CN213933708U - Ultrasonic detection reference block for heterogeneous inertia friction welding line of turbine rotor of aircraft engine - Google Patents
Ultrasonic detection reference block for heterogeneous inertia friction welding line of turbine rotor of aircraft engine Download PDFInfo
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- CN213933708U CN213933708U CN202021045527.3U CN202021045527U CN213933708U CN 213933708 U CN213933708 U CN 213933708U CN 202021045527 U CN202021045527 U CN 202021045527U CN 213933708 U CN213933708 U CN 213933708U
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Abstract
The heterogeneous inertia friction welding seam ultrasonic phased array of aeroengine turbine rotor subassembly detects uses the whole arc structure that is of reference block, and the reference block material is GH4169 superalloy and FGH97 powder superalloy respectively, and its structure and size are the exact same with waiting to detect work piece inertia friction welding seam department, the actual detection operating mode of the heterogeneous inertia friction welding seam of full simulation turbine rotor subassembly. The utility model discloses a heterogeneous inertia friction welding seam ultrasonic phased array of turbine rotor subassembly detects uses contrast test block for the local structure in complete turbine rotor subassembly inertia friction welding seam district, has characteristics such as small and exquisite light, simple structure and size precision height, can detect the instrument that provides the detection frequency of high accuracy, gain and gate value and the calibration work of probe combination sensitivity for the ultrasonic phased array of the heterogeneous inertia friction welding seam of turbine rotor subassembly.
Description
Technical Field
The utility model relates to a heterogeneous inertia friction welding seam ultrasonic testing reference block of aeroengine turbine rotor.
Background
Aeroengine turbine rotor subassembly manufacturing materials are mostly materials such as superalloy and powder superalloy, have that grain structure is thick, and the acoustic impedance is higher characteristic, leads to the ultrasonic wave to have great energy attenuation in superalloy and powder superalloy material inside propagation process, leads to the ultrasonic testing precision of this kind of material to seriously reduce, is unfavorable for the effective detection to inside little defect. Secondly, the width of the fusion line of the inertia friction welding line is on the micron scale, the size of the inertia friction welding line is far smaller than that of the fusion welding line, meanwhile, the inertia friction welding line of the heterogeneous material has larger acoustic impedance difference, so that the welding line still can generate larger reflection echo to the ultrasonic wave even in the absence of defects, thereby forming pseudo defects, and the defects on the inertia friction welding line also have the characteristics of small size, two-dimensional distribution and dispersion distribution. In addition, the inertia friction welding seam of the turbine rotor assembly of the aircraft engine and the structure form of the nearby space are complex, the effective detection space is narrow, and the arrangement of an ultrasonic detection probe and the good propagation of ultrasonic waves are not facilitated. The above multiple adverse factors all result in the unable effective ultrasonic testing who realizes the tiny defect of aeroengine turbine rotor subassembly heterogeneous inertia friction welding seam, have seriously influenced inertia friction welding process and have welded the application in aeroengine turbine rotor subassembly.
As a novel nondestructive testing technology newly developed in recent years, a phased array probe of the ultrasonic phased array testing technology is provided with a plurality of piezoelectric wafers which are independent from each other, and each piezoelectric wafer can finish the transmission and the reception of ultrasonic waves under the coordination of a digital control system, so that the real-time dynamic change of the focusing and the deflection of a plurality of ultrasonic beams in a workpiece is realized. Compared with the ultrasonic detection of a conventional single crystal probe, the focused sound beam of the ultrasonic phased array has higher energy density, higher detection sensitivity and precision on the tiny defects, is more suitable for detecting the tiny defects on the inertia friction welding seam of the rotor assembly of the aircraft engine, and has higher detectable rate on the defects of possible tiny size cracks, flaky oxide slag inclusion and the like on the welding seam. In addition, the artifical defect size of contrast test block is great for the calibration of conventional ultrasonic testing detectivity, structural style is single and different with the curved surface structure of inertia friction welding seam, can not realize the effective unity of calibration condition and waiting to detect the welding seam, and the artifical defect size on the current conventional contrast test block is also great in addition, the heterogeneous inertia friction welding seam of satisfying aeroengine turbine rotor subassembly that can not be better is to the high calibration precision requirement of detectivity, also can reduce the relevance ratio to the small defect of inertia friction welding seam simultaneously.
At present, the prior art has not realized unified standard aiming at a reference block for inertia friction weld ultrasonic phased array detection of a solid phase welding process, and the reference block for conventional fusion weld ultrasonic detection is mostly adopted to calibrate the detection sensitivity, but the defect size on the inertia friction weld is smaller, and the artificial defect on the reference block for conventional fusion weld ultrasonic detection cannot improve the higher calibration precision required by the inertia friction weld ultrasonic detection. In addition, the defects on the inertia friction welding seam of the high-temperature alloy material are mostly micro cracks distributed in the axial direction or the circumferential direction and extremely thin flaky oxide slag inclusion. Therefore, axial and circumferential artificial grooves are respectively etched on the inner surface and the outer surface of the test block to simulate the defect types and distribution states of microcracks, oxide slag inclusion and the like on the inertia friction weld joint.
Disclosure of Invention
The utility model aims at providing a heterogeneous inertia friction welding seam ultrasonic phased array of aeroengine turbine rotor subassembly detects contrast test block of usefulness provides a calibration work of easy operation, quick and high accuracy before detecting for the heterogeneous inertia friction welding seam ultrasonic phased array of engine turbine rotor, makes the combined sensitivity between probe frequency, gain and the gate value in the detection reach the optimum, improves the detection precision of the small size defect of the heterogeneous inertia friction welding seam of turbine rotor. The technical scheme of the utility model is that: a heterogeneous inertia friction welding line ultrasonic detection reference block of an aircraft engine turbine rotor is characterized in that the inner surface and the outer surface of the reference block are of a curved surface arc structure, an inertia friction welding line W is arranged on the outer surface of the arc structure of the reference block at a position 50mm of a reference surface B, a step a is arranged on the outer surface of the arc structure within a 30mm interval of the reference surface B, the first width of the step a is 11:30mm, a step B is arranged on the outer surface of the arc structure at a position 72mm of the reference surface B, and the second width of the step B is 18:8 mm; a first rectangular groove 1-1 is arranged on the outer surface of the inertial friction welding seam W of the reference block, and the distance from the first straight line of the reference plane C is 15: 34mm, second rectangular groove 2-1, second linear spacing from datum plane C16: 69mm, third rectangular groove 3-1, third linear spacing 17 from datum plane C: 104mm, a fourth rectangular groove 1-2 is arranged on the inner surface of the inertial friction welding seam W of the reference block, and the distance from the first straight line of the reference plane C is 15: 34mm, fifth rectangular groove 2-2, second linear spacing from datum plane C of 16: 69mm, sixth rectangular groove 3-2, third linear spacing 17 from datum level C: 104 mm.
The sizes of the arc surface radius and the arc wall thickness in the arc structure comparison test block are R1 respectively: 105mm corresponds to C3: 23.5 mm; r2: 89.5mm for C1: 8 mm; r3: 94.5mm for C2: 13 mm; arc radius R4 of the inner surface of the arc structure: 81.5 mm.
The rectangular slots comprise three size types, wherein the length, width and height of the size of the first rectangular slot 1-1 and the fourth rectangular slot 1-2 are: 0.94 plus or minus 0.02mm plus or minus 0.15 plus or minus 0.02mm plus or minus 0.3 plus or minus 0.02mm, the second rectangular groove 2-1 and the fifth rectangular groove 2-2 are 0.63 plus or minus 0.02mm plus or minus 0.15 plus or minus 0.02mm plus or minus 0.2 plus or minus 0.02mm in length, width and height, and the third rectangular groove 3-1 and the sixth rectangular groove 3-2 are 0.4 plus or minus 0.02mm plus or minus 0.15 plus or minus 0.03mm plus or minus 0.1 plus or minus 0.02mm in length, width and height.
The first rectangular groove 1-1, the fifth rectangular groove 2-2 and the sixth rectangular groove 3-2 are circumferentially distributed notches, the length direction of the rectangular grooves is parallel to the outer circle surface of the reference block, the fourth rectangular groove 1-2, the second rectangular groove 2-1 and the third rectangular groove 3-1 are axially distributed notches, and the length direction of the rectangular grooves is perpendicular to the outer circle surface of the reference block.
Principle of operation
The array probe is controlled by an electronic system of the ultrasonic flaw detector to send out a focused beam, the focused beam can generate echo reflection when encountering the defects of the rectangular grooves on the inner surface and the outer surface of the welding seam in the internal propagation process of the comparison test block along the circumferential direction, and the detection frequency, the detection gain and the detection gate value are adjusted by the relative ratio of the height of the reflected echo to the size and the depth of the known defects of the rectangular grooves, so that the parameters such as the detection frequency gain and the detection gate value reach the optimal detection value. Wherein the artifacts on the reference block act as both a reflection of the focused beam and a size contrast.
Technical effects
The utility model discloses aeroengine turbine rotor subassembly is FGH97 powder superalloy and GH4169 superalloy dissimilar material manufacturing to through inertia friction welding process with two rotating parts welding one-piece structures of FGH97 powder superalloy and GH4169 superalloy, the inside and outside surface of welding seam is the curved surface shape, and the welding seam about both sides space narrowly all have the step to exist, has seriously restricted laying of probe and the transmission process of ultrasonic beam inside the work piece. Secondly, the high temperature summation of the powder FGH97 as the material for manufacturing the turbine rotor assembly and the grain structure of the GH4169 high-temperature alloy material are coarse, the acoustic impedance is high, the ultrasonic beam has large energy attenuation when propagating in the turbine rotor assembly, and the effective detection of the micro-size defects is not facilitated. Meanwhile, the inertia friction welding seam of the heterogeneous material has larger acoustic impedance difference, so that the welding seam still can generate larger reflection echo to the ultrasonic wave under the condition of no defect, thereby forming a pseudo defect, and the defect on the inertia friction welding seam has the characteristics of small size, two-dimensional distribution and dispersion distribution. The above multiple adverse factors all result in the unable effective ultrasonic testing who realizes the tiny defect of aeroengine turbine rotor subassembly heterogeneous inertia friction welding seam, have seriously influenced inertia friction welding process and have welded the application in aeroengine turbine rotor subassembly.
The problem that the heterogeneous inertia friction welding seam ultrasonic phased array detection of the turbine rotating part is difficult is solved, and the situation that the material, the structure and the artificial defect size of a conventional reference block are not appropriate is solved. A local area of an inertia friction welding joint of a turbine rotor without welding defects is processed to manufacture a reference block for ultrasonic detection. On the manufacturing material of the comparison test block, the FGH97 powder superalloy and GH4169 superalloy which are completely the same as the actual turbine rotor component to be detected are adopted, so that the comparison test block and the workpiece to be detected have completely the same acoustic impedance characteristics, and the ultrasonic wave has the same attenuation coefficient as the actual workpiece in the propagation process in the comparison test block; in the design of structural shape and size, the reference block is completely taken from the local structural size of the actual workpiece to be detected in the whole circumferential direction, has the structural characteristics and size completely the same as those of the actual workpiece, and can fully simulate the reflection condition of the structural characteristics of the ultrasonic beam on the sound beam in the process of propagating the ultrasonic beam in the workpiece. Therefore, the reference block fully simulates the actual working condition of the inertia friction welding seam of the turbine rotor assembly in material, structural shape and size. Meanwhile, the rectangular groove defects with the same size and different distribution directions are processed on the inner surface and the outer surface of the same position of the welding line, the minimum size of the rectangular groove defects is smaller than the size of artificial defects on a conventional test block, the calibration precision before detection can be greatly improved, and the possibility is provided for detecting tiny defects on heterogeneous inertia friction welding lines. The utility model discloses a heterogeneous inertia friction welding seam for ultrasonic testing of turbine rotor is the local arc structure of actual work piece with reference test block, the surface radius of reference test block welding seam department is 89.5mm, internal surface radius is 81.5mm, welding seam left side step width is 30mm, welding seam right side step width is 8mm, the step size of the inside and outside footpath size of welding seam department and both sides is the same completely with turbine rotor waits to detect regional relevant dimensional parameter, the reference test block of abundant assurance with wait to detect the uniformity of work piece. Meanwhile, rectangular grooves with the sizes of 0.94mm multiplied by 0.15mm multiplied by 0.3mm, 0.63mm multiplied by 0.15mm multiplied by 0.2mm and 0.4mm multiplied by 0.15mm multiplied by 0.1mm are respectively arranged on the inner surface and the outer surface of the welding line W of the reference block to simulate the crack defects with different sizes on the inertia friction, the defects of the two rectangular grooves on the inner side and the outer side of the same welding line position can accurately display the welding line position with extremely small width on a fluorescent screen of a flaw detector, the detection and calibration accuracy of the ultrasonic phased array of the inertia friction welding line of the turbine rotor assembly can be improved to the maximum extent, and the detection rate of the micro-size crack defects on the heterogeneous inertia friction welding line is improved. Therefore, the utility model discloses a heterogeneous inertia friction welding seam ultrasonic phased array of turbine rotor detects with reference to the test block can realize frequency, gain and gate value isoparametric before detecting quick, accurate calibration work.
Drawings
Fig. 1 is the utility model discloses a front view of comparison test block design paper.
Fig. 2 is the utility model discloses an axial section of comparison test block design paper.
Detailed Description
To the function of this reference block, it is right through the example the utility model discloses do the detailed description.
As shown in fig. 1, for reference test block design drawing main view, fig. 2 is reference test block design drawing, fig. 2 is shown for the axial planing surface picture on the basis of fig. 1, the reference test block for the ultrasonic testing of the heterogeneous inertia friction weld of the turbine rotor comprises a test block body and two parts of artificial defects, the test block body structure is an arc-shaped curved surface structure and is provided with an inertia friction weld W, and the axial dimension of the reference test block and the radius dimension of the inner and outer surfaces of the arc are completely the same as the inertia friction weld of the workpiece to be tested.
As shown in figure 1, the ultrasonic testing reference block for the heterogeneous inertia friction welding seam of the turbine rotor of the aircraft engine is characterized in that: the inner surface and the outer surface of the reference block are of curved surface arc structures, an inertia friction welding seam W is arranged on the outer surface of the arc structure of the reference block at a position 50mm away from a reference surface B, a step a is arranged on the outer surface of the arc structure within a 30mm interval of the reference surface B, the first width of the step a is 11:30mm, a step B is arranged on the outer surface of the arc structure at a position 72mm away from the reference surface B, and the second width of the step B is 18:8 mm; a first rectangular groove 1-1 is arranged on the outer surface of the inertial friction welding seam W of the reference block, and the distance from the first straight line of the reference plane C is 15: 34mm, second rectangular groove 2-1, second linear spacing from datum plane C16: 69mm, third rectangular groove 3-1, third linear spacing 17 from datum plane C: 104mm, a fourth rectangular groove 1-2 is arranged on the inner surface of the inertial friction welding seam W of the reference block, and the distance from the first straight line of the reference plane C is 15: 34mm, fifth rectangular groove 2-2, second linear spacing from datum plane C of 16: 69mm, sixth rectangular groove 3-2, third linear spacing 17 from datum level C: 104 mm.
As shown in fig. 2, the sizes of the arc-shaped structure comparative test block corresponding to the radius of the outer surface of the arc-shaped surface and the wall thickness of the arc-shaped surface are R1: 105mm corresponds to C3: 23.5 mm; r2: 89.5mm for C1: 8 mm; r3: 94.5mm for C2: 13 mm; arc radius R4 of the inner surface of the arc structure: 81.5 mm.
The heterogeneous inertia friction welding seam ultrasonic testing reference block of the turbine rotor of the aircraft engine is characterized in that: the materials that arc structure contrast test block inertia friction weld W both sides were adopted are M1 respectively: FGH97 powder superalloy and M2: GH4169 high temperature alloy.
Heterogeneous inertia friction welding seam ultrasonic testing reference block of aeroengine turbine rotor, characterized by: the rectangular slots comprise three size types, wherein the length, width and height of the size of the first rectangular slot 1-1 and the fourth rectangular slot 1-2 are: 0.94 plus or minus 0.02mm plus or minus 0.15 plus or minus 0.02mm plus or minus 0.3 plus or minus 0.02mm, the second rectangular groove 2-1 and the fifth rectangular groove 2-2 are 0.63 plus or minus 0.02mm plus or minus 0.15 plus or minus 0.02mm plus or minus 0.2 plus or minus 0.02mm in length, width and height, and the third rectangular groove 3-1 and the sixth rectangular groove 3-2 are 0.4 plus or minus 0.02mm plus or minus 0.15 plus or minus 0.03mm plus or minus 0.1 plus or minus 0.02mm in length, width and height.
The first rectangular groove 1-1, the fifth rectangular groove 2-2 and the sixth rectangular groove 3-2 are circumferentially distributed notches, the length direction of the rectangular grooves is parallel to the outer circle surface of the reference block, the fourth rectangular groove 1-2, the second rectangular groove 2-1 and the third rectangular groove 3-1 are axially distributed notches, and the length direction of the rectangular grooves is perpendicular to the outer circle surface of the reference block.
Before detection is carried out, proper array probes and wedge blocks are selected according to the size and the structure of a workpiece, the array probes and the wedge blocks are placed in a comparison test block area c, the array probes with different frequencies are replaced, gain and gate values are adjusted, and a group of array probe frequency, gain and gate value combination parameters with the minimum error between the ultrasonic detection size and the actual size of the artificial defect are found and serve as ultrasonic detection parameters of the actual workpiece.
Claims (4)
1. The utility model provides an aeroengine turbine rotor heterogeneous inertia friction welding seam ultrasonic testing reference block, characterized by: the inner surface and the outer surface of the reference block are of curved surface arc structures, an inertia friction welding seam W is arranged on the outer surface of the arc structure of the reference block at a position 50mm away from a reference surface B, a step a is arranged on the outer surface of the arc structure within a 30mm interval of the reference surface B, the first width (11) of the step a is 30mm, a step B is arranged on the outer surface of the arc structure at a position 72mm away from the reference surface B, and the second width (18) of the step B is 8 mm; the outer surface of the inertial friction welding seam W of the reference block is provided with a first rectangular groove (1-1) and a first linear interval (15) from the reference plane C: 34mm, second rectangular groove (2-1), second linear distance (16) from reference plane C: 69mm, third rectangular groove (3-1), third linear distance (17) from reference plane C: 104mm, a fourth rectangular groove (1-2) is arranged on the inner surface of the inertial friction weld W of the reference block, and the first linear distance (15) from the reference plane C is as follows: 34mm, fifth rectangular groove (2-2), second linear spacing (16) from reference plane C: 69mm, sixth rectangular groove (3-2), third linear distance (17) from reference plane C: 104 mm.
2. The ultrasonic testing reference block for the heterogeneous inertia friction welding seam of the turbine rotor of the aircraft engine as claimed in claim 1, wherein: the sizes of the arc surface radius and the arc wall thickness in the arc structure comparison test block are R1 respectively: 105mm corresponds to C3: 23.5 mm; r2: 89.5mm for C1: 8 mm; r3: 94.5mm for C2: 13 mm; arc radius R4 of the inner surface of the arc structure: 81.5 mm.
3. The ultrasonic testing reference block for the heterogeneous inertia friction welding seam of the turbine rotor of the aircraft engine as claimed in claim 1, wherein: the rectangular grooves comprise three size types, wherein the length, the width and the height of the size of the first rectangular groove (1-1) and the fourth rectangular groove (1-2) are respectively as follows: 0.94 plus or minus 0.02mm plus or minus 0.15 plus or minus 0.02mm plus or minus 0.3 plus or minus 0.02mm, the length, width and height of the second rectangular groove (2-1) and the fifth rectangular groove (2-2) are 0.63 plus or minus 0.02mm plus or minus 0.15 plus or minus 0.02mm plus or minus 0.2 plus or minus 0.02mm, and the length, width and height of the third rectangular groove (3-1) and the sixth rectangular groove (3-2) are 0.4 plus or minus 0.02mm plus or minus 0.15 plus or minus 0.03mm plus or minus 0.1 plus or minus 0.02 mm.
4. The ultrasonic testing reference block for the heterogeneous inertia friction welding seam of the turbine rotor of the aircraft engine as claimed in claim 1, wherein: the first rectangular groove (1-1), the fifth rectangular groove (2-2) and the sixth rectangular groove (3-2) are circumferentially distributed notches, the length direction of the rectangular grooves is parallel to the outer circle surface of the reference block, the fourth rectangular groove (1-2), the second rectangular groove (2-1) and the third rectangular groove (3-1) are axially distributed notches, and the length direction of the rectangular grooves is perpendicular to the outer circle surface of the reference block.
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| CN202021045527.3U CN213933708U (en) | 2020-06-09 | 2020-06-09 | Ultrasonic detection reference block for heterogeneous inertia friction welding line of turbine rotor of aircraft engine |
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| CN202021045527.3U CN213933708U (en) | 2020-06-09 | 2020-06-09 | Ultrasonic detection reference block for heterogeneous inertia friction welding line of turbine rotor of aircraft engine |
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