CN112629842A - Heating and cooling integrated device for strength test of aero-engine wheel disc - Google Patents
Heating and cooling integrated device for strength test of aero-engine wheel disc Download PDFInfo
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- CN112629842A CN112629842A CN202011367306.2A CN202011367306A CN112629842A CN 112629842 A CN112629842 A CN 112629842A CN 202011367306 A CN202011367306 A CN 202011367306A CN 112629842 A CN112629842 A CN 112629842A
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- cooling
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- heat
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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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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25D—REFRIGERATORS; COLD ROOMS; ICE-BOXES; COOLING OR FREEZING APPARATUS NOT OTHERWISE PROVIDED FOR
- F25D31/00—Other cooling or freezing apparatus
- F25D31/005—Combined cooling and heating devices
Abstract
The application provides a heating and cooling integrated device for an aircraft engine wheel disc strength test, which comprises a heat insulation layer (1), a heating body (2) and a cooling body (3), wherein the heat insulation layer (1) is of a circular cavity structure, and the aircraft engine wheel disc is placed inside the heat insulation layer; the heating body (2) comprises a plurality of mutually independent heating bodies, the cooling body (3) comprises a plurality of mutually independent cooling pipes, and a cooling medium is introduced into each cooling pipe; heating bodies (2) are arranged in the heating area of the upper surface and the heating area of the lower surface in the heat-insulating layer (1), and cooling bodies (3) are arranged in the cooling area of the upper surface and the cooling area of the lower surface in the heat-insulating layer (1); a first temperature measuring hole is formed between a heating area and a cooling area at the lower end in the heat insulation layer (1), a second temperature measuring hole is formed in the middle area of the lower end in the heat insulation layer (1), and the diameter ranges of the first temperature measuring hole and the second temperature measuring hole cover the wheel disc of the aero-engine.
Description
Technical Field
The application relates to the field of aero-engines, in particular to a heating and cooling integrated device for an aero-engine wheel disc strength test.
Background
The strength test of the disk of the aero-engine is a research and examination test subject which must be developed in the engine development process, the main test aim is to simulate the real working state of the disk on a disk tester, examine the strength and service life reserve of the disk under corresponding working conditions and provide test data support for service setting. When the engine works, the temperature of the wheel disc is gradually reduced from the wheel rim to the wheel center, the temperature difference of the wheel rim and the wheel center can reach 200 ℃, the method is limited to the existing wheel disc test heating control technology, the designed wheel disc strength test is mostly equivalent to a uniform temperature field, but the test result can be influenced when the difference with the actual working condition is larger, particularly in a low-cycle test, the test result with larger difference with the engine state can be caused, and the test is invalid. On a wheel disc tester, in order to ensure the accuracy of the test, the same temperature gradient field in the service of the wheel disc must be truly reproduced.
The conventional heating device for the strength test of the wheel disc in China is a common upper and lower furnace disc type universal large-space radiation heating device, and is suitable for carrying out over-rotation and low-cycle tests on wheel discs with different structures. The heating device in the invention patent CN 109798771A only considers the lowest part of the life for the low-cycle fatigue test of the engine turbine disk, and is limited to providing a uniform temperature field for a test piece. The invention patent CN 110987390A provides a rotary fatigue test device capable of realizing a turbine blade gradient temperature field, which adopts electromagnetic induction heating to quickly heat a turbine blade, and adopts a cooling water cooling heat dissipation mode for a turbine disk body to realize the temperature gradient between the blade and the disk body, but the temperature of the disk body has no specific control target value. The device is only suitable for heating the rotating blades, but cannot be used for a wheel disc with a larger diameter.
At present, a common method for establishing a large-size wheel disc gradient temperature field at home and abroad is to add a path of cooling medium (gas or water) to a disc center, take away heat of the disc center, and heat from the disc edge part at the same time to form the gradient temperature field. However, since the disk center is limited to a small size, the cooling device is limited in structure, and the region affected by the cooling medium is limited, it is difficult to form a stable gradient temperature field.
The existing radiant heating furnace plate structure is generally in an up-and-down symmetrical structure, heating wires are arranged in a ring shape, the power of each heating wire can be controlled independently, and the structural schematic diagram is shown in fig. 1 and fig. 2. The existing heating device is a cylindrical cavity and comprises two heating furnace plates which are symmetrical up and down, wherein fig. 1 is a structural schematic diagram of the existing heating device, and fig. 2 is a structural schematic diagram of a lower furnace plate of the existing heating furnace. The structure consists of a heat-insulating layer 1, a heating area 12, a heating area 13, a heating area 14, a heating area 15 and a temperature measuring hole 16. The structure can realize the heating of the rotating part in the heating device by independently controlling the power of the heating area 12, the heating area 13, the heating area 14 and the heating area 15.
In the prior art, in the strength test of an aeroengine wheel disc, the temperature gradient of the wheel disc in the radial direction is difficult to maintain for a long time in the process of rotating and heating the wheel disc.
Disclosure of Invention
In order to solve the technical problem, the application provides an aeroengine rim plate intensity is experimental with cooling integrative device that heats, can keep rim plate radial direction temperature gradient for a long time.
The application provides an aeroengine rim plate intensity test is with cooling integrative device that heats, the device includes heat preservation (1), heats body (2) and cooling body (3), wherein:
the heat-insulating layer (1) is of a circular cavity structure, and an aero-engine wheel disc is placed inside the heat-insulating layer; the heating body (2) comprises a plurality of mutually independent heating bodies, the cooling body (3) comprises a plurality of mutually independent cooling pipes, and a cooling medium is introduced into each cooling pipe; the upper surface in the heat-insulating layer (1) comprises a heating area and a cooling area, the lower surface in the heat-insulating layer (1) comprises a heating area and a cooling area, the heating area on the upper surface in the heat-insulating layer (1) and the heating area on the lower surface in the heat-insulating layer are arranged oppositely, and the cooling area on the upper surface in the heat-insulating layer (1) and the cooling area on the lower surface in the heat-insulating layer (1) are arranged oppositely; heating bodies (2) are arranged in the heating area of the upper surface and the heating area of the lower surface in the heat-insulating layer (1), and cooling bodies (3) are arranged in the cooling area of the upper surface and the cooling area of the lower surface in the heat-insulating layer (1); a first temperature measuring hole (4) is formed between a heating area and a cooling area of the lower end in the heat preservation layer (1), a second temperature measuring hole (5) is formed in the middle area of the lower end in the heat preservation layer (1), and the diameter ranges of the first temperature measuring hole (4) and the second temperature measuring hole (5) cover the wheel disc of the aero-engine.
Specifically, a heating body (2) is arranged in a heating area on the upper surface and a heating area on the lower surface in the heat-insulating layer (1) in a mechanical fixing mode;
a cooling body (3) is arranged in the cooling area of the upper surface and the cooling area of the lower surface in the heat-insulating layer (1) in a mechanical fixing mode;
specifically, the mechanical fixing mode includes bolt fixing and welding fixing.
Specifically, the heating element comprises a resistance wire.
Specifically, binding post is reserved outside heat preservation (1), binding post is connected with a plurality of heat-generating bodies in the region of heating, binding post is used for the power of heating of each heat-generating body of independent control.
Specifically, a cooling medium supply line joint and a loop joint are reserved outside the heat insulation layer (1), and the supply line joint and the loop joint are connected with a plurality of cooling pipes in a cooling area and used for providing circulating cooling medium for each cooling pipe and adjusting the flow and pressure of the cooling medium in the cooling pipes.
Specifically, the heating body (2) comprises a plurality of mutually independent arc-shaped heating bodies.
Specifically, the cooling body (3) comprises a plurality of independent arc-shaped cooling pipes.
In conclusion, the heating and cooling integrated device for the strength test of the aero-engine wheel disc can achieve the purposes that different areas of the wheel disc in the radial direction are heated and cooled simultaneously in the rotating heating test process, the heat absorption balance of the different areas of the wheel disc in the radial direction is achieved, and a temperature field with gradient, which can be kept in the radial direction of the wheel disc for a long time, is established.
Drawings
FIG. 1 is a schematic structural diagram of a heating device in the prior art;
FIG. 2 is a schematic view of a lower plate structure of a heating furnace in the prior art;
FIG. 3 is a schematic structural diagram of a heating and cooling integrated device for an aircraft engine wheel disc strength test provided by the application;
wherein: 11-a heat-insulating layer; 12-heating zone 1; 13-heating zone 2; 14-heating zone 3; 15-heating zone 4; 16-temperature measuring holes; 1-an insulating layer; 2-heating the body; 3-a cooling body; 4-a first temperature measuring hole; 5-second temperature measuring hole.
Detailed Description
The invention still adopts a symmetrical structure of an upper furnace plate and a lower furnace plate (as shown in figure 1), on the basis, the heating area 12, the heating area 13, the heating area 14 and the heating area 15 which are in the circle in figure 2 are changed into a semi-ring shape, cooling bodies (3) corresponding to the heating area 12, the heating area 13, the heating area 14 and the heating area 15 are added, and a continuous stable temperature gradient is established by controlling the heating power of the corresponding positions of the heating area and the flow and pressure of a cooling medium of the corresponding positions of the cooling area. The structure of the invention is shown in figure 3.
The structure of the invention is composed of a heat-insulating layer 1, a heating body (2) and a cooling body (3). The heating body and the cooling body are fixed on the heat-insulating layer (1) in a mechanical fixing mode, a wiring terminal is reserved outside the heat-insulating layer (1) to supply power to each heating body of the heating area, and the heating power of the heating body at different positions can be independently controlled; the cooling medium supply and loop joints are reserved to provide circulating cooling medium for each path of the cooling body, and the circulating cooling medium is provided by a circulating cooling system, and the system can adjust the flow and the pressure.
In the heating test of the rotating part, the heating power, the flow and the pressure of the cooling medium in the cooling pipe can be adjusted according to the structure of a test piece, so that a stable temperature field with radial temperature gradient is established, and a stable uniform temperature field can also be established.
The method can be applied to the gradient temperature field heating test of the strength test of the aircraft engine wheel disc. Utilize current heating apparatus to heat the engine wheel dish, adjust corresponding heating zone power, can't effectively adjust the rotating member on corresponding position temperature, the reason is that the radial temperature transfer rate of rotating member is fast, can't last stable temperature gradient.
Claims (8)
1. The utility model provides an aeroengine rim plate intensity is experimental with integrative device of cooling that heats which characterized in that, the device includes heat preservation (1), heats body (2) and cooling body (3), wherein:
the heat-insulating layer (1) is of a circular cavity structure, and an aero-engine wheel disc is placed inside the heat-insulating layer; the heating body (2) comprises a plurality of mutually independent heating bodies, the cooling body (3) comprises a plurality of mutually independent cooling pipes, and a cooling medium is introduced into each cooling pipe; the upper surface in the heat-insulating layer (1) comprises a heating area and a cooling area, the lower surface in the heat-insulating layer (1) comprises a heating area and a cooling area, the heating area on the upper surface in the heat-insulating layer (1) and the heating area on the lower surface in the heat-insulating layer are arranged oppositely, and the cooling area on the upper surface in the heat-insulating layer (1) and the cooling area on the lower surface in the heat-insulating layer (1) are arranged oppositely; heating bodies (2) are arranged in the heating area of the upper surface and the heating area of the lower surface in the heat-insulating layer (1), and cooling bodies (3) are arranged in the cooling area of the upper surface and the cooling area of the lower surface in the heat-insulating layer (1); a first temperature measuring hole (4) is formed between a heating area and a cooling area of the lower end in the heat preservation layer (1), a second temperature measuring hole (5) is formed in the middle area of the lower end in the heat preservation layer (1), and the diameter ranges of the first temperature measuring hole (4) and the second temperature measuring hole (5) cover the wheel disc of the aero-engine.
2. The apparatus of claim 1,
a heating body (2) is arranged in a heating area on the upper surface and a heating area on the lower surface in the heat-insulating layer (1) in a mechanical fixing mode;
the cooling body (3) is arranged in the cooling area of the upper surface and the cooling area of the lower surface in the heat-insulating layer (1) in a mechanical fixing mode.
3. The apparatus of claim 2, wherein the mechanical fastening means comprises bolting and welding.
4. The apparatus of claim 1, wherein the heat generating body comprises a resistance wire.
5. The device according to claim 1, characterized in that a terminal is reserved outside the heat-insulating layer (1), the terminal is connected with a plurality of heating elements in the heating area, and the terminal is used for independently controlling the heating power of each heating element.
6. The device according to claim 1, characterized in that a cooling medium supply connection and a cooling medium return connection are reserved outside the heat insulation layer (1), and are connected with a plurality of cooling pipes of the cooling area for supplying circulating cooling medium to each cooling pipe and adjusting the flow and pressure of the cooling medium in the cooling pipes.
7. The device according to claim 1, wherein the heating body (2) comprises a plurality of arc-shaped heating bodies independent of each other.
8. The device according to claim 1, characterized in that the cooling body (3) comprises a plurality of mutually independent curved cooling pipes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011367306.2A CN112629842B (en) | 2020-11-27 | 2020-11-27 | Heating and cooling integrated device for strength test of aero-engine wheel disc |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011367306.2A CN112629842B (en) | 2020-11-27 | 2020-11-27 | Heating and cooling integrated device for strength test of aero-engine wheel disc |
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| CN112629842A true CN112629842A (en) | 2021-04-09 |
| CN112629842B CN112629842B (en) | 2022-06-28 |
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| CN202011367306.2A Active CN112629842B (en) | 2020-11-27 | 2020-11-27 | Heating and cooling integrated device for strength test of aero-engine wheel disc |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113865876A (en) * | 2021-08-24 | 2021-12-31 | 东南大学 | Turbine detection system in high-temperature environment |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113865876A (en) * | 2021-08-24 | 2021-12-31 | 东南大学 | Turbine detection system in high-temperature environment |
| CN113865876B (en) * | 2021-08-24 | 2023-11-24 | 东南大学 | Detection system of turbine in high temperature environment |
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