Aircraft impulse engine heat protection structure, impulse engine and aircraft

Abstract

The utility model discloses an aircraft impulse engine heat-proof structure, an impulse engine and an aircraft, and relates to the aerodynamic thermal protection design technology of high-speed aircrafts, the aircraft impulse engine heat-proof structure comprises a heat-proof assembly, and the heat-proof assembly comprises a spray pipe heat-proof blocking cover used for being connected with the outflow end of an engine spray pipe. The hot blocking prevention cover of the spray pipe comprises a hot blocking prevention cover disc face used for covering the outflow end of the engine spray pipe. The circulation assembly comprises an annular blocking cover groove formed in the side face, facing the impulse engine, of the heat-proof blocking cover disc face, and the annular blocking cover groove is inwards concaved by a certain depth in the thickness direction of the heat-proof blocking cover disc face so that an annular thickness weak area can be formed in the heat-proof blocking cover disc face and used for preventing the heat-proof blocking cover disc face from being damaged when the impulse engine works. When the aircraft flies, the airflow exhausted from the engine jet pipe rushes through the annular thickness weak area, and when the aircraft flies, the airflow exhausted from the engine jet pipe rushes through the annular thickness weak area, so that normal circulation of heat flow can be guaranteed, and meanwhile, hot air is prevented from entering an engine compartment.

Description

Technical Field

[0001] The present invention relates to the technology of aerodynamic heat protection design for high-speed aircraft, and particularly relates to a heat protection structure for an impulse engine of an aircraft, an impulse engine, and an aircraft. Background Art

[0002] With the increase in range, the reentry Mach number increases, and hypersonic aircraft face severe aerodynamic heating during flight. For box-launched hypersonic aircraft, when launching out of the box, an impulse engine needs to be designed on the aircraft to resist the pitching moment of the aircraft caused by the inconsistent out-of-box time of the front and rear sliders and the gravity factor, and to adjust the attitude of the aircraft. Considering the working requirements of the impulse engine, when the aircraft is in a parked state, a plug structure is required at the impulse engine to effectively prevent dust and moisture from entering the interior of the impulse engine, thereby protecting the impulse engine from damage. When the aircraft is in a flight state, the plug structure is automatically unloaded under the action of the nozzle gas.

[0003] Based on the above structure, after the plug structure is separated, during the high Mach number flight of the aircraft after leaving the box, there is no plug at the outflow part of the impulse engine nozzle, forming a local pit, and the outflow part of the impulse engine nozzle is exposed. In a high-temperature environment, the detachment of the plug structure may allow more hot air to enter the engine compartment, thereby increasing the heat dissipation burden and threatening the flight safety of the hypersonic aircraft, bringing greater potential safety hazards. Summary of the Utility Model

[0004] The present application provides a heat protection structure for an impulse engine of an aircraft, an impulse engine, and an aircraft, which can solve the technical problem in the prior art that during the high Mach number flight of the aircraft, the dust-proof plug at the outlet of the impulse engine will be automatically unloaded, resulting in the exposure of the outflow part of the impulse engine nozzle. In a high-temperature environment, the detachment of the nozzle plug may allow more hot air to enter the engine compartment, thereby increasing the heat dissipation burden, threatening the flight safety of the aircraft, and bringing greater potential safety hazards.

[0005] In a first aspect, an embodiment of the present application provides a heat protection structure for an impulse engine of an aircraft, including:

[0006] A heat protection component, the heat protection component includes a nozzle heat protection plug for connecting the outflow end of the engine nozzle, and the nozzle heat protection plug includes a heat protection plug disk surface for covering the outflow end of the engine nozzle;

[0007] The flow component, the flow component includes an annular plugging groove formed on the side of the heat insulation plugging cover plate facing the impulse engine, and the annular plugging groove is recessed inward by a certain depth in the thickness direction of the heat insulation plugging cover plate to form an annular thickness weak area on the heat insulation plugging cover plate, so as to be used for when the impulse engine works, the airflow discharged from the engine nozzle blows open the annular thickness weak area.

[0008] Combined with the first aspect, in an embodiment, the annular plugging groove is concentrically arranged with the heat insulation plugging cover plate.

[0009] In an embodiment, the depth of the annular plugging groove is less than the thickness of the heat insulation plugging cover plate.

[0010] In an embodiment, the nozzle heat insulation plugging cover further includes a heat insulation plugging cover ring surface for sleeving on the outer periphery of the outflow end of the engine nozzle.

[0011] In an embodiment, a connection unit for detachably connecting with the outer periphery of the engine nozzle is arranged on the heat insulation plugging cover ring surface.

[0012] In an embodiment, the connection unit includes at least two connection screw holes formed on the heat insulation plugging cover ring surface, and any two opposite connection screw holes are radially symmetric along the heat insulation plugging cover ring surface.

[0013] In an embodiment, a connection bolt for penetrating the tube body of the engine nozzle is arranged in the connection screw hole.

[0014] In the second aspect, an embodiment of the present application provides an impulse engine, and the above-mentioned engine heat insulation structure is arranged at the outflow end of the nozzle of the impulse engine.

[0015] Combined with the second aspect, in an embodiment, an adiabatic material layer is arranged on the inner wall of the nozzle of the impulse engine.

[0016] In the third aspect, an embodiment of the present application provides an aircraft, and at least one of the above-mentioned impulse engines is arranged on the aircraft.

[0017] The beneficial effects brought by the technical solution provided by the embodiment of the present application include:

[0018] 1. The heat insulation structure of the impulse engine of the aircraft provided by the embodiment of the present application can set an annular plugging groove on the heat insulation plugging cover plate in the nozzle heat insulation plugging cover and form an annular thickness weak area, so that during the flight of the aircraft, the airflow discharged from the engine nozzle blows open the annular thickness weak area, which can prevent hot air from entering the engine compartment while ensuring the normal circulation of heat flow, and reduce the heat dissipation burden of the aircraft;

[0019] 2. The heat protection structure of the impulse engine of the aircraft provided by the embodiment of the present application can effectively prevent foreign objects such as dust, moisture, and small animals from entering the impulse engine during the parking or ground maintenance of the aircraft by setting a nozzle heat protection plug cover at the engine nozzle, thereby protecting the impulse engine from damage. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0021] Figure 1 It is a schematic longitudinal sectional view of a heat protection structure of an impulse engine of an aircraft provided by an embodiment of the present application;

[0022] Figure 2 It is a schematic structural view of a connection unit in a heat protection structure of an impulse engine of an aircraft provided by an embodiment of the present application;

[0023] Figure 3 It is a schematic view of the installation position of an impulse engine in an aircraft provided by an embodiment of the present application.

[0024] In the figure: 1. Nozzle heat protection plug cover; 101. Heat protection plug cover disk surface; 102. Heat protection plug cover ring surface; 2. Ring-shaped plug groove; 3. Ring-shaped thickness weak area; 4. Connection screw hole; 5. Connection bolt; 6. Engine nozzle; 7. Thermal insulation material layer. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0025] In order to enable those skilled in the art to better understand the solutions of the present application, the following will clearly and completely describe the technical solutions in the embodiments of the present application in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only some embodiments of the present application, rather than all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present application.

[0026] In the first aspect, the embodiment of the present application provides a heat protection structure of an impulse engine of an aircraft, which can solve the technical problem existing in the prior art that during the high Mach number flight of the aircraft, the dust-proof plug cover at the outlet part of the impulse engine will be automatically unloaded, resulting in the exposure of the outlet part of the impulse engine. In a high-temperature environment, the detachment of the nozzle plug cover may allow more hot air to enter the engine compartment, thereby increasing the heat dissipation burden and threatening the flight safety of the aircraft, bringing greater potential safety hazards.

[0027] The heat protection structure of the impulse engine of the aircraft in this application includes a heat protection component and a circulation component. When the assembly is completed, the heat protection component is sleeved on the outflow end of the engine nozzle 6, and the circulation component is arranged on the heat protection component. When the aircraft is stationary, the circulation component can play a role in preventing dust from the engine nozzle 6. When the aircraft is running, some structures in the circulation component automatically fall off, playing a role in heat insulation while ensuring the normal circulation of the hot air ejected from the engine nozzle 6.

[0028] Specifically, Figure 1 FIG. is a schematic longitudinal sectional view of a heat protection structure of an impulse engine of an aircraft provided by an embodiment of this application. Figure 2 FIG. is a schematic structural view of a connection unit in a heat protection structure of an impulse engine of an aircraft provided by an embodiment of this application. As Figure 1 、 Figure 2 shown, the heat protection component includes a nozzle heat protection plug cover 1 for connecting the outflow end of the engine nozzle 6. The nozzle heat protection plug cover 1 includes a heat protection plug cover disk surface 101 for covering the outflow end of the engine nozzle 6. The circulation component includes an annular plug cover groove 2 opened on the side surface of the heat protection plug cover disk surface 101 facing the impulse engine. The annular plug cover groove 2 is recessed inward by a certain depth in the thickness direction of the heat protection plug cover disk surface 101 to form an annular thickness weak area 3 on the heat protection plug cover disk surface 101, so as to be used for when the impulse engine works, the heat flow discharged from the engine nozzle 6 flushes open the annular thickness weak area 3.

[0029] Based on the installation position and action mechanism, the nozzle heat protection plug cover 1 in this application is made of a material with high strength, high hardness, high temperature, and high thermal stability. In an embodiment of this application, the material of the nozzle heat protection plug cover 1 is a high silica fiber reinforced phenolic resin molded product, which can withstand high-temperature ablation occasions, and while meeting the strength requirements, can also reduce weight and improve the overall performance.

[0030] The diameter of the heat-blocking cover disk 101 is equal to the diameter of the outlet end of the engine nozzle 6. After assembly, the heat-blocking cover disk 101 completely covers the outlet of the engine nozzle 6. In the absence of external force, the annular cover groove 2 opens at one end facing the impulse engine nozzle 6 and is recessed to a certain depth on the heat-blocking cover disk 101 in the direction away from the engine nozzle 6. The recessed depth of the annular cover groove 2 is less than the thickness of the heat-blocking cover disk 101. The annular cover groove 2 is cocentrically arranged with the heat-blocking cover disk 101. Based on this arrangement, the thickness of the portion of the heat-blocking cover disk 101 provided with the annular cover groove 2 is less than the thickness of other areas, thereby forming An annular thickness weak area 3. When the impulse engine is running, the heat flow flowing out from the impulse engine nozzle 6 enters the annular plugging cover groove 2. When the impact force of the heat flow reaches a certain level, the plate body of the annular thickness weak area 3 can be opened. At this point, part of the plate body of the heat-proof plugging cover disk 101 within the inner circumference of the annular plugging cover groove 2 falls off from the heat-proof plugging cover disk 101, and the airflow discharged from the engine nozzle 6 flows out from the place where part of the plate body of the heat-proof plugging cover disk 101 falls off. The remaining plate body of the heat-proof plugging cover disk 101 is still connected to the outflow end of the engine nozzle 6, thereby achieving normal discharge of the impulse engine heat flow while effectively preventing external hot air from entering the engine compartment.

[0031] Furthermore, the nozzle heat-blocking cover 1 also includes a heat-blocking cover annular surface 102 for being sleeved on the outer periphery of the outlet end of the engine nozzle 6. The nozzle heat-blocking cover 1 is in a cover shape as a whole and the nozzle heat-blocking cover 1 is detachably connected to the engine nozzle 6. The heat-blocking cover annular surface 102 is fixedly connected to the heat-blocking cover disk 101 to form a whole. After the assembly is completed, the heat-blocking cover annular surface 102 is connected to the outer periphery of the engine nozzle 6 to facilitate the replacement of the nozzle heat-blocking cover 1.

[0032] Furthermore, a connection unit for detachably connecting to the outer periphery of the engine nozzle 6 is provided on the annular surface 102 of the heat shield. The heat shield 1 and the engine nozzle 6 can be detachably connected in a variety of ways, including but not limited to threaded connection, snap-fit connection, etc. The connection between the heat shield 1 and the engine nozzle 6 needs to consider the ease of disassembly and the stability of the connection. Therefore, in one embodiment of the present application, the heat shield 1 and the engine nozzle 6 are preferably connected by bolts.

[0033] Specifically, the connecting unit includes at least two connecting screw holes 4 formed on the toroidal surface 102 of the heat-proof plug cover. Any two opposite connecting screw holes 4 are radially symmetric along the toroidal surface 102 of the heat-proof plug cover. A connecting bolt 5 for penetrating the tube body of the engine nozzle 6 is provided in the connecting screw hole 4. To ensure connection stability and uniform force distribution, the number of connecting screw holes 4 is at least two radially symmetrically arranged along the toroidal surface 102 of the heat-proof plug cover. When the number of connecting screw holes 4 is multiple, the multiple connecting screw holes 4 are equidistantly arranged. At the same time, fitting screw holes equal in number and position to the connecting bolts 5 are formed on the tube body of the engine nozzle 6. Subsequently, the connecting bolts 5 pass through the connecting screw holes 4 and the fitting screw holes to achieve the detachable connection between the heat-proof plug 1 and the engine nozzle 6.

[0034] In a second aspect, the present application further provides an impulse engine. The outflow end of the nozzle of the impulse engine is provided with the above-mentioned engine heat-proof structure, and the outflow end of the nozzle of the impulse engine is detachably connected to the above-mentioned engine heat-proof structure. At the same time, to further implement the heat protection measures for the impulse engine, an adiabatic material layer 7 is provided on the inner wall of the nozzle of the impulse engine. The adiabatic material layer 7 is leveled at the connection between the heat-proof plug 1 and the engine. Based on this setting, not only can the heat-proof efficiency of the impulse engine be improved, but also local pits, protrusions and reverse air flow steps can be avoided.

[0035] In an embodiment of the present application, the adiabatic material layer 7 is a heat protection coating. Generally, commonly used heat protection coatings include aerogel thermal insulation coatings, ceramic thermal insulation coatings, vacuum glass microsphere heat insulation coatings, nano heat insulation coatings, etc. The specific material can be determined according to actual usage requirements and is not specifically limited in the present application.

[0036] In a third aspect, the present application further provides an aircraft. The aircraft is provided with at least one of the above-mentioned impulse engines, and the impulse engines are evenly arranged on the aircraft. Taking the number of impulse engines as four as an example, Figure 3 is a schematic diagram of the installation position of the impulse engine in an aircraft provided by an embodiment of the present application. As Figure 3 shown, the four impulse engines are respectively located at 45° in the I quadrant biased towards the II quadrant, 45° in the II quadrant biased towards the III quadrant, 45° in the III quadrant biased towards the IV quadrant, and 45° in the IV quadrant biased towards the I quadrant of the aircraft cabin section.

[0037] The quadrants here refer to dividing the cabin section into four quadrants, namely the I, II, III, and IV quadrants, along its longitudinal axis and transverse axis. This is a commonly used engineering analysis method and will not be elaborated here.

[0038] The heat protection structure of the impulse engine of the aircraft provided by the embodiment of the present application can effectively prevent foreign objects such as dust, moisture, and small animals from entering the internal part of the impulse engine during the parking or ground maintenance of the aircraft by setting an annular plug groove 2 on the heat protection plug surface 101 of the nozzle heat protection plug cover 1 and forming an annular thickness weak area 3, thereby protecting the impulse engine from damage. During the flight of the aircraft, the airflow discharged from the engine nozzle 6 flushes open the annular thickness weak area 3, causing part of the plate body of the heat protection plug surface 101 to fall off, which can prevent hot air from entering the engine compartment while ensuring the normal circulation of heat flow, and reducing the heat dissipation burden.

[0039] In the description of the present application, it should be noted that the orientation or positional relationship indicated by terms such as "upper" and "lower" is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present application. Unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0040] It should be noted that in the present application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variation thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not expressly listed, or also includes elements inherent to such process, method, article or device. Without further limitation, the element defined by the statement "including a..." does not exclude the existence of additional identical elements in the process, method, article or device including the element.

[0041] The above are only the specific embodiments of the present application, enabling those skilled in the art to understand or implement the present application. Various modifications to these embodiments will be obvious to those skilled in the art. The general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will be accorded the widest scope consistent with the principles and novel features claimed herein.

Claims

1. A heat protection structure for an impulse engine of an aircraft, characterized in that, Comprising: A heat protection component, the heat protection component includes a nozzle heat protection plug cover (1) for connecting to the outflow end of the engine nozzle (6), and the nozzle heat protection plug cover (1) includes a heat protection plug cover disk surface (101) for covering the outflow end of the engine nozzle (6); A circulation component, the circulation component includes an annular plug cover groove (2) formed on the side of the heat protection plug cover disk surface (101) facing the impulse engine, and the annular plug cover groove (2) is recessed a certain depth in the thickness direction towards the heat protection plug cover disk surface (101) to form an annular thickness weak area (3) on the heat protection plug cover disk surface (101), so as to be used for when the impulse engine works, the airflow discharged from the engine nozzle (6) to blow open the annular thickness weak area (3).

2. The heat protection structure of an impulse engine for an aircraft according to claim 1, wherein, The annular plug cover groove (2) is concentric with the heat protection plug cover disk surface (101).

3. The thermal protection structure of an impulse engine for an aircraft according to claim 2, characterized in that, The depth of the annular plug cover groove (2) is less than the thickness of the heat protection plug cover disk surface (101).

4. The heat protection structure of an impulse engine for an aircraft according to claim 1, characterized in that The nozzle heat protection plug cover (1) further includes a heat protection plug cover ring surface (102) for sleeving on the outer periphery of the outflow end of the engine nozzle (6).

5. The heat protection structure of an impulse engine for an aircraft according to claim 4, wherein The heat protection plug cover ring surface (102) is provided with a connection unit for detachably connecting to the outer periphery of the engine nozzle (6).

6. The thermal protection structure of an impulse engine for an aircraft according to claim 5, characterized in that, The connection unit includes at least two connection screw holes (4) formed on the heat protection plug cover ring surface (102), and any two opposite connection screw holes (4) are radially symmetric along the heat protection plug cover ring surface (102).

7. The heat protection structure of an impulse engine for an aircraft according to claim 6, characterized in that, A connection bolt (5) for penetrating the tube body of the engine nozzle (6) is provided in the connection screw hole (4).

8. An impulse engine, characterized in that, The impulse engine of the aircraft is provided with the heat protection structure for the impulse engine of the aircraft according to any one of claims 1 to 7 at the outflow end of its nozzle.

9. The impulse engine according to claim 8, wherein, An adiabatic material layer (7) is provided on the inner wall of the nozzle of the impulse engine.

10. An aircraft, characterized in that, The aircraft is provided with at least one impulse engine according to claim 9.

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