CN114526920B - Method for testing asymmetric loading fatigue strength of fan blade in vacuum environment - Google Patents
Method for testing asymmetric loading fatigue strength of fan blade in vacuum environment Download PDFInfo
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- CN114526920B CN114526920B CN202210158927.2A CN202210158927A CN114526920B CN 114526920 B CN114526920 B CN 114526920B CN 202210158927 A CN202210158927 A CN 202210158927A CN 114526920 B CN114526920 B CN 114526920B
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- 238000012360 testing method Methods 0.000 title claims abstract description 30
- 238000011068 loading method Methods 0.000 title claims abstract description 28
- 238000000034 method Methods 0.000 title claims abstract description 19
- 238000009661 fatigue test Methods 0.000 claims abstract description 26
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 13
- 230000007246 mechanism Effects 0.000 claims abstract description 13
- 239000010959 steel Substances 0.000 claims abstract description 13
- 230000005284 excitation Effects 0.000 claims abstract description 5
- 239000000463 material Substances 0.000 claims abstract description 5
- 239000000853 adhesive Substances 0.000 claims description 7
- 230000001070 adhesive effect Effects 0.000 claims description 7
- 230000011218 segmentation Effects 0.000 claims description 3
- 230000001143 conditioned effect Effects 0.000 claims 1
- 230000005540 biological transmission Effects 0.000 abstract description 2
- 150000001875 compounds Chemical class 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 125000004122 cyclic group Chemical group 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
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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
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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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
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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- 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
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Combustion & Propulsion (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a method for testing asymmetric loading fatigue strength of a fan blade in a vacuum environment, which comprises the following steps of radially segmenting the fan blade, and calculating centrifugal load and applied load of each section after the density and the rotating speed of a given material; determining the maximum bearing capacity of a single anchor point through a test, obtaining the preliminary position of each anchor point according to the cross section centroid of the fan blade, and determining the specific position of each anchor point and the minimum applied load and the maximum applied load value of each anchor point by combining with anchor point load linear programming; installing the fan blade in the fatigue test device, and fixing an anchor point; after the fatigue test device heats up and achieves a vacuum environment, the excitation frequency and the thrust of the fan blade are given, and meanwhile, the minimum applied load and the maximum applied load of each anchor point are given according to the circulation frequency, so that a test result is obtained. According to the invention, load transmission and control are realized through the steel wire pulley mechanism, and the load borne by the asymmetric anchor point is combined with the vibration table to realize an asymmetric loading fatigue test.
Description
Technical Field
The invention relates to the technical field of aero-engine design, in particular to a method for testing asymmetric loading fatigue strength of a fan blade in a vacuum environment.
Background
The fan blade structure of modern aero-engine is thin, centrifugal load is big, especially big duct is than fan blade, and its vibration and low cycle life problem are outstanding. The centrifugal stress field of the fan blade is gradually reduced from the blade root to the blade tip, and the traditional low-cycle fatigue test of the fan blade cannot accurately simulate the centrifugal stress field of the fan blade, so that the test result has limitation on the service life evaluation of the fan blade.
At present, the high-low cycle compound fatigue test of the fan blade mostly adopts the blade tip loading centrifugal force, and the blade body is provided with a vibration exciter to realize the high-low cycle compound fatigue test of the blade.
Disclosure of Invention
In order to reduce air flow disturbance caused in the vibration process of the blade, the test piece is required to be carried out in a heated vacuum environment, and asymmetric loading is realized through the steel wire pulley mechanism.
In order to achieve the above purpose, the invention provides a method for testing asymmetric loading fatigue strength of a fan blade in a vacuum environment, comprising the following steps:
1. radial segmentation is carried out on the fan blades, and centrifugal load and applied load of each section are calculated after the density and the rotating speed of the materials are given;
2. determining the maximum bearing capacity of a single anchor point through a pulling test, thereby determining the number of anchor points required by each section, obtaining the preliminary position of each anchor point according to the section centroid of the blade, and determining the specific position of each anchor point and the minimum applied load and the maximum applied load value of the anchor point by combining with the linear programming of the anchor point load;
3. installing the fan blade in the fatigue test device, and fixing an anchor point;
4. after the fatigue test device heats up and achieves a vacuum environment, the excitation frequency and the thrust of the fan blade are given, and meanwhile, the minimum applied load and the maximum applied load of each anchor point are given according to the circulation frequency, so that a test result is obtained.
The centrifugal load of each section in the first step adopts the formula f=mω 2 R is calculated, and the applied load is obtained by subtracting the centrifugal load of the next section from the centrifugal load of the current section.
Wherein: f is the centrifugal load of the section; m is the segment mass; omega is the angular velocity; r is the centroid radius.
And in the second step, the anchor point load linear programming is carried out on the condition that each anchor point of the same section does not generate additional moment in the X direction after the load is applied.
And in the fourth step, the minimum applied load of the anchor point is 1.56% of the maximum applied load of the anchor point.
And in the fourth step, the anchor points respectively correspond to a group of steel wire pulley mechanisms, and each group of steel wire pulley mechanisms applies corresponding pulling force to each anchor point according to the circulation frequency.
The fatigue test device comprises a vibrating table and a steel wire pulley mechanism, wherein the vibrating table is used for fixing the fan blade through a clamp, the steel wire pulley mechanism comprises a traction rope, one end of the traction rope is connected with an anchor point on the fan blade, and the other end of the traction rope is connected with a hydraulic rod through a pulley.
The anchor point adopts the sticky mode to fix on fan blade surface, and the anchor point includes the bonding board, bonding board surface mounting has rings and lock nut, and lock nut is located rings top.
The fatigue test device is arranged in the vacuum box, and the pulley and the hydraulic rod are supported and fixed through the framework.
The top of the vacuum box is connected with a vacuum pump and a hydraulic pump through different pipelines respectively.
And a resistance wire controlled by a temperature controller is arranged in the vacuum box, and the hydraulic pump is communicated with the hydraulic rod and controlled by a hydraulic servo controller.
The invention has the beneficial effects that:
1. according to the invention, a centrifugal stress field of the fan blade is applied to the blade body through a sectional loading method, load transmission and control are realized by utilizing a steel wire pulley mechanism, the load borne by an asymmetric anchor point is combined with a vibrating table to realize an asymmetric loading fatigue test, and meanwhile, vacuum and heating environments are introduced to realize accurate simulation of the working environment of the fan blade.
2. The test method can be popularized to a high-low cycle compound fatigue test of the asymmetric loading low cycle fatigue test of the fan blade and other large-size structural parts, and can effectively solve the problem of life-fixing of the fan blade.
Drawings
Fig. 1 is a schematic view of a radial segment of a fan blade according to the present invention.
Fig. 2 is a schematic view of a wire pulley mechanism provided by the present invention.
Fig. 3 is a diagram showing the location and quantity distribution of anchor points according to the present invention.
Fig. 4 is a schematic diagram of an anchor point position design according to the present invention.
FIG. 5 is a chart of a low cycle fatigue test of a fan blade according to the present invention.
FIG. 6 is a graph of stress field contrast for three loading modes provided by the present invention.
Fig. 7 is a schematic diagram of a fatigue test apparatus according to the present invention.
Fig. 8 is a schematic diagram of an anchor structure provided in the present invention.
FIG. 9 is a schematic view of a fatigue test apparatus provided in the present invention in a vacuum heated environment.
In the figure: 1-anchor point, 11-bonding plate, 12-hanging ring, 13-locking nut, 2-traction rope, 3-pulley, 4-hydraulic rod, 5-vibration table, 6-clamp, 7-vacuum box, 8-vacuum pump, 9-hydraulic pump and 10-control table
Detailed Description
Specific embodiments of the invention will be further described with reference to the drawings, but the scope of the claims is not limited thereto.
Example 1
The invention provides a method for testing asymmetric loading fatigue strength of a fan blade in a vacuum environment, which comprises the following steps:
1. radial segmentation of fan blades, given material density and rotational speed, using the formula f=mω 2 R calculates centrifugal load of each section and further obtains applied load of each section as shown in fig. 1:
specifically, the blade is divided into 11 sections based on the bottom surface of the blade root, and 10 sections are formed, and the radial distance between each section is 100mm. Using the formula f=mω 2 R is calculated to obtain the centrifugal load of each section, wherein the density of the material is 4440kg/m 3 The mass m and the radius R of the mass center of each segment are read through a three-dimensional model of the blade, such as UG software analysis, measuring body function, the rotating speed n is 4000 revolutions per minute, the angular speed omega = n is 2 pi/60, and the section applied load is obtained by subtracting the centrifugal load of the next section from the centrifugal load of the present section.
TABLE 1 maximum centrifugal load and load applied values applied to respective sections
| Cross section of | Centrifugal load in cross section | Section applied load | Cross section of | Centrifugal load in cross section | Section applied load |
| 1 | 8611300N | 886100N | 6 | 2666000N | 949200N |
| 2 | 7725200N | 1136600N | 7 | 1716800N | 616400N |
| 3 | 6588600N | 1311200N | 8 | 1100400N | 431080N |
| 4 | 5277400N | 1371400N | 9 | 669320N | 350420N |
| 5 | 3906000N | 1240000N | 10 | 318900N | 318900N |
Wherein the minimum centrifugal load and the applied load value of each section are 1.56% of the maximum centrifugal load and the applied load value of the section, and the rotation speed n is calculated to be 500 revolutions per minute.
TABLE 2 minimum centrifugal load and applied load values applied to respective sections
| Cross section of | Centrifugal load in cross section | Section applied load | Cross section of | Centrifugal load in cross section | Section applied load |
| 1 | 134550N | 13840N | 6 | 41657N | 14832N |
| 2 | 120710N | 17760N | 7 | 26825N | 9632N |
| 3 | 102950N | 20490N | 8 | 17193N | 6735N |
| 4 | 82460N | 21428N | 9 | 10458N | 5475.2N |
| 5 | 61032N | 19375N | 10 | 4982.8N | 4982.8N |
2. Determining the maximum bearing capacity of a single anchor point through a pulling test, thereby determining the number of anchor points required by each section, obtaining the preliminary position of each anchor point according to the section centroid of the blade, and determining the specific position of each anchor point by utilizing the condition that each anchor point of the same section does not generate additional moment in the X direction after loading is applied:
specifically, the maximum bearing capacity of an anchor point is tested by a pull test through a steel wire pulley mechanism, as shown in fig. 2, the anchor point is arranged on the surface of a blade in an adhesive mode, a traction rope tied on the anchor point is connected to a hydraulic rod through a pulley, the maximum bearing capacity of a single anchor point is determined to be 400kN through the tension force applied by the hydraulic rod, the maximum applied load value of each section is divided by the maximum load bearable by the anchor point, the number of anchor points required by each section is calculated, the position of the anchor point is primarily determined by utilizing the centroid of the section, the anchor points are all arranged on the front edge and the tail edge of the fan blade, the steel wire friction on the surface of the blade is prevented, the error of the test result is avoided, and the number of anchor points and the primary position distribution of the surface of the blade are shown in fig. 3.
The anchor point position and the minimum applied load and the maximum applied load value are designed by taking the section A as an example. As shown in fig. 4, with the moment balance in the X direction and the Y direction as constraint conditions, using Excel to perform linear programming solution of anchor load, preferably ensuring the moment balance in the X direction, where the solution conforming to the constraint conditions is (M1, M2, M3, M4) = (282916.7n, 400000n,228283.3 n), where m1+m2+m3+m4=maximum applied load of section a, satisfying the moment balance in the X direction: 282916.7n×230mm+400000n×180 mm= 137070833n·mm=400000n×200mm+228283.3n×250mm, each anchor point having a minimum applied load of 1.56% of the maximum applied load of that anchor point. Although the influence degree of the residual moment of the unbalanced moment in the Y direction on the whole stress of the blade is smaller, the residual moment in the Y direction is reduced to the greatest extent, so that a better test effect is achieved, the minimum residual moment in the Y direction is 400000N multiplied by 23.18mm+228283.3N multiplied by 1.55mm-282916.7N multiplied by 93.17mm+400000N multiplied by 67.57 mm= -44469185 N.mm, and the specific position of each anchor point and the minimum applied load and the maximum applied load value thereof are obtained through the above process.
3. The method comprises the steps of installing a blade in a fatigue test device, fixing anchor points, and transmitting load borne by the anchor points through a traction rope, wherein one anchor point corresponds to a group of hydraulic rods;
4. after the fatigue test device heats up and achieves a vacuum environment, the excitation frequency and the thrust of the fan blade are given, and meanwhile, the minimum applied load and the maximum applied load of each anchor point are given according to the circulation frequency, so that a test result is obtained.
Specifically, the residual pressure in the vacuum box is controlled to be not more than 0.01MPa by a vacuum pump, and the control console heats the resistance wire to 80 ℃. The excitation frequency of the vibration table is 67Hz, the thrust is 15 tons, the minimum applied load and the maximum applied load of each anchor point are obtained in the second step, the corresponding load is applied to the anchor points by the hydraulic rod, the asymmetric cyclic loading is started according to the low cyclic fatigue test spectrum of the fan blade shown in fig. 5, the anchor points are stopped for 3s at the minimum applied load and the maximum applied load, and the total test times are 1206 times until the fan blade is damaged by fatigue.
As shown in FIG. 6, the stress field generated by the invention and the stress field generated by the blade tip loading are sequentially centrifugal stress field, and the stress field generated by centrifugal load cannot be effectively simulated by the blade tip loading mode, and the stress size and the stress position of the checking point cannot be accurately simulated. The stress field generated by the invention can better simulate the real centrifugal stress field, the stress of the maximum stress point of the root of the blade can be checked in place, the high-low cycle compound working condition of the main vibration mode superposition centrifugal stress of the fan blade can be better simulated, the accurate simulation of the working environment of the fan blade is realized, and the service life fixing problem of the fan blade is effectively solved.
The fatigue test device is shown in fig. 7, and comprises a vibrating table 5, wherein a blade is fixed on the vibrating table 5 through a clamp 6, the load is transmitted through a traction rope, one end of the traction rope 2 is connected with an anchor point 1 on the blade, the other end of the traction rope is connected with a hydraulic rod 4 for applying the load, a pulley structure is adopted between the anchor point 1 and the hydraulic rod 4, and the load borne by an asymmetric anchor point is combined with the vibrating table to realize an asymmetric loading fatigue test.
The anchor point 1 comprises an adhesive plate 11, a hanging ring 12 and a locking nut 13 are arranged on the surface of the adhesive plate 11, the locking nut 13 is positioned at the top of the hanging ring 12, and the anchor point is fixed on the surface of the blade in an adhesive mode, as shown in fig. 8.
The fatigue test device is arranged in a vacuum box 7, wherein a pulley 3 and a hydraulic rod 4 are supported and fixed through a framework, and the top of the vacuum box 7 is connected with a vacuum pump 8 and a hydraulic pump 9 through different pipelines respectively; a resistance wire controlled by a temperature controller is arranged in the vacuum box 7 to heat the blade; the hydraulic pump 9 is communicated with the hydraulic rod and is controlled by a hydraulic servo controller, and the hydraulic servo controller comprises a PLC programmable controller, an oil pressure sensor and an electromagnetic valve. The console 10 includes a control panel, a display, and a computer connected to the temperature controller and the hydraulic servo controller, as shown in fig. 9.
Claims (10)
1. A method for testing the asymmetric loading fatigue strength of a fan blade in a vacuum environment is characterized by comprising the following steps:
1. radial segmentation is carried out on the fan blades, and centrifugal load and applied load of each section are calculated after the density and the rotating speed of the materials are given;
2. determining the maximum bearing capacity of a single anchor point through a pulling test, thereby determining the number of anchor points required by each section, obtaining the preliminary position of each anchor point according to the section centroid of the blade, and determining the specific position of each anchor point and the minimum applied load and the maximum applied load value of the anchor point by combining with the linear programming of the anchor point load;
3. installing the fan blade in the fatigue test device, and fixing an anchor point;
4. after the fatigue test device heats up and achieves a vacuum environment, the excitation frequency and the thrust of the fan blade are given, and meanwhile, the minimum applied load and the maximum applied load of each anchor point are given according to the circulation frequency, so that a test result is obtained.
2. The method for testing the asymmetrical loading fatigue strength of a fan blade in a vacuum environment according to claim 1, wherein the centrifugal load of each section in the step one is expressed by the formula f=mω 2 R is calculated, and the applied load is obtained by subtracting the centrifugal load of the next section from the centrifugal load of the current section;
wherein: f is the centrifugal load of the section; m is the segment mass; omega is the angular velocity; r is the centroid radius.
3. The method for testing the asymmetrical loading fatigue strength of the fan blade in the vacuum environment according to claim 1, wherein the anchor point load linear programming in the second step is conditioned on that each anchor point of the same cross section does not generate additional moment in the X direction after the load is applied.
4. The method for testing the asymmetrical loading fatigue strength of a fan blade in a vacuum environment according to claim 1, wherein the minimum applied load of the anchor point in the fourth step is 1.56% of the maximum applied load of the anchor point.
5. The method for testing the asymmetrical loading fatigue strength of the fan blade in the vacuum environment according to claim 1, wherein the anchor points in the fourth step correspond to a group of steel wire pulley mechanisms respectively, and each group of steel wire pulley mechanisms applies corresponding loads to each anchor point according to the circulation frequency.
6. The method for testing the asymmetric loading fatigue strength of the fan blade in the vacuum environment according to claim 1, wherein the fatigue testing device comprises a vibrating table (5) and a steel wire pulley mechanism, the fan blade is fixed by the vibrating table (5) through a clamp (6), the steel wire pulley mechanism comprises a traction rope (2), one end of the traction rope (2) is connected with an anchor point (1) on the fan blade, and the other end of the traction rope is connected with a hydraulic rod (4) through a pulley (3).
7. The method for testing the asymmetric loading fatigue strength of the fan blade in the vacuum environment according to claim 6, wherein the anchor point (1) is fixed on the surface of the fan blade in an adhesive mode, the anchor point (1) comprises an adhesive plate (11), a hanging ring (12) and a locking nut (13) are arranged on the surface of the adhesive plate, and the locking nut (13) is located at the top of the hanging ring (12).
8. The method for testing the asymmetric loading fatigue strength of the fan blade in the vacuum environment according to claim 7, wherein the fatigue testing device is arranged in a vacuum box (7), and the pulley (3) and the hydraulic rod (4) are supported and fixed through a framework.
9. The method for testing the asymmetric loading fatigue strength of the fan blade in the vacuum environment according to claim 8, wherein the top of the vacuum box (7) is connected with a vacuum pump (8) and a hydraulic pump (9) through different pipelines respectively.
10. The method for testing the asymmetrical loading fatigue strength of the fan blade in the vacuum environment according to claim 9, wherein a resistance wire controlled by a temperature controller is arranged in the vacuum box (7), and the hydraulic pump (9) is communicated with the hydraulic rod and controlled by a hydraulic servo controller.
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| CN114705473B (en) * | 2022-06-07 | 2022-08-26 | 中国飞机强度研究所 | Airplane vibration superposition fatigue strength testing system and low-rigidity load applying method thereof |
| CN115452627A (en) * | 2022-10-10 | 2022-12-09 | 沈阳航空航天大学 | Method for determining loading frequency range of magnesium alloy component in engineering |
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| US6679121B2 (en) * | 2000-07-07 | 2004-01-20 | Test Devices, Inc. | Blade vibration test apparatus and method |
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