is carried out in the reverberation chamber 8.
For the hartmann sound source sounder disclosed in the above embodiments, it can be understood by those skilled in the art that, when it is applied to the aero-engine component strength test, the effective depth of the resonant cavity tube 5 can be adjusted by sliding the piston 6 along the axial direction of the resonant cavity tube 5 to adjust the frequency of the noise, so as to ensure the requirement of the aero-engine component strength test on the frequency of the noise, and the opening degree of the flow regulating valve 2 can be adjusted to adjust the air flow rate introduced into the ventilation tube 1 to adjust the strength of the noise, so as to ensure the requirement of the aero-engine component strength test on the noise strength, and in addition, the distance between the resonant cavity tube 5 and the nozzle 3 can be adjusted by moving the resonant cavity tube 5 toward or away from the nozzle 3, so as to achieve a larger sounding noise strength with a smaller air flow rate, so as to optimize the efficiency.
The effective depth of the resonant cavity tube 5 is adjusted by the axial sliding of the piston 6 along the resonant cavity tube 5 to adjust the frequency of the noise, and the principle is as follows:
Figure BDA0003383962410000051
wherein,
f is the noise frequency;
c is the speed of sound;
ddeep toIs the effective depth of the resonant chamber tube 5;
DchamberIs the equivalent diameter of the resonant cavity tube 5;
k is a fixed coefficient, and can be 0.7;
effective depth d of resonant chamber tube 5 at c speed of soundDeep toThe equivalent diameter D of the resonant cavity tube 5ChamberThe fixed coefficient k is determined by the effective depth d of the resonant cavity 5Deep toTherefore, the effective depth of the resonant cavity tube 5 can be adjusted by the axial sliding of the piston 6 along the resonant cavity tube 5, and the adjustment of the noise frequency is realized.
In some alternative embodiments, in the hartmann sound source sounder described above, the support 4 has a support hole;
the resonance cavity tube 5 is screwed in the supporting hole, and the resonance cavity tube 5 can be conveniently moved towards or away from the nozzle 3 by screwing the resonance cavity tube 5.
In some alternative embodiments, in the hartmann sound source sounder described above,
the radial dimension of the nozzle 3 is smaller than the radial dimension of the resonant chamber tube 5.
In some alternative embodiments, in the hartmann sound source sounder described above, the resonant cavity tube 5 is a circular tube.
In some optional embodiments, in the hartmann sound source sounder described above, further comprising:
and the electric cylinder 7 is arranged in the resonant cavity tube 5 and is connected with the piston 6 so as to drive the piston 6 to slide along the axial direction of the resonant cavity tube 5.
In another aspect, an aircraft engine component strength testing apparatus is provided, comprising:
a reverberation chamber 8 having perforations thereon;
in any of the above hartmann sound source generators, the outlet of the snorkel 1 and its nozzle 3 extend into the reverberation chamber 8 through a perforation, and the support 4, the resonant cavity tube 5 and its piston 6 are disposed in the reverberation chamber 8.
For the aircraft engine component strength testing device disclosed in the above embodiment, including the hartmann sound source sounder disclosed in the above embodiment, the technical effects of the relevant parts of the hartmann sound source sounder may also be referred to, and details are not repeated herein.
In some optional embodiments, the aircraft engine component strength testing apparatus further includes:
a microphone 9 is provided in the reverberation chamber 8 to be able to measure the noise in the reverberation chamber 8.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.

Claims (7)

1. A hartmann sound source sounder, comprising:
a breather pipe (1);
a flow control valve (2) disposed on the vent pipe (1);
the nozzle (3) is connected to the outlet part of the vent pipe (1);
a support (4);
the resonance cavity tube (5) is connected to the bracket (4), the inlet of the resonance cavity tube is opposite to the outlet of the nozzle (3), and the resonance cavity tube can move towards the direction close to or away from the nozzle (3);
and the piston (6) is arranged in the resonant cavity tube (5) and can slide along the axial direction of the resonant cavity tube (5).
2. Hartmann sound source generator according to claim 1,
the bracket (4) is provided with a supporting hole;
the resonance cavity pipe (5) is screwed in the support hole.
3. Hartmann sound source generator according to claim 1,
the radial dimension of the nozzle (3) is smaller than the radial dimension of the resonance chamber tube (5).
4. Hartmann sound source generator according to claim 1,
the resonance cavity tube (5) is a circular tube.
5. Hartmann sound source generator according to claim 1,
further comprising:
and the electric cylinder (7) is arranged in the resonant cavity tube (5) and is connected with the piston (6) so as to drive the piston (6) to axially slide along the resonant cavity tube (5).
6. An aeroengine component strength test device, characterized by, includes:
a reverberation chamber (8) having perforations thereon;
a Hartmann sound source sounder according to any of the claims 1-5, wherein the outlet of the snorkel (1) and its nozzle (3) extend from the perforation into the reverberation chamber (8), and wherein the support (4), the resonance chamber tube (5) and its piston (6) are arranged in the reverberation chamber (8).
7. The aircraft engine component strength testing apparatus of claim 6,
further comprising:
and a microphone (9) disposed in the reverberation chamber (8).
CN202111442930.9A 2021-11-30 2021-11-30 Hartmann sound source sounder and aero-engine component strength test device thereof Pending CN114515683A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202111442930.9A CN114515683A (en) 2021-11-30 2021-11-30 Hartmann sound source sounder and aero-engine component strength test device thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202111442930.9A CN114515683A (en) 2021-11-30 2021-11-30 Hartmann sound source sounder and aero-engine component strength test device thereof

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CN114515683A true CN114515683A (en) 2022-05-20

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Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111551380A (en) * 2020-04-30 2020-08-18 天津航天瑞莱科技有限公司 Movable small reverberation chamber
CN112620058A (en) * 2020-12-23 2021-04-09 北京强度环境研究所 Hartmann sound generator with laval nozzle

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111551380A (en) * 2020-04-30 2020-08-18 天津航天瑞莱科技有限公司 Movable small reverberation chamber
CN112620058A (en) * 2020-12-23 2021-04-09 北京强度环境研究所 Hartmann sound generator with laval nozzle

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
杨松等: "喷注式高频声学噪声发声器的试验研究", 《环模技术》 *

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Application publication date: 20220520