Coolant stable supply structure and method for sweating cooling system of hot end part of aircraft

Abstract

The invention discloses a stable coolant supply structure for a sweating cooling system of a hot end component of an aircraft, the hot end component is arranged to be of a porous structure, that is, directional pore channels are densely distributed in the hot end component of the aircraft in the advancing direction; meanwhile, the inner space of the aircraft hot end component is divided into one or more coolant cavities, the front end of each coolant cavity corresponds to a directional pore channel of the corresponding cooling area, and the rear end of each coolant cavity is communicated with a branch pipeline with a control valve. The branch pipelines are gathered and then communicated with an output port of the coolant driving system, and all the control valves are connected with the regulator. The invention further discloses a stable coolant supply method of the sweating cooling system for the hot end part of the aircraft. The invention belongs to the technical field of thermal protection of aerospace aircrafts, and solves the problem that a coolant in a sweating cooling system of a hot end component of an aircraft cannot be stably supplied in a variable incoming flow environment in the prior art.

Description

Technical Field

[0001] The present invention belongs to the field of thermal protection technology for aerospace vehicles, and relates to a stable supply structure for coolant in a sweat cooling system of a hot end component of an aircraft. The present invention also relates to a stable supply method for coolant in a sweat cooling system of a hot end component of an aircraft. Background Art

[0002] During high-speed flight, the hot end parts of the aircraft, such as the stationary area and the leading edge of the wing, will be subjected to severe aerodynamic heating, and the engine combustion chamber and throat will also face extreme thermal loads. With the increasing requirements for the missions assigned to aircraft (such as higher flight speeds, more flight time, more accurate landing accuracy, and reusability), the sweat cooling active thermal protection technology is considered to be one of the thermal protection technologies with the most development potential.

[0003] However, in actual flight, the hot end components of the aircraft (including the aircraft stagnation area, wing leading edge, engine combustion chamber and other non-flat shaped special-shaped structural parts, the hot end components of the stagnation area are taken as an example below, and other hot end components are also applicable) are subject to severe and changing aerodynamic loads. The existing technology uses uniform random pores as a porous structure of the coolant carrier, which is difficult to cope with the changing aerodynamic loads (including aerodynamic thermal loads and aerodynamic loads). For example, during flight, the aerodynamic loads suffered by the stagnation position are the most severe, and more coolant flow distribution is also required to meet the thermal protection effect. However, since the temperature of the stagnation position is higher than that of other positions in the stagnation area, the aerodynamic load resistance of the incoming flow to the coolant outlet is the largest, and the coolant will tend to flow out from the position with lower temperature and smaller incoming flow resistance in the stagnation area, resulting in the high temperature stagnation position. It is difficult to obtain a stable supply of coolant, and it is impossible to effectively cool it, which causes the hot end components to burn out at high temperature, resulting in the failure of the entire thermal protection system.

[0004] At present, under a changing flow environment, there is no technology or method for the stable supply and regulation of coolant in the transpiring cooling system of aircraft hot end components (including aircraft stationary areas, wing leading edges, engine combustion chambers and other non-flat shaped special-shaped structural parts), and there is an urgent need to develop relevant technical solutions. Summary of the invention

[0005] The purpose of the present invention is to provide a stable coolant supply structure for the perspiration cooling system of the hot end components of an aircraft, thereby solving the problem in the prior art that the coolant in the perspiration cooling system of the hot end components of an aircraft cannot be kept stably supplied under a changing incoming flow environment.

[0006] Another object of the present invention is to provide a method for stably supplying coolant to the perspiration cooling system of aircraft hot end components, thereby solving the problem in the prior art that it is difficult to stably supply coolant to aircraft hot end components due to factors such as aerodynamic loads, aerodynamic shapes, flight conditions and local blockages.

[0007] The technical solution adopted by the present invention is that the coolant stable supply structure of the aircraft hot end component sweat cooling system, the hot end component is set to a porous structure, that is, directional pore channels are densely distributed in the aircraft hot end component along the forward direction; At the same time, the internal space of the hot end component of the aircraft is divided into one or more coolant chambers. The front end of each coolant chamber corresponds to the directional pore channel of the respective cooling area, and the rear end of each coolant chamber is connected to a branch pipe with a control valve. After the multiple branch pipes are aggregated, they are connected to the output port of the coolant drive system, and all control valves are connected to the regulators respectively.

[0008] Another technical solution adopted by the present invention is a method for stably supplying coolant to a hot end component sweat cooling system of an aircraft, the specific process of which is as follows: First, determine the hardware structure of the hot end component: design and prepare a hot end component with a directional pore channel, and at the same time, set the internal space of the hot end component as one or more independent coolant chambers, each coolant chamber is connected to the coolant drive system through a branch pipeline with a control valve, the coolant drive system and all the control valves are connected to the regulator, and the regulator is also connected to the aircraft attitude control system; Then, determine the flow rate and pressure of the coolant stable supply: According to the flight conditions of the hot end components, the regulator adjusts the opening of each control valve to regulate the flow rate and pressure of the coolant in the corresponding coolant chamber to meet the thermal protection requirements of the hot end components in different parts and different flight conditions.

[0009] The beneficial effect of the present invention is that, under the condition of changing (size and direction) high-temperature and high-speed incoming flow, by adjusting the directional pore microchannel direction and size design of the internal porous structure of the aircraft hot end component (such as the aircraft stagnation area, the wing leading edge, the engine combustion chamber and other non-flat shape special-shaped structural parts), and adjusting the coolant driving pressure and flow size in the modular coolant chamber, the problem of the hot end component burning failure caused by the difficulty of stable supply of coolant in the special-shaped hot end component under the condition of non-uniform incoming flow is overcome. The coolant stable supply structure technology and method of the sweating cooling system make up for the problem that the hot end component of the aircraft (such as the aircraft stagnation area, the wing leading edge, the engine combustion chamber and other non-flat shape special-shaped structural parts) is difficult to stably supply coolant under the condition of non-uniform incoming flow, causing the hot end component to burn failure. The structure and method are easy to implement, and can avoid the problem of the porous structure overheating failure caused by the difficulty of stable supply of coolant in the hot end component of the aircraft in the prior art due to factors such as aerodynamic load, aerodynamic shape, flight conditions and local blockage, which is of great significance. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 It is a two-dimensional plane schematic diagram of the sweating cooling mechanism of the directional pore channel in the stagnation area of ​​the hot end component of the aircraft in the device of the present invention; Figure 2 It is a schematic diagram of the arrangement of the modular coolant chambers in the hot end component stationary area of ​​the aircraft in the device of the present invention (taking two coolant chambers as an example); Figure 3 This is a schematic diagram of the sweating cooling mechanism of the traditional uniform random porous structure in the stagnation area of ​​the hot end component of the traditional aircraft; Figure 4 It is a schematic diagram of the sweating cooling mechanism of the porous structure of the directional pore channel in the stationary area of ​​the hot end component of the aircraft in the device of the present invention; Figure 5 It is a schematic diagram of the arrangement structure of a chamber of a modular coolant for directional sweating cooling in the stagnation area of ​​a hot end component of an aircraft in the device of the present invention; Figure 6 It is a schematic diagram of the arrangement structure of two chambers of the modular coolant for directional sweat cooling in the stagnation area of ​​the hot end component of the aircraft in the device of the present invention; Figure 7 It is a schematic diagram of the arrangement structure of three chambers of the modular coolant for directional sweat cooling in the stationary area of ​​the hot end component of the aircraft in the device of the present invention; Figure 8 It is a schematic diagram of the structural arrangement of four chambers of modular coolant for directional sweating cooling in the stationary area of ​​the hot end component of the aircraft in the device of the present invention.

[0011] In the figure, 1. coolant drive system, 2. control valve, 3. branch pipeline, 4. coolant chamber. DETAILED DESCRIPTION

[0012] The present invention is described in detail below with reference to the accompanying drawings and specific embodiments.

[0013] like Figure 1 , Figure 2 As shown, the coolant stable supply structure of the aircraft hot end component sweat cooling system of the present invention includes two aspects of improved settings: On the one hand, the hot end component (especially the pointed part or the front protrusion) is set as a porous structure, that is, directional pore channels are densely distributed in the hot end component along the forward direction, and the directional pore channels are all facing forward, or the divergence direction of the directional pore channels is adjusted according to factors such as specific flight conditions and the external structure of the hot end component; the density, spacing size and pore size range of the pore channels are also regulated according to factors such as flight conditions and the external structure of the hot end component. The directional pore channels serve as flow channels for the coolant, and the pore size of the directional pore channels is in the order of several microns to tens of microns, which can realize the sweating mode, and is used to constrain and regulate the flow direction of the coolant during the sweating cooling process. At the same time, it can improve the thermal physical properties and strength of the hot end component, which is helpful to improve the heat exchange between the porous structure of the hot end component and the coolant. The structure of the present invention is compared with the traditional uniform random pore channels. The present invention focuses on proposing the design concept of directional microstructure pore channels (mainly facing forward), and the specific arrangement form is adjusted according to the actual situation.

[0014] On the other hand, the internal space of the hot end component is divided into one or more coolant chambers 4, and the number of coolant chambers 4 is determined according to factors such as the shape of the hot end component and the flight conditions; the front end of each coolant chamber 4 corresponds to the directional pore channel of the respective cooling area, and the rear end of each coolant chamber 4 is connected to a branch pipe 3 with a control valve 2. After the multiple branch pipes 3 are aggregated, they are connected to the output port of the coolant drive system 1 of the coolant, which is responsible for the supply of coolant required by all coolant chambers 4; each control valve 2 is connected to the regulator respectively, so as to realize the individual and precise control of the control valve 2 on each branch pipe 3, and provide the coolant flow or pressure corresponding to each coolant chamber 4 according to actual needs.

[0015] The coolant drive system 1 is used to provide a stable coolant supply.

[0016] The regulator is connected to the aircraft attitude control system, which is used to sense the flight conditions of the aircraft (for example, using the aircraft's own attitude sensor, ground measurement and control, or satellite measurement and control to sense the aircraft's flight status, so as to obtain the real-time flow conditions of the hot end components during the analysis process); the regulator is pre-installed with control process software, which adjusts the opening of each control valve 2 according to factors such as the shape of the hot end components, flight conditions, and real-time flow conditions, so as to achieve different requirements for coolant flow or pressure in each coolant chamber 4.

[0017] The manufacturing method of the coolant stable supply structure of the aircraft hot end component sweat cooling system of the present invention comprises the following two main steps: The first step is to obtain a hot end component-shaped structural part with directional pore channels through porous material design and process control (such as ice template method, extrusion molding method, biological template method or 3D printing technology, etc.), which can be formed in one step, or the decomposed components of various parts of the hot end component can be prepared and spliced ​​to obtain a complete hot end component structural part. The structural part can be applicable to metals, ceramics, composite materials and other materials; In the second step, according to the shape of the hot end component and the flight conditions of the actual service conditions, the internal space of the hot end component is divided into one or more independent coolant chambers 4. Each coolant chamber 4 is connected to the coolant drive system 1 through a branch pipe 3. A control valve 2 is provided on the branch pipe 3. Each control valve 2 is individually connected to the regulator by signal.

[0018] The method for stably supplying coolant to the aircraft hot end component sweat cooling system of the present invention comprises the following two parts: First, determine the hardware structure of the hot end component: design and prepare a hot end component with directional pore channels, the pore size of the directional pore channels is in the order of a few microns to tens of microns, and the direction and distribution of the directional pore channels are designed according to the actual service conditions such as the appearance and flight conditions of the hot end component; at the same time, the internal space of the hot end component is set as one or more independent coolant chambers 4, each coolant chamber 4 is connected to the coolant drive system 1 through a branch pipe 3 with a control valve 2, the coolant drive system 1 and all the control valves 2 are connected to the regulator, and the regulator is also connected to the aircraft attitude control system; Then, determine the flow rate and pressure of the coolant stable supply: according to the flight conditions of the hot end components, accurately adjust the opening of each control valve 2, and regulate the flow rate and pressure of the coolant in the corresponding coolant chamber 4 to meet the thermal protection requirements of the hot end components in different parts and different flight conditions.

[0019] The method for stably supplying coolant to the aircraft hot end component sweat cooling system of the present invention can adapt to the following two flight modes: Method 1: When the incoming flow direction is parallel to the directional pore channel, that is, the flight direction of the aircraft is parallel to the pore channel direction. like Figure 3 As shown in the figure, for the conventional uniform isotropic porous structure, the coolant in the pore channel at the stagnation point position on the surface of the hot end component is forced to flow to the position near the stagnation point area due to the aerodynamic load, resulting in insufficient coolant cooling at the stagnation point position and overheating damage; like Figure 4As shown, the present invention performs directional design on the porous channels of the hot end components in the stagnation area. When the incoming flow is parallel to the directional porous channels, the aerodynamic loads on the internal coolant in the directional porous channels in the stagnation area are close in magnitude, and the flow direction of the coolant is constrained by the directional porous channels, forcing the coolant to reach the stagnation position along the directional porous channels, thereby effectively avoiding damage to the stagnation position due to insufficient coolant.

[0020] Method 2: When the incoming flow direction is not parallel to the directional pore channel, that is, when the hot end component is turning or maneuvering with the aircraft, there is a certain angle between the incoming flow direction and the directional pore channel. like Figure 5 , Figure 6 , Figure 7 , Figure 8 As shown, the present invention modularly designs the coolant chamber 4 inside the stagnation area, and sets the coolant chamber 4 to 1, 2, 3, 4... and other multiple independent coolant chambers 4, each coolant chamber 4 independently corresponds to its own directional pore channel, each coolant chamber 4 is respectively connected to a branch pipe 3 with a control valve 2, which is responsible for the supply of coolant inside the coolant chamber 4, and multiple branch pipes 3 are merged and connected to the coolant drive system 1, and the control valve 2 on each branch pipe 3 is respectively precisely controlled to provide the coolant flow or pressure of the corresponding coolant chamber 4.

[0021] The arrangement and modular number of the coolant chamber 4 can be determined according to factors such as the shape of the stationary area of ​​the hot end component of the actual aircraft, in order to ensure that under any conditions of the incoming flow direction and the angle between the directional pore channel, the coolant flow and pressure in the coolant chamber 4 can be regulated by the control valve 2 on the branch pipe 3, respectively, to meet the different coolant requirements of the stationary area of ​​the hot end component, and achieve the purpose of modular control cooling of the stationary area of ​​the hot end component.

[0022] Example 1 Targeting the stationing area of ​​hypersonic aircraft.

[0023] like Figure 1 , Figure 5 As shown, the coolant stable supply structure of the hot end component sweat cooling system is, On the one hand, the hot end component is set to a porous structure, that is, directional pore channels are densely distributed in the hot end component along the forward direction, the pore size of the directional pore channels is 8 microns, and the directions of all directional pore channels are all forward; On the other hand, the internal space of the hot end component is divided into a coolant chamber 4, the front end of the coolant chamber 4 corresponds to all the directional pore channels in the cooling area, and the rear end of the coolant chamber 4 is connected to a branch pipe 3 with a control valve 2, and the branch pipe 3 is connected to the output port of the coolant drive system 1 of the coolant, which is responsible for the supply of the coolant required by the coolant chamber 4; the control valve 2 is connected to the regulator to achieve precise control of the control valve 2 on the branch pipe 3, and provide the coolant flow or pressure corresponding to the coolant chamber 4 according to actual needs.

[0024] Example 2 Targeting the stationing area of ​​hypersonic aircraft.

[0025] like Figure 1 , Figure 6 As shown, the coolant stable supply structure of the front end hot end component sweat cooling system is: On the one hand, the aircraft stationary area is set as a directional porous structure, that is, directional pore channels are densely distributed in the hot end component at the front end of the nose along the forward direction, the pore size of the directional pore channels is on the order of 10 microns, and all the directional pore channels are oriented forward; On the other hand, the internal space of the hot end component at the front end of the head is divided into two coolant chambers 4 (see Figure 6 The front end of each coolant chamber 4 corresponds to the directional pore channel of the respective cooling area, and the rear end of each coolant chamber 4 is connected to a branch pipe 3 with a control valve 2. The two branch pipes 3 are connected to the output port of the coolant drive system 1 after being collected, and are responsible for the supply of coolant required by all coolant chambers 4; the two control valves 2 are respectively connected to the regulator to realize the individual and precise control of the control valve 2 on each branch pipe 3, and provide the coolant flow or pressure corresponding to each coolant chamber 4 according to actual needs.

[0026] Example 3 Targeting the leading edge of hypersonic aircraft wings.

[0027] like Figure 1 , Figure 7 As shown, the coolant stable supply structure of the hot end component sweat cooling system is: On the one hand, the wing leading edge hot end component is set to a porous structure, that is, directional pore channels are densely distributed in the wing leading edge hot end component along the forward direction, the pore size of the directional pore channels is on the order of 5 microns, and the directions of all the directional pore channels are all forward; On the other hand, the internal space of the wing leading edge hot end component is divided into three coolant chambers 4 (see Figure 7In the figure, the front end of each coolant chamber 4 corresponds to the directional pore channel of the respective cooling area, and the rear end of each coolant chamber 4 is connected to a branch pipe 3 with a control valve 2. After the multiple branch pipes 3 are aggregated, they are connected to the output port of the coolant drive system 1 of the coolant, which is responsible for the supply of coolant required by all coolant chambers 4; all control valves 2 are connected to the regulators respectively to realize the individual and precise control of the control valve 2 on each branch pipe 3.

[0028] Example 4 Focusing on the throat position of a certain type of hypersonic aircraft engine combustion chamber.

[0029] like Figure 1 , Figure 8 As shown, the coolant stable supply structure of the combustion chamber throat hot end component sweat cooling system is, On the one hand, the hot end component is set to a porous structure, that is, directional pore channels are densely distributed in the hot end component along the forward direction, the pore size of the directional pore channels is on the order of 20 microns, and the directions of all directional pore channels are all forward; On the other hand, the internal space of the hot end part is divided into four coolant chambers 4 (see Figure 8 In the figure, the front end of each coolant chamber 4 corresponds to the directional pore channel of the respective cooling area, and the rear end of each coolant chamber 4 is connected to a branch pipe 3 with a control valve 2. After the multiple branch pipes 3 are aggregated, they are connected to the output port of the coolant drive system 1 of the coolant, which is responsible for the supply of coolant required by all coolant chambers 4; all control valves 2 are connected to the regulators respectively to realize the individual and precise control of the control valve 2 on each branch pipe 3.

[0030] Example 5 Targeting the stationing area of ​​hypersonic aircraft.

[0031] The method for stably supplying coolant in the hot end component sweat cooling system of the present invention comprises the following two steps: First, determine the hardware structure for stable coolant supply: process directional pore channels in the structural parts of the stationary area, and all directional pore channels are densely distributed in the hot end component along the forward direction; at the same time, set the internal space of the hot end component as an independent coolant chamber 4, and the coolant chamber 4 is connected to the coolant drive system 1 through a branch pipe 3 with a control valve 2, and the coolant drive system 1 and all the control valves 2 are connected to the regulator, and the regulator is also connected to the aircraft attitude control system; Then, determine the flow rate and pressure of the coolant stable supply: according to the aircraft flight conditions, adjust the opening of the control valve 2 to regulate the flow rate and pressure of the coolant in the corresponding coolant chamber 4 to meet the thermal protection requirements of the hot end components in different parts and different flight conditions.

[0032] Example 6 Targeting the stationing area of ​​hypersonic aircraft.

[0033] The method for stably supplying coolant in the hot end component sweat cooling system of the present invention comprises the following two steps: First, determine the hardware structure for stable coolant supply: process directional pore channels in the structural parts of the hot end component in the stationary area, and all directional pore channels are densely distributed in the hot end component along the forward direction; at the same time, set the internal space of the hot end component as two independent coolant chambers 4, each coolant chamber 4 is connected to the coolant drive system 1 through a branch pipe 3 with a control valve 2, the coolant drive system 1 and all the control valves 2 are connected to the regulator, and the regulator is also connected to the aircraft attitude control system; Then, determine the flow rate and pressure of the coolant stable supply: according to the aircraft flight conditions, adjust the opening of the control valve 2 to regulate the flow rate and pressure of the coolant in the corresponding coolant chamber 4 to meet the thermal protection requirements of the hot end components in different parts and different flight conditions.

[0034] Example 7 Targeting the leading edge of hypersonic aircraft wings.

[0035] The method for stably supplying coolant in the hot end component sweat cooling system of the present invention comprises the following two steps: First, determine the hardware structure for stable coolant supply: process directional pore channels in the structural part in the shape of the hot end component of the wing leading edge, and all directional pore channels are densely distributed in the hot end component along the forward direction; at the same time, set the internal space of the hot end component as three independent coolant chambers 4, each coolant chamber 4 is connected to the coolant drive system 1 through a branch pipe 3 with a control valve 2, the coolant drive system 1 and all the control valves 2 are connected to the regulator, and the regulator is also connected to the aircraft attitude control system; Then, determine the flow rate and pressure of the coolant stable supply: according to the flight conditions of the aircraft, adjust the opening of the control valve 2 to regulate the flow rate and pressure of the coolant in the corresponding coolant chamber 4 to meet the thermal protection requirements of the hot end components in different parts and different flight conditions.

[0036] Example 8 Focusing on the throat position of a certain type of hypersonic aircraft engine combustion chamber.

[0037] The method for stably supplying coolant in the hot end component sweat cooling system of the present invention comprises the following two steps: First, determine the hardware structure for stable coolant supply: process directional pore channels in the structure of the hot end component in the throat of the combustion chamber, and all directional pore channels are densely distributed in the hot end component along the forward direction; at the same time, set the internal space of the hot end component as four independent coolant chambers 4, each coolant chamber 4 is connected to the coolant drive system 1 through a branch pipe 3 with a control valve 2, the coolant drive system 1 and all the control valves 2 are connected to the regulator, and the regulator is also connected to the aircraft attitude control system; Then, determine the flow rate and pressure of the coolant stable supply: according to the flight conditions of the engine, adjust the opening of the control valve 2 to regulate the flow rate and pressure of the coolant in the corresponding coolant chamber 4 to meet the thermal protection requirements of the hot end components in different parts and different flight conditions.

Claims

1. A coolant stable supply structure for a hot end component sweat cooling system of an aircraft, characterized in that: The hot end component is configured as a porous structure, that is, directional pore channels are densely distributed in the hot end component of the aircraft along the forward direction; At the same time, the internal space of the aircraft hot end component is divided into one or more coolant chambers (4), the front end of each coolant chamber (4) corresponds to a directional pore channel of a respective cooling area, and the rear end of each coolant chamber (4) is connected to a branch pipeline (3) with a control valve (2). The multiple branch pipelines (3) are connected to the output port of the coolant drive system (1) after being collected, and all the control valves (2) are connected to the regulators respectively.

2. The coolant stable supply structure of the aircraft hot end component sweat cooling system according to claim 1, characterized in that: The coolant driving system (1) is used to provide a stable coolant supply.

3. The coolant stable supply structure of the aircraft hot end component sweat cooling system according to claim 1, characterized in that: The regulator is connected to the aircraft attitude control system and is used to adjust the opening of each control valve (2).

4. The coolant stable supply structure of the aircraft hot end component sweat cooling system according to claim 1, characterized in that: The pore size of the directional pore channel is from several microns to tens of microns.

5. A method for stabilizing the supply of coolant to a hot end component sweat cooling system of an aircraft, characterized in that: The specific process is: First, the hardware structure of the hot end component is determined: a hot end component with a directional pore channel is designed and prepared, and at the same time, the internal space of the hot end component is set as one or more independent coolant chambers (4), each coolant chamber (4) is connected to the coolant drive system (1) through a branch pipeline (3) with a control valve (2), the coolant drive system (1) and all the control valves (2) are connected to the regulator, and the regulator is also connected to the aircraft attitude control system; Then, the flow rate and pressure of the coolant stable supply are determined: according to the flight conditions of the hot end components, the regulator adjusts the opening of each control valve (2) to control the flow rate and pressure of the coolant in the corresponding coolant chamber (4) to meet the thermal protection requirements of the hot end components in different parts and different flight conditions.

6. The method for stable supply of coolant to the aircraft hot end component transpiring cooling system according to claim 5, characterized in that: The pore size of the directional pore channel is in the order of several microns to tens of microns.

7. The method for stably supplying coolant to a hot end component transpiring cooling system of an aircraft according to claim 5, characterized in that: The direction and distribution of the directional pore channels are determined according to the shape of the hot end components and the actual service conditions of the flight conditions.

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