CN111319789B - Full-size propeller blade icing wind tunnel test method - Google Patents
Full-size propeller blade icing wind tunnel test method Download PDFInfo
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- CN111319789B CN111319789B CN202010271699.0A CN202010271699A CN111319789B CN 111319789 B CN111319789 B CN 111319789B CN 202010271699 A CN202010271699 A CN 202010271699A CN 111319789 B CN111319789 B CN 111319789B
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Abstract
The invention discloses a full-size propeller blade icing wind tunnel test method. Firstly, truncating the blade tip of a full-size blade in the length direction to adapt to the size of the wind tunnel, secondly, vertically installing the blade on a wind tunnel turntable and adjusting the chord line on a truncation section to be parallel to the horizontal line of the wind tunnel, thereby determining the installation angle of the blade, and then deducting the initial included angle between the section chord line and the blade angle chord line according to the test requirement to obtain the actual rotation angle of the blade. The invention provides a feasible method for a full-size propeller icing wind tunnel test, and simultaneously solves the problem that the full-size propeller blades cannot be positioned at an angle in the wind tunnel at present, and if the angle cannot be determined, the related test cannot be carried out.
Description
Technical Field
The invention relates to the field of wind tunnel tests, in particular to a full-size propeller blade icing wind tunnel test method.
Background
According to the requirement of aeroengine airworthiness standard of 33 th part of civil aviation regulation in China (CCAR-33 part), under the continuous maximum or discontinuous maximum icing state specified in appendix C of 25 th part of civil aviation regulation in China, in the operation of the engine in the whole flight power range, icing conditions which influence the operation of the engine or cause serious power or thrust loss do not occur on engine parts. Therefore, in the process of obtaining the evidence of the model of the aircraft engine, the icing wind tunnel test becomes a necessary conformity method for verifying whether the engine meets the requirements of icing terms in the CCAR-33 part.
The propeller is used as an important part of a propeller type engine, and an icing wind tunnel test is required to be carried out to verify whether the propeller meets the safety requirements in flight under icing meteorological conditions, so that the deicing capability of the propeller is verified as one of necessary conditions for whether the propeller can be safely applied. Although the propellers of most types of airplanes adopt an electric heating anti-icing/deicing mode at the front edge and other positions to meet the safety requirements at present, an icing wind tunnel test is still required to be carried out for safety check and verification before the propellers are applied.
As shown in fig. 1, the propeller engine is a schematic structural diagram, and includes a plurality of blades, and the plurality of blades rotate around an engine rotation axis. Because the full-size propeller blade has larger size, if the components are also considered to be combined and driven to rotate, higher requirements are put forward on the size of the icing wind tunnel, and the actual wind tunnel size cannot meet the requirements. Only a single blade can be used for testing, as shown in the schematic diagram of fig. 2. According to the requirement for ensuring the precision of the test result of the icing wind tunnel, the test model needs to be consistent with the external dimension, the structural form, the material composition and the like of the real propeller. The actual full-size propeller model is generally large, and the size of the conventional test section of the icing wind tunnel is difficult to meet the actual working condition requirement. If the blade model with the size of 1:1 is placed in the wind tunnel, as shown in fig. 3, the wind tunnel cannot completely place the blades or the blades are not in the uniform cloud airflow area of the wind tunnel, so that effective tests cannot be carried out.
When the conventional propeller blade icing wind tunnel safety examination verification test is carried out, because the speed working conditions of the sections at different diameters are different, and the wind tunnel test cannot provide a hierarchical speed field, the examination verification test needs to be carried out on different sections one by one, and each blade needs to carry out test verification on a plurality of examined sections. For the propeller with the size of 1:1 to be installed and tested in the wind tunnel, because the propeller has certain torsion resistance, the propeller cannot accurately calibrate the angle positions of different sections by a conventional measuring means, and because the related projects are not developed in the existing wind tunnel test, a reasonable and effective test method needs to be designed to facilitate the development of the propeller blade safety assessment test work.
Disclosure of Invention
The invention aims to provide a novel icing wind tunnel test method according to a tested object, so that accurate installation and calibration of a propeller in an icing wind tunnel are realized, and the rotation angle of the propeller can be accurately measured in the test process.
In order to achieve the purpose, the invention adopts the following technical scheme:
a full-size propeller blade icing wind tunnel test method comprises the following steps:
s1, cutting the blade tip of the propeller blade test piece in the length direction when the propeller blade test piece is designed and manufactured, exposing a cut section parallel to the end face, and finding out an included angle value between a cut section chord line and an examined section chord line on a digital-analog model, wherein the included angle value is a preset angle value;
s2, taking one blade of the tested propeller, and fixing the blade on a turntable of the wind tunnel test section by taking a propeller hub as a support;
s3, adjusting the initial installation angle of the paddle to 0 degree;
s4, rotating the paddle, adjusting the paddle angle to the test angle, and starting the wind tunnel test;
in S3, the process of implementing blade setting angle zeroing includes the following steps:
s31, arranging a laser level meter in the wind tunnel, and adjusting the laser line and the airflow line to be parallel according to the reference line of the wind tunnel test section;
s32, finding out the chord line on the truncation section, and measuring the included angle between the chord line and the laser line;
s33, rotating the paddle to make the chord line of the truncation section be horizontally parallel or coincident with the laser line, namely completing the adjustment of the initial angle of the paddle installation to 0 degree;
in S4, when it is necessary to rotate the blade to the test angle:
and iterating to obtain the difference between the test angle and the preset angle value, and rotating the turntable to eliminate the difference angle to obtain the angle value required by the test.
In the technical scheme, the blades are full-size blades cut off in the length direction, the section is parallel to the horizontal plane after the blades are installed in the wind tunnel, and the chord line is a connecting line of the central points of the front end and the rear end of the section.
In the technical scheme, the string is connected with the central points at two ends of the section in a line drawing mode in the section plane, and the laser line and the line drawing are parallelly coincided to judge that the initial installation angle is zeroed.
In the above technical solution, the chord line is not in the truncation section, and the angle value of the chord line of the examined section cannot be directly obtained, and then the included angle between the truncation section chord line and the chord line of the examined section is firstly measured on the design model, that is, the preset angle value is obtained, and when the angle of the test model is adjusted, the preset angle value is deducted from the actual rotation angle.
In the above technical solution, during the wind tunnel test, the test wind speed is determined as follows:
the forward flight speed of the real airplane and the linear speed of the blade rotating around the rotation axis of the engine are combined to obtain the real speed of the single blade, namely the wind speed in the wind tunnel test.
In the technical scheme, a certain section airfoil of the propeller blade is taken, the relative speed of the airfoil and air is determined by the linear speed and the flight speed of the blade movement, and the linear speed of the section of the section is matched with the distance between the section of the airfoil and the root and the tip of the blade.
In the technical scheme, the closer the section of the section is to the blade root, the smaller the linear velocity is; the closer the cross-sectional area is to the tip, the greater the linear velocity.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
the method has the greatest advantage of solving the problem that the angle positioning cannot be carried out on the full-size propeller blade in the wind tunnel at present, and if the angle cannot be determined, the related test cannot be carried out.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic view of a propeller configuration;
FIG. 2 is a schematic structural view of a single blade;
FIG. 3 is a schematic view of the installation of a full-sized single blade in a wind tunnel;
FIG. 4 is a schematic view of a blade of the present invention in a wind tunnel.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification (including any accompanying claims, abstract and drawings), may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
In the embodiment, in order to ensure the normal operation of the test, a blade truncation mode is adopted, the blade tip part is removed, and the part to be tested is reserved, so that the size of the blade is reduced, and the blade can be installed in the wind tunnel test section.
As shown in figure 4, the blades are installed in the wind tunnel, the single blade is fixed by taking the hub as a support, and a fixed bracket is installed between the bottom of the wind tunnel and the hub. The fixed bolster can adopt multiple form, and the flange circle cover structure is adopted to this embodiment, and the ring flange can pass through the fix with screw on the wind-tunnel carousel, and wheel hub passes through the thread tightening or the pin carries out the lock joint with the flange cover.
The mounted blade cannot acquire the blade angle, so that the test cannot be performed in such a case. Therefore, the blade angle needs to be adjusted to 0 degrees for the initial installation angle value, so that the test can be accurately performed at any angle. In the present embodiment, the blade angle refers to the angle between the section chord line of the propeller and the rotation plane of the propeller, and the blade angle changes along with the change of the radius. In the technical field, technicians are used to use a blade angle value at 70% of the diameter as a name value of the blade angle, and for blades installed on a wind tunnel test section, the blade angle is an included angle between a section chord line to be checked and airflow.
The specific 0-adjusting process of the blade angle is as follows:
firstly, arranging a laser level meter at the wind tunnel end provided with a blade, and firstly adjusting a laser line and an airflow line to be parallel according to a reference line of a wind tunnel test section;
secondly, drawing out (or drawing) a cut section chord line of the paddle by using a thin line, obtaining an included angle between the chord line and a laser line at the moment, and then rotating a wind tunnel test section turntable to adjust the chord line to be parallel to the laser line;
the third step: and acquiring the blade angle of the section to be checked. The chord line of the section to be checked can not be directly obtained by physical means, but can only be obtained by indirect means; therefore, in this embodiment, an included angle between the truncated section chord line and the examined section chord line is measured on the design model of the blade, that is, a preset angle value is measured, and then, after the truncated section chord line is parallel to the laser line, the preset angle value needs to be deducted, so as to obtain the initial installation angle of the examined section.
The fourth step: in the test process, when the test is carried out at any angle, the value of the angle minus the initial installation angle is used, namely the angle which needs to be actually rotated.
The fifth step: and (4) determining the test wind speed. The blades on a real propeller engine are operated such that the aircraft rotates about its own axis of rotation while flying forward. So when a single blade is used for testing, the test wind speeds must be combined. The forward flight speed of the aircraft and the linear speed of the rotation of the blades around the rotation axis of the engine are combined to obtain the real speed of a single blade, so that the test wind speed is determined. For a certain section airfoil of the propeller blade, the relative speed of the airfoil and the air is determined by the linear speed and the flying speed of the blade movement, and the linear speed is smaller as the section is closer to the root and is larger as the section is closer to the tip. During the test, after the examination section is determined, the linear speed of the examination section can be obtained according to the rotating speed of the propeller, and the resultant speed of the linear speed and the flying speed is the wind tunnel test wind speed.
Example one
In a test, the examined section needs to be tested under 26 degrees.
Firstly, acquiring a preset angle value of the section as 17 degrees from a design model of the propeller blade, and then rotating the blade to enable a chord line of the truncated section to be parallel to a laser line. The angle 9 ° is obtained by subtracting 17 ° from 26 °, and then the final test angle is obtained by rotating the turntable by 9 °.
Then starting the motor to adjust the wind speed to a test wind speed (such as 120 m/s), and then starting the systemCooling the system, adjusting the temperature to the test temperature (e.g., -15 deg.C), adjusting the number of nozzles in the spray system (e.g., 1000) and the pressure of water gas (e.g., 0.2MPa, 0.18 MPa), and adjusting the cloud parameters of water droplet diameter and liquid water content to the test requirements (e.g., 20 μm, 0.5 g/m)3). Then, the solenoid valve in front of the nozzle was opened to start spraying, and the test was started.
Example two
In a test, the section to be examined needs to be tested at 30 °.
Firstly, acquiring a preset angle value of the section as-21 degrees from a design model of the propeller blade, and then rotating the blade to enable the chord line of the truncated section to be parallel to the laser line.
The angle 51 is obtained by subtracting-21 from 30, and then the final test angle is obtained by rotating the turntable by 51.
Then starting a motor to adjust the wind speed to a test wind speed (such as 180 m/s), then starting a refrigerating system, adjusting the temperature to a test temperature (such as-25 ℃), adjusting the using number (such as 1000) of nozzles of the spraying system and the pressure of water gas (such as 0.2MPa and 0.15 MPa), and adjusting the cloud parameters of the diameter of water drops and the liquid water content to the test requirements (such as 20 mu m and 0.5g/m 3). Then, the solenoid valve in front of the nozzle was opened to start spraying, and the test was started.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (5)
1. A full-size propeller blade icing wind tunnel test method comprises the following steps:
s1, cutting the blade tip of the propeller blade test piece in the length direction when the propeller blade test piece is designed and manufactured, exposing a cut section parallel to the end face, and finding out an included angle value between a cut section chord line and an examined section chord line on a design model, wherein the included angle value is a preset angle value;
s2, taking one blade of the tested propeller, and fixing the blade on a turntable of the wind tunnel test section by taking a propeller hub as a support;
s3, adjusting the initial installation angle of the paddle to 0 degree;
s4, rotating the paddle, adjusting the paddle angle to a test angle, wherein the paddle angle is the included angle between the chord line of the section to be checked and the airflow, and starting a wind tunnel test;
the method is characterized in that:
in S3, the process of implementing blade setting angle zeroing includes the following steps:
s31, arranging a laser level meter in the wind tunnel, and adjusting the laser line and the airflow line to be parallel according to the reference line of the wind tunnel test section;
s32, finding out the chord line on the truncation section, and measuring the included angle between the chord line and the laser line;
s33, rotating the paddle to make the chord line of the truncation section be horizontally parallel or coincident with the laser line, namely completing the adjustment of the initial angle of the paddle installation to 0 degree;
in S4, when it is necessary to rotate the blade to the test angle:
and iterating to obtain the difference between the test angle and the preset angle value, and rotating the turntable to eliminate the difference angle to obtain the angle value required by the test.
2. The icing wind tunnel test method for the full-size propeller blade according to claim 1, wherein the blade is cut off in the length direction, the cross section of the blade is parallel to the horizontal plane after the blade is installed in the wind tunnel, and the chord line is a connecting line of central points of the front end and the rear end of the cross section.
3. The icing wind tunnel test method for the full-size propeller blade according to claim 2, wherein the icing wind tunnel test method comprises the following steps:
the string of a musical instrument is in cutting the section, connects the central point at cross-section both ends through the mode of setting-out, carries out parallel coincidence through laser line and setting-out and judges initial installation angle zero setting.
4. The icing wind tunnel test method for the full-size propeller blade according to claim 2, wherein the icing wind tunnel test method comprises the following steps:
the chord line is not in the truncation section, the angle value of the chord line of the examined section cannot be directly obtained, the included angle between the truncation section chord line and the chord line of the examined section is firstly measured on the design model, namely the preset angle value is obtained, and the preset angle value is deducted from the test angle when the angle of the test model is adjusted.
5. The full-size propeller blade icing wind tunnel test method according to claim 1, wherein in the wind tunnel test, the test wind speed is determined by the following method:
the forward flight speed of the real airplane and the linear speed of the blade rotating around the rotation axis of the engine are combined to obtain the real speed of the single blade, namely the wind speed in the wind tunnel test.
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| FR2940437B1 (en) * | 2008-12-22 | 2013-02-15 | Airbus France | TOOL, TOOL ASSEMBLY, AND METHOD OF ADJUSTING THE FLANGE OF BLADES OF A MODEL PROPELLER |
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