CN112903275B - Sectional type pull rod sealing system for thermal engine coupling fatigue test of blade - Google Patents
Sectional type pull rod sealing system for thermal engine coupling fatigue test of blade Download PDFInfo
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- CN112903275B CN112903275B CN202110140583.8A CN202110140583A CN112903275B CN 112903275 B CN112903275 B CN 112903275B CN 202110140583 A CN202110140583 A CN 202110140583A CN 112903275 B CN112903275 B CN 112903275B
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- G01M13/00—Testing of machine parts
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Abstract
The invention provides a sectional type pull rod sealing system for a blade thermal engine coupling fatigue test, which comprises a tension mechanism, a labyrinth sealing sleeve and a honeycomb sealing sleeve, wherein the labyrinth sealing sleeve is arranged on the tension mechanism; the tension mechanism comprises a tension machine main body and a pull rod for outputting tension, and a first cooling channel is arranged in the pull rod along the longitudinal direction; the labyrinth sealing sleeve and the honeycomb sealing sleeve are sequentially sleeved on the pull rod; the comb tooth sealing sleeve is connected with the honeycomb sealing sleeve through a flange connecting structure, the connecting part of the comb tooth sealing sleeve is hollow, the pull rod is divided into a first section rod and a second section rod which are connected through the flange connecting structure, and the position where the first section rod is connected with the second section rod through the flange connecting structure is located in the hollow connecting part between the comb tooth sealing sleeve and the honeycomb sealing sleeve. The invention solves the problems that the pull rod is easy to deform and damage in a high-temperature environment and needs to be replaced frequently, and the test chamber is sealed in the high-temperature environment.
Description
Technical Field
The invention relates to the field of aeroengines, in particular to a sectional type pull rod sealing system for a thermal engine coupling fatigue test of a blade.
Background
The thermal-mechanical coupling fatigue failure of the turbine blade of the aircraft engine is a main failure mode during the service period of the aircraft engine, and the service life of the aircraft engine is seriously influenced. The thermal mechanical coupling fatigue test is carried out on the turbine blade of the aero-engine, so that the important significance and the engineering value are achieved for examining the design level of the turbine blade and formulating the production standard of the turbine blade in the industry.
The traditional thermal-mechanical coupling fatigue test method for the turbine blade mostly adopts electric heating to provide a heat source and adopts a fatigue testing machine to provide a mechanical load. Although the currently known thermo-mechanical coupling fatigue testing machine can realize the cooperative loading of the maximum temperature and the maximum tensile force, the mechanical load needs to be applied by a tensile machine outside the experiment chamber through the pull rod, and the pull rod is easy to deform and damage in a high-temperature environment, so that the reliability and the accuracy of the test result are difficult to further improve; the tie rods need to be replaced frequently, resulting in increased test costs. Accordingly, there is a need to provide a segmented tie rod sealing system for thermal-mechanical coupling fatigue testing of blades to overcome the above problems.
Disclosure of Invention
The invention provides a sectional type pull rod sealing system for a thermal engine coupling fatigue test of a blade, which aims to solve the problem that a pull rod is easy to deform and damage in a high-temperature environment and needs to be replaced frequently. In addition, the method is not limited to the thermal-mechanical coupling fatigue test of the blade, and can be applied to the test of providing the tension for the blade in a high-temperature environment.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows:
a sectional type pull rod sealing system for a blade thermal engine coupling fatigue test comprises a tension mechanism, a labyrinth sealing sleeve and a honeycomb sealing sleeve;
the tension mechanism comprises a tension machine main body and a pull rod used for outputting tension, a connecting part used for being connected with the end part of the turbine blade to be tested is arranged at the free end of the pull rod, and a first cooling channel is arranged in the pull rod along the longitudinal direction;
the labyrinth sealing sleeve and the honeycomb sealing sleeve are sequentially sleeved on the pull rod, one end of the labyrinth sealing sleeve is used for being connected with the outer wall of a liquid cooling device which provides a gas test environment for the turbine blade to be tested, and the other end of the labyrinth sealing sleeve is connected with the honeycomb sealing sleeve; a sealing assembly is arranged between one end of the honeycomb sealing sleeve, which is far away from the labyrinth sealing sleeve, and the pull rod;
the labyrinth sealing sleeve is connected with the honeycomb sealing sleeve through a flange connecting structure, the connecting part of the labyrinth sealing sleeve is free of a labyrinth structure and a honeycomb structure, the pull rod is divided into a first section of rod and a second section of rod which are connected through the flange connecting structure, and the position where the first section of rod is connected with the second section of rod through the flange connecting structure is located in the connecting part between the labyrinth sealing sleeve and the honeycomb sealing sleeve.
Preferably, the sealing assembly comprises a sealing gasket, and the sealing gasket is sleeved on the pull rod.
Preferably, the sealing assembly further comprises a cover plate and a bolt, a through hole matched with the pull rod is formed in the middle of the cover plate, the pull rod is inserted into the through hole, the cover plate is in close contact with the pull rod, and the cover plate is fixedly connected with the honeycomb sealing sleeve through the bolt after pressing the sealing washer downwards.
Preferably, the first cooling channel is U-shaped, and the bent portion of the first cooling channel is close to the connecting portion of the tie bar for connecting with the turbine blade to be tested.
Preferably, the sum of the length of the honeycomb sealing sleeve and the length of the labyrinth sealing sleeve is less than the length of the pull rod.
Preferably, the labyrinth sealing sleeve is provided with a second cooling channel, and the second cooling channel is distributed in the side wall of the labyrinth sealing sleeve and in the labyrinth structure.
Preferably, the side wall of the labyrinth sealing sleeve is provided with an inlet and an outlet of the second cooling channel.
Preferably, the inlet is arranged on the side wall of one end of the labyrinth sealing sleeve, and the outlet is arranged on the side wall of the other end of the labyrinth sealing sleeve.
Preferably, the inlet and the outlet are respectively positioned at two longitudinal ends of the labyrinth sealing sleeve.
Preferably, the first cooling channel and the second cooling channel are both used for introducing cooling air or cooling liquid.
Compared with the prior art, the invention has the following beneficial effects:
1. the environment of mechanical load applied to the turbine blade in the working process of the engine is accurately simulated through the tension mechanism, the sealing assembly, the labyrinth sealing sleeve and the honeycomb sealing sleeve are used for sealing, the outward leakage amount of gas in a gas test environment can be effectively reduced, the reliability and accuracy of a test result are effectively improved, the pull rod is effectively cooled, the service life of the pull rod is prolonged, the replacement frequency of the pull rod is reduced, and the test cost is reduced;
2. by using the two sections of pull rods, the replacement of the whole pull rod is avoided, and only the section of the pull rod close to the turbine blade is replaced, so that the test cost is reduced;
3. the labyrinth seal sleeve and the honeycomb seal sleeve are communicated through a flange connecting structure, the communicated part is hollow, and the connecting positions of the two sections of pull rods through the flange connecting structure are positioned in the hollow part, so that the sealing is further enhanced.
Drawings
FIG. 1 is a schematic structural diagram of a segmented tie rod sealing system for blade thermal-mechanical coupling fatigue testing according to some embodiments of the present invention.
FIG. 2 is another schematic structural view of a segmented tie rod sealing system for thermal-mechanical coupling fatigue testing of blades according to some embodiments of the present invention.
FIG. 3 is a schematic diagram of a first cooling gallery in accordance with some embodiments of the present invention.
Fig. 4 is a schematic structural view of a outrigger according to some embodiments of the present invention.
Reference numerals: 1 is the pulling force machine main part, 2 is the pull rod, 3 is the labyrinth sleeve pipe of obturating, 4 is the honeycomb sealed sleeve pipe, 5 is the turbine blade that awaits measuring, 6 is first cooling channel, 7 is the liquid cooling device, 8 is flange joint structure, 9 is first section pole, 10 is second section pole, 11 is seal ring, 12 is the apron, 13 is the bolt, 14 is second cooling channel, 15 is the entry, 16 is the export, 17 is the workstation, 18 is the load bearing, 19 is the thermocouple, 20 is the pressure pipe, 21 is hydraulic cylinder, 22 is the cooling gas pipeline, 23 is the tenon connector, 24 is the inlet tube.
Detailed Description
The technical solutions of the present invention are further described in detail below with reference to the accompanying drawings, but the scope of the present invention is not limited to the following.
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings of the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. Thus, the following detailed description of the embodiments of the present invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention.
The present invention will be further described with reference to the following examples, which are intended to illustrate only some, but not all, of the embodiments of the present invention. Based on the embodiments of the present invention, other embodiments used by those skilled in the art without any creative effort belong to the protection scope of the present invention.
Referring to fig. 1 to 4, an embodiment of the present invention is shown, which is for illustration purposes only and is not limited to this structure.
FIG. 1 illustrates a structural schematic diagram of a segmented tie rod sealing system for blade thermo-mechanical coupling fatigue testing in accordance with certain embodiments of the present invention.
The invention discloses a sectional type pull rod sealing system for a blade thermal engine coupling fatigue test, which comprises a tension mechanism, a labyrinth sealing sleeve 3 and a honeycomb sealing sleeve 4.
The tension mechanism comprises a tension machine main body 1 and a pull rod 2 used for outputting tension, a connecting portion used for being connected with the end portion of a turbine blade 5 to be tested is arranged at the free end of the pull rod 2, and a first cooling channel 6 is arranged inside the pull rod 2 along the longitudinal direction.
The pull rod 2 is sequentially sleeved with the labyrinth sealing sleeve 3 and the honeycomb sealing sleeve 4, one end of the labyrinth sealing sleeve 3 is used for being connected with the outer wall of a liquid cooling device 7 which provides a gas test environment for the turbine blade 5 to be tested, and the other end of the labyrinth sealing sleeve 3 is connected with the honeycomb sealing sleeve 4; and a sealing component is arranged between one end of the honeycomb sealing sleeve 4 far away from the labyrinth sealing sleeve 3 and the pull rod 2.
The labyrinth sealing sleeve 3 and the honeycomb sealing sleeve 4 are connected through a flange connecting structure 8, the connecting part is free of a labyrinth structure and a honeycomb structure, the pull rod 2 is divided into a first section of rod 9 and a second section of rod 10 which are connected through the flange connecting structure 8, and the connecting position of the first section of rod 9 and the second section of rod 10 through the flange connecting structure 8 is located in the connecting part between the labyrinth sealing sleeve 3 and the honeycomb sealing sleeve 4. The flange connecting structure 8 comprises a flange, a nut and a bolt 13, wherein the flange, the nut and the bolt 13 are made of special high-temperature-resistant alloy, and the temperature resistance is at least 1000K. The first rod section 9 is in threaded connection with the second rod section 10.
In other embodiments, the first rod segment 9 and the second rod segment 10 are connected by a self-locking structure in the form of an autoclave. The end part of the first section of rod 9 is embedded and screwed with the second section of rod 10 through rod teeth, and the joint surfaces are sealed through sealing rings.
In some embodiments, the flange connection structure 8 is provided with the sealing gasket 11 for enhancing the sealing effect of the flange connection structure 8.
In some embodiments, the flange in the flange connection structure 8 is thickened, such as from 1cm to 2cm, or from 2cm to 4 cm; doubling and thickening the number of the bolts 13, for example, doubling from the original 4 bolts to 8 bolts, for example, thickening from the original M3 bolt to M6 bolt, or thickening from the original 8mm bolt to 16mm bolt; the sealing washer 11 is more flexible and can withstand the high temperature of 800-1100K, for example, the sealing washer is made of more flexible and high temperature resistant material, so as to reduce the gap between the first rod section 9 and the second rod section 10, thereby reducing the leakage.
In some embodiments, the contact surfaces of the flange edges in the flange connection structure 8 are filled and sealed by high-temperature sealant, and the high-temperature sealant is formed by polymerizing high-performance heat-resistant resin and various heat-resistant materials, and has the advantages of high bonding strength, good sealing performance, high temperature resistance (300-.
In some embodiments, the sealing assembly includes a sealing washer 11, a cover plate 12 and a bolt 13, and the sealing washer 11 is sleeved on the pull rod 2. The sealing assembly further comprises a through hole matched with the pull rod 2 is formed in the middle of the cover plate 12, the pull rod 2 is inserted into the through hole, the cover plate 12 is in close contact with the pull rod 2, and the cover plate 12 presses the sealing washer 11 downwards and then is fixedly connected with the honeycomb sealing sleeve 4 through the bolt 13.
In some embodiments, the first cooling channel 6 is U-shaped and its bend is close to the connection of the tie rod 2 for connection with the turbine blade 5 to be tested.
In some embodiments, the sum of the length of the honeycomb seal casing 4 and the length of the labyrinth seal casing 3 is less than the length of the tie rod 2.
In some embodiments, as shown in fig. 2, the labyrinth sealing sleeve 3 is provided with second cooling channels 14, and the second cooling channels 14 are distributed in the side wall of the labyrinth sealing sleeve 3 and in the labyrinth structure, so as to achieve sufficient cooling inside the labyrinth sealing sleeve 3.
In some embodiments, a cooling sleeve is arranged on the outer wall of the labyrinth sealing sleeve 3, the cooling sleeve is partially of a cylindrical structure and is sleeved on the outer wall of the sealing sleeve structure, a water outlet is formed in the upper end of the cylindrical structure, one part of the cooling sleeve is tightly attached to the outer wall of the liquid cooling device, a water inlet is formed in the tail end of the cooling sleeve, the cooling sleeve can rapidly guide away the heat of the fuel gas in the sealing sleeve structure, and the sealing sleeve structure can be effectively cooled.
In some embodiments, as shown in fig. 2, the side wall of the labyrinth sealing sleeve 3 is provided with an inlet 15 and an outlet 16 of the second cooling channel 14. The inlet 15 is arranged on the side wall of one end of the labyrinth sealing sleeve 3, and the outlet 16 is arranged on the side wall of the other end of the labyrinth sealing sleeve 3. The inlet 15 and the outlet 16 are respectively positioned at two longitudinal ends of the labyrinth sealing sleeve 3, and the labyrinth sealing sleeve 3 is cooled after cooling air or cooling liquid is introduced through the inlet 15 and the outlet 16, so that heat of gas is rapidly taken away, the labyrinth sealing sleeve 3 cannot be burnt out, and the flange connecting structure 8 cannot be burnt out.
In some embodiments, the first cooling channel 6 and the second cooling channel 14 are used for introducing cooling air or cooling liquid.
In some embodiments, as shown in fig. 3, the first cooling channel 6 is a single channel, and a water inlet pipe 24 is disposed in the channel, the water inlet pipe 24 extends into the bottom of the first cooling channel 6, and cooling air or cooling liquid enters from the water inlet pipe 24 to the bottom of the first cooling channel 6 and then exits through the channel between the water inlet pipe 24 and the first cooling channel 6, so as to cool the tie rod 2.
In some embodiments, the liquid cooling device 7 is a double-layer cylindrical structure, the front end of the liquid cooling device 7 is used for being connected with the outlet of the combustion chamber, at least one circle of liquid inlet hole is formed in the outer wall of the front end, the rear end of the liquid cooling device 7 is used for being connected with the exhaust device, at least one circle of liquid outlet hole is formed in the outer wall of the rear end, and a through passage for the end portion of the turbine blade 5 to be tested to be connected with the connecting portion of the pull rod 2 to enter and exit the cylinder is formed between the two layers of wall surfaces of the liquid cooling device 7.
In some embodiments, the cooling liquid in the liquid cooling device 7 may be water. The water used as the cooling liquid can be water at normal temperature or liquid cooling water which is cooled to be close to zero. In some embodiments, the cooling liquid in the liquid cooling device 7 may be a liquid with a lower freezing point than water. In other embodiments, the cooling liquid in the liquid cooling device 7 is cutting liquid commonly used in a machine tool cooling system. The lowest freezing point and heat exchange capacity are considered when selecting the cooling liquid.
In some embodiments, the inner wall surface of the liquid cooling device 7 is formed by welding high temperature alloy plates. The high-temperature alloy plate can be made of titanium alloy materials, single crystal materials, GH3044 materials and other materials capable of bearing high-temperature fuel gas of at least 1000K and even up to about 1200K.
In some embodiments, the outer wall surface of the liquid cooling device 7 is a stainless steel sleeve. Because the outer wall surface of the liquid cooling device 7 is not in direct contact with the high-temperature gas on the one hand, and is in contact with the external air environment on the other hand, the temperature of the internal cooling liquid heated by the high-temperature gas only needs to be borne.
In some embodiments, an interlayer is arranged between the stainless steel sleeve and the high-temperature alloy plate, and a cooling liquid for cooling is filled in the interlayer. In other embodiments, a drainage structure is arranged inside the liquid cooling device 7, so that the flow path and the flow time of the cooling liquid in the liquid cooling device 7 can be prolonged, sufficient heat exchange is realized, and the liquid cooling device 7 is cooled as much as possible.
In some embodiments, the cooling fluid in the first cooling channel 6 and the second cooling channel 14 may be water. The water used as the cooling liquid can be water at normal temperature or liquid cooling water which is cooled to be close to zero. In some embodiments, the cooling liquid in the first cooling channel 6 and the second cooling channel 14 may be a liquid with a lower freezing point than water. In other embodiments, the coolant in the first cooling channel 6 and the second cooling channel 14 is cutting fluid commonly used in machine tool cooling systems. The selection of the cooling liquid requires consideration of a freezing point as low as possible and good heat exchange capacity.
In some embodiments, the liquid cooling device 7 is provided with a temperature measuring mechanism and a pressure measuring mechanism, and the temperature measuring mechanism and the pressure measuring mechanism are respectively used for detecting the temperature and the pressure of the gas passing through the liquid cooling wall cylinder.
In some embodiments, the temperature measuring mechanism is a thermocouple 19. In some embodiments, the thermometry mechanism is also used to detect the surface temperature of the turbine blade 5 being tested.
In some embodiments, the pressure measurement mechanism is a pressure tube 20. In some embodiments, the thermometry mechanism includes a thermocouple 19 for flush mounting on the turbine blade 5 to be tested and detecting the surface temperature of the turbine blade 5 to be tested.
In some embodiments, the labyrinth sealing sleeve 3 is made of a high-temperature resistant material, and at least needs to withstand a high temperature of more than 1000K. In other embodiments, the labyrinth sealing sleeve 3 is made of a titanium alloy material, a single crystal material, a GH3044 material and other materials capable of bearing high-temperature fuel gas of at least 1000K and even up to about 1200K.
In some embodiments, a workbench 17 is disposed below the liquid cooling device 7, and the workbench 17 is used for being connected with a linear motion device and driving the turbine blade 5 to be tested to enter and exit the cylinder of the liquid cooling device 7 in a direction perpendicular to the longitudinal direction of the liquid cooling device 7 under the driving of the linear motion device.
In some embodiments, a force bearing support 18 is arranged on the working platform 17, and the working platform 17 is in supporting connection with the liquid cooling device 7 through the force bearing support 18.
In some embodiments, the force bearing support 18 is fixedly connected with the workbench 17 and the liquid cooling device 7 through bolts 13.
In some embodiments, the outrigger 18 is provided with a tenon connector 23, and the tenon connector 23 is used for fixing the tenon of the turbine blade 5 to be tested.
In some embodiments, the outrigger 18 is an i-shaped mount.
In some embodiments, as shown in fig. 4, the force bearing support 18 is a combined support, and is divided into at least two parts for combination, the force bearing support 18 clamps the tenon connector 23 in the middle, a groove is formed in the side wall of the force bearing support 18 facing the tenon connector 23, a protrusion matched with the groove is arranged at a position corresponding to the groove of the tenon connector 23, and the protrusion is clamped into the groove, so that the tenon connector 23, the force bearing support 18 and the workbench 17 can better bear the tensile force of the test turbine blade 5 as a whole, and the test turbine blade 5 can be limited in the horizontal direction, so that the shaking of the test turbine blade 5 is reduced, and the test accuracy is improved.
In some embodiments, a sealing gasket 11 is arranged between the force bearing support 18 and the liquid cooling device 7.
In some embodiments, a sealing gasket 11 is arranged between the force bearing support 18 and the workbench 17.
In some embodiments, the outrigger 18 is provided with a cooling gas duct 22, and the cooling gas duct 22 is used for introducing gas from an external gas supply device to cool the inside of the turbine blade 5 to be tested and form a gas film on the surface of the turbine blade 5 to be tested.
In some embodiments, a cooling gas pipe 22 is connected to the turbine blade 5 to be tested from the bottom of the workbench 17 through the workbench 17, the outrigger 18 and the tenon connector 23 in sequence.
In some embodiments, the linear motion device is a hydraulic ram 21.
In some embodiments, the tension mechanism is mounted to the ground by a fixture (not shown) to enable the tension mechanism to apply a mechanical load to the turbine blade 5 to be tested. In other embodiments, the tension mechanism is adapted to be suspended from a cross-beam mounted in a laboratory.
The above-described embodiments are intended to be illustrative, not limiting, of the invention, and therefore, variations of the example values or substitutions of equivalent elements are intended to be within the scope of the invention.
From the foregoing detailed description, it will be apparent to those skilled in the art that the foregoing objects and advantages of the invention have been achieved in accordance with the provisions of the patent statutes.
Claims (10)
1. A sectional type pull rod sealing system for a blade thermal engine coupling fatigue test is characterized by comprising a tension mechanism, a labyrinth sealing sleeve (3) and a honeycomb sealing sleeve (4);
the tensile mechanism comprises a tensile machine main body (1) and a pull rod (2) used for outputting tensile force, a connecting part used for being connected with the end part of a turbine blade (5) to be tested is arranged at the free end of the pull rod (2), and a first cooling channel (6) is arranged in the pull rod (2) along the longitudinal direction;
the labyrinth seal sleeve (3) and the honeycomb seal sleeve (4) are sequentially sleeved on the pull rod (2), one end of the labyrinth seal sleeve (3) is used for being connected with the outer wall of a liquid cooling device (7) for providing a gas test environment for the turbine blade (5) to be tested, and the other end of the labyrinth seal sleeve is connected with the honeycomb seal sleeve (4); a sealing assembly is arranged between one end, far away from the labyrinth sealing sleeve (3), of the honeycomb sealing sleeve (4) and the pull rod (2);
the labyrinth seal sleeve comprises a labyrinth seal sleeve (3) and a honeycomb seal sleeve (4), wherein the honeycomb seal sleeve (4) is connected through a flange connecting structure (8) and is connected with a non-labyrinth structure and a honeycomb structure at a connecting part, a pull rod (2) is divided into a first section rod (9) and a second section rod (10) which are connected through the flange connecting structure (8), and the first section rod (9) and the second section rod (10) are connected through the flange connecting structure (8) at a position which is positioned in the connecting part between the labyrinth seal sleeve (3) and the honeycomb seal sleeve (4).
2. The segmented tie rod sealing system for the thermal-engine coupling fatigue test of the blades as claimed in claim 1, wherein the sealing assembly comprises a sealing washer (11), and the sealing washer (11) is sleeved on the tie rod (2).
3. The segmented tie rod sealing system for the thermal-mechanical coupling fatigue test of the blade is characterized in that the sealing assembly further comprises a cover plate (12) and a bolt (13), a through hole matched with the tie rod (2) is formed in the middle of the cover plate (12), the tie rod (2) is inserted into the through hole, the cover plate (12) is in close contact with the tie rod (2), and the cover plate (12) is fixedly connected with the honeycomb sealing sleeve through the bolt (13) after downwards pressing the sealing washer (11).
4. A segmented tie rod sealing system for thermal-mechanical coupling fatigue testing of blades according to claim 1, characterized in that said first cooling channel (6) is U-shaped with its bend close to said connection of said tie rod (2) for connection with said turbine blade (5) to be tested.
5. The segmented tie rod sealing system for the blade thermo-mechanical coupling fatigue test as claimed in claim 1, wherein the sum of the length of the honeycomb sealing sleeve and the length of the labyrinth sealing sleeve (3) is smaller than the length of the tie rod (2).
6. The sectional type pull rod sealing system for the thermal-mechanical coupling fatigue test of the blades as claimed in claim 1, wherein the labyrinth sealing sleeve (3) is provided with a second cooling channel (14), and the second cooling channel (14) is distributed in the side wall of the labyrinth sealing sleeve (3) and in the labyrinth structure.
7. The segmented tie rod sealing system for blade thermo-mechanical coupling fatigue test according to claim 6, characterized in that the side wall of the labyrinth seal sleeve (3) is provided with the inlet (15) and outlet (16) of the second cooling channel (14).
8. The segmented tie rod sealing system for the thermal-mechanical coupling fatigue test of the blades as claimed in claim 7, wherein the inlet (15) is arranged on the side wall of one end of the labyrinth sealing sleeve (3), and the outlet (16) is arranged on the side wall of the other end of the labyrinth sealing sleeve (3).
9. The segmented tie rod sealing system for the thermal-mechanical coupling fatigue test of the blades as claimed in claim 8, wherein the inlet (15) and the outlet (16) are respectively located at the longitudinal two ends of the labyrinth seal sleeve (3).
10. The segmented tie rod sealing system for thermal-mechanical coupling fatigue testing of blades according to claim 6, wherein the first cooling channel (6) and the second cooling channel (14) are used for introducing cooling air or cooling liquid.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110140583.8A CN112903275B (en) | 2021-02-02 | 2021-02-02 | Sectional type pull rod sealing system for thermal engine coupling fatigue test of blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110140583.8A CN112903275B (en) | 2021-02-02 | 2021-02-02 | Sectional type pull rod sealing system for thermal engine coupling fatigue test of blade |
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| CN112903275A CN112903275A (en) | 2021-06-04 |
| CN112903275B true CN112903275B (en) | 2022-07-08 |
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| CN114486222A (en) * | 2022-01-26 | 2022-05-13 | 沈阳航空航天大学 | Composite experimental device for movable blade heat engine of air seal type gas turbine |
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2021
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| WO2009155591A1 (en) * | 2008-06-20 | 2009-12-23 | Test Devices Inc. | Systems and methods for producing thermal mechanical fatigue on gas turbine rotors in a spin test environment |
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| CN106383143A (en) * | 2016-10-20 | 2017-02-08 | 北京航空航天大学 | Rotating disc type thermal fatigue testing device for thermal barrier coating |
| CN108087549A (en) * | 2017-12-11 | 2018-05-29 | 中国航发沈阳发动机研究所 | Aero engine turbine blades cooling test sealing structure |
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