CN119666611A - A high temperature impact test device and method for engine blades - Google Patents
A high temperature impact test device and method for engine blades Download PDFInfo
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- CN119666611A CN119666611A CN202510204720.8A CN202510204720A CN119666611A CN 119666611 A CN119666611 A CN 119666611A CN 202510204720 A CN202510204720 A CN 202510204720A CN 119666611 A CN119666611 A CN 119666611A
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Abstract
本申请属于结构力学试验技术领域，特别涉及一种发动机叶片高温冲击试验装置及方法。试验装置包括：叶片试验件、试验件支持单元、加热单元、气炮加载单元、高速摄像机以及控制单元。本申请的发动机叶片高温冲击试验装置，设计的加热单元能够对叶片试验件进行均匀加热，温度最高可达1050℃；设计的弹托以及弹托分离器使得小直径弹丸可以高速精准撞击到目标位置；满足了直径在4mm以内的发动机叶片涂层脱落物等细小碎片以及颗粒在高温环境下的冲击试验需求。
The present application belongs to the field of structural mechanics test technology, and in particular, relates to a high-temperature impact test device and method for engine blades. The test device includes: a blade test piece, a test piece support unit, a heating unit, an air gun loading unit, a high-speed camera, and a control unit. The engine blade high-temperature impact test device of the present application has a heating unit that is designed to uniformly heat the blade test piece, with the temperature reaching up to 1050°C; the designed sabot and sabot separator allow small-diameter projectiles to accurately hit the target position at high speed; it meets the impact test requirements of small fragments and particles such as engine blade coating shedding with a diameter of less than 4 mm in a high-temperature environment.
Description
Technical Field
The application belongs to the technical field of structural mechanics tests, and particularly relates to a high-temperature impact test device and method for an engine blade.
Background
Aero-engine blades are typically in a high temperature service environment, with material properties and structural integrity facing serious challenges. The high temperature not only exacerbates the material degradation of the blade, but may also induce more complex damage patterns under the impact of foreign objects. In order to ensure the normal operation and safety of the aeroengine in the high-temperature environment, the impact mechanical properties of the engine blade in the high-temperature environment need to be obtained, and the dynamic mechanical behaviors and failure mechanisms of the engine blade in the high-temperature service environment need to be analyzed.
The air cannon method has high simulation precision and strong repeatability, is considered as a test method capable of accurately simulating foreign object impact, and is widely applied at home and abroad. In recent years, a great deal of test research is carried out on the aspect of simulating damage of foreign matters on blades by using an air cannon at home and abroad, but the air cannon basically stays at a normal temperature level, test means and data under a high temperature environment are relatively deficient, and simulated impact is mainly caused by objects with larger sizes such as birds, hail, broken stones and the like. Less research is conducted on coating falling objects and fine sand impact in the working process of the engine. The existing test method cannot meet the influence test requirement of fine particulate impact on the performance of the engine blade in a high-temperature environment.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a high-temperature impact test device and method for an engine blade, which are used for solving at least one problem existing in the prior art.
The technical scheme of the application is as follows:
A first aspect of the present application provides an engine blade high temperature impact test apparatus comprising:
the blade test piece is provided with an impacted part;
The test piece supporting unit comprises a test bench, a fixed frame, a blade root supporting component and a blade crown supporting component;
The fixed frame is arranged on the test bed;
The blade root supporting component is arranged at the lower end of the fixed frame and is used for positioning the blade root of the blade test piece;
the blade shroud supporting component is arranged at the upper end of the fixed frame and is used for positioning the blade shroud of the blade test piece;
The heating unit comprises a flexible ceramic heater, a lifting mechanism and a thermocouple;
the flexible ceramic heater is wrapped at the impacted part of the blade test piece and used for heating the impacted part of the blade test piece;
the lifting mechanism is respectively connected with the flexible ceramic heater and the fixed frame and is used for moving the flexible ceramic heater away from the impacted part of the blade test piece;
the thermocouple is arranged at the impacted part of the blade test piece;
the air cannon loading unit comprises a projectile which is used for applying impact load to the impacted part of the blade test piece;
a high speed camera for monitoring the projectile;
And the control unit is used for controlling the heating unit, the air cannon loading unit and the high-speed camera.
In at least one embodiment of the present application, the blade root support assembly includes a support knob, a jack bolt, left and right knob, front and rear knob, and a baffle, wherein,
The supporting jacking block is arranged on the fixed frame through the jacking bolt and is abutted against the lower surface of the tenon of the blade root of the blade test piece;
The left and right jacking blocks are arranged on the fixed frame and are abutted against the left and right surfaces of the tenons of the blade roots of the blade test pieces, and positioning inclined planes matched with the tenons of the blade roots of the blade test pieces are arranged on the left and right jacking blocks;
The front and rear jacking blocks are installed on the fixed frame through the baffle plates, and the front and rear jacking blocks are abutted against the front and rear surfaces of the tenons of the blade roots of the blade test pieces.
In at least one embodiment of the application, the tip shroud support assembly includes an upper retaining plate and a stop block, wherein,
The upper fixing plate is arranged on the fixing frame and is provided with a sliding rail;
the two limiting sliding blocks are respectively and slidably mounted on the sliding rail, and the two limiting sliding blocks clamp the left side and the right side of the blade crown of the blade test piece and are fixedly connected with the upper fixing plate through bolts.
In at least one embodiment of the application, the flexible ceramic heater is a caterpillar structure made of nichrome wire sheathed aluminum oxide ceramic insulator.
In at least one embodiment of the application, the thermocouple is a K-type contact thermocouple.
In at least one embodiment of the application, the air cannon loading unit further comprises an air source, an air reservoir, a gun barrel, a sabot and a sabot separator;
the air storage chamber is connected with the air source;
One end of the gun barrel is connected with the air storage chamber, and an electromagnetic valve is arranged at the joint;
The bullet support is slidably arranged in the gun barrel, and a bullet accommodating groove is formed in the bullet support;
the bullet support separator is arranged at the other end of the gun barrel and is provided with a through hole;
the projectile is installed in the projectile accommodating groove, and when the projectile support is blocked by the projectile support separator to stop, the projectile is penetrated out of the through hole of the projectile support separator under the action of self inertia.
In at least one embodiment of the application, a plurality of rubber rings are arranged at the connection part of the bullet holder and the gun barrel.
In at least one embodiment of the application, the contact areas of the sabot and the sabot separator are provided with mutually matching centering bevels.
In at least one embodiment of the application, the pellets are ceramic pellets or steel pellets having a diameter of no more than 4 mm.
A second aspect of the present application provides a high temperature impact test method for an engine blade, based on the high temperature impact test apparatus for an engine blade as described above, comprising:
calibration test:
recording the time t1 from the removal of the flexible ceramic heater from the impacted part of the blade test piece to the impact of the projectile on the impacted part of the blade test piece;
Heating the impacted part of the blade test piece to a target temperature T through a heating unit, removing the flexible ceramic heater from the impacted part of the blade test piece through a lifting mechanism, monitoring the temperature of the impacted part of the blade test piece to obtain a temperature change curve, and obtaining a temperature change delta T in time T1 according to the temperature change curve;
formal test:
The impact part of the blade test piece is heated to the temperature T+DeltaT through the heating unit, the flexible ceramic heater is moved away from the impact part of the blade test piece through the lifting mechanism, and the air cannon loading unit is used for launching the projectile to impact the impact part of the blade test piece.
The invention has at least the following beneficial technical effects:
The high-temperature impact test device for the engine blade improves the uniformity of temperature loading, can realize the research on the impact resistance of tiny fragments such as coating falling objects of the engine blade and particles on the engine blade under the high-temperature service environment, and provides support for understanding and predicting the damage behavior and failure mechanism of the engine blade under the high-temperature condition.
Drawings
FIG. 1 is an overall schematic view of an engine blade high temperature impact test apparatus according to one embodiment of the present application;
FIG. 2 is a schematic view of a test piece holding unit and a heating unit according to an embodiment of the present application;
FIG. 3 is a side view of a blade root support assembly according to one embodiment of the present application;
FIG. 4 is a top view of a tip shroud support assembly according to one embodiment of the present application;
FIG. 5 is a schematic diagram of an air cannon loading unit in accordance with one embodiment of the present application;
fig. 6 is a cross-sectional view of a sabot and sabot separator according to one embodiment of the application.
Wherein:
1-blade test piece, 2-test piece supporting unit, 21-test bench, 22-fixed frame, 23-supporting top block, 24-top bolt, 25-left and right top block, 26-front and rear top block, 27-baffle plate, 28-upper fixed plate, 29-limit slide block, 3-heating unit, 4-air gun loading unit, 41-air source, 42-air storage chamber, 43-gun tube, 44-bullet holder, 45-bullet holder separator, 46-bullet, 47-rubber ring and 5-high-speed camera.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are illustrative and intended to explain the present application and should not be construed as limiting the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, merely to facilitate describing the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of the present application.
The application is described in further detail below with reference to fig. 1 to 6.
The first aspect of the application provides a high-temperature impact test device for an engine blade, which comprises a blade test piece 1, a test piece supporting unit 2, a heating unit 3, an air cannon loading unit 4, a high-speed camera 5 and a control unit.
Specifically, the blade test piece 1 is an engine blade, and comprises a blade main body, a blade root and a blade crown, wherein the blade main body is provided with an impacted part, and the blade test piece 1 is positioned by clamping the blade root and the blade crown.
As shown in fig. 1-2, the test piece support unit 2 includes a test bed 21, a stationary frame 22, a blade root support assembly, and a shroud support assembly. The blade root support assembly is arranged at the lower end of the fixed frame 22 and used for positioning the blade root of the blade test piece 1, and the blade crown support assembly is arranged at the upper end of the fixed frame 22 and used for positioning the blade crown of the blade test piece 1. In this embodiment, the test stand 21 adopts a reinforcement cage structure as a support of the test piece supporting unit 2, and the fixing frame 22 includes a lower frame, an upper frame, and a connection frame connecting the lower frame and the upper frame, the installation of the blade root supporting component is realized through the lower frame, and the installation of the blade shroud supporting component and the lifting mechanism is realized through the upper frame.
In a preferred embodiment of the application, in order to simulate the clamping state of the blade test piece 1 in the actual operating mode, a blade root support assembly is provided for the dovetail design of the blade root, and a blade tip support assembly is provided for the blade tip. As shown in fig. 2 to 3, the blade root supporting assembly comprises a supporting top block 23, a tightening bolt 24, a left top block 25, a right top block 25, a front top block 26 and a rear top block 26, wherein the supporting top block 23 is mounted on a lower frame of the fixed frame 22 through the tightening bolt 24, the supporting top block 23 is abutted against the lower surface of the tenon of the blade root of the blade test piece 1, the left top block 25 and the right top block 25 are mounted on the fixed frame 22, the left top block 25 is abutted against the left surface and the right surface of the tenon of the blade root of the blade test piece 1, positioning inclined surfaces matched with the tenon of the blade root of the blade test piece 1 are arranged on the left top block 25 and the right top block 25, the front top block 26 and the rear top block 26 are mounted on the lower frame of the fixed frame 22 through the baffle 27, and the front top block 26 is abutted against the front surface and the rear surface of the tenon of the blade root of the blade test piece 1. The supporting jacking block 23 is pushed to move upwards by adjusting the jacking bolts 24 so as to contact the lower surface of the tenon, meanwhile, two inclined planes of the tenon structure are tightly attached to positioning inclined planes of the left jacking block and the right jacking block 25 to fix the blade test piece 1, so that the up-down and left-right movement of the blade root is limited, in addition, the front jacking block and the rear jacking block 26 are in threaded fit with the baffle 27, and the front jacking block and the rear jacking block 26 are adjusted so as to be abutted against the front surface and the rear surface of the tenon, so that the front-rear movement of the blade root is limited. As shown in fig. 2 and 4, the shroud support assembly comprises an upper fixing plate 28 and limiting slide blocks 29, wherein the upper fixing plate 28 is mounted on an upper frame of the fixing frame 22, the limiting slide blocks 29 comprise two limiting slide blocks 29 which are respectively and slidably mounted on sliding rails, the two limiting slide blocks 29 are respectively positioned on the left side and the right side of the shroud of the blade test piece 1, the shroud of the blade test piece 1 can be adjusted in the left-right direction and the front-back direction before the limiting slide blocks 29 are fixedly connected with the upper fixing plate 28, after the position of the shroud of the blade test piece 1 is determined, the left side and the right side of the shroud of the blade test piece 1 are clamped through the two limiting slide blocks 29, and finally the two limiting slide blocks 29 are fixedly connected with the upper fixing plate 28 through bolts, so that the up-down, left-right and front-back movement of the shroud is limited.
The heating unit 3 comprises a flexible ceramic heater, a lifting mechanism and a thermocouple, wherein the flexible ceramic heater is wrapped at the impacted part of the blade test piece 1 and is used for heating the impacted part of the blade test piece 1, the lifting mechanism is respectively connected with the flexible ceramic heater and the fixed frame 22 and is used for moving the flexible ceramic heater away from the impacted part of the blade test piece 1, and the thermocouple is installed at the impacted part of the blade test piece 1. In the preferred embodiment of the application, the flexible ceramic heater adopts a crawler-type structure made of a nichrome wire cable sleeved with an alumina ceramic insulator, and can be bent and wound to heat an object with an irregular appearance when in use, the heating temperature can reach 1050 ℃ at the highest, the lifting mechanism adopts a hydraulic actuating mechanism, the thermocouple adopts a K-type contact thermocouple, and the temperature change of a heating area is monitored in real time by arranging 2 thermocouples at the impacted part. It will be appreciated that other means of monitoring temperature changes may be employed, such as a hand-held infrared high temperature gun.
The air cannon loading unit 4 includes a shot 46, and the shot 46 is used for applying an impact load to the impacted portion of the blade test piece 1. Specifically, as shown in fig. 5-6, the air cannon loading unit 4 further comprises an air source 41, an air storage chamber 42, a gun barrel 43, a bullet holder 44 and a bullet holder separator 45, wherein the air storage chamber 42 is connected with the air source 41, one end of the gun barrel 43 is connected with the air storage chamber 42, an electromagnetic valve is arranged at the joint, the bullet holder 44 is slidably arranged in the gun barrel 43, a bullet accommodating groove is formed in the bullet holder 44, the bullet holder separator 45 is arranged at the other end of the gun barrel 43, a through hole is formed in the bullet holder separator 45, and a bullet 46 is arranged in the bullet accommodating groove, and when the bullet holder 44 is stopped by the bullet holder separator 45, the bullet 46 penetrates out of the through hole of the bullet holder separator 45 under the action of self inertia. Advantageously, in this embodiment, the connection of the sabot 44 to the barrel 43 is provided with a plurality of rubber rings 47 to improve the tightness, and the contact areas of the sabot 44 and sabot separator 45 are provided with mutually matching centering bevels. When the air supply 41 is in operation, after the air supply 41 charges air into the air storage chamber 42 to a preset pressure value, the control unit turns on the electromagnetic valve switch, the high-pressure air in the air storage chamber 42 is instantaneously released to apply work to push the projectile holder 44 in the gun barrel 43 to accelerate, the projectile holder 44 is stopped at the tail end of the gun barrel 43 by the projectile holder separator 45, and the projectile 46 continues to move at a high speed under the action of self inertia to finally strike the blade test piece 1. By designing the contact areas of the sabot 44 and sabot separator 45 as matching centering ramps to ensure centering, a more accurate impact location of the projectile 46 is ensured.
The fine fragments and particles of the coating falling object of the engine blade are lighter in weight and the diameter is generally within 4mm, and the application adopts the principle of energy equivalence to simulate the fine fragments and particles of the coating falling object of the engine blade. According to the different materials of the falling object, fine fragments such as the falling object of the coating of the engine blade and the like and particles can be equivalent to ceramic shots or steel shots with the diameter not exceeding 4 mm.
The high-temperature impact test device for the engine blade further comprises a high-speed camera 5 and a control unit, wherein the high-speed camera 5 is arranged in a test area and used for monitoring the flight track and impact speed of the projectile 46, and the control unit is used for controlling the heating unit 3, the air cannon loading unit 4 and the high-speed camera 5.
According to the high-temperature impact test device for the engine blade, the designed heating unit 3 can uniformly heat the blade test piece 1, the temperature can reach 1050 ℃, the designed bullet support 44 and the bullet support separator 45 enable small-diameter bullets 46 to impact a target position accurately at high speed, and the impact test requirements of fine fragments such as coating falling objects of the engine blade with the diameter within 4mm and particles in a high-temperature environment are met.
Based on the high-temperature impact test device for the engine blade, the second aspect of the application provides a high-temperature impact test method for the engine blade, which comprises two test stages:
calibration test:
recording the time t1 from the removal of the flexible ceramic heater from the impacted part of the blade test piece 1 to the impact of the projectile 46 on the impacted part of the blade test piece 1;
heating the impacted part of the blade test piece 1 to a target temperature T through a heating unit 3, moving the flexible ceramic heater away from the impacted part of the blade test piece 1 through a lifting mechanism, monitoring the temperature of the impacted part of the blade test piece 1 to obtain a temperature change curve, and obtaining a temperature change delta T in time T1 according to the temperature change curve;
formal test:
The impact part of the blade test piece 1 is heated to a temperature T+DeltaT by the heating unit 3, the flexible ceramic heater is moved away from the impact part of the blade test piece 1 by the lifting mechanism, and the shot 46 is launched by the air cannon loading unit 4 to impact the impact part of the blade test piece 1.
In order to accurately control the temperature of the projectile 46 when striking the blade test piece 1, the high-temperature impact test method of the engine blade of the application firstly needs to calibrate the cooling process of the blade test piece 1. In the calibration test phase, the time T1 from the removal of the flexible ceramic heater to the impact of the projectile 46 on the blade test piece 1 is recorded, and the temperature change Δt in the time T1 is acquired. In the formal test stage, the impact part of the blade test piece 1 is heated to the temperature T+DeltaT through the heating unit 3, so that the temperature when the projectile 46 impacts the blade test piece 1 is ensured to meet the test requirement, the temperature is kept for 5-10 min after the temperature T+DeltaT is reached, the temperature uniformity of the heating area of the blade test piece 1 is ensured, then the air storage chamber 42 is inflated to the preset pressure, the flexible ceramic heater is quickly lifted through the lifting mechanism, the flexible ceramic heater is removed from the impact part, and then the projectile 46 is launched to impact the impact part of the blade test piece 1 through the air cannon loading unit 4, so that the test is completed.
According to the high-temperature impact test method for the engine blade, disclosed by the application, the temperature of the blade test piece 1 is accurately controlled by calibrating the cooling process of the blade test piece 1 before a formal test. The application can realize impact test of fine fragments such as coating falling objects of the engine blade and particles in a high-temperature environment, and has strong test operability, high efficiency and high reliability of test results.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202510204720.8A CN119666611A (en) | 2025-02-24 | 2025-02-24 | A high temperature impact test device and method for engine blades |
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| CN202510204720.8A CN119666611A (en) | 2025-02-24 | 2025-02-24 | A high temperature impact test device and method for engine blades |
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| CN119666611A true CN119666611A (en) | 2025-03-21 |
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| CN202510204720.8A Pending CN119666611A (en) | 2025-02-24 | 2025-02-24 | A high temperature impact test device and method for engine blades |
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| WO2014107827A1 (en) * | 2013-01-10 | 2014-07-17 | 湘潭大学 | Testing device for simulating service environment of thermal barrier coating and detecting failure of thermal barrier coating in real time |
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