CN115406618A - Noise wind tunnel test method for engine body/fan installation effect - Google Patents

Noise wind tunnel test method for engine body/fan installation effect Download PDF

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Publication number
CN115406618A
CN115406618A CN202210840495.3A CN202210840495A CN115406618A CN 115406618 A CN115406618 A CN 115406618A CN 202210840495 A CN202210840495 A CN 202210840495A CN 115406618 A CN115406618 A CN 115406618A
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fan
noise
wind tunnel
nacelle
tunnel test
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徐文强
陈宝
包安宇
周国成
杨帅
单永正
高小荣
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AVIC Aerodynamics Research Institute
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AVIC Aerodynamics Research Institute
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/08—Aerodynamic models
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/02—Wind tunnels
    • G01M9/04—Details
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/06—Measuring arrangements specially adapted for aerodynamic testing

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  • Fluid Mechanics (AREA)
  • General Physics & Mathematics (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

The invention discloses a wind tunnel test method for noise of a machine body/fan installation effect, which belongs to the technical field of noise measurement and comprises the following steps: arranging pulsating pressure measuring points on the surface of the machine body model; arranging an acoustic mode measuring point and a pressure measuring rake on the inner wall of the fan duct; arranging optical sensors in the nacelle shell and the engine body model, and arranging accelerometers in the transmission shaft sleeve and the nacelle shell; arranging far field directional noise acquisition measuring points; calculating the fan-level pressure increase ratio and the flow state according to the pressure measuring rake data; and performing a pneumatic noise test, calculating the modal order and amplitude according to the acoustic modal acquisition point data, and respectively calculating the fluctuating pressure of the surface of the body, the sound pressure level of far-field noise and the directional distribution characteristic. And respectively carrying out difference comparison with noise wind tunnel test data of an independent machine body model and noise wind tunnel test data of an independent fan nacelle simulator to obtain the aerodynamic noise characteristics of the machine body/fan installation effect. The invention can reflect the noise characteristic of the installation effect of the machine body/fan more comprehensively and accurately.

Description

Noise wind tunnel test method for engine body/fan installation effect
Technical Field
The invention belongs to the technical field of noise measurement, and relates to a noise wind tunnel test method for a machine body/fan installation effect.
Background
The engine body mounting effect noise refers to noise generated by mutual interference between the engine body and the engine. The mounting effect noise is a complex problem related to crossing of aerodynamic and acoustic multidisciplinary, and the noise reduction and verification technology relates to a special wind tunnel test technology of interaction of a fan rotating part, a machine body and the like. Accurate recognition of aerodynamic and acoustic properties caused by the body/fan mounting effect is a design basis for developing the body and engine integrated layout. The wind tunnel test is an important means for researching the noise problem of the installation effect of the machine body/the fan. Because the aerodynamic noise of the turbofan aircraft is obviously influenced by the interference of the airframe and the engine, an airframe/fan installation effect noise wind tunnel test method needs to be established.
Disclosure of Invention
The invention aims to provide a wind tunnel test method for the installation effect noise of a machine body/fan, which can realize the pneumatic and acoustic characteristic test of the surface of the machine body, the interior of a nacelle and a far field, is used for reflecting the installation effect noise characteristic of the machine body/fan more comprehensively and accurately and provides verification and correction for the pneumatic layout design and the noise reduction scheme of the machine body/engine.
The technical scheme adopted by the invention is as follows: a wind tunnel test method for noise of a machine body/fan installation effect comprises the following steps:
step 1, building a supporting structure which is respectively used for supporting a machine body model and a fan nacelle simulation device, wherein the supporting structure comprises a four-degree-of-freedom platform and a hydraulic supporting system, the machine body model is vertically installed on the four-degree-of-freedom platform, the hydraulic supporting system is used for supporting and adjusting the change of the attack angle of the fan nacelle model, and the rotation of a fan in the fan nacelle simulation device is realized through a hydraulic supporting front-end motor and a transmission shaft connected with the hydraulic supporting front-end motor;
step 2, arranging a plurality of pulsating pressure acquisition measuring points on the surface of the body model;
step 3, arranging acoustic modal noise acquisition and measurement points on the wall surface of a duct near the lip of the fan nacelle simulation device, wherein the acoustic modal noise acquisition and measurement points are used for measuring the front acoustic transmission mode of a fan, and arranging pressure measurement rakes in front of the fan and behind a guide vane and used for measuring and calibrating the fan-level pressure increase ratio and flow;
step 4, arranging accelerometers in the nacelle shell and the transmission shaft sleeve for detecting the vibration quantity of the fan nacelle simulation device, and arranging optical sensors on the surfaces of the nacelle shell and the machine body model of the fan nacelle simulation device for detecting the relative distance between the machine body model and the fan nacelle simulation device;
step 5, arranging a plurality of far field directional noise acquisition measuring points in a far field linear array;
step 6, determining input working condition conditions of the noise wind tunnel test of the single engine model, including incoming flow wind speed and engine model attack angle; carrying out a wind tunnel test under the condition of input working conditions, and measuring a far-field linear array and the pulsating pressure on the surface of the machine body;
step 7, determining input working condition conditions of the noise wind tunnel test of the single fan nacelle simulation device, wherein the input working condition conditions comprise incoming flow wind speed, fan rotating speed and attack angle of the fan nacelle simulation device; carrying out a wind tunnel test under the condition of input working conditions, and measuring a fan-level pressure increase ratio, flow, a far-field linear array and a fan front sound transmission mode;
step 8, determining the input working condition of the body/fan installation effect noise wind tunnel test, comprising the following steps: the method comprises the following steps of (1) incoming flow wind speed, fan rotating speed, an attack angle of a machine body model, a relative distance between the machine body model and a fan nacelle simulation device; carrying out a wind tunnel test under the condition of input working conditions, and measuring the pulsating pressure on the surface of the machine body, the fan-level pressure ratio, the flow, the far-field linear array and the fan front sound transmission mode;
step 9, calculating the fan-level pressure increase ratio and the flow rate according to the pressure measurement rake data, and calibrating the pneumatic state parameters of the fan nacelle simulation device; calculating the pulsating pressure of the surface of the body according to the time domain data of the pulsating pressure measuring points on the surface of the body model; calculating the forward sound transmission modal order of the fan according to the time domain data of the acoustic modal measurement point of the duct wall; calculating far-field noise sound pressure level and directivity characteristics according to far-field linear array acquisition point time domain data;
step 10, respectively comparing the noise wind tunnel test data of the installation effect of the engine body/fan with the noise wind tunnel test data of the model of the independent engine body and the noise wind tunnel test data of the simulation device of the nacelle of the independent fan, wherein the comparison contents comprise: body surface pulsating pressure, far field noise sound pressure level.
Further, in the step 2, the pulsating pressure acquisition measuring points are arranged, and the pulsating pressure acquisition measuring points are respectively arranged on the lower wing surfaces of the slat, the main wing and the flap by taking 1.5 times of the diameter of the tail nozzle of the fan nacelle simulator as the reference range of the tail jet flow influence area.
Further, in step 3, before the noise wind tunnel test including the fan nacelle simulation device, the fan-level front-rear pressure boost ratio and the flow rate are required to be measured, the acoustic mode collection points are arranged at equal intervals along the circumferential direction, the arrangement section is arranged in front of the acoustic liner installation area, and the pressure measuring rakes are divided into two groups, including: respectively selecting static pressure measuring points in front of the fan and behind the guide vane, and arranging 4 measuring points in each group along the circumferential direction at equal intervals in the windward direction; arranging flow pressure measuring points at a position which is one time of the diameter of the fan, and if the length of the nacelle does not meet the one time diameter condition, obtaining the arrangement flow pressure measuring points in a pressure stable area of a central area in the duct by using a numerical simulation method; at least 3 pressure measuring points are arranged in the boundary layer range, 1 pressure measuring point is arranged in the flow center area, and the flow in the duct is calculated by utilizing the Venturi tube principle.
Further, in step 5, the far field linear array measures the spacing degrees to be 5 °, and the array can move along the axial direction.
The invention has the advantages and beneficial effects that: the invention provides a wind tunnel test method for installation effect noise of a machine body/fan, which realizes the test of the installation effect aerodynamic noise characteristics of the machine body and an engine fan by arranging a pulsating pressure sensor and a microphone on the surfaces of a scaled machine body and a fan nacelle simulation device model, provides a reliable method for the measurement of the installation effect noise of an airplane, and provides verification and correction for the numerical simulation and noise reduction scheme of the aerodynamic noise of the airplane. Meanwhile, by reasonably arranging far field test points, far field noise directivity test can be realized. Through comparison of different test state working conditions, the influence of parameters such as fan rotating speed, incoming flow wind speed and relative position distance on the noise of the engine body/fan installation effect can be comprehensively evaluated, and the method is used for guiding the integrated noise reduction design of the engine body/engine.
Drawings
FIG. 1 is a flow chart of a wind tunnel test method for body/fan mounting effect noise.
FIG. 2 is a schematic view of a machine body/fan installation effect noise wind tunnel test device.
FIG. 3 is a schematic view of a fan nacelle simulator.
FIG. 4 is a schematic view of a simulation apparatus for a nacelle model and a nacelle fan.
FIG. 5 is a far field linear array position relationship diagram.
The system comprises a sound mode collecting point 1, a pressure measuring rake 2, a nacelle shell 3, a transmission shaft sleeve 4, a fan 5, a guide vane 6, a transmission shaft 7, a fan nacelle simulation device 8, a machine body model 9, a wind tunnel collector 10, a machine body model 11, a wind tunnel nozzle 12, a hydraulic support system 13 and a four-degree-of-freedom platform 14.
Detailed Description
The technical solution of the present invention will be described in more detail below by way of example with reference to the accompanying drawings.
Example 1
As shown in fig. 1, a wind tunnel test method for noise caused by installation effect of a machine body/fan includes the following steps:
step 1, as shown in fig. 2, a support structure is built and is respectively used for supporting a machine body model and a fan nacelle simulation device, the support structure comprises a four-degree-of-freedom platform and a hydraulic support system, the machine body model is vertically installed on the four-degree-of-freedom platform, and the four-degree-of-freedom platform structure comprises: the fan nacelle simulation device comprises a ball screw, a linear unit and a turntable, the freedom degree of a machine body model is adjusted through the ball screw, the linear unit and the turntable together to realize change, a hydraulic support system is used for supporting and adjusting the change of the attack angle of a fan nacelle model, the hydraulic support structure comprises a crank arm structure, a lifting upright post, a lifting guide rail, a follow-up cable and a shaft, the rotation of a fan in the fan nacelle simulation device is realized through a hydraulic support front end motor and a transmission shaft connected with the hydraulic support front end motor, and the change of the attack angle of the fan nacelle simulation device is realized through the crank arm structure;
step 2, arranging a plurality of pulsating pressure acquisition and measurement points on the surface of the engine body model, taking 1.5 times of the diameter of a tail nozzle of a fan nacelle simulator as a reference range of a tail jet flow influence area, and arranging the pulsating pressure acquisition and measurement points on lower wing surfaces of a slat, a main wing and a flap respectively as shown in FIG. 4;
and 3, arranging acoustic modal noise acquisition measuring points on the wall surface of the duct near the lip of the fan nacelle simulator as shown in fig. 3, wherein the acoustic modal noise acquisition measuring points are used for measuring the forward acoustic mode of the fan. Arrange the pressure measurement harrow before the fan and behind the stator for measure and mark fan level pressure boost ratio and flow, all need to measure fan level front and back pressure boost ratio and flow before experimental, acoustic mode acquisition point arranges along circumference equidistant, arranges the cross-section before acoustic liner installing zone, and the pressure measurement harrow divide into two sets ofly, includes: respectively selecting static pressure measuring points in front of the fan and behind the guide vane, and arranging 4 measuring points in each group along the circumferential direction at equal intervals in the windward direction; arranging flow pressure measuring points at a position which is one time of the diameter of the fan, and if the length of the nacelle does not meet the one time diameter condition, obtaining the arrangement flow pressure measuring points in a pressure stable area of a central area in the duct by using a numerical simulation method; at least 3 pressure measuring points are arranged in the boundary layer range, 1 pressure measuring point is arranged in the flow center area, and the flow in the duct is calculated by utilizing the Venturi tube principle;
and 4, arranging accelerometers in the nacelle shell and the transmission shaft sleeve for detecting the vibration quantity of the fan simulation device. Arranging optical sensors on the surfaces of the nacelle shell and the engine body model, wherein the optical sensors are used for detecting the relative distance between the engine body model and the fan nacelle simulation device; when the vibration quantity of an accelerometer in a transmission shaft sleeve exceeds the standard or the relative distance between a nacelle and a machine body exceeds the standard, emergency stop is required;
step 5, as shown in fig. 5, arranging a plurality of far field directional noise acquisition measurement points in a far field linear array, wherein the circumferential directional range of the far field linear array measurement is 50-115 degrees, the interval degree is 5 degrees, and the array can move along the axial direction;
step 6, determining input working conditions of the noise wind tunnel test of the single machine body model, including incoming flow wind speed and machine body model attack angle, performing the wind tunnel test under the input working conditions, and measuring far field linear array and machine body surface pulsating pressure;
and 7, determining input working condition conditions of the noise wind tunnel test of the individual fan nacelle simulation device, including incoming flow wind speed, fan rotating speed and attack angle of the fan nacelle simulation device. Carrying out a wind tunnel test under the condition of input working conditions, and measuring a fan-level pressure increase ratio, flow, a far-field linear array and a fan front sound transmission mode;
step 8, determining the input working condition of the body/fan installation effect noise wind tunnel test, comprising the following steps: the system comprises an incoming flow wind speed, a fan rotating speed, an attack angle of a machine body model, a relative distance between the machine body model and a fan nacelle simulation device. Carrying out a wind tunnel test under the condition of input working conditions, and measuring the pulsating pressure on the surface of the machine body, the fan-level pressure ratio, the flow, the far-field linear array and the fan front sound transmission mode;
step 9, calculating the fan-level pressure increase ratio and the flow rate according to the pressure measuring rake data, and calibrating the pneumatic state parameters of the fan nacelle simulation device; calculating the pulsating pressure of the surface of the body according to the time domain data of the pulsating pressure measuring points on the surface of the body model; calculating the forward sound transmission modal order of the fan according to the time domain data of the acoustic modal measurement point of the duct wall; calculating far-field noise sound pressure level and directivity characteristics according to the far-field linear array acquisition point time domain data;
step 10, respectively comparing the machine body/fan installation effect noise wind tunnel test data with the noise wind tunnel test data of the single machine body model and the noise wind tunnel test data of the single fan nacelle simulation device, wherein the comparison contents comprise: the pulsating pressure on the surface of the body and the sound pressure level of far-field noise.
Example 2
Before testing, the ground debugging of the fan nacelle simulator is carried out, including the dynamic balance test of the fan and the transmission test of the motor. In addition, the surface of the test support equipment is subjected to surface sound attenuation treatment to reduce the influence of sound reflection. Calibrating the acoustic measurement device using a calibrator. During testing, the center of the fan nacelle simulation device is over against the center of the wind tunnel nozzle, and the corresponding height of the body model support is adjusted. After the model is installed in place, the installation condition of the model is checked, the running condition of the testing device is checked, the model is accurately installed, and the testing device can run normally. After the states of the test equipment and the model are determined, an acoustic test can be developed, the wind tunnel wind speed and the fan rotating speed are gradually increased from low to high, after the safety is determined, a formal test is carried out according to the test content, a PXI bus data acquisition system is adopted to acquire data, the result is processed and output, all test points are completed, and the wind tunnel test of the installation effect noise of the engine body/fan specifically comprises the following steps: starting a fan driving motor to increase the rotating speed of the fan to a certain working rotating speed; starting the wind tunnel to enable the wind speed to rise to a fixed working point; collecting the fan-level pressure increase ratio and flow, outputting and calibrating a test result, and determining the fan-level pneumatic state; collecting noise and pulsating pressure measuring points and outputting results; changing the rotating speed and the wind speed of the fan and the relative position of the machine body/the fan, acquiring data, processing an output result and completing all test points; and (5) stopping the wind tunnel. And after the airframe/fan mounting effect noise wind tunnel test data are obtained, difference quantity comparison is respectively carried out on the airframe/fan mounting effect noise wind tunnel test data and the single fan nacelle simulation device noise wind tunnel test data, and the characteristics of the airframe/fan mounting effect aerodynamic noise are obtained.
The notes of the experiment included: 1. and (4) safety monitoring: in the test process, special attention needs to be paid to monitoring the vibration characteristic of the model, the protection is automatically started when a safety threshold is reached, meanwhile, the alarm is given by sound, and the condition displayed by the camera outside the tunnel is monitored in real time, so that the safety of each system is ensured; 2. emergency measures: in the process of the wind tunnel test, the test method is strictly carried out according to the correct starting and stopping steps, so that the test model is prevented from being damaged.

Claims (4)

1. A wind tunnel test method for noise of a machine body/fan installation effect is characterized by comprising the following steps:
step 1, building a supporting structure which is respectively used for supporting a machine body model and a fan nacelle simulation device, wherein the supporting structure comprises a four-degree-of-freedom platform and a hydraulic supporting system, the machine body model is vertically installed on the four-degree-of-freedom platform, the hydraulic supporting system is used for supporting and adjusting the change of the attack angle of the fan nacelle model, and the rotation of a fan in the fan nacelle simulation device is realized through a hydraulic supporting front-end motor and a transmission shaft connected with the hydraulic supporting front-end motor;
step 2, arranging a plurality of pulsating pressure acquisition measuring points on the surface of the body model;
step 3, arranging acoustic modal noise acquisition and measurement points on the wall surface of a duct near the lip of the fan nacelle simulation device, wherein the acoustic modal noise acquisition and measurement points are used for measuring the front acoustic transmission mode of a fan, and arranging pressure measurement rakes in front of the fan and behind a guide vane and used for measuring and calibrating the fan-level pressure increase ratio and flow;
step 4, arranging accelerometers in the nacelle shell and the transmission shaft sleeve for detecting the vibration quantity of the fan nacelle simulation device, and arranging optical sensors on the surfaces of the nacelle shell and the machine body model of the fan nacelle simulation device for detecting the relative distance between the machine body model and the fan nacelle simulation device;
step 5, arranging a plurality of far field directional noise acquisition measuring points in a far field linear array;
step 6, determining input working condition conditions of the noise wind tunnel test of the single engine model, including incoming flow wind speed and engine model attack angle; carrying out a wind tunnel test under the condition of input working conditions, and measuring a far-field linear array and the pulsating pressure on the surface of the machine body;
step 7, determining input working condition conditions of the noise wind tunnel test of the single fan nacelle simulation device, wherein the input working condition conditions comprise incoming flow wind speed, fan rotating speed and attack angle of the fan nacelle simulation device; carrying out a wind tunnel test under the condition of input working conditions, and measuring a fan-level pressure increase ratio, flow, a far-field linear array and a fan front sound transmission mode;
step 8, determining the input working condition of the body/fan installation effect noise wind tunnel test, comprising the following steps: the method comprises the following steps of (1) incoming flow wind speed, fan rotating speed, an attack angle of a machine body model, a relative distance between the machine body model and a fan nacelle simulation device; carrying out a wind tunnel test under the condition of input working conditions, and measuring the pulsating pressure on the surface of the machine body, the fan-level pressure ratio, the flow, the far-field linear array and the fan front sound transmission mode;
step 9, calculating the fan-level pressure increase ratio and the flow rate according to the pressure measurement rake data, and calibrating the pneumatic state parameters of the fan nacelle simulation device; calculating the pulsating pressure of the surface of the body according to the time domain data of the pulsating pressure measuring points on the surface of the body model; calculating the forward sound transmission modal order of the fan according to the time domain data of the duct wall sound modal measurement point; calculating far-field noise sound pressure level and directivity characteristics according to the far-field linear array acquisition point time domain data;
step 10, respectively comparing the noise wind tunnel test data of the installation effect of the engine body/fan with the noise wind tunnel test data of the model of the independent engine body and the noise wind tunnel test data of the simulation device of the nacelle of the independent fan, wherein the comparison contents comprise: the pulsating pressure on the surface of the body and the sound pressure level of far-field noise.
2. The machine body/fan mounting effect noise wind tunnel test method according to claim 1, wherein in the step 2, the pulsating pressure acquisition measuring points are arranged, the pulsating pressure acquisition measuring points are respectively arranged on the lower wing surfaces of the slat, the main wing and the flap by taking 1.5 times of the diameter of the tail nozzle of the fan nacelle simulator as a reference range of a tail jet flow influence area.
3. The machine body/fan installation effect noise wind tunnel test method of claim 1, wherein in step 3, before the noise wind tunnel test including the fan nacelle simulation device, the front-rear boost ratio and the flow rate of a fan level need to be measured, the acoustic mode acquisition points are arranged at equal intervals along the circumferential direction, the arrangement section is arranged in front of the acoustic liner installation area, and the pressure measurement rakes are divided into two groups, including: respectively selecting static pressure measuring points in front of the fan and behind the guide vane, and arranging 4 measuring points in each group along the circumferential direction at equal intervals in the windward direction; arranging flow pressure measuring points at the position which is one time of the diameter of the fan, and if the length of the nacelle does not meet the one time diameter condition, obtaining the flow pressure measuring points arranged on the pressure stabilizing section of the central area in the duct by using a numerical simulation method; at least 3 pressure measuring points are arranged in the boundary layer range, 1 pressure measuring point is arranged in the flow center area, and the flow in the duct is calculated by utilizing the Venturi tube principle.
4. A wind tunnel test method for body/fan mounting effect noise according to any one of claims 1 to 3, wherein in step 5, the far field linear array is measured at intervals of 5 ° and the array can move axially.
CN202210840495.3A 2022-07-18 2022-07-18 Noise wind tunnel test method for engine body/fan installation effect Pending CN115406618A (en)

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