阅读说明：本技术 一种复合型燃烧室热防护壁面结构 (Compound combustion chamber thermal protection wall surface structure ) 是由 胥蕊娜 姜培学 廖致远 于 2019-09-20 设计创作，主要内容包括：本发明公开一种复合型燃烧室热防护壁面结构,涉及飞行器热防护领域,包括沿高速高温主流的流动方向依次分区布置的自抽吸发汗冷却结构和燃油再生冷却通道,自抽吸发汗冷却结构包括储水层和发汗层,储水层通过输水管路与外部贮水箱连接；燃油再生冷却通道由燃烧室外壳和燃烧室内壁面之间的间隙形成,燃油再生冷却通道内设置有强化换热结构。通过采用水自抽吸发汗冷却和燃油再生冷却结合的复合冷却方法对燃烧室壁面进行热防护,降低了燃烧室壁面的热流密度,具有综合冷却剂耗量小、热防护热流密度大、结构简单的特点,可以广泛应用于各种超燃冲压发动机燃烧室内壁面的热防护作业中,实用性强。(The invention discloses a composite combustion chamber thermal protection wall surface structure, which relates to the field of aircraft thermal protection and comprises a self-suction sweating cooling structure and a fuel regeneration cooling channel which are sequentially arranged in a partition manner along the flowing direction of high-speed high-temperature main flow, wherein the self-suction sweating cooling structure comprises a water storage layer and a sweating layer, and the water storage layer is connected with an external water storage tank through a water conveying pipeline; the fuel regeneration cooling channel is formed by a gap between the combustion chamber shell and the inner wall surface of the combustion chamber, and an enhanced heat exchange structure is arranged in the fuel regeneration cooling channel. The composite cooling method combining water self-suction sweating cooling and fuel regeneration cooling is adopted to carry out thermal protection on the wall surface of the combustion chamber, so that the heat flux density of the wall surface of the combustion chamber is reduced, the composite cooling method has the characteristics of small comprehensive coolant consumption, large thermal protection heat flux density and simple structure, can be widely applied to thermal protection operation of the inner wall surface of the combustion chamber of various scramjet engines, and has strong practicability.)

1. The utility model provides a compound combustion chamber thermal protection wall structure which characterized in that: the self-suction sweating cooling structure comprises a water storage layer and a sweating layer which are sequentially arranged from outside to inside and are mutually communicated, and the water storage layer is connected with an external water storage tank through a water conveying pipeline; the fuel oil regeneration cooling channel is formed by a gap between a combustion chamber shell and the inner wall surface of the combustion chamber, a heat exchange enhancement structure is arranged in the fuel oil regeneration cooling channel, and the front end of the fuel oil regeneration cooling channel is connected with a combustion chamber oil injection support plate; the self-suction sweating cooling structure is used for heat protection of a front section area of a combustion area and forming a protective gas film to weaken heat flux density of a downstream area of the combustion area, the fuel oil regeneration cooling channel is used for heat protection of a rear section area of the combustion area, and fuel oil is injected into the fuel injection support plate of the combustion chamber to complete combustion after exchanging heat with high-speed high-temperature main flow in the fuel oil regeneration cooling channel.

2. A composite combustion chamber thermal protection wall structure according to claim 1, wherein: the reservoir stratum includes the reservoir stratum shell and fills the water storage piece in the reservoir stratum shell, it connects to sweat the layer through sealing connecting piece the below of water storage piece, just sealing connecting piece's top with the sealed butt joint of bottom of reservoir stratum shell.

3. A composite combustion chamber thermal protection wall structure according to claim 2, wherein: the water storage block is made of one of capillary tubes, fiber materials or porous materials with micron-millimeter level pores.

4. A composite combustion chamber thermal protection wall structure according to claim 2, wherein: the shell of the water storage layer is a metal shell or a rubber shell.

5. A composite combustion chamber thermal protection wall structure according to claim 1, wherein: the sweat-emitting layer is composed of a porous medium with micro-nano-scale pores, and the porous medium is made of one of metal particles, carbon-based ceramics or silicon-based ceramics.

6. A composite combustion chamber thermal protection wall structure according to claim 1, wherein: the heat exchange enhancement structure is a micro-nano heat exchange enhancement structure, and the micro-nano heat exchange enhancement structure is one of a micro rib, an etched micro channel or a micro-nano composite structure.

7. A composite combustion chamber thermal protection wall structure according to claim 1, wherein: the fuel regeneration cooling channel is internally provided with a plurality of supporting ribs, the supporting ribs are formed on the inner wall surface of the combustion chamber, and the supporting ribs are welded with the combustion chamber shell.

8. A composite combustion chamber thermal protection wall structure according to claim 7, wherein: the combustion chamber shell, the inner wall surface of the combustion chamber and the support ribs are all made of high-temperature-resistant alloy materials.

Technical Field

The invention relates to the field of thermal protection of aircrafts, in particular to a composite type combustion chamber thermal protection wall surface structure.

Background

With the development of aerospace technology, the cruising speed and the thrust of the aircraft are greatly improved, the hypersonic (Ma >5, Ma is Mach number) aircraft is rapidly developed, and the pneumatic heating and the temperature of an engine combustion chamber are improved, so that the thermal protection is a key problem. The scramjet engine is a common engine in a hypersonic aircraft, and is a typical structural schematic diagram of the scramjet engine as shown in fig. 1. When the flight Mach number reaches 8, the total temperature of the main flow in the scramjet engine exceeds 3000K, and high-temperature airflow in the scramjet engine flows at supersonic speed, so that the wall surface of the combustion chamber bears extremely high aerodynamic heat flux density. The traditional cooling mode is to adopt fuel regenerative cooling to carry out thermal protection on the wall surface, but as the speed of the aircraft is further increased, the combustion temperature is continuously increased, and the simple regenerative cooling technology faces the technical problems of insufficient fuel heat sink, insufficient heat exchange capacity and the like, so that the wall surface of the combustion chamber of the hypersonic engine needs to be cooled by adopting a more efficient and stable thermal protection mode to adapt to the rapid development of the existing aircraft technology.

Disclosure of Invention

The invention aims to provide a composite thermal protection wall surface structure which can carry out thermal protection on the wall surface of a combustion chamber of an impact engine by utilizing water self-suction sweating cooling and fuel oil regeneration cooling in high-speed and high-temperature main flow.

In order to achieve the purpose, the invention provides the following scheme:

the invention provides a composite combustion chamber thermal protection wall surface structure, which comprises a self-suction sweating cooling structure and a fuel regeneration cooling channel which are sequentially arranged in a partition mode along the flowing direction of high-speed high-temperature main flow, wherein the self-suction sweating cooling structure is positioned at the front section of a combustion chamber and comprises a water storage layer and a sweating layer which are sequentially arranged from outside to inside and are mutually communicated, and the water storage layer is connected with an external water storage tank through a water conveying pipeline; the fuel oil regeneration cooling channel is formed by a gap between a combustion chamber shell and the inner wall surface of the combustion chamber, a heat exchange enhancement structure is arranged in the fuel oil regeneration cooling channel, and the front end of the fuel oil regeneration cooling channel is connected with a combustion chamber oil injection support plate; the self-suction sweating cooling structure is used for heat protection of a front section area of a combustion area and forming a protective gas film to weaken heat flux density of a downstream area of the combustion area, the fuel oil regeneration cooling channel is used for heat protection of a rear section area of the combustion area, and fuel oil is injected into the fuel injection support plate of the combustion chamber to complete combustion after exchanging heat with high-speed high-temperature main flow in the fuel oil regeneration cooling channel.

Optionally, the reservoir includes the reservoir shell and fills the reservoir block in the reservoir shell, the sweat layer passes through sealing connecting piece to be connected the below of reservoir block, just sealing connecting piece's top with the sealed butt joint of bottom of reservoir shell.

Optionally, the water storage block is made of one of capillary tubes, fiber materials or porous materials with micro-millimeter pores.

Optionally, the water storage layer shell is a metal shell or a rubber shell.

Optionally, the sweat-generating layer is made of a micro-nano-porous medium made of one of metal particles, carbon-based ceramics or silicon-based ceramics.

Optionally, the heat exchange enhancement structure is a micro-nano heat exchange enhancement structure, and the micro-nano heat exchange enhancement structure is one of a micro rib, an etched micro channel or a micro-nano composite structure.

Optionally, a plurality of support ribs are arranged in the fuel regeneration cooling channel, the support ribs are formed on the inner wall surface of the combustion chamber, and the support ribs are welded with the combustion chamber shell.

Optionally, the combustion chamber housing, the inner wall surface of the combustion chamber, and the support rib are all made of high-temperature-resistant alloy materials.

Compared with the prior art, the invention has the following technical effects:

the invention provides a composite combustion chamber thermal protection wall surface structure, which is formed by compounding a self-suction sweating cooling structure for sucking cooling water by utilizing the capillary force of a porous medium and a fuel regeneration cooling channel for sucking fuel of an aircraft; the capillary force of the porous medium is used as the driving force of cooling water, the cooling water is continuously pumped from the water storage layer to the surface of the sweating layer and evaporated under the action of an external high-temperature environment, a large amount of heat is taken away, and a protective gas film is formed, so that the heat transfer of a high-speed high-temperature main flow to the wall surface of a downstream fuel oil regeneration cooling area is reduced, the requirement on the heat protection capability of the downstream regeneration cooling area is reduced, and the injection of a small amount of water also plays a role in catalyzing the combustion reaction of a combustion chamber; meanwhile, under the condition of the change of the thermal environment of the combustion chamber, the capillary force of the porous medium can automatically adjust the suction quantity of the cooling water within the limit range according to the high-speed high-temperature heat flow density, and the self-adaptive adjustment of the flow quantity of the cooling water relative to the heat flow density can be realized. The composite cooling method combining water self-suction sweating cooling and fuel oil regeneration cooling is adopted to carry out thermal protection on the wall surface of the combustion chamber, so that the heat flow density of the wall surface of the combustion chamber is reduced, the composite cooling method has the characteristics of small comprehensive coolant consumption, large thermal protection heat flow density and simple structure, can be widely applied to thermal protection operation of the inner wall surface of the combustion chamber of various scramjet engines, and has strong practicability.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.

FIG. 1 is a schematic view of the combustion principle of a prior art scramjet engine;

FIG. 2 is a system schematic view of a composite combustion chamber thermal barrier wall construction of the present invention; (ii) a

FIG. 3 is a schematic diagram of the cooling water supply of the self-pumping transpiration cooling structure of the present invention;

FIG. 4 is a schematic diagram of the self-pumping transpiration cooling structure and the distribution of fuel regeneration cooling channels of the present invention;

wherein the reference numerals are: 1. a water storage layer; 1-1, a water storage layer shell; 1-2, a water storage block; 2. a sweating layer; 3. a sealing connection; 4. a fuel regeneration cooling channel; 5. a combustion zone; 6. a water delivery pipeline; 7. an external water storage tank; 8. a combustion chamber housing; 9. an inner wall surface of the combustion chamber; 10. a heat exchange structure is strengthened; 11. an oil injection support plate of the combustion chamber; 12. and a support rib.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The invention aims to provide a composite thermal protection wall surface structure which can carry out thermal protection on the wall surface of a combustion chamber of an impact engine by utilizing water self-suction sweating cooling and fuel oil regeneration cooling in high-speed and high-temperature main flow.

Based on the above, the invention provides a composite combustion chamber thermal protection wall surface structure, which comprises a self-suction sweating cooling structure and a fuel regeneration cooling channel which are sequentially arranged in a partition manner along the flowing direction of high-speed high-temperature main flow, wherein the self-suction sweating cooling structure is positioned at the front section of a combustion chamber and comprises a water storage layer and a sweating layer which are sequentially arranged from outside to inside and are mutually communicated, and the water storage layer is connected with an external water storage tank through a water conveying pipeline; the fuel oil regeneration cooling channel is formed by a gap between the outer shell of the combustion chamber and the inner wall surface of the combustion chamber, a heat exchange enhancement structure is arranged in the fuel oil regeneration cooling channel, and the front end of the fuel oil regeneration cooling channel is connected with a fuel injection support plate of the combustion chamber; the self-suction sweating cooling structure is used for heat protection of a front section area of a combustion area and forming a protective gas film to weaken heat flux density of a downstream area of the combustion area, the fuel regeneration cooling channel is used for heat protection of a rear section area of the combustion area, and fuel is injected into a fuel injection support plate of a combustion chamber to complete combustion after exchanging heat with high-speed high-temperature main flow in the fuel regeneration cooling channel.

The invention provides a composite combustion chamber thermal protection wall surface structure, which is formed by compounding a self-suction sweating cooling structure for sucking cooling water by utilizing the capillary force of a porous medium and a fuel regeneration cooling channel for sucking fuel of an aircraft; the capillary force of the porous medium is used as the driving force of cooling water, the cooling water is continuously pumped from a water storage layer to the surface of an sweating layer and evaporated under the action of an external high-temperature environment, a large amount of heat is taken away, and a protective gas film is formed, so that the heat transfer of a high-speed high-temperature main flow to the wall surface of a downstream fuel oil regeneration cooling area is reduced, the requirement on the heat protection capability of the downstream regeneration cooling area is reduced, and the injection of a small amount of water also plays a role in catalyzing the combustion reaction of a combustion chamber; meanwhile, under the condition of the change of the thermal environment of the combustion chamber, the capillary force of the porous medium can automatically adjust the suction quantity of the cooling water within the limit range according to the high-speed high-temperature heat flow density, and the self-adaptive adjustment of the flow quantity of the cooling water relative to the heat flow density can be realized. The invention carries out thermal protection on the wall surface of the combustion chamber by adopting a composite cooling method of water self-suction sweating cooling and fuel oil regeneration cooling, reduces the heat flux density of the wall surface of the combustion chamber, has the characteristics of small comprehensive coolant consumption, large thermal protection heat flux density and simple structure, can be widely applied to the thermal protection operation of the inner wall surface of the combustion chamber of various scramjet engines, and has strong practicability.

In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.