Heat insulation board structure

Abstract

The heat insulation plate structure for blocking heat transfer between the target component and the engine tail nozzle includes multiple layers of annular radiation shielding plates and an air guiding pipe. The multiple layers of annular radiation shielding plates respectively enclose an internal cavity and multiple annular cavities, and the air guiding pipe is used to introduce cooling gas; the internal cavity is communicated with the air guiding pipe and is used to accommodate and cool the target component, and one or more of the multiple annular cavities are communicated with the air guiding pipe and provide a flow space for the cooling gas. The above heat insulation plate structure can increase the thermal resistance of heat transfer between the engine and the target component, thereby greatly reducing heat transfer.

Description

Technical Field

[0001] The present invention relates to the field of thermal design of aero-engines, and particularly to heat dissipation components. Background Art

[0002] Generally, the temperature of components close to the mainstream side is high, while the temperature of components far from the mainstream side is relatively low. With the continuous development of aero-engines, this temperature difference further increases. Since the radiant heat transfer amount is proportional to the fourth power difference value of the absolute temperature, the radiant heat transfer in the disk cavity is generally not negligible. In order to reduce the risk of exceeding the material allowable temperature caused by the radiation of high-temperature components to low-temperature components, a radiation shielding plate structure is adopted in the design to reduce the radiant heat transfer.

[0003] In the experiment, a telemetry device needs to be installed to measure the relevant parameters of the rotating parts. The telemetry device is installed in the inner cavity of the tail cone and is affected by the radiation of the high-temperature tail nozzle. To ensure the accuracy of the measured parameters, the radiation effect also needs to be eliminated. Therefore, a simple, effective and feasible heat insulation plate for radiation prevention and cooling of the telemetry device needs to be designed. Summary of the Invention

[0004] An object of the present invention is to provide a heat insulation plate structure to block the heat transfer between the target component and the engine tail nozzle.

[0005] The heat insulation plate structure for achieving the above object includes multiple layers of annular radiation shielding plates and an air inlet pipe. The multiple layers of annular radiation shielding plates respectively enclose an internal cavity and multiple annular cavities. The air inlet pipe is used to introduce cooling gas; wherein, the internal cavity is communicated with the air inlet pipe and is used to accommodate and cool the target component, and one or more of the multiple annular cavities are communicated with the air inlet pipe and provide a flow space for the cooling gas.

[0006] In one or more embodiments, the multiple layers of annular radiation shielding plates are three layers of annular radiation shielding plates, and the three layers of annular radiation shielding plates respectively enclose an internal cavity, an intermediate annular cavity and an external annular cavity.

[0007] In one or more embodiments, each of the annular radiation shielding plates includes an annular outer wall and sealing walls located on both sides of the annular outer wall, and the air inlet pipe penetrates through the sealing walls.

[0008] In one or more embodiments, the outer surface of the external annular cavity includes ventilation holes, and the ventilation holes communicate the external annular cavity with the inner cavity of the tail nozzle.

[0009] In one or more embodiments, the air inlet pipe passes through the load-bearing casing and is used to drain the cooling gas in the outer casing of the engine.

[0010] In one or more embodiments, the annular radiation shielding plates are fixedly connected to the load-bearing casing to form a support structure.

[0011] In one or more embodiments, the annular radiation shielding plate is welded or bolted to the load-bearing casing.

[0012] In one or more embodiments, the outer surface of the annular radiation shielding plate is coated with a radiation shielding material.

[0013] In one or more embodiments, the target component is a telemetry device, and the telemetry device is installed at the tail end of the air duct in the engine tail cone.

[0014] In one or more embodiments, at least one layer of the annular cavity is a vacuum cavity.

[0015] By designing multiple layers of annular radiation shielding plates and the annular cavities formed thereby, the above-mentioned heat insulation plate structure can effectively increase the thermal resistance in the heat transfer path, reduce the temperature difference of the heat source component, and thus reduce the radiation heat transfer amount; at the same time, a cooling air flow is introduced into one or more of the internal cavity, the intermediate annular cavity, and the external annular cavity formed by the multiple layers of annular radiation shielding plates, and the convective heat transfer effect of the cooling air flow can be used to further reduce the heat transfer. If the target component is a component that needs to be cooled, the risk of overheating caused by the radiation of the high-temperature heat source to the target component can be effectively reduced, ensuring the safety of the target component; if the target component is a heat-generating component, the temperature difference between the engine and the target component can also be reduced, thereby significantly reducing the heat transfer. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The above and other features, properties, and advantages of the present invention will become more apparent from the following description in conjunction with the drawings and embodiments, where:

[0017] Figure 1 is an external view schematic diagram of the engine tail nozzle;

[0018] Figure 2 is a side view of the external appearance of the engine tail nozzle;

[0019] Figure 3 is a schematic diagram of an embodiment of the heat insulation plate structure;

[0020] Figure 4 is a schematic diagram of another embodiment of the heat insulation plate structure.

[0021] DESCRIPTION OF THE REFERENCE NUMERALS

[0022] 100 Tail nozzle

[0023] 150 Inner cavity of the tail nozzle

[0024] 200 Target component

[0025] 300 Heat insulation plate structure

[0026] 301 First outer-layer annular radiation shielding plate

[0027] 302 First middle-layer annular radiation shield

[0028] 303 First inner-layer annular radiation shield

[0029] 304 First air intake pipe

[0030] 311 Vent hole

[0031] 320 First outer ring cavity

[0032] 421 Annular outer wall

[0033] 422 Sealing wall

[0034] 330 First intermediate ring cavity

[0035] 340 First internal cavity

[0036] 404 Second air intake pipe

[0037] 401 Second outer-layer annular radiation shield

[0038] 402 Second middle-layer annular radiation shield

[0039] 403 Second inner-layer annular radiation shield

[0040] 420 Second outer ring cavity

[0041] 430 Second intermediate ring cavity

[0042] 440 Second internal cavity Detailed implementation manners

[0043] The following further describes the present invention in conjunction with specific embodiments and the accompanying drawings. More details are set forth in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from this description. Those skilled in the art can make similar generalizations and deductions according to the actual application situation without departing from the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment. It should be noted that these and subsequent other drawings are only examples, and they are not drawn under the condition of equal proportions, and should not be used to limit the actual required protection scope of the present invention.

[0044] The heat insulation plate structure involved in the present disclosure is installed inside the engine and is used to block the heat transfer between the target component and the engine tail nozzle. Refer to Figure 1 and Figure 2 As shown, the target component 200 is generally installed inside the engine tail nozzle 100, and the heat insulation plate structure 300 is arranged between the target component 200 and the tail nozzle 100, which can effectively block the heat transfer between the target component 200 and the engine tail nozzle 100.

[0045] In one embodiment, the target component 200 is a telemetry device installed at the rear side of the tail end of the air duct within the engine tail cone. During the engine test run, the telemetry device can measure the relevant parameters of rotating components, such as components like turbine rotors and disk wheels. The telemetry device needs to be maintained at an appropriate temperature during the measurement process; otherwise, the measurement accuracy will be affected. Therefore, it is necessary to reduce the high-temperature radiation of the tail pipe 100 on the telemetry device and block the heat transfer between the telemetry device and the engine tail pipe 100.

[0046] In addition, the target component is not limited to the above-mentioned telemetry device that needs to be cooled. It can also be a high-temperature heat-generating component. In this case, the heat insulation plate structure is used to block the heat generated by the high-temperature heat-generating component from dissipating into the engine inner cavity to inhibit the increase in the internal temperature of the engine.

[0047] The heat insulation plate structure 300 for achieving the above object includes multiple layers of annular radiation shielding plates and air inlet pipes. The multiple layers of annular radiation shielding plates respectively enclose an internal cavity and multiple annular cavities, and the air inlet pipes are used to introduce cooling gas; the internal cavity is communicated with the air inlet pipes and is used to accommodate and cool the target component, and one or more of the multiple annular cavities are communicated with the air inlet pipes and provide a flow space for the cooling gas.

[0048] In one embodiment, the multiple layers of annular radiation shielding plates are three layers of annular radiation shielding plates, and the three layers of annular radiation shielding plates respectively enclose an internal cavity, an intermediate annular cavity, and an external annular cavity. Figure 3 Understood in combination, the first inner-layer annular radiation shielding plate 303 encloses the first internal cavity 340, and the target component 200 is located in the first internal cavity 340. The first middle-layer annular radiation shielding plate 302 and the first inner-layer annular radiation shielding plate 303 jointly define the first intermediate annular cavity 330, and the first outer-layer annular radiation shielding plate 301 and the first middle-layer annular radiation shielding plate 302 jointly define the first external annular cavity 320.

[0049] The air inlet pipe passes through the load-bearing casing and is used to drain the cooling gas in the outer casing of the engine to the heat insulation plate structure. In Figure 3 the illustrated embodiment, the first internal cavity 340 is provided with ventilation holes to communicate with the first air inlet pipe 304 to cool the target component 200. In addition, one or more of the multiple annular cavities can also be communicated with the first air inlet pipe 304 to provide a flow space for the cooling gas and increase the convective heat transfer.

[0050] In one embodiment, the first air inlet pipe 304 has a plurality of openings. The first opening communicates with the first inner annular radiation shield plate 303 to supply cooling gas to the first internal cavity 340, and the second opening is used to supply cooling gas to the first intermediate annular cavity 330. In another embodiment, a plurality of ventilation holes 311 are formed in the first inner annular radiation shield plate 303. The first internal cavity 340 and the first intermediate cavity 330 communicate with each other through the ventilation holes 311 in the first inner annular radiation shield plate 303 to enable the flow of cooling gas.

[0051] Continuing to refer to Figure 3 As shown, preferably, the outer surface of the first outer annular cavity 320 includes ventilation holes 311. The ventilation holes 311 on the first outer annular cavity 320 communicate the first outer annular cavity 320 with the inner cavity 150 of the tail nozzle, and are used to introduce the cooling air flow in the first outer annular cavity 320 into the inner cavity 150 of the tail nozzle to maintain the continuous input of the cooling air flow in the annular cavity.

[0052] By providing multiple layers of annular radiation shield plates, the thermal resistance in the heat transfer process can be effectively increased. For radiation shield plates with the same emissivity, the radiative heat exchange between heat sources can be reduced to 1 / 2, effectively reducing the radiative heat exchange.

[0053] In addition, by introducing cooling gas into the internal cavities and multiple annular cavities formed by the multiple layers of annular radiation shield plates, the flow cooling effect can be further utilized to reduce the temperature, and the thermal resistance in the heat transfer process can be continuously increased, thereby further reducing the radiative heat and reducing the risk of overheating of the target component due to being irradiated by a high-temperature heat source.

[0054] In one embodiment, the outer surface of the radiation shield plate is coated with a radiation shielding material, or the radiation shield plate itself is a radiation-proof penetration material or a surface radiation protection material, such as radiation-proof glass, metal material, or inorganic non-metallic material, etc. Materials with radiation shielding functions can all be applied to the annular radiation shield plate, and preferably materials with a high radiation protection coefficient are used to enhance the heat insulation effect.

[0055] As in Figure 4 In another embodiment of the heat insulation plate structure shown, the second inner annular radiation shield plate 403 encloses a second internal cavity 440, and the target component 200 is located in the second internal cavity 440. The second middle annular radiation shield plate 402 and the second inner annular radiation shield plate 403 jointly define a second intermediate annular cavity 430, and the second outer annular radiation shield plate 401 and the second middle annular radiation shield plate 402 jointly define a second outer annular cavity 420.

[0056] In one embodiment, the annular radiation shield plates all include an annular outer wall and sealing walls located on both sides of the annular outer wall. The second air inlet pipe 404 penetrates through the sealing walls to enter the annular cavity. To Figure 4Taking the second outer annular radiation shield 401 as an example, the second outer annular radiation shield 401 includes an annular outer wall 421 and sealing walls 422 located at both ends of the annular outer wall 421. That is, the sealing walls 422 located at both axial ends of the engine and the annular outer wall 421 together enclose an annular space. The second air duct 404 passes through the sealing wall 422 on one side and enters the second outer annular cavity 420 and the second intermediate annular cavity 430. The opening at one end is communicated with the opening on the second middle annular radiation shield 402, and is used to release cooling gas into the second inner cavity 440. The second air duct 404 may further include other openings located in the spaces of the second intermediate annular cavity 430 and the second outer annular cavity 420, and is used to transport cooling gas into the spaces of the second intermediate annular cavity 430 and the second outer annular cavity 420 to realize the convective flow of the cooling air flow in the annular cavity.

[0057] The sufficient flow of the cooling air flow B in the second intermediate annular cavity 430 and the cooling air flow A in the second outer annular cavity 420 can enhance the convective heat transfer effect, further reduce the stability of the annular radiation shield itself, and thus also play the role of reducing the radiation heat. The cooling air flow A in the second outer annular cavity 420 will also release the cooling air flow into the inner cavity 150 of the tail nozzle through the ventilation holes to maintain the continuous input of the cooling air flow in the annular cavity.

[0058] In addition, the annular cavity formed by the multi-layer annular radiation shields can also be a vacuum annular cavity to further play the role of isolating heat transfer.

[0059] The above multi-layer annular radiation shields are fixedly connected to the load-bearing casing to form a support structure. In one embodiment, the annular radiation shield is welded to the load-bearing casing to form a support structure, effectively preventing vibration caused by the structure. In another embodiment, the annular radiation shield is bolted to the load-bearing casing to achieve the effect of detachable installation. The ways of fixedly connecting the multi-layer annular radiation shields to the load-bearing casing include but are not limited to the above embodiments. In other embodiments, the multi-layer annular radiation shields and the load-bearing casing can also adopt connection methods such as key connection to play a role in fixed support. Those skilled in the art should understand that any connection method that can fixedly connect the multi-layer annular radiation shields and the load-bearing casing can be applied to this disclosure without exceeding the scope of this disclosure.

[0060] By setting multi-layer radiation shields and introducing cooling secondary air flow into the annular cavity formed by the radiation shields, the above heat insulation plate structure can reduce the temperature difference between heat source components. The design of increasing the spatial radiation thermal resistance and the convective heat transfer effect of the cooling air flow can effectively reduce the radiation heat transfer amount, effectively reduce the heat transfer of temperature-sensitive components such as telemetry devices, and ensure the accuracy of measurement and the durability of the device.

[0061] While the invention has been disclosed above in preferred embodiments, it is not intended to limit the invention. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the invention. Therefore, all modifications, equivalent changes and decorations made to the above embodiments based on the technical essence of the invention without departing from the technical solution of the invention shall fall within the protection scope defined by the claims of the invention.

Claims

1. A heat insulation plate structure for blocking heat transfer between a target component and an engine tail nozzle, the target component being located inside the tail nozzle, characterized in that, The structure includes: multiple layers of annular radiation shielding plates, which respectively enclose an internal cavity and multiple layers of annular cavities; an air inlet pipe for introducing cooling gas; wherein, the internal cavity is communicated with the air inlet pipe and is used for accommodating and cooling the target component, and one or more of the multiple layers of annular cavities are communicated with the air inlet pipe and provide a flow space for the cooling gas.

2. The heat insulation board structure according to claim 1, wherein The multiple layers of annular radiation shielding plates are three-layer annular radiation shielding plates, which respectively enclose an internal cavity, an intermediate annular cavity and an external annular cavity.

3. The heat insulation board structure according to claim 2, wherein, Each of the annular radiation shielding plates includes an annular outer wall and sealing walls located on both sides of the annular outer wall, and the air inlet pipe penetrates through the sealing walls.

4. The heat insulation board structure according to claim 2, characterized in that, The outer surface of the external annular cavity includes ventilation holes, and the ventilation holes communicate the external annular cavity with the inner cavity of the tail nozzle.

5. The heat insulation board structure according to claim 1, wherein, The air inlet pipe passes through the load-bearing casing and is used for draining the cooling gas in the outer casing of the engine.

6. The heat insulation board structure according to claim 1, wherein The annular radiation shielding plates are fixedly connected to the load-bearing casing to form a support structure.

7. The heat insulation board structure according to claim 6, wherein, The annular radiation shielding plates are welded or bolted to the load-bearing casing.

8. The heat insulation board structure according to claim 1, wherein, The outer surface of the annular radiation shielding plates is coated with radiation shielding material.

9. The heat insulation board structure according to claim 1, wherein, The target component is a telemetry device, and the telemetry device is installed at the tail end of the air duct in the engine tail cone.

10. The heat insulation board structure according to claim 1, wherein, At least one layer of the annular cavities is a vacuum cavity.

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