CN215860357U - Radiation-proof heat-transfer engine rear casing and aircraft engine comprising same - Google Patents
Radiation-proof heat-transfer engine rear casing and aircraft engine comprising same Download PDFInfo
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- CN215860357U CN215860357U CN202120741169.8U CN202120741169U CN215860357U CN 215860357 U CN215860357 U CN 215860357U CN 202120741169 U CN202120741169 U CN 202120741169U CN 215860357 U CN215860357 U CN 215860357U
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Abstract
The utility model discloses a radiation-proof heat-transfer rear engine casing and an aero-engine comprising the same. According to the utility model, the radiation-proof heat insulation plate is arranged on the casing body of the rear casing of the engine, so that the situation that high-temperature heat generated in the operation process of the engine is transferred to the casing body in a thermal radiation mode can be avoided, the situation that the local area temperature of the rear casing of the engine is sharply increased to generate stress concentration can be avoided, the structural strength of the rear casing of the engine is further ensured not to be greatly influenced, and the safety of the engine is improved.
Description
Technical Field
The utility model relates to a radiation-proof heat-transfer engine rear casing and an aircraft engine comprising the same.
Background
When the aircraft engine is in actual working process, radiation heat transfer exists besides heat conduction between solids and convection heat exchange between the surface of the solids and fluid. Radiant heat transfer, which is one of three forms of heat transfer, exists non-negligibly, particularly in areas of high temperature and large temperature differences, the effect of which is even more non-negligible.
Radiation is often not negligible in areas where the temperature of hot end components of an aircraft engine is high and the temperature difference is large. Because the area of the tail nozzle is exposed in main stream fuel gas and is influenced by high-temperature fuel gas, the wall surface temperature of the tail nozzle is generally higher, and the wall surface temperature is close to the fuel gas temperature and can reach the high temperature of more than 1000K. In contrast, the temperature of the casing wall surface is similar to the temperature of the secondary flow and is far lower than the temperature of the main fuel gas when the secondary flow cooling effect is applied to the rear casing of the engine connected with the tail nozzle. In this case, the radiation of the jet pipe from the rear casing of the engine is particularly significant. Under partial high working conditions, the temperature of a rear casing of the engine is sharply increased under the influence of radiation, so that the strength problems such as large temperature gradient, stress concentration and the like occur, and the safety of the engine is further influenced.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that in the prior art, high temperature at a tail nozzle of an aircraft engine is easy to transfer heat into a rear case in a radiation mode, so that the temperature of the rear case is rapidly increased to generate stress concentration and influence the structural strength, and provides a radiation-proof heat-transfer rear case of the engine and the aircraft engine comprising the same.
The utility model solves the technical problems through the following technical scheme:
the utility model provides a radiation-proof heat-transfer rear engine casing which comprises a casing body and a radiation-proof heat insulation plate, wherein the radiation-proof heat insulation plate is arranged on the casing body, and is provided with a radiation-proof layer and a heat insulation layer, and the radiation-proof layer is positioned on one side far away from the casing body.
In this scheme, through set up the heat insulating board of protecting against radiation on the quick-witted casket body of quick-witted casket behind the engine, the condition that can avoid the engine to produce high temperature heat in the operation process and transmit to the quick-witted casket body through the form of heat radiation takes place to can avoid appearing the local region temperature sharply-rising of quick-witted casket behind the engine and produce the condition that stress concentrates, and then guarantee that the structural strength of quick-witted casket behind the engine does not receive great influence, improves engine security.
Preferably, the radiation-proof heat-insulating board and the casing body are detachably mounted.
In this scheme, adopt above-mentioned structural style, can change the radiation protection heat insulating board of different specifications according to thermal-insulated demand, convenient maintenance and change simultaneously.
Preferably, the radiation protection layer is made of metal with a smooth surface.
In the scheme, the metal has lower radiation emissivity after being subjected to smooth surface treatment, so that the absorption of radiation heat from a high-temperature component is reduced, and the influence of a high-temperature heat source is weakened.
Preferably, the thermal insulation layer is made of ceramic fibers.
In this scheme, ceramic fiber has light in weight, high temperature resistant, thermal stability is good, heat conductivity low grade advantage, can effectively strengthen the thermal-insulated ability of radiation protection heat insulating board.
Preferably, the radiation-proof heat insulation board further comprises a reinforcing layer, and the reinforcing layer is arranged on one side, away from the radiation-proof layer, of the heat insulation layer.
In this scheme, set up the enhancement layer and play the effect of protection and support, avoid the insulating layer to suffer damage, influence thermal-insulated ability.
The utility model provides an aircraft engine which comprises an engine rear case with radiation protection and heat transfer functions.
Preferably, the aircraft engine further comprises a tail pipe, wherein the tail pipe is provided with a central cone inner cavity which is communicated with an inner cavity of the rear engine casing;
the anti-radiation heat-insulation plate is arranged between the rear engine casing and the tail jet pipe, and the inner cavity of the central cone is isolated from the inner cavity of the rear engine casing by the anti-radiation heat-insulation plate.
In the scheme, the radiation-proof heat-insulating plate is arranged between the rear engine casing and the tail jet pipe, so that the thermal radiation generated by high temperature on the wall surface of the tail jet pipe is prevented from being transmitted to the rear engine casing through the central cone cavity of the tail jet pipe in a radiation heat transfer mode, the temperature of the rear engine casing can be always kept around the secondary flow temperature, and the situation that the structural strength is influenced by stress concentration caused by rapid increase of the local area temperature of the rear engine casing is avoided.
Preferably, the rear engine case is provided with an exhaust port, the radiation-proof heat-insulating plate is provided with a through hole, and two ends of the through hole are respectively communicated with the exhaust port and the inner cavity of the central cone.
In this scheme, through set up the through-hole that corresponds with the gas vent on the casing behind the engine on the heat insulating board of protecting against radiation for the secondary flow gas that gets into the inner chamber of casing behind the engine can be through the normal discharge of gas vent, avoids influencing in subsequent secondary flow gas gets into the casing behind the engine, makes the casing behind the engine can continuously carry out the secondary flow cooling, guarantees that the temperature of casing behind the engine maintains a state microthermal relatively.
Preferably, the exhaust nozzle is detachably mounted with the rear engine casing through a bolt, and a through hole for the bolt to pass through is formed in the radiation-proof heat-insulating plate.
In this scheme, adopt above-mentioned structural style, the jet nozzle passes through bolt and engine rear case demountable installation, can conveniently install the radiation protection heat insulating board between engine rear case and jet nozzle.
The positive progress effects of the utility model are as follows: according to the utility model, the radiation-proof heat insulation plate is arranged on the casing body of the rear casing of the engine, so that the situation that high-temperature heat generated in the operation process of the engine is transferred to the casing body in a thermal radiation mode can be avoided, the situation that the local area temperature of the rear casing of the engine is sharply increased to generate stress concentration can be avoided, the structural strength of the rear casing of the engine is further ensured not to be greatly influenced, and the safety of the engine is improved.
Drawings
FIG. 1 is a schematic view of the installation position of a radiation-proof heat-insulating board in an aircraft engine in the preferred embodiment of the utility model.
Fig. 2 is a schematic structural view of a radiation-proof heat-insulating board in a preferred embodiment of the present invention.
Description of reference numerals:
radiation protection heat insulation board 100
Radiation protective layer 101
Reinforcing layer 103
Detailed Description
The utility model will be more clearly and completely described below by way of examples and with reference to the accompanying drawings, without thereby limiting the scope of the utility model to these examples.
As shown in fig. 1, the aircraft engine 200 of the present embodiment includes a fan 201, a compressor 202, a combustion chamber 203, a turbine 204, and an exhaust nozzle 205. The aircraft engine 200 further includes an engine casing formed by splicing a plurality of modules, and the casing which is arranged at the rear side of the engine, surrounds the outer side of the turbine, and is connected with the tail nozzle 205 is called an engine rear casing.
The rear engine case comprises a case body and a radiation-proof heat-insulating board 100, wherein the radiation-proof heat-insulating board 100 is arranged on the case body. As shown in fig. 2, the radiation-proof and heat-insulating panel 100 has a radiation-proof layer 101 and a heat-insulating layer 102. The radiation protection layer 101 is located on the side away from the casing body. The radiation-proof heat-insulating plate 100 is arranged on the casing body of the rear casing of the engine, so that the situation that high-temperature heat generated in the operation process of the engine is transferred to the casing body in a thermal radiation mode can be avoided, the situation that the local area temperature of the rear casing of the engine is sharply increased to generate stress concentration can be avoided, the structural strength of the rear casing of the engine is not greatly influenced, and the safety of the engine is improved.
The jet nozzle 205 of the aircraft engine 200 has a central cone cavity that communicates with the cavity of the aft engine case. In this embodiment, as shown in fig. 1, a radiation protection heat shield 100 is provided between the rear engine case and the jet nozzle 205, and the radiation protection heat shield 100 isolates the inner cavity of the central cone from the inner cavity of the rear engine case.
According to the scheme, the radiation-proof heat-insulating plate 100 is arranged between the rear engine casing and the tail nozzle 205, so that the heat radiation generated by high temperature on the wall surface of the tail nozzle 205 is prevented from being transmitted to the rear engine casing through the cavity of the central cone of the tail nozzle in a radiation heat transfer mode, the temperature of the rear engine casing can be always kept around the secondary flow temperature, and the situation that the structural strength is influenced by stress concentration caused by rapid increase of the local area temperature of the rear engine casing is avoided.
The rear engine casing has an exhaust port, and the radiation-proof heat-insulating board 100 is provided with a through hole (not shown in the figure), and two ends of the through hole are respectively communicated with the exhaust port and the inner cavity of the central cone. Through the through hole which is arranged on the radiation-proof heat-insulating plate 100 and corresponds to the exhaust port on the rear engine casing, the secondary flow gas entering the inner cavity of the rear engine casing can be normally discharged through the exhaust port, the influence on the subsequent secondary flow gas entering the rear engine casing is avoided, the rear engine casing can be continuously cooled by the secondary flow, and the temperature of the rear engine casing is ensured to be maintained in a relatively low-temperature state.
In this embodiment, the exhaust nozzle 205 is detachably mounted to the rear casing of the engine by bolts, and the radiation-proof heat-insulating panel 100 is provided with through holes for the bolts to pass through. The tail pipe 205 is detachably mounted with the rear engine casing through bolts, so that the radiation-proof heat-insulating board 100 can be conveniently mounted between the rear engine casing and the tail pipe 205.
In this embodiment, the radiation-proof and heat-insulating panel 100 is detachably mounted to the casing body. The radiation-proof heat-insulating board 100 with different specifications can be replaced according to the heat-insulating requirement, and meanwhile, the maintenance and the replacement are convenient.
In this embodiment, the radiation protection layer 101 is a metal whose surface is subjected to a smooth surface treatment. The metal may be copper, aluminum, or an alloy containing copper and aluminum. The metal has lower radiation emissivity after being subjected to smooth surface treatment, so that the absorption of radiation heat from a high-temperature component is reduced, and the influence of a high-temperature heat source is weakened.
In the present embodiment, the thermal insulation layer 102 is made of ceramic fibers. The ceramic fiber has the advantages of light weight, high temperature resistance, good thermal stability, low thermal conductivity and the like, and can effectively enhance the heat insulation capability of the radiation-proof heat-insulating board 100. The thermal insulation layer 102 made of ceramic fiber can prevent the radiant heat obtained from the high-temperature wall surface from being further transferred to the low-temperature wall surface side, so that the engine rear case is better protected.
In other embodiments, the material of the thermal insulation layer 102 may also be other materials with high temperature resistance, good thermal stability and low thermal conductivity.
In this embodiment, the radiation-proof and heat-insulating board 100 further includes a reinforcing layer 103, and the reinforcing layer 103 is disposed on a side of the heat-insulating layer 102 away from the radiation-proof layer 101. In the present embodiment, metal is also used for the reinforcement layer 103. The reinforcing layer 103 is arranged to play a role in protection and support, so that the heat insulation layer 102 is prevented from being damaged and the heat insulation capability is prevented from being affected.
In other embodiments, the reinforcement layer 103 may not be provided, or the reinforcement layer 103 may be other materials that can meet the strength requirements.
While specific embodiments of the utility model have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the utility model is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the utility model, and these changes and modifications are within the scope of the utility model.
Claims (9)
1. A radiation-proof heat-transfer engine rear casing is characterized in that: the rear engine case comprises a case body and a radiation-proof heat insulation plate, wherein the radiation-proof heat insulation plate is arranged on the case body, the radiation-proof heat insulation plate is provided with a radiation-proof layer and a heat insulation layer, and the radiation-proof layer is positioned on one side far away from the case body.
2. The anti-radiation heat-transfer engine rear case of claim 1, wherein said anti-radiation heat-insulating board is detachably mounted with said case body.
3. The engine aft case that protects against radiation and transfers heat of claim 1, wherein said radiation protective layer is a metal with a smooth finish on its surface.
4. The anti-radiation heat-transfer engine aft case of claim 1, wherein the thermal insulation layer is made of ceramic fiber.
5. The radiation and heat transfer resistant engine rear case of claim 1, wherein said radiation shield and heat shield further comprises a reinforcing layer disposed on a side of said insulating layer facing away from said radiation shield layer.
6. An aircraft engine, characterized in that it comprises an anti-radiation heat-transfer engine aft case according to any one of claims 1-5.
7. The aircraft engine of claim 6, further comprising a jet nozzle having a central cone interior cavity in communication with an interior cavity of said aft engine case;
the anti-radiation heat-insulation plate is arranged between the rear engine casing and the tail jet pipe, and the inner cavity of the central cone is isolated from the inner cavity of the rear engine casing by the anti-radiation heat-insulation plate.
8. The aircraft engine according to claim 7, wherein the rear engine casing has an exhaust port, the radiation-proof heat-insulating plate is provided with a through hole, and two ends of the through hole are respectively communicated with the exhaust port and the inner cavity of the central cone.
9. The aircraft engine according to claim 7, wherein the jet nozzle is detachably mounted to the rear engine casing through a bolt, and the radiation-proof heat-insulating plate is provided with a through hole for the bolt to pass through.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120741169.8U CN215860357U (en) | 2021-04-08 | 2021-04-08 | Radiation-proof heat-transfer engine rear casing and aircraft engine comprising same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120741169.8U CN215860357U (en) | 2021-04-08 | 2021-04-08 | Radiation-proof heat-transfer engine rear casing and aircraft engine comprising same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215860357U true CN215860357U (en) | 2022-02-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120741169.8U Active CN215860357U (en) | 2021-04-08 | 2021-04-08 | Radiation-proof heat-transfer engine rear casing and aircraft engine comprising same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215860357U (en) |
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2021
- 2021-04-08 CN CN202120741169.8U patent/CN215860357U/en active Active
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