CN109632285B - Turbine blade high temperature fatigue test anchor clamps - Google Patents
Turbine blade high temperature fatigue test anchor clamps Download PDFInfo
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- CN109632285B CN109632285B CN201910137320.4A CN201910137320A CN109632285B CN 109632285 B CN109632285 B CN 109632285B CN 201910137320 A CN201910137320 A CN 201910137320A CN 109632285 B CN109632285 B CN 109632285B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
- G01N3/04—Chucks
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/18—Performing tests at high or low temperatures
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Abstract
The invention relates to a turbine blade high-temperature fatigue test fixture which comprises an upper chuck, a halved inner clamping block, an upper supporting plate, a mortise clamping block, a baffle and a lower chuck, wherein the upper chuck and the lower chuck are respectively connected with a fatigue testing machine, a rectangular block at the lower end of the upper supporting plate and the mortise clamping block is positioned in a groove of the upper chuck and the lower chuck and can slide along the groove, the upper part of a turbine blade body is connected with the halved inner clamping block and then is arranged in an inverted trapezoidal cavity in the middle of the upper supporting plate, a turbine blade tenon is connected with the mortise clamping block, and the baffle is fixed on the mortise clamping block through bolts and limits the movement of the turbine blade tenon along the axis of. The front, the back, the left and the right of the upper chuck and the lower chuck are respectively provided with two screw holes, the positions of the upper supporting plate and the mortise clamping block can be changed by controlling the screwing-in depth of the adjusting screw in the test process, so that the relative position of the central line of the turbine blade and the axial load of the fatigue machine is changed, when the central line of the turbine blade and the axial load of the fatigue machine are not overlapped, the turbine blade can bear additional bending load besides the single-axis load, and therefore a complex stress field of the.
Description
Technical Field
The invention relates to a high-temperature fatigue test for a turbine blade of an aero-engine, belongs to the technical field of aero-engines, and can be used for carrying out a high-temperature fatigue test for simulating a complex stress field of an examination section of the turbine blade on the basis of the high-temperature fatigue test to test the service life of the turbine blade, thereby providing guarantee for the safe and reliable work of the aero-engine.
Background
The service condition of the turbine blade of the aircraft engine is severe, the centrifugal load in a high-speed rotation state enables the turbine blade to generate tensile stress, and the turbine blade with the stacking line not superposed with the radial line also generates bending stress under the action of the centrifugal load; the aerodynamic loads act on the turbine blade surface mainly in the form of surface pressure, and the turbine blade will also bear bending moment and torsional moment due to the non-uniformity of the aerodynamic load distribution at different parts of the blade. The complex stress field of the turbine blade is difficult to simulate by a standard test piece and a blade approximate test piece, so that the development of a high-temperature fatigue test on the basis of accurately simulating the complex stress state of a real turbine blade examination section has important significance on the life-fixing research, the fault analysis and the prevention of the turbine blade.
A turbine blade clamp (Yan Xiao Jun, Ningxu, directional crystallization turbine blade creep/fatigue life test and analysis [ J ] aeronautical dynamics, 2005,20(6):925-931.) is developed for turbine blade fatigue tests by North aviation Yan Xiao Jun et al, and the clamp connects main parts of the clamp by two pairs of mutually perpendicular pins, two parts connected by each pin form a steering knuckle, and the parts can rotate around the pins in a small range; the part has a gap at the pin shaft connection part, and the included angle between the turbine blade and the main shaft of the fatigue testing machine can be changed by adjusting the gap at the pin shaft connection part, so that the bending load is applied to the turbine blade. On the basis, Rongqiang North aviation, et al (CN102539135A, CN201710769710.4) establish a turbine blade thermal mechanical fatigue test system and a thermal mechanical fatigue test system of a turbine blade with superimposed high-cycle vibration. The DD6 single crystal turbine blade thermal-mechanical comprehensive fatigue test research [ J ] gas turbine test and research, 2015,28(5):29-32.) is based on the clamp, a two-displacement adjusting mechanism is designed to adjust the stress field of the blade, and the two-displacement adjusting mechanism mainly utilizes a screw rod mechanism to adjust the front and back and left and right positions of the blade crown clamp in a plane coordinate system (x, y), so that the loading center position of the turbine blade is adjusted, and the bending load of the turbine blade is applied.
However, the clamp invented by north navigation depends on pin shaft connection, and pin shaft holes need to be processed on main parts, which inevitably causes stress concentration at the pin shaft holes, thereby affecting the strength of the clamp; in addition, the clamp needs four fork structures in total to adjust the relative position of blade central line and tired quick-witted unipolar load, vertical connection between the fork leads to the overall length overlength of clamp, and tired quick-witted crossbeam height has certain restriction, and this kind of anchor clamps of messenger can't be applicable to the turbine blade of length longer. The designed two-displacement adjusting mechanisms of the beam texts, the Shiweis, the Zhao Wei and the like have complicated structures and are inconvenient to use, and moreover, structures such as screw holes need to be machined, stress concentration can be generated at the screw holes, and the strength of the clamp is influenced.
In summary, the design of the current turbine blade high-temperature fatigue test fixture is not perfect, and a large improvement space is still left.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the turbine blade high-temperature fatigue test fixture which is simple in structure, low in processing cost and convenient to use is provided, the turbine blade high-temperature (500-1200 ℃) fatigue test is carried out on the basis of accurately simulating the complex stress field of the examination section of the turbine blade, the service life of the turbine blade is tested, and the safety and reliability of the operation of an aeroengine are guaranteed.
The technical solution of the invention is as follows: the utility model provides a turbine blade high temperature fatigue test anchor clamps which characterized in that includes chuck, halving interior clamp splice, goes up backup pad, tongue-and-groove clamp splice, baffle, lower chuck. The middle parts of the upper chuck and the lower chuck are cavities, and the lower parts of the upper chuck and the lower chuck are bearing teeth with grooves. The upper clamping head and the lower clamping head are respectively connected with a fatigue testing machine, the rectangular blocks at the lower ends of the upper supporting plate and the mortise clamping block are positioned in the grooves of the upper clamping head and the lower clamping head and can slide along the grooves, the upper part of the blade body of the turbine blade is connected with the half inner clamping block and then is filled in the inverted trapezoidal cavity at the middle part of the upper supporting plate, the tenon of the turbine blade is connected with the mortise clamping block, and the baffle is fixed on the mortise clamping block through a bolt and limits the movement of the tenon of the blade along the axis. The height of the middle cavity of the upper chuck and the lower chuck is 0.5-1mm higher than that of the rectangular blocks at the lower ends of the upper supporting plate and the mortise clamping block, so that the rectangular blocks at the lower ends of the upper supporting plate and the mortise clamping block can enter the inner cavity of the upper chuck and the lower chuck from the side. The length of the upper chuck groove and the lower chuck groove is 20-30mm longer than that of the rectangular block at the lower end of the upper supporting plate and the mortise clamping block, the width of the upper chuck groove and the lower chuck groove is 20-30mm wider than that of the rectangular block at the lower end of the upper supporting plate and the mortise clamping block, and the distance between the lower bearing tooth edge of the upper chuck and the lower chuck and the turbine blade is 10-20mm, so that the rectangular block at the lower end of the upper supporting plate and the mortise clamping block can slide along the upper chuck groove. The front, the back, the left and the right of the upper chuck and the lower chuck are respectively provided with two screw holes, the positions of the upper supporting plate and the mortise clamping block can be changed by controlling the screwing-in depth of the adjusting screw in the test process, so that the relative position of the central line of the turbine blade and the axial load of the fatigue machine is changed, when the central line of the turbine blade and the axial load of the fatigue machine are not overlapped, the turbine blade can bear additional bending load besides the single-axis load, and a complex stress field in the service process.
Compared with the prior art, the invention has the advantages that: the invention has simple assembly and convenient use, can realize accurate simulation of complex stress fields of the turbine blade examination sections and stable clamping of the turbine blade in a high-temperature fatigue test, can be used for the fatigue test of the specific examination sections of the turbine blade at high temperature (500-1200 ℃), does not need to consider the problem of insufficient strength of the clamp caused by connection modes such as a pin shaft hole and the like, can be used for re-processing corresponding halved inner clamping blocks and mortise clamping blocks for different turbine blades, does not need to process other components of the clamp for multiple times, and can reduce the processing cost.
Drawings
FIG. 1 is a view of an upper chuck of the present invention, wherein (a) is an external view; (b) is a left view; (c) is a front view; (d) is a top view;
FIG. 2 is a fragmentary inner clamping block diagram of the present invention, wherein (a) is a leaf basin inner clamping block diagram; (b) is a leaf back inner clamping block diagram;
FIG. 3 is a view of the upper supporting plate of the present invention, wherein (a) is an external view; (b) is a left view; (c) is a front view; (d) is a top view;
FIG. 4 is a schematic view of a turbine blade;
FIG. 5 is a view of a tongue and groove block of the present invention, wherein (a) is an external view; (b) is a left view; (c) is a front view; (d) is a top view;
FIG. 6 is a view of the baffle plate of the present invention, wherein (a) is an external view; (b) is a left view; (c) is a front view; (d) is a top view;
FIG. 7 is a view of the lower chuck of the present invention, wherein (a) is an external view; (b) is a left view; (c) is a front view; (d) is a top view;
FIG. 8 is a component part of the upper and lower chucks of the present invention, wherein A is a gripping end; b is a groove; c is a lower bearing tooth;
FIG. 9 is an assembly view of the turbine blade high temperature fatigue test fixture of the present invention.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings.
As shown in fig. 1-9, the invention mainly aims at a high-temperature fatigue test fixture suitable for turbine blades, and the fixture mainly comprises an upper chuck 1, a halved inner clamping block 2, an upper supporting plate 3, a tongue-and-groove clamping block 5, a baffle 6 and a lower chuck 7. The clamping ends A of the upper chuck 1 and the lower chuck 7 are respectively connected with a fatigue testing machine, the lower ends of the upper supporting plate 3 and the mortise clamping block 5 are positioned in the grooves B of the upper chuck 1 and the lower chuck 7 and can slide along the grooves B, the upper part of the blade body of the turbine blade 4 is connected with the half inner clamping block 2 and then is filled in the inverted trapezoidal cavity in the middle of the upper supporting plate 3, the tenon of the turbine blade 4 is connected with the mortise clamping block 5, and the baffle 6 is fixed on the mortise clamping block 5 through a bolt and limits the movement of the tenon of the turbine blade 4 along the axis of the mortise. The height of the middle cavity of the upper chuck 1 and the lower chuck 7 is 0.5-1mm higher than that of the lower rectangular block of the upper support plate 3 and the mortise clamp block 5, so that the lower rectangular blocks of the upper support plate 3 and the mortise clamp block 5 can enter the inner cavity of the upper chuck 1 and the lower chuck 7 from the side.
The length of the groove B of the upper chuck 1 and the lower chuck 7 is 20-30mm longer than that of the rectangular block at the lower end of the upper support plate 3 and the mortise clamping block 5, the width of the groove B of the upper chuck 1 and the lower chuck 7 is 20-30mm wider than that of the rectangular block at the lower end of the upper support plate 3 and the mortise clamping block 5, and the edge of the lower bearing tooth C of the upper chuck 1 and the lower chuck 7 is 10-20mm away from the turbine blade, so that the lower ends of the upper support plate 3 and the mortise clamping block 5 can slide along the groove B of the upper chuck 1 and the lower chuck 7.
The assembly drawing of the fixture in the test process is shown in fig. 9, and the assembly process is divided into 5 steps:
1. clamping the clamping end A of the upper clamping head 1 on a fatigue testing machine;
2. the upper part of the blade body of the turbine blade 4 is connected with the half inner clamping block 2 and then is arranged in the inverted trapezoidal cavity in the middle of the upper supporting plate 3, and the upper supporting plate 3 is put on the groove B of the upper clamping head 1;
3. the mortise clamping block 5 is connected with the mortise of the turbine blade 4, and the baffle 6 is fixed on the mortise clamping block 5 through bolts;
4. the groove B of the lower chuck 7 is lapped on the lower part of the mortise clamping block 5;
5. adjusting screws are arranged at the front, the rear, the left and the right of the upper chuck 1 and the lower chuck 7, and a clamping end A of the lower chuck 7 is clamped on the fatigue testing machine.
The adjusting of the complex stress field of the turbine blade examination section in the test process is mainly realized by adjusting screws, two screw holes are respectively arranged at the front, the back, the left and the right of the upper chuck 1 and the lower chuck 7, each screw hole is provided with one adjusting screw, the positions of the upper supporting plate and the mortise clamping block can be changed by controlling the screwing-in depth of the adjusting screws in the test process, so that the relative position of the central line of the turbine blade and the axial load of the fatigue machine is changed, when the two parts are not coincident, the turbine blade can bear additional bending load besides the single-axis load, and the complex stress field of the turbine blade in the examination section service.
Since turbine blades are generally subjected to tensile loads during actual service, alternating tensile loads are also applied when testing turbine blade qualifying sections under laboratory conditions. At the moment, the fixture can meet the stable loading of the turbine blade, can realize the accurate simulation of the complex stress field of the turbine blade examination section, and can be used for the fatigue test of the specific examination section of the turbine blade at high temperature (500-1200 ℃); in addition, the clamp is simple to assemble and convenient to use, the problem of insufficient strength of the clamp caused by connection modes such as pin shaft holes and the like is not needed to be considered, corresponding halved inner clamping blocks and mortise clamping blocks can be machined for different turbine blades again, other components of the clamp are not needed to be machined repeatedly, and machining cost can be reduced.
The invention has not been described in detail and is within the skill of the art.
The scope of the invention is defined by the appended claims. Various equivalent substitutions and modifications can be made without departing from the spirit and principles of the invention, and are intended to be within the scope of the invention.
Claims (3)
1. The utility model provides a turbine blade high temperature fatigue test anchor clamps which characterized in that: the fixture is used for fatigue test of the turbine blade at the high temperature of 500-1200 ℃, and comprises an upper chuck, a halved inner clamping block, an upper supporting plate, a tongue-and-groove clamping block, a baffle and a lower chuck; the middle parts of the upper chuck and the lower chuck are cavities, and the lower parts of the upper chuck and the lower chuck are bearing teeth with grooves; the lower end of the mortise clamping block is a rectangular block; the upper chuck is connected with the upper end of the fatigue testing machine; the lower chuck is connected with the lower end of the fatigue testing machine; the upper supporting plate is positioned in the groove of the upper chuck and slides along the groove; the rectangular block at the lower end of the mortise clamping block is positioned in the groove of the lower chuck and slides along the groove; the upper part of the blade body of the turbine blade is connected with the half inner clamping block and then is arranged in the inverted trapezoidal cavity in the middle of the upper supporting plate; the tenon of the turbine blade is connected with the mortise clamping block; the baffle is fixed on the mortise clamping block through a bolt to limit the movement of the turbine blade tenon along the axis of the mortise;
the front, the rear, the left and the right of the upper chuck and the lower chuck are respectively provided with two screw holes, the positions of the upper supporting plate and the mortise clamping block are changed by controlling the screwing-in depth of the adjusting screw, and the relative position of the central line of the turbine blade and the axial load of the fatigue testing machine is further changed; when the center line of the turbine blade is not coincident with the axial load of the fatigue testing machine, the turbine blade bears the uniaxial load and the additional bending load, so that a complex stress field in the service process of the examination section of the turbine blade is simulated;
the length of the groove of the upper chuck is 20-30mm longer than that of the upper support plate, the widths of the upper chuck and the groove are 20-30mm wider than that of the upper support plate, and the distance from the edge of the lower bearing tooth of the upper chuck to the turbine blade is 10-20mm, so that the upper support plate can slide along the groove of the upper chuck;
the length of the groove of the lower chuck is 20-30mm longer than that of the rectangular block at the lower end of the mortise clamping block, the width of the lower chuck and the groove is 20-30mm wider than that of the rectangular block at the lower end of the mortise clamping block, and the distance between the edge of the lower bearing tooth of the lower chuck and the turbine blade is 10-20mm, so that the rectangular block at the lower end of the mortise clamping block slides along the groove of the lower chuck.
2. The turbine blade high temperature fatigue test fixture of claim 1, characterized in that: the height of the middle cavity of the upper chuck is 0.5-1mm higher than that of the upper supporting plate, so that the upper supporting plate can enter the inner cavity of the upper chuck from the side.
3. The turbine blade high temperature fatigue test fixture of claim 1, characterized in that: the height of the middle cavity of the lower chuck is 0.5-1mm higher than that of the rectangular block at the lower end of the mortise clamping block, so that the rectangular block at the lower end of the mortise clamping block can enter the cavity in the lower chuck from the side.
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| CN110631933B (en) * | 2019-09-20 | 2020-11-20 | 北京航空航天大学 | High-temperature large-load test fixture and test method for turbine blade joggle joint structure |
| CN110672412B (en) * | 2019-09-30 | 2021-12-21 | 太原理工大学 | Plate belt tension simulation device suitable for universal tensile testing machine |
| CN111811762B (en) * | 2020-07-10 | 2022-07-15 | 中国航发沈阳发动机研究所 | Blade fatigue test fixture |
| CN112393889A (en) * | 2020-11-13 | 2021-02-23 | 中国航发沈阳发动机研究所 | Blade mechanical property test device based on uniform-section blade profile simulation piece |
| CN113310680B (en) * | 2021-07-06 | 2022-05-13 | 杭州汽轮动力集团有限公司 | Measure test device of tenon assembly structure flow coefficient |
| CN114295501A (en) * | 2021-12-22 | 2022-04-08 | 苏州长菱测试技术有限公司 | Device for positioning on blade body of blade and marking method thereof |
| CN115436161B (en) * | 2022-09-05 | 2024-08-06 | 北京航空航天大学 | Ceramic matrix composite joggle structure tensile-tensile fatigue test fixture and test method |
| CN115420592A (en) * | 2022-11-07 | 2022-12-02 | 清华大学 | Eccentric loading auxiliary device for metal fatigue test |
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