A method and system for phased array ultrasonic non-destructive testing of a gas turbine rotor blade

Abstract

The present application relates to the technical field of detection, in particular to a kind of smoke turbine moving blade phased array ultrasonic nondestructive testing method and system, method includes: selecting and moving blade corresponding simulation test block, according to simulation test block to phased array probe is verified processing, to each piece of to be examined smoke turbine moving blade is numbered and identified confirmation and pretreatment generates blade pretreatment record table;According to detection process parameter respectively to moving blade's blade main part and blade root transition part Fan-shaped scanning is implemented, obtains atlas data;Atlas data is judged to be defective type processing, according to the judgment result and blade pretreatment record table to each piece of moving blade is carried out comprehensive quality assessment, obtains detection result.This application utilizes the electronic deflection, dynamic focusing and multi-angle fan scanning characteristics of phased array technology, realize the effective sound beam coverage and imaging of blade full area, especially the curvature variation, thickness mutation blade body and root transition zone, improve the comprehensiveness and defect detection reliability of detection.

Description

Technical Field

[0001] This invention relates to the field of testing technology, and more specifically, to a phased array ultrasonic non-destructive testing method and system for flue gas turbine motor blades. Background Technology

[0002] Flue gas turbine blades operate under harsh conditions of high temperature, high pressure, and high-speed rotation, making them highly susceptible to internal and surface defects such as fatigue cracks, corrosion pits, and foreign object damage. If these defects are not detected and assessed in a timely manner, they can directly lead to blade breakage, increased unit vibration, and even serious accidents, causing significant economic losses and safety hazards. Current technologies for non-destructive testing of flue gas turbine blades primarily utilize methods such as ultrasonic testing, penetrant testing, magnetic particle testing, and conventional radiographic testing. While these methods can identify some surface or near-surface defects to a certain extent, they are insufficient to meet the comprehensive and reliable quality assessment requirements of blades under complex service conditions.

[0003] Existing non-destructive testing methods suffer from a severe mismatch between detection coverage and defect detection reliability when applied to moving blades of flue gas turbines. Due to the complex curved geometry, variable cross-section structure, and dramatic thickness variations in the transition zone between the blade body and root, existing detection methods are often limited by fixed incident angles and single scanning paths. This results in the sound beam or detection signal failing to effectively cover the entire blade area, especially in the root transition zone and deep internal locations where minute defects easily create detection blind spots or generate numerous geometric interference echoes. These interference signals are difficult to distinguish from the echoes of genuine defects, significantly increasing the probability of false positives or false negatives.

[0004] In summary, while existing non-destructive testing (NDT) technologies for turbine blades have seen some application, they still suffer from insufficient coverage and low overall reliability under complex geometries and high service stress conditions. Therefore, there is an urgent need for a NDT method that can adapt to complex blade shapes, achieve effective full-area coverage, and improve the accuracy of defect identification, in order to better ensure the long-term stable operation of the equipment. Summary of the Invention

[0005] The main objective of this invention is to provide a phased array ultrasonic non-destructive testing method and system for flue gas turbine blades, aiming to overcome the technical problems of insufficient detection coverage and low accuracy of defect judgment in the prior art.

[0006] To address the aforementioned problems, this invention proposes a phased array ultrasonic non-destructive testing method for turbine blades in flue gas systems, the method comprising: A simulated test block corresponding to the moving blade is selected, and the phased array probe is verified based on the simulated test block to obtain the detection process parameters; Each turbine blade to be inspected is numbered, identified, and pre-treated, and a blade pre-treatment record table is generated. According to the detection process parameters, a fan-shaped scan is performed on the main body of the moving blade and the transition part at the root of the blade to obtain spectral data; The defect type of the spectrum data is determined, and the quality of each moving blade is comprehensively evaluated based on the determination result and the blade pretreatment record table to obtain the test result. Further, the step of selecting a simulated test block corresponding to the moving blade, and verifying the phased array probe based on the simulated test block to obtain the detection process parameters includes: The material properties and geometric structure of the moving blade are analyzed, and a simulation test block corresponding to the moving blade is selected based on the analysis structure. Based on the simulated test block, the phased array probe and instrument are set and preliminarily calibrated to obtain preliminary detection parameters. The phased array probe includes a shear wave phased array probe and a longitudinal wave phased array probe. The simulated test block is subjected to sector-shaped verification processing using the preliminary detection parameters to obtain the corresponding detection process parameters.

[0007] Furthermore, the step of performing sector-shaped verification processing on the simulated test block using the preliminary detection parameters to obtain the corresponding detection process parameters further includes: Under the aforementioned preliminary detection parameters, the simulated test block is subjected to a sector scan by the shear wave phased array probe and the longitudinal wave phased array probe, respectively, to obtain echo signal data. The preliminary detection parameters are verified and adjusted based on the echo signal data to obtain qualified detection process parameters.

[0008] Furthermore, the step of numbering, identifying, and pre-processing each turbine blade to be inspected, and generating a blade pre-processing record table, includes: Each turbine blade to be inspected is assigned a serial number for identification. The identified turbine blades are then subjected to visual inspection to obtain the visual inspection results. Based on the visual inspection results, the moving blades are subjected to contaminant removal treatment to obtain clean blades. The sequence number, appearance inspection results, and cleanliness status of the blades are integrated to form the blade pretreatment record table.

[0009] Furthermore, the main body of the blade comprises a working surface and a back surface. The step of performing a fan-shaped scan on the main body of the moving blade according to the detection process parameters includes: According to the detection process parameters, shear wave fan-shaped scanning is performed on the working surface and back surface of the blade to obtain scanning pattern data of the working surface and back surface of the blade. During the sector scanning process, the probe posture is adjusted according to the change in the curvature of the moving blade. The scanning data of the working surface and back of the blade are synthesized from multiple angles, and the synthesized data is processed to correspond with the time axis to obtain the blade image data.

[0010] Furthermore, the transition portion at the leaf root is the junction between the leaf root and the leaf blade. The step of performing a fan-shaped scan on the transition portion at the leaf root of the moving blade according to the detection process parameters includes: Based on the detection process parameters, the longitudinal wave phased array probe at the root transition section of the blade is switched to a sector scan preparation process to obtain the longitudinal wave scan settings. According to the longitudinal wave scanning settings, a fan-shaped scan is performed on the transition portion of the blade root to obtain multiple types of scan pattern data; The root transition portion of the leaf is processed using multi-view data correspondence based on the multi-type scanning map data to obtain root transition map data; The root transition map data and the leaf map data are integrated and correlated to obtain the map data.

[0011] Furthermore, the step of performing defect type determination processing on the atlas data includes: Feature analysis was performed on the echo signals in the aforementioned spectral data to obtain defect echo feature data: The propagation path and beam angle of the ultrasonic wave are obtained based on the detection process parameters. The defect location information is then obtained by performing defect localization processing on the spectral data based on the defect echo characteristic data, the ultrasonic wave propagation path, and the beam angle. Based on the defect location information and the defect echo feature data, defect type identification processing is performed to obtain the defect type judgment result.

[0012] Furthermore, the step of comprehensively evaluating the quality of each moving blade based on the judgment result and the blade pretreatment record table to obtain the test result includes: The defect type judgment result is compared with the preset acceptance standard to obtain the single blade defect judgment result. The defect determination results of each individual blade are correlated with the appearance inspection results in the blade pretreatment record table to obtain the quality inspection results of each moving blade.

[0013] This invention also proposes a phased array ultrasonic non-destructive testing system for turbine blades, comprising: The verification module is used to select a simulated test block corresponding to the moving blade, and to perform verification processing on the phased array probe based on the simulated test block to obtain the detection process parameters. The processing module is used to number, identify, confirm, and pre-process each turbine blade to be inspected, and generate a blade pre-processing record table. The scanning module is used to perform fan-shaped scanning on the main body of the moving blade and the transition part at the root of the blade according to the detection process parameters to obtain spectral data; The evaluation module is used to determine the defect type of the spectrum data and to perform a comprehensive quality evaluation of each moving blade based on the determination result and the blade pretreatment record table to obtain the test result.

[0014] Compared with the prior art, this application has the following beneficial effects: This application proposes a phased array ultrasonic non-destructive testing method and system for flue gas turbine blades. This method overcomes the prominent problems of existing ultrasonic, penetrant, magnetic particle, and conventional X-ray testing methods in flue gas turbine blade applications, such as insufficient coverage due to fixed incident angles and single scanning paths, numerous geometric interference echoes, blind spots caused by deep micro-defects, and high rates of false positives and false negatives. By utilizing the electronic deflection, dynamic focusing, and multi-angle sector scanning characteristics of phased array technology, this method achieves effective acoustic beam coverage and high-resolution imaging of the entire blade area, especially the blade body and root transition area with dramatic curvature changes and abrupt thickness changes. This significantly improves the comprehensiveness of the inspection and the reliability of defect detection, and significantly reduces the risk of blade breakage, unit vibration, and even major safety accidents caused by the failure to detect defects such as internal fatigue cracks, corrosion pits, or foreign object damage in a timely manner. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] The structures, proportions, sizes, etc., shown in the accompanying drawings are only for the purpose of assisting those skilled in the art in understanding and reading the content disclosed in the specification, and are not intended to limit the implementation conditions of this application. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in the proportions, or adjustments to the size should still fall within the scope of the technical content disclosed in this application, provided that they do not affect the effects and purposes that this application can produce.

[0017] Figure 1This is a schematic diagram of the steps of a phased array ultrasonic non-destructive testing method for a flue gas turbine motor blade in one embodiment of the present invention; Figure 2 This is a schematic block diagram of a phased array ultrasonic non-destructive testing system for a flue gas turbine motorized blade according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the distribution of a simulated test block of a flue gas turbine motorized blade and an artificial defect groove in one embodiment of the present invention; Figure 4 This is a cross-sectional schematic diagram of a simulated test block of a flue gas turbine blade in one embodiment of the present invention.

[0018] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0020] Those skilled in the art will understand that, unless specifically stated otherwise, the singular forms “a,” “an,” “the,” and “the” used herein may also include the plural forms. It should be further understood that the term “comprising” as used in this specification means the presence of features, integers, steps, operations, elements, modules, and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, modules, components, and / or groups thereof. It should be understood that when an element is referred to as “connected” or “coupled” to another element, it may be directly connected or coupled to the other element, or there may be intermediate elements. Furthermore, “connected” or “coupled” as used herein may include wireless connection or wireless coupling. The term “and / or” as used herein includes all or any modules and all combinations of one or more associated listed items.

[0021] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless specifically defined as herein.

[0022] Reference Figure 1 This invention provides a phased array ultrasonic non-destructive testing method for turbine blades, comprising the following steps: S1: Select a simulated test block corresponding to the moving blade, and verify the phased array probe according to the simulated test block to obtain the detection process parameters; In step S1, before the actual blade is inspected, the performance and parameters of the inspection system are calibrated using a controllable reference object with known defects, thereby ensuring that the subsequent inspection of a large number of actual in-service blades yields reliable, repeatable, and highly consistent results. The simulated test block is a custom-made or selected reference block corresponding to the turbine blades of the flue gas turbine. The material properties of the simulated test block must be basically consistent with those of the real blade; it can be made of high-temperature alloys with the same or highly similar acoustic properties as the real blade, and its geometric structure must be highly similar, at least in the main areas to be tested (the thickness range of the blade body, the variation law of the blade body curvature radius, and the typical step height and angle of the blade root transition zone). The internal structure must have pre-fabricated artificial defects of known size, location, and orientation. These artificial defects are created through methods such as electrical discharge machining, wire cutting, laser etching, or embedding thin sheets. Common types include volumetric defects (such as flat-bottomed holes or side-drilled holes with an equivalent diameter of φ1.0mm~φ3.0mm, used to simulate inclusions and porosity) and area defects (such as artificial cracks or narrow slits of varying depths and lengths of 2mm~10mm, used to simulate fatigue cracks or stress corrosion cracks). The phased array probe is an ultrasonic transducer with a multi-element linear array or matrix array, capable of beam deflection, focusing, and scanning through electronic delay control. The specific implementation process of the verification process involves the inspector mounting the selected phased array probe on a dedicated scanning frame or encoder, ensuring good contact with the surface of the simulated test block via water immersion or contact coupling (using water-based or oil-based coupling agents); programming and inputting the focal law into the phased array flaw detector (defect detector), which defines the deflection angle, focusing depth, and number of emitting crystal groups for different sound beams; initiating a fan-shaped scan, allowing the sound beam to scan from a negative angle to a positive angle at a certain angular step (0.5°~1°), forming a fan-shaped coverage area. This area should be able to cover all critical depths and lateral positions of the pre-fabricated artificial defects in the simulated test block. During the scanning process, the instrument will collect data in real time in various display modes, including A-scan (a waveform of the echo amplitude at a single location over time (or sound path); sectorial scan (a fan-shaped image formed by superimposing multiple A-scans at different angles, displaying reflection points at different depths); C-scan (a depth-selected planar view); and D-scan (a side view along the scanning direction). These graphs can be used to determine whether an echo appears for each known artificial defect, whether the echo amplitude reaches a preset reference level (which can be quantified using DAC curves or DGS methods), whether the positioning error is within an acceptable range (depth positioning error ≤ 1 mm, lateral positioning error ≤ 2 mm), whether the signal-to-noise ratio is high enough (typically ≥ 6 dB or even higher), and whether there are serious spurious signals or grass wave interference.Based on this, the total angle range of the sector scan is adjusted (e.g., -35° to +35° or greater) to ensure coverage of the thickest and thinnest parts of the blade. The focusing depth is adjusted to improve the resolution of different depth regions. The gain curve (TCG time-compensated gain or DAC distance-amplitude correction curve) is adjusted to compensate for deep acoustic wave attenuation. Instrument settings such as pulse repetition frequency, sampling rate, and filter bandwidth are adjusted to obtain the optimal signal-to-noise ratio and resolution. After multiple rounds of adjustments and comparisons, when all key artificial defects meet the design requirements (e.g., stable detection of φ1.5mm flat-bottomed holes or 2mm deep artificial cracks), spurious signals are effectively suppressed, and repeatability is good, the verification is considered successful, and the current set of parameters forms a complete set of detection process parameters. It is worth noting that the detection process parameters include, but are not limited to, the following: probe model and serial number, operating frequency, number and spacing of wafers, wedge angle (if it is a wedge-type probe), sector scan angle range and step size, focusing rule table (transmitting / receiving wafer number, delay, and focusing depth for each rule), gain reference value, TCG / DAC curve parameters, filter settings, scanning speed, encoder resolution, coupling method, etc.

[0023] S2: Number, identify, and pre-process each turbine blade to be inspected, and generate a blade pre-processing record table. In step S2, cross-verification can be performed based on the fixed stamped number of the moving blade at the factory or in combination with the physical position of the blade on the rotor (e.g., which stage of moving blade, which position). This avoids misalignment or duplication of the numbering. After confirming the numbering, a comprehensive inspection and necessary cleaning of the blade surface are carried out. The pretreatment is based on visual inspection. Under lighting conditions of no less than 5000 lux, the inspectors systematically observe all exposed surfaces of each blade, focusing on key areas such as the working surface of the blade body (inner arc surface, usually the surface directly impacted by the combustion gas), the back surface of the blade body (outer arc surface), the inlet edge, the outlet edge, the blade tip area, the exposed surfaces of the tenons at the blade root, and the rounded corner area between the blade body and the blade root. During the inspection, surface anomalies that may affect the coupling quality or generate false signals are looked for, including splashed metal droplets, thick high-temperature oxide scale, carbon deposits, oil residue, grease adhesion, pitting corrosion, mechanical scratches, dents, blade tip ablation and thinning, and local plastic deformation of the blade body. Surface condition determines whether a phased array probe can achieve optimal fit and sound beam incidence. If the surface is contaminated with oil, the coupling agent will be difficult to spread evenly, leading to significant sound energy loss. A thick oxide layer will cause multiple reflections at the interface, creating clutter that is difficult to distinguish from actual defects. Significant geometric deformation makes it difficult to maintain probe stability, easily resulting in localized detection blind spots or sound beam deviation from the expected path. It is worth noting that the above inspections can be performed using auxiliary equipment, such as an industrial endoscope to conduct detailed inspections of areas inside the blade that are difficult to observe directly, or by using a surface roughness meter to quantitatively assess the surface roughness of key areas. For different anomalies found during inspection, light oil stains, dust, or thin oxide layers can be wiped with a neutral, non-abrasive cleaner and a lint-free cloth or soft nylon brush until the surface regains its metallic luster and leaves no residue. For more stubborn carbon deposits or hard oxides, a plastic scraper can be used to carefully remove them, or low-pressure dry ice spray cleaning can be used under strict protective conditions, but any mechanical damage to the substrate or the introduction of new stress should be avoided throughout the process. If scratches, dents, or bumps are found, the specific size, depth, length, and orientation of the anomaly should be recorded using calipers or depth measuring tools, and close-up photos should be taken. When obvious deformation of the blade is observed (e.g., the exhaust edge of the blade tip bends in the direction of the back arc beyond the technically permissible range), in addition to describing the deformation characteristics in detail, a warning label can be affixed to the blade surface, and special notes should be made in the record to remind subsequent analysts to consider the potential impact of geometric changes on sound path and positioning accuracy when judging defects, thus forming a blade pretreatment record table.

[0024] S3: Perform fan-shaped scanning on the main body of the moving blade and the transition part at the root of the blade according to the detection process parameters to obtain spectral data; In step S3, the blade body (blade) is scanned. The blade body is the main aerodynamic working part of the moving blade, including a distinct inner arc surface (working surface) and an outer arc surface (back surface). The thickness gradually decreases from the blade root to the blade tip, and there is a certain degree of torsion and bending. Based on the shear wave phased array probe verified in step S1 (an array probe with a frequency between 2.25MHz and 5MHz can be selected), and according to the fixed process parameters, including the fan sweep angle range, focusing rule, gain curve, transmission voltage, pulse repetition frequency, etc., the probe is tightly attached to the working surface (inner arc surface) of the blade body using an appropriate amount of water-based or oil-based coupling agent. The role of the coupling agent is to eliminate air between the probe and the blade surface, ensuring that the ultrasonic waves can be efficiently transmitted into the interior of the material without causing serious reflection loss. Under instrument control, the phased array probe uses electronic delay to control the excitation time difference of each crystal array element, forming multiple shear wave beams at different angles. These beams sweep through the interior of the blade body in a fan-shaped pattern, forming a fan-shaped scan. In this embodiment, shear waves were chosen because fatigue cracks and stress corrosion cracks in the turbine blades often propagate perpendicularly or nearly perpendicular to the principal stress direction. Shear waves have higher reflectivity when encountering such defect interfaces perpendicular to the propagation direction, generating stronger echo signals. During the scanning process, the instrument calculates and records the round-trip time of each sound beam in real time using the Time of Flight (TOF) method to determine the depth position of the reflection point. Simultaneously, combined with the probe's current placement coordinates (by pre-marking a grid on the blade surface or recording the scanning path using an encoder), the instrument achieves preliminary positioning of the defect in the three-dimensional space of the blade and simultaneously acquires various types of spectral data. The A-type scan displays the change in echo amplitude of a single sound beam over time, used to observe echo height and waveform characteristics; the C-type scan presents the defect distribution within a fixed depth layer in a depth-position plane; the D-type scan provides a side projection view, facilitating the determination of defect extension along the thickness direction; and the S-type scan achieves volumetric imaging through the synthesis of multi-angle sound beams, approaching the effect of three-dimensional reconstruction. After scanning the working surface (inner arc surface) of the blade, move the probe to the back surface (outer arc surface) of the blade and repeat the fan-shaped scanning operation with the same process parameters. Due to the curvature and torsion of the blade, the operator needs to continuously fine-tune the probe's attitude and pressure during the scanning process to maintain the optimal incident angle of the sound beam and avoid mode conversion losses or pseudo-signal interference caused by excessively large or small incident angles. Start near the blade root and gradually move the probe upwards along the blade height to cover the entire blade area, ensuring no critical areas are missed, such as the high-stress area in the middle of the blade or the small fatigue sources that are prone to appear at the blade tip exhaust edge. After completing the entire blade scanning, perform a fan-shaped scan on the transition area at the blade root.The blade root transition area refers to the arc-shaped transition zone between the blade body and the blade root tenon, as well as the lower part of the blade body near the blade root. This area exhibits significant stress concentration and more complex geometry, often featuring steps, rounded corners, and varying thicknesses, making it prone to early or extended cracks. A longitudinal wave phased array probe is used to perform auxiliary fan-shaped scanning of the exposed steps at the blade root, specifically on the stepped surfaces at the junction of the blade root and blade body (three or more accessible exposed steps). The probe is placed on each step surface, and potential defects (such as cracks parallel to the teeth) in areas like the blade root grooves and bottom slots are detected using longitudinal wave incident radiation. The scanning position, sound path, and reflected signals are recorded using a time-based method, and multi-mode scanning data (A / C / D / S types) is acquired. Due to spatial limitations in some blade structures (such as the inability of the sound beam to effectively enter the working surface at the blade root junction), only physically accessible areas are scanned; unaccessible areas are clearly marked as uninspected areas in the records. After the scan is completed, all collected spectral data (including multiple views such as A, C, D, and S) along with scan path records, probe parameter logs, time and location correspondence tables, etc., are recorded to generate spectral data.

[0025] S4: Perform defect type judgment processing on the above spectrum data, and conduct comprehensive quality evaluation on each moving blade according to the judgment result and the blade pretreatment record table to obtain the detection result.

[0026] In step S4, all the map data are imported into a dedicated phased array ultrasound post-processing software, for example, an analysis platform supporting instruments such as Olympus or GE, or a third-party image processing system dedicated to non-destructive testing. Necessary post-processing optimization is performed on the original map in the software environment to improve the identifiability of defect signals. Specifically, Time Corrected Gain (TCG) or Distance-Amplitude Correction (DAC) curves can be applied to compensate the echo amplitudes at different depths, so that defects of the same size at different thickness positions of the blade theoretically exhibit similar echo heights; at the same time, smoothing filtering and denoising algorithms (such as median filtering or wavelet denoising) are applied to suppress instrument noise, clutter caused by uneven coupling, and grass echo interference caused by material grain scattering, and the signal-to-noise ratio of the optimized map data is significantly improved. Abnormal echo signals are searched in the multi-view map, that is, isolated or continuous high-amplitude echoes that obviously deviate from the background echo of the normal material. The judgment is mainly based on the following characteristic parameters: whether the echo amplitude exceeds the reference sensitivity threshold determined in the process verification stage (based on the echo height of the artificial defect on the test block, for example, the DAC curve corresponding to 80% full screen height); whether the duration or envelope width of the echo corresponds to a certain size; the most important is the dynamic response characteristic of the echo at different scanning angles and different probe positions. For example, if an echo signal appears stably in sector scans at multiple consecutive angles, its position moves predictably with the deflection of the sound beam, and presents clear point-like, line-like or surface-like features in the C-scan (depth-circumferential plane) or S-scan, it is highly suspected to be a real defect; on the contrary, if it only appears at a specific angle, has a low amplitude and is accompanied by obvious side lobe artifact signal features, it may be judged as a geometric artifact echo or surface multiple reflection interference. After confirming that the abnormal echo is a potential defect, the defect type is further classified and judged, which can be comprehensively analyzed by combining the echo feature, orientation and location of the defect. For the common superalloy materials of gas turbine moving blades, the frequently encountered defect types mainly include fatigue cracks, stress corrosion cracks, inclusions, porosity, abnormal structure echoes caused by coarse grains, and tiny metallurgical defects formed during casting or forging. Among them, the typical map features of crack-type defects are sharp echoes, high amplitudes, strong reflection interfaces extending linearly at multiple angles, and the defect orientation often has a certain correlation with the main stress direction of the blade (along the blade height or circumferential direction); inclusions mostly appear as isolated point-like or mass-like echoes with medium to high echo amplitudes but no obvious extensibility; porosity or pore-type defects often appear as volume-type scattering clusters in the S-scan, with fuzzy echo boundaries and strong trailing grass echoes. By comparing these features and referring to the typical map examples and quantitative descriptions of various defects in industry standards, the specific type of defect is determined, such as a fatigue crack in the middle of the blade body parallel to the blade height, a stress concentration crack at the bottom of the gullet in the blade root transition zone, or an oxide inclusion inside the main body of the blade, etc.After completing the defect type identification and quantitative characterization of all ultrasonic data, a correlation comparison was performed using the blade pretreatment record table. The pretreatment record table includes information such as the blade's identification number, visual inspection photos, and descriptions of surface anomalies (e.g., minor scratches, oil stains before cleaning, degree of blade tip deformation, etc.). Through data cross-validation, the nature of some suspected defects can be effectively eliminated or confirmed, improving the accuracy of the judgment. For example, if the pretreatment record shows a known surface microcrack or severe deformation in a certain area, and a high-amplitude linear echo appears at the corresponding location in the ultrasonic spectrum, the confidence in the authenticity of the defect can be increased, avoiding misjudgment as a false signal. Based on all the information, a final quality assessment conclusion is given for each moving blade. For example, if no defect signals exceeding the Level I (or the enterprise-specified acceptable level) acceptance standard are found, and there are no major anomalies in the pre-processing records that significantly affect the reliability of the test, the blade is deemed acceptable and can continue to be used. If defects that do not meet the acceptance standards in terms of length, height, or orientation are detected (e.g., fatigue crack length exceeding 2mm, inclusion size exceeding the standard in high-stress areas, etc.), the blade is deemed unacceptable, and further subdivided into suggested categories such as rework, downgrading, or direct scrapping based on the severity of the defects. For blades on the verge of being unacceptable, they can be marked as requiring follow-up monitoring or it can be recommended to expand the sampling scope. The entire assessment process requires the formation of a detailed defect list for each blade, including defect number, type, size, location coordinates, location (blade body or root transition area), echo characteristic description, assessment level, and final conclusion, along with image screenshots, to generate the test results.

[0027] In summary, this application rigorously verifies the phased array probe's process by selecting a simulated test block with a height similar to that of an actual moving blade, obtaining optimized detection process parameters to ensure the controllable and reliable propagation behavior of the sound beam in complex curved surfaces and structures with varying thicknesses. Subsequently, each blade to be inspected undergoes standardized numbering and surface pretreatment, forming a traceable pretreatment record table. Then, based on the verification parameters, multi-mode spectral data are acquired using a fan-shaped scanning method for the main body of the blade and the root transition zone. Combined with intelligent defect type judgment and pretreatment records, a comprehensive quality assessment is performed, ultimately outputting objective detection results. This method overcomes the limitations of traditional ultrasonic, penetrant, magnetic particle, and conventional methods. X-ray inspection in the application of flue gas turbine blades suffers from prominent problems such as insufficient coverage due to fixed incident angle and single scanning path, numerous geometric interference echoes, blind spots caused by deep and minute defects, and high false positive and false negative rates. By utilizing the electronic deflection, dynamic focusing, and multi-angle sector scanning characteristics of phased array technology, effective acoustic beam coverage and high-resolution imaging of the entire blade area, especially the blade body and root transition area with abrupt changes in curvature and thickness, can be achieved. This significantly improves the comprehensiveness of inspection and the reliability of defect detection, and significantly reduces the risk of blade breakage, unit vibration, and even major safety accidents caused by the failure to detect defects such as internal fatigue cracks, corrosion pits, or foreign object damage in a timely manner.

[0028] In one specific embodiment, a simulated test block is fabricated using a moving blade with the same or similar material grade, manufacturing process, and acoustic properties as the moving blade of the flue gas turbine to be tested. The blade curvature, blade thickness variation, blade root step, blade root tenon, and transition structure between the blade body and blade root of the simulated test block all correspond to the moving blade to be tested, so that the propagation path, interface reflection, and sound beam deflection of the ultrasonic waves in the simulated test block can approximately reflect the testing state of the actual moving blade.

[0029] like Figure 3 As shown, multiple artificial defect grooves are set in the blade region, the blade-root junction region, and the root region of the simulated test block. The artificial defect grooves are formed by electrical discharge machining (EDM). The groove width is 0.5 mm, the groove length is 5 mm, and the groove depth is DP1. In this embodiment, DP1 is 1.0 mm. The artificial defect grooves are used to simulate fatigue cracks, stress corrosion cracks, and other area-type defects that may form during the service of the moving blade.

[0030] Four artificial defect slots were installed in the blade area, two on the working surface and two on the back surface, with the slots on the working surface and the back surface staggered along the blade height. This arrangement allowed for verification of the shear wave phased array probe's ability to detect defects at different surfaces, heights, and acoustic path positions when performing a fan-shaped scan from both the working and back surfaces of the blade.

[0031] Four artificial defect grooves are set in the transition area where the blade and blade root meet, with two on the working side of the blade and two on the back side of the blade. The artificial defect grooves are arranged near the upper step and transition rounded corner of the blade root to simulate cracks formed at the junction of the blade and blade root due to abrupt changes in cross-section and stress concentration, and to verify the acoustic beam coverage capability of the longitudinal wave phased array probe in the blade root transition area.

[0032] Eleven artificial defect grooves were installed in the blade root region, with three in the middle and four on each side. Each groove was located near the blade root step, the tenon side, or the tooth root, simulating potential tooth root cracks, step cracks, and near-surface fatigue cracks in the blade root region. By placing artificial defect grooves at different heights and lateral positions at the blade root, it was possible to determine whether the longitudinal wave phased array acoustic beam covered the main stress concentration areas at the blade root.

[0033] like Figure 4 As shown, the artificial defect groove extends from the outer surface of the simulated test block into the blade thickness direction, and the depth direction of the artificial defect groove is basically perpendicular to the local surface at its location. The cross-section can determine the positional relationship between the artificial defect groove and the blade's internal contour, blade root step, and tenon structure, and can verify the response of ultrasonic waves incident from the accessible surface at the blade root to artificial defect grooves of different depths.

[0034] Before testing, a water-based coupling agent was coated on the surface of the simulated test block. A 5MHz shear wave phased array probe was used to perform a fan-shaped scan of the working surface and back surface of the blade. The shear wave fan-scan angle was set to 35°~75° with an angle step of 1°. Multiple focusing depths were set according to the thickness variation of the blade, and the probe attitude was adjusted to ensure that the sound beam covered the near-surface, middle, and far-surface areas of the blade.

[0035] A longitudinal wave phased array probe with a frequency of 2.25 MHz was used to perform a fan-shaped scan of the blade root step and the blade root transition region. The longitudinal wave fan-scan angle was set to 0°~30° with an angle step of 1°. The probe was placed on each accessible step surface of the blade root, and by changing the sound beam angle and focusing depth, the blade root step, tenon teeth, tooth base, and the boundary area between the blade body and the blade root were covered.

[0036] During the scanning process, the detection gain was adjusted based on the highest echo of the artificial defect groove to ensure that the echo amplitude of the reference artificial defect groove reached 80% of the full screen height. A time-corrected gain curve was established to compensate for echo attenuation caused by different sound paths. A-mode, S-mode, C-mode, and D-mode scan images were acquired respectively, and the sound path, beam angle, echo amplitude, and location of each artificial defect groove were recorded.

[0037] when Figure 3The artificial defect grooves in the blade area, the blade root transition area, and the blade root area can be stably displayed. The signal-to-noise ratio of the artificial defect echo is not less than 6dB, the defect depth positioning error is not greater than 1mm, the planar positioning error along the blade surface is not greater than 2mm, and the difference in echo amplitude obtained from three consecutive scans of the same artificial defect is not greater than 2dB. The current detection parameters are then deemed to be qualified.

[0038] The verified probe frequency, number of array elements, sector scan angle range, angle step, focusing depth, detection gain, time-corrected gain curve, scanning speed, and coupling method are solidified as detection process parameters. The actual turbine blades to be inspected are then tested according to these parameters, ensuring effective acoustic beam coverage of the blade body, blade root transition area, and blade root tenon area, thereby improving the reliability of detecting crack-like defects in complex curved surfaces and areas with abrupt thickness changes.

[0039] In one embodiment, the step of selecting a simulated test block corresponding to the moving blade, and verifying the phased array probe based on the simulated test block to obtain the detection process parameters includes: The material properties and geometric structure of the moving blade are analyzed, and a simulation test block corresponding to the moving blade is selected based on the analysis structure. Based on the simulated test block, the phased array probe and instrument are set and preliminarily calibrated to obtain preliminary detection parameters. The phased array probe includes a shear wave phased array probe and a longitudinal wave phased array probe. The simulated test block is subjected to sector-shaped verification processing using the preliminary detection parameters to obtain the corresponding detection process parameters.

[0040] In the above embodiments, a systematic analysis is conducted on the material properties (such as sound velocity, attenuation coefficient, and grain scattering characteristics of high-temperature alloys) and geometric structures (such as gradual curvature, thickness distribution, and root steps) of the turbine blades under test. Based on the analysis conclusions, a simulated test block with highly matched acoustic performance and geometric dimensions is selected. The simulated test block is manufactured using the same grade of material and incorporates standard artificial defects. Using the selected transverse wave phased array probe and longitudinal wave phased array probe, as well as phased array instruments, comprehensive parameter settings and preliminary calibrations are performed on the probes and equipment, including determining the sector scan angle range, focusing depth and rule, gain curve, sound velocity value, and pulse repetition frequency, forming a set of preliminary detection parameters. Using this set of preliminary parameters, a complete sector scan verification is performed on the simulated test block. By acquiring echo signals under sound beams at different angles, the signal-to-noise ratio, positioning accuracy, resolution, and pseudo-echo suppression effect of the defects are evaluated. If the verification results show that the parameters are not ideal, targeted adjustments are made based on the reflection characteristics of known defects on the test block. For example, the wedge incident angle is optimized, the array element excitation sequence is modified, the dynamic focusing position or gain compensation method is adjusted, and after multiple scans and iterative optimizations, the qualified detection process parameters are obtained.

[0041] In one embodiment, the step of performing sector verification processing on the simulated test block using the preliminary detection parameters to obtain the corresponding detection process parameters further includes: Under the aforementioned preliminary detection parameters, the simulated test block is subjected to a sector scan by the shear wave phased array probe and the longitudinal wave phased array probe, respectively, to obtain echo signal data. The preliminary detection parameters are verified and adjusted based on the echo signal data to obtain qualified detection process parameters.

[0042] In the above embodiments, while keeping the initial detection parameters unchanged, shear wave phased array probes and longitudinal wave phased array probes are used to perform complete sector scans on different areas of the simulated test block or for different types of artificial defects, thereby acquiring comprehensive echo signal data, including A-scan waveforms, S-scan images, and C-scan slices. By analyzing the amplitude, arrival time, envelope shape, and multiple reflection characteristics of these signals in detail, it is determined whether the current parameters meet the requirements at different depths and angles. For example, whether the shear wave can effectively detect tilted defects, whether the longitudinal wave has sufficient resolution for near-surface defects, and whether there are serious mode conversion interferences or sidewall spurious signals. If deficiencies are found, the initial detection parameters are verified and adjusted. For example, increasing the excitation voltage to enhance penetration, optimizing the time correction curve to improve positioning accuracy, reducing the sector scan step size to improve resolution, and increasing the signal averaging frequency to suppress random noise, etc., are performed. This adjustment cycle continues until all target defects on the simulated test block can be stably detected with a high signal-to-noise ratio by both probes, the positioning error is controlled within the allowable range, and the defect equivalent assessment is accurate and reliable. Verified and qualified detection process parameters are then obtained and can be directly applied to actual blade inspection.

[0043] In one embodiment, the step of numbering, identifying, and pre-processing each turbine blade to be inspected, and generating a blade pre-processing record table, includes: Each turbine blade to be inspected is assigned a serial number for identification. The identified turbine blades are then subjected to visual inspection to obtain the visual inspection results. Based on the visual inspection results, the moving blades are subjected to contaminant removal treatment to obtain clean blades. The sequence number, appearance inspection results, and cleanliness status of the blades are integrated to form the blade pretreatment record table.

[0044] In the above embodiments, each blade to be inspected is assigned a unique serial number, which can be combined with the original steel stamp, installation location, or inspection batch information. After numbering, the identified blades undergo visual inspection using a combination of visual inspection and magnification tools or endoscopes. The inspection focuses on the working surface, back arc surface, blade tip area, blade root tooth surfaces, and transition areas for mechanical scratches, corrosion pits, metal splashes, oil accumulation, surface cracks, obvious deformation, and other abnormalities. Multi-angle photographs are taken as objective evidence, forming a detailed visual inspection result. If contaminants affecting ultrasonic coupling or potentially introducing false signals are found, such as grease, scale, or adhering particles, they can be removed promptly using process-verified and approved cleaning methods, such as wiping with specialized cleaning agents, non-destructive polishing, or ultrasonic cleaning, until the blade surface reaches a clean, residue-free, and well-coupled state, resulting in a clean blade. The serial number, all abnormal descriptions and photograph numbers recorded during the visual inspection, and comparisons of the state before and after cleaning are fully integrated to form a blade pretreatment record table.

[0045] In one embodiment, the main body of the blade comprises the working surface and the back surface of the blade. The step of performing a fan-shaped scan on the main body of the moving blade according to the detection process parameters includes: According to the detection process parameters, shear wave fan-shaped scanning is performed on the working surface and back surface of the blade to obtain scanning pattern data of the working surface and back surface of the blade. During the sector scanning process, the probe posture is adjusted according to the change in the curvature of the moving blade. The scanning data of the working surface and back of the blade are synthesized from multiple angles, and the synthesized data is processed to correspond with the time axis to obtain the blade image data.

[0046] In the above embodiments, based on verified and qualified detection process parameters, a shear wave fan-shaped scan is performed on the working surface (inner concave surface) of the blade. The probe is tightly attached to the surface with the aid of a coupling agent, and the instrument excites multi-angle sound beams according to a preset rule, covering the complete thickness range of the blade from the near surface to the far surface, and acquiring the scan pattern data of the working surface. Subsequently, a shear wave fan-shaped scan is performed on the back surface (outer convex surface) of the blade with the same parameters to obtain the back surface scan pattern data. Throughout the scanning process, because the curvature of the blade gradually changes from the blade root to the blade tip, the thickness decreases, and there is torsion, the probe posture, pressure, and scanning trajectory are dynamically adjusted according to the coupling status and pattern quality to keep the sound beam incident angle as optimized as possible, so as to reduce refraction distortion, energy loss, and blind spots, and ensure that key areas are fully covered. After the scan is completed, the original scan pattern data of the working surface and the back surface are subjected to multi-angle synthesis processing, that is, the information acquired from different sound beam angles is fused to improve the clarity and completeness of defect display; the synthesized pattern is correlated with the time axis or encoder position during the scanning process to form blade pattern data with accurate spatial positioning information.

[0047] In one embodiment, the blade root transition portion is the junction between the blade root and the blade body. The step of performing a fan-shaped scan on the blade root transition portion of the moving blade according to the detection process parameters includes: Based on the detection process parameters, the longitudinal wave phased array probe at the root transition section of the blade is switched to a sector scan preparation process to obtain the longitudinal wave scan settings. According to the longitudinal wave scanning settings, a fan-shaped scan is performed on the transition portion of the blade root to obtain multiple types of scan pattern data; The root transition portion of the leaf is processed using multi-view data correspondence based on the multi-type scanning map data to obtain root transition map data; The root transition map data and the leaf map data are integrated and correlated to obtain the map data.

[0048] In the above embodiment, the blade root transition section is the area where the blade root meets the blade body. Based on previously verified testing process parameters, the transition section undergoes a longitudinal wave phased array probe switching preparation process. This includes loading the corresponding longitudinal wave focusing rules, fan-scan angle range, gain curve, and sound velocity correction values ​​onto the phased array instrument to form a longitudinal wave scanning setup specifically for the root transition area. These settings ensure that the sound beam can effectively avoid geometric reflection interference and cover the blade root step, transition fillet, and potential crack propagation path. The longitudinal wave phased array probe is tightly coupled to the exposed accessible surface of the blade root (such as the step surface or side surface). Multiple sets of electronically deflected and focused sound beams are excited by the instrument to perform a complete fan-shaped scan of the root transition section. Echoes from different angles are acquired in real time during the scanning process. The signals are used to generate various types of scanning data, including A-scan and S-scan, which reflect the interface reflection, defect scattering, and bottom echo characteristics encountered by longitudinal waves propagating in the material. Specialized post-processing software is used to perform multi-view data correspondence processing on the acquired multi-type scanning data, that is, to superimpose, align, and fuse images from different sector scan angles to form clear three-dimensional or quasi-three-dimensional root transition data. This process uses Time-of-Flight (TOF) and beam path correction to eliminate geometric distortion and improve defect location accuracy. The obtained root transition data is then integrated and correlated with the previously obtained blade shear wave scanning data, for example, by using unified blade numbering, scanning position coordinates, and time axis correspondence to form complete single-blade data.

[0049] In one embodiment, the step of performing defect type determination processing on the atlas data includes: Feature analysis was performed on the echo signals in the aforementioned spectral data to obtain defect echo feature data: The propagation path and beam angle of the ultrasonic wave are obtained based on the detection process parameters. The defect location information is then obtained by performing defect localization processing on the spectral data based on the defect echo characteristic data, the ultrasonic wave propagation path, and the beam angle. Based on the defect location information and the defect echo feature data, defect type identification processing is performed to obtain the defect type judgment result.

[0050] In the above embodiments, feature analysis is performed on the echo signals in the spectrum data, including extracting parameters such as echo amplitude, phase, width, rise / fall time, and multiple reflection characteristics to form defect echo feature data. These features can distinguish between real defect signals and geometric interface reflections or noise. Based on the preset ultrasonic propagation path model and beam direction information at various angles (such as sector sweep start angle, step angle, and focusing depth) in the detection process parameters, combined with the defect echo feature data, defect localization processing is performed on the abnormal signals in the spectrum. By calculating the sound path, refraction angle, and time difference, the three-dimensional coordinates of the defect are accurately located, including depth, position along the blade axial direction, and circumferential offset, thereby generating accurate... The system obtains defect location information and uses joint analysis of defect location information and defect echo characteristic data to identify defect types. For example, if the echo is sharp, has a high amplitude, and is accompanied by multiple clear harmonics, it tends to be a crack-type defect. If the echo is diffuse and accompanied by grass-like signals, it may be an inclusion or looseness. If the location is close to the geometric interface, false defects need to be excluded. This identification can be completed with the assistance of pattern recognition algorithms or empirical threshold rules, and the defect type judgment result is output, such as fatigue crack, metallurgical inclusion, lack of fusion, etc., and the severity is initially graded. Multi-angle imaging of phased array avoids the misjudgment of type caused by the single angle in traditional single-probe detection, ensuring the scientificity and repeatability of defect classification.

[0051] In one embodiment, the step of comprehensively evaluating the quality of each moving blade based on the judgment result and the blade pretreatment record table to obtain the test result includes: The defect type judgment result is compared with the preset acceptance standard to obtain the single blade defect judgment result. The defect determination results of each individual blade are correlated with the appearance inspection results in the blade pretreatment record table to obtain the quality inspection results of each moving blade.

[0052] In the above embodiments, the defect type judgment result is compared with the preset acceptance criteria (such as the allowable size, quantity, location, and type threshold of defects specified in industry standards or internal enterprise guidelines) for item-by-item compliance judgment. For example, if the crack length is less than the allowable value and is not in a high-stress area, the item is qualified; otherwise, it is unqualified, thus forming the defect judgment result of a single blade. The result includes a qualified / unqualified conclusion and a specific description of the defect exceeding the standard. The defect judgment result of a single blade is correlated with the appearance inspection results in the blade pretreatment record table. For example, if ultrasound reveals an internal crack while the appearance record shows obvious impact dents on the blade body, the comprehensive judgment is that it may be fatigue propagation induced by external injury, which is of higher risk. If the appearance is clean and there are no abnormalities, the focus is on metallurgical defects. Through cross-verification of internal ultrasound and external visual information, the blind spots of a single method are avoided and the accuracy of the assessment is improved. Based on the comprehensive analysis, the quality inspection result of each moving blade is output. If it is qualified, it can continue to be used, needs repair, or is recommended for replacement, etc., and a complete record containing number, map summary, defect details, appearance correlation, and conclusion is generated.

[0053] Reference Figure 2 A phased array ultrasonic non-destructive testing system for turbine blades in flue gas combustion, comprising: The verification module 100 is used to select a simulated test block corresponding to the moving blade, and to perform verification processing on the phased array probe according to the simulated test block to obtain the detection process parameters. Processing module 200 is used to number, identify, confirm, and pre-process each flue gas turbine blade to be inspected, and generate a blade pre-processing record table. The scanning module 300 is used to perform fan-shaped scanning on the main body of the moving blade and the transition part at the root of the blade according to the detection process parameters to obtain spectral data; The evaluation module 400 is used to perform defect type judgment processing on the spectrum data, and to perform comprehensive quality evaluation on each moving blade based on the judgment result and the blade pretreatment record table to obtain the test result.

[0054] It is worth noting that the modules here correspond to specific steps. In actual implementation, the system can be executed either computerized and automated, or partially or entirely manually (for example, when on-site conditions are limited, equipment is incomplete, or small-batch testing is required, qualified testing personnel can manually perform the corresponding steps). For instance, a phased array ultrasonic testing instrument can be connected to a phased array probe (transverse and longitudinal wave probes, typically 64 elements or similar specifications, with delay wedges or wheel-type probes), along with dedicated analysis software (integrated into the instrument or PC-based post-processing software, such as OmniPC, Capture, Ultranalysis, etc.) to set the sector scan angle, focusing rule, gain curve, TCG / DAC curve, signal-to-noise ratio evaluation, etc., to perform sector verification scanning on the simulated test block, and to automatically or semi-automatically optimize and solidify process parameters. Alternatively, experienced Level II / III ultrasonic testing personnel can manually set instrument parameters, scan the simulated test block angle by angle, manually record echo characteristics, and adjust parameters until verification is successful.

[0055] The above description is merely a preferred embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural or procedural transformations made based on the content of the present invention's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of the present invention.

Claims

1. A phased array ultrasonic non-destructive testing method for turbine blades in flue gas, characterized in that, include: A simulated test block corresponding to the moving blade is selected, and the phased array probe is verified based on the simulated test block to obtain the detection process parameters; Each turbine blade to be inspected is numbered, identified, and pre-treated, and a blade pre-treatment record table is generated. According to the detection process parameters, a fan-shaped scan is performed on the main body of the moving blade and the transition part at the root of the blade to obtain spectral data; The defect type of the spectrum data is determined, and the quality of each moving blade is comprehensively evaluated based on the determination result and the blade pretreatment record table to obtain the test result.

2. The method for phased array ultrasonic non-destructive testing of turbine blades according to claim 1, characterized in that, The steps of selecting a simulated test block corresponding to the moving blade, verifying the phased array probe based on the simulated test block, and obtaining the detection process parameters include: The material properties and geometric structure of the moving blade are analyzed, and a simulation test block corresponding to the moving blade is selected based on the analysis structure. Based on the simulated test block, the phased array probe and instrument are set and preliminarily calibrated to obtain preliminary detection parameters. The phased array probe includes a shear wave phased array probe and a longitudinal wave phased array probe. The simulated test block is subjected to sector-shaped verification processing using the preliminary detection parameters to obtain the corresponding detection process parameters.

3. The phased array ultrasonic non-destructive testing method for turbine blades according to claim 2, characterized in that, The step of performing sector verification processing on the simulated test block using the preliminary detection parameters to obtain the corresponding detection process parameters further includes: Under the aforementioned preliminary detection parameters, the simulated test block is subjected to a sector scan by the shear wave phased array probe and the longitudinal wave phased array probe, respectively, to obtain echo signal data. The preliminary detection parameters are verified and adjusted based on the echo signal data to obtain qualified detection process parameters.

4. The method for phased array ultrasonic non-destructive testing of turbine blades according to claim 1, characterized in that, The steps of numbering, identifying, and pre-processing each turbine blade to be inspected, and generating a blade pre-processing record table, include: Each turbine blade to be inspected is assigned a serial number for identification. The identified turbine blades are then subjected to visual inspection to obtain the visual inspection results. Based on the visual inspection results, the moving blades are subjected to contaminant removal treatment to obtain clean blades. The sequence number, appearance inspection results, and cleanliness status of the blades are integrated to form the blade pretreatment record table.

5. The phased array ultrasonic non-destructive testing method for turbine blades according to claim 1, characterized in that, The main body of the blade consists of the working surface and the back surface. The step of performing a fan-shaped scan on the main body of the moving blade according to the detection process parameters includes: According to the detection process parameters, shear wave fan-shaped scanning is performed on the working surface and back surface of the blade to obtain scanning pattern data of the working surface and back surface of the blade. During the sector scanning process, the probe posture is adjusted according to the change in the curvature of the moving blade. The scanning data of the working surface and back of the blade are synthesized from multiple angles, and the synthesized data is processed to correspond with the time axis to obtain the blade image data.

6. The phased array ultrasonic non-destructive testing method for turbine blades according to claim 5, characterized in that, The blade root transition portion is the junction between the leaf root and the leaf blade. The step of performing a fan-shaped scan on the blade root transition portion of the moving blade according to the detection process parameters includes: Based on the detection process parameters, the longitudinal wave phased array probe at the root transition section of the blade is switched to a sector scan preparation process to obtain the longitudinal wave scan settings. According to the longitudinal wave scanning settings, a fan-shaped scan is performed on the transition portion of the blade root to obtain multiple types of scan pattern data; The root transition portion of the leaf is processed using multi-view data correspondence based on the multi-type scanning map data to obtain root transition map data; The root transition map data and the leaf map data are integrated and correlated to obtain the map data.

7. The method for phased array ultrasonic non-destructive testing of turbine blades according to claim 1, characterized in that, The step of performing defect type determination processing on the spectral data includes: Feature analysis was performed on the echo signals in the aforementioned spectral data to obtain defect echo feature data: The propagation path and beam angle of the ultrasonic wave are obtained based on the detection process parameters. The defect location information is then obtained by performing defect localization processing on the spectral data based on the defect echo characteristic data, the ultrasonic wave propagation path, and the beam angle. Based on the defect location information and the defect echo feature data, defect type identification processing is performed to obtain the defect type judgment result.

8. The method for phased array ultrasonic non-destructive testing of turbine blades according to claim 1, characterized in that, The step of comprehensively evaluating the quality of each moving blade based on the judgment result and the blade pretreatment record table to obtain the test result includes: The defect type judgment result is compared with the preset acceptance standard to obtain the single blade defect judgment result. The defect determination results of each individual blade are correlated with the appearance inspection results in the blade pretreatment record table to obtain the quality inspection results of each moving blade.

9. A phased array ultrasonic non-destructive testing system for turbine blades of flue gas, characterized in that, include: The verification module is used to select a simulated test block corresponding to the moving blade, and to perform verification processing on the phased array probe based on the simulated test block to obtain the detection process parameters. The processing module is used to number, identify, confirm, and pre-process each turbine blade to be inspected, and generate a blade pre-processing record table. The scanning module is used to perform fan-shaped scanning on the main body of the moving blade and the transition part at the root of the blade according to the detection process parameters to obtain spectral data; The evaluation module is used to determine the defect type of the spectrum data and to perform a comprehensive quality evaluation of each moving blade based on the determination result and the blade pretreatment record table to obtain the test result.

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