Cooling method and device for aircraft hot surface

Abstract

The present invention relates to the field of aviation technology, and discloses a cooling method and device for aircraft thermal surfaces, including dividing regions, determining cooling regions and adjacent regions, determining unit cooling heat, the nozzle corresponding to the current cooling region spraying cold air to the region at three times the unit cooling heat per second, the first adjacent region spraying cold air to the current cooling region at two times the unit cooling heat per second, and the second adjacent region spraying cold air at the unit cooling heat per second; the spraying of the first adjacent region and the second adjacent region is performed at intervals; all regions to be cooled are cooled in turn according to step three until the current temperature values ​​of all regions to be cooled are lower than the specified temperature value. The present invention can effectively avoid mutual interference among the nozzles.

Description

Technical Field

[0001] The invention relates to the field of aviation technology, and in particular to a cooling method and a device for a hot surface of an aircraft. Background Art

[0002] If the surface of an aircraft or the surface of a major operating device (such as an engine) is very hot and forms a hot surface, once a fuel leak occurs, the fuel will drip onto the hot surface and easily catch fire, creating a fire hazard. In order to avoid the occurrence of hot surfaces, heat exchange cooling is generally performed in a timely manner on the hot surfaces of aircraft or aircraft engines.

[0003] Conventional heat exchange cooling uses impingement cooling, which sprays cooling airflow through a nozzle onto the high-temperature thermal surface to achieve the purpose of heat exchange with the high-temperature thermal surface, thereby reducing the temperature of the high-temperature thermal surface.

[0004] Usually, there is an impact hole inside a high-temperature surface, and cold air with a lower temperature than the high-temperature hot surface is ejected with high pressure to impact the hot surface to prevent the local temperature from being too high. However, the impact holes are arranged in an array, and other impact holes are arranged in an array around one impact hole. The cold air ejected from the holes will interfere with each other, making the direction of the ejected cooling airflow disordered, and even worse, it may cause the impact hole to be blocked. Summary of the invention

[0005] The present invention is intended to provide a cooling method for a hot surface of an aircraft, so as to solve the problem of nozzles interfering with each other when cooling the hot surface of the aircraft.

[0006] To solve the above problems, the present invention adopts the following technical solutions:

[0007] A method for cooling a hot surface of an aircraft, comprising the following steps:

[0008] Step 1: Divide the area, divide the impact hole and its corresponding nozzle according to the sensor installation position, and form multiple temperature areas;

[0009] Step 2: determine the cooling area and adjacent areas, calculate the current temperature value of each temperature area, compare it with the preset specified temperature value, arrange all temperature areas whose current temperature value is higher than the specified temperature value in order from high to low temperature to form a cooling sequence and areas to be cooled, and the area whose turn is to be cooled in order is defined as the current cooling area; other temperature areas adjacent to and equidistant from the current cooling area are adjacent areas; adjacent areas are divided into at least a first adjacent area close to the current cooling area and a second adjacent area far from the current cooling area according to their distance from the current cooling area;

[0010] Step 3, determining the unit cooling heat, the nozzle corresponding to the current cooling area sprays cold air to the area at three times the unit cooling heat per second, the first adjacent area sprays cold air to the current cooling area at two times the unit cooling heat per second, and the second adjacent area sprays cold air to the current cooling area at two times the unit cooling heat per second; the spraying of the first adjacent area and the second adjacent area is performed at intervals;

[0011] Step 4: Cool all the areas to be cooled in turn according to step 3 until the current temperature values ​​of all the areas to be cooled are lower than the specified temperature value.

[0012] Furthermore, the unit cooling heat is 1 / 10 of the difference between the highest temperature in all temperature zones and the specified temperature.

[0013] Further, at least one group of adjacent areas rotates synchronously with the nozzle of the current cooling area.

[0014] Furthermore, the nozzles in the current cooling area spray cold air in a 270-degree rotation direction.

[0015] Furthermore, when the nozzles of the first adjacent area and the second adjacent area spray toward the current cooling area, their inclination angles are different; the spray paths of the nozzles of the current cooling area, the first adjacent area and the second adjacent area do not intersect within a specified height from the aircraft hot surface.

[0016] Furthermore, all nozzles spray the cold air intermittently in pulses and continuously according to the unit spraying time.

[0017] Further, the ratio of the spraying time of the nozzles of the first adjacent area and the second adjacent area toward the designated cooling area to the unit spraying time is the ratio of the difference between the temperature of the designated cooling area and the designated temperature to the designated temperature.

[0018] The present invention also provides a cooling device for the hot surface of an aircraft, which is applied to the aforementioned cooling method for the hot surface of an aircraft, comprising a base plate arranged on the hot surface of the aircraft, the base plate being evenly provided with impact holes, and the base plate being provided with nozzles passing through the impact holes; the nozzles are connected to a central control unit via a connecting portion, and the central control unit is provided with a microcontroller for controlling each nozzle to rotate and spray cold air according to a preset strategy.

[0019] The present invention also provides a cooling device for an aircraft thermal surface, which is applied to the aforementioned cooling method for an aircraft thermal surface, comprising a base plate arranged on the opposite side of the aircraft thermal surface, the base plate being evenly provided with impact holes, and the base plate being provided with nozzles passing through the impact holes; the nozzles are connected to a central control unit via a connecting portion, and the central control unit is provided with a microcontroller for controlling each nozzle to rotate and spray cold air according to a preset strategy.

[0020] The advantages of the present invention are:

[0021] This solution is based on the existing ordinary array arrangement of impact holes. The injection time of each column of impact holes is controlled at intervals according to the different injection directions, forming an effect similar to pulse injection, avoiding mutual interference between the impact holes. It can not only accurately apply the cooling airflow formed by cold air directly to the high-temperature hot surface for rapid cooling, but also effectively save the driving kinetic energy wasted due to mutual interference. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic structural diagram of a cooling device for aircraft hot surfaces in Embodiment 1 of the present invention.

[0023] Figure 2 for Figure 1 Top view of the .

[0024] Figure 3 for Figure 1 Front view of.

[0025] Figure 4 for Figure 1 Bottom view of .

[0026] Figure 5 A schematic diagram of the division of the current cooling area and adjacent areas.

[0027] Figure 6 Another schematic diagram of the division of the current cooling area and adjacent areas. DETAILED DESCRIPTION

[0028] The following is further described in detail through specific implementation methods:

[0029] The reference numerals in the drawings of the specification include: a base plate 100 , an impact hole 110 , a pipe 200 , a nozzle 210 , a central control unit 300 , a connection unit 310 , and a sensor 320 .

[0030] Embodiment 1

[0031] The cooling device for the hot surface of an aircraft in this embodiment is installed on a common hot surface of an aircraft or at a position relative to a common hot surface, and includes a base plate 100 and a pipe 200 for introducing cold air. The base plate 100 is provided with impact holes 110 distributed in a uniform array, and each pipe 200 is connected to a plurality of nozzles 210 extending out of the impact holes 110. The cold air channel formed by the pipe 200 and the nozzle 210 sprays cold air onto the hot surface of the aircraft.

[0032] like Figure 2 and Figure 3 As shown, between adjacent pipes 200, a connecting portion 310 is installed for connecting the corresponding nozzles 210 on the two pipes 200. Figure 1 As shown, above the pipe 200 and the connecting part 310, there is a central control unit 300 connecting the connecting part 310 together. The central control unit 300 controls the nozzle 210 connected to the connecting part 310 to spray cold air according to a preset strategy, and the impact holes 110 arranged in an array are passed through to cool the high-temperature hot surface of the aircraft without interfering with each other. While saving energy, the cold air can be sent to the designated hot surface position to cool the hot surface.

[0033] In this embodiment, the central control unit 300 has an inverted U-shaped structure in the longitudinal section, which is convenient for connection with the connection part and can save installation space. The central control unit 300 includes a microcontroller for writing preset strategies, and a shell for protecting and installing the microcontroller. The shell forms a hollow horizontal space for installing the microcontroller, and a vertical space for connecting the cable to the connection part 310. The inverted U-shaped structure formed by the horizontal space and the vertical space is firm and easy to install.

[0034] Preferably, if the number of pipes 200 corresponding to the impact holes 110 is greater, the vertical spaces formed by the outer shell of the central control unit 300 are also increased accordingly, forming an E-shaped structure or a comb structure in which a horizontal space is connected to multiple vertical spaces.

[0035] like Figure 3 As shown, in this embodiment, the connection part 310 connected to each vertical space in the central control part 300 includes a connection cable and a rectangular shell that wraps these connection cables, which is convenient for wiring and protects and facilitates installation. When the connection cable is connected to each nozzle 210, one connection cable passes through the rectangular shell and is connected to the nozzle 210, and the other connection cable passes through the impact hole 110 and is connected to the sensor 320 on the other side of the bottom plate 100. The sensor 320 is used to detect the spray effect of the cold air. In this embodiment, the sensor 320 is a temperature sensor 320, which can determine the cooling condition of the hot surface of the aircraft adjacent to it by detecting the ambient temperature of the area. In this embodiment, the connection cables of the connection part 310 are multiple wires arranged side by side.

[0036] like Figure 4 As shown, the sensors 320 are distributed in regions according to the array arrangement of the impact holes 110, and multiple groups of sensors 320 are set starting from the edge of the impact hole 110 array. The number of sensors 320 is small and the ambient temperature of the surface of the bottom plate 100 and the area adjacent to the bottom plate 100 can be accurately detected. In order to achieve this goal, the first group of sensors 320 is arranged at the position of one row apart from the edge of the impact hole 110 array, and then the middle area of ​​the impact hole 110 is evenly divided into multiple impact hole 110 units, and a group of sensors 320 is installed in the central area of ​​each unit.

[0037] The preset air injection strategy in this embodiment is:

[0038] First, by comparing the detection signals of two adjacent groups of sensors 320, the temperature of the area space corresponding to each impact hole 110 is determined, and the high temperature area is determined;

[0039] Then, the high temperature values ​​are arranged from the highest temperature to the lowest temperature, and the high temperature area exceeding the specified temperature at this time is regarded as the cooling area that needs emergency cooling. The specified temperature is set according to the working status of the aircraft, and is generally related to the normal temperature of the outer surface of each device when the aircraft is working normally.

[0040] The third step is to reduce the heat in units of 1 / 10 of the difference between the highest temperature and the specified temperature based on all cooling areas and the calculated current specified temperature.

[0041] In the fourth step, in the order of temperature from high to low, when it is the turn of the cooling area to cool, the nozzles 210 in the corresponding cooling area are controlled by the connection part 310, and cold air is sprayed according to three or more unit heat reduction heat as the required cooling heat. The unit heat reduction heat is defined as the sum of the cold air spray volume per second of all nozzles 210 in a certain area, which is equal to the actual spray volume of the nozzle 210 per second multiplied by the number of all nozzles 210 in the group. The required cooling heat is the heat corresponding to the temperature that the cooling area should be cooled under the joint action of the nozzles 210 in the area and the nozzles 210 in the adjacent area.

[0042] Step 5: Control the nozzles 210 of other regions adjacent to the region and at equal distances to the region to spray the region with two units of heat reduction. Figure 5 and Figure 6 As shown, the equidistant and similar areas closest to the current cooling area are called first adjacent areas, and other areas that are slightly farther from the cooling area and equidistant are called second adjacent areas. The current cooling area has at least two first adjacent areas, and when dividing the areas, each area should have at least one set of sensors 320. While the first adjacent area is turning, the second adjacent area turns to the adjacent area nozzle 210, and the inclination angle of the jet airflow formed does not intersect with the jet angle of the jet airflow formed by the second adjacent area. All nozzles 210 in the second adjacent area also use the heat as the jet amount per second according to the unit of heat reduction. Except that the nozzle 210 in the cooling area turns from 270 degrees to spray, the nozzles 210 in the second adjacent area and the first adjacent area rotate synchronously with the nozzle 210 in the cooling area, but the direction of their rotation angle is the same as the rotation direction of the nozzle 210 in the cooling area, but the inclination angle of the sprayed cold air flow does not intersect at the position located on the hot surface.

[0043] Among them, when the nozzles 210 of the first adjacent area and the second adjacent area cool the designated cooling area, an interval spraying method is adopted, that is, the nozzles 210 of the first adjacent area and the second adjacent area spray cold air toward the designated cooling area for a period of time, and then turn to other areas to spray cold air, wherein the ratio of the spraying time toward the designated cooling area to the unit spraying time is the ratio of the difference between the temperature of the designated cooling area and the designated temperature to the designated temperature. The unit spraying time in this embodiment refers to the spraying time of all nozzles 210 continuously spraying cold air, which is generally 15 minutes to one hour. Setting the unit spraying time facilitates each nozzle 210 to concentrate cold air for spraying, avoiding the occurrence of insufficient cold air supply due to transmission and other reasons, and at the same time, it can form a situation similar to pulse spraying, which can better ensure the impact force of the cold air sprayed by the nozzle 210, and facilitate sufficient heat exchange with the high-temperature hot surface of the aircraft. The designated cooling area does not only refer to the current cooling area, but also refers to the temperature area that becomes the current cooling area in a certain period of time.

[0044] This solution, by confirming a new nominal value of unit heat reduction, enables the total amount of cooling in the cooling area to be rapidly and non-interferingly pulse-cooled through the cooling area and adjacent areas.

[0045] Embodiment 2

[0046] Different from the first embodiment, the sensors 320 connected to the respective connection parts 310 in this embodiment are not installed on the bottom plate 100, but are directly installed at the corresponding position of the hot surface of the aircraft. In order to better connect to the hot surface of the aircraft and not affect the normal operation of the sensor 320, and to facilitate the disassembly and assembly of the sensor 320, each sensor 320 is also installed with a heat-conductive connection seat, which can semi-enclose the sensor 320 through the connection, and the sensor 320 is clamped therein. The bottom surface of the connection seat is directly bonded to the hot surface of the aircraft by high-temperature tape. The high-temperature tape, as a consumable, needs to be replaced after a certain number of uses.

[0047] Such a configuration can more accurately associate the detection signal of the sensor 320 with the actual situation of the aircraft's thermal surface, so that all nozzles 210 can more accurately perform cold air injection and be more consistent with the actual situation according to the preset strategy.

[0048] By dividing the array-arranged nozzles 210 corresponding to all array impact holes 110 into cooling areas and adjacent areas, the steering and injection speed of the nozzles 210 in each area can be more accurately regulated, and the cold air flows ejected from the nozzles 210 can be ensured not to interfere with each other, and all the cold air flows can be applied to the hot surface of the aircraft for effective cooling.

[0049] A cooling method for a hot surface of an aircraft is provided, wherein a cooling device for the hot surface of the aircraft is installed at a relative position of the seat surface of the aircraft.

[0050] In the first step, the aircraft thermal surface temperature is detected by sensor 320 to obtain the current aircraft thermal surface specified temperature. According to a preset strategy, the aircraft thermal surface is divided into multiple temperature zones and the corresponding spatial areas are divided into multiple temperature zones. From the highest temperature to the lowest temperature, the temperature zones higher than the specified temperature are arranged in sequence into multiple cooling zones.

[0051] In the second step, the impact holes 110 and the nozzles 210 on the cooling device corresponding to the cooling area are controlled as a whole according to the temperature area of ​​the corresponding area. Starting from the cooling area with the highest temperature, all the nozzles 210 in this area rotate at an angle according to the preset strategy, so that the cold air flow formed by all the nozzles 210 in this area covers the aircraft hot surface in this temperature area. At the same time, for this temperature area, the nozzles 210 in other adjacent areas rotate synchronously according to the inclination angle in the preset strategy. The cold air flow formed by the nozzles 210 in all areas directly acts on the aircraft hot surface corresponding to this area. In the space above the aircraft hot surface exceeding the preset designated height, the spraying routes of all the nozzles 210 do not intersect. The designated height can be different according to the temperature of the corresponding aircraft hot surface. The designated height is generally within 10 cm from the aircraft hot surface. When the temperature of the designated cooling area drops to the designated temperature, except that the nozzles 210 in this area continue to rotate and spray according to the preset strategy, the nozzles 210 in other areas change their directions and no longer spray. When the temperature of all cooling areas drops below the original designated temperature, all nozzles 210 perform conventional spray cooling according to the conventional spraying method, and no longer perform designated cooling according to the preset strategy.

[0052] When cooling a cooling area according to the preset strategy, the nozzle 210 of the cooling area sprays cold air at three times the unit cooling heat. The first adjacent area sprays cold air at twice the unit cooling heat. The second adjacent area sprays at the unit heat of cooling heat. All nozzles 210 spray and turn within the unit spray time to form a pulse-like spray path. The interval time of adjacent areas is staggered, so that the cooling device can always spray cold air flow to the hot surface of the aircraft, while avoiding mutual interference, maximizing the exchange of hot and cold air, and saving energy at the same time.

[0053] The above is only an embodiment of the present invention, and the common knowledge such as the known specific technical solutions and / or characteristics in the solution is not described in detail here. It should be pointed out that for those skilled in the art, without departing from the technical solution of the present invention, several modifications and improvements can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicality of the patent. The scope of protection required by this application shall be based on the content of its claims, and the specific implementation methods and other records in the specification can be used to interpret the content of the claims.

Claims

1. A method for cooling a hot surface of an aircraft, characterized in that The following steps are involved: Step 1: Divide the area, divide the impact hole and its corresponding nozzle according to the sensor installation position, and form multiple temperature areas; Step 2: determine the cooling area and adjacent areas, calculate the current temperature value of each temperature area, compare it with the preset specified temperature value, arrange all temperature areas whose current temperature value is higher than the specified temperature value in order from high to low temperature to form a cooling sequence and areas to be cooled, and the area whose turn is to be cooled in order is defined as the current cooling area; other temperature areas adjacent to and equidistant from the current cooling area are adjacent areas; adjacent areas are divided into at least a first adjacent area close to the current cooling area and a second adjacent area far from the current cooling area according to their distance from the current cooling area; Step 3, determining the unit cooling heat, the nozzle corresponding to the current cooling area sprays cold air to the area at three times the unit cooling heat per second, the first adjacent area sprays cold air to the current cooling area at two times the unit cooling heat per second, and the second adjacent area sprays cold air to the current cooling area at two times the unit cooling heat per second; the spraying of the first adjacent area and the second adjacent area is performed at intervals; Step 4: Cool all the areas to be cooled in turn according to step 3 until the current temperature values ​​of all the areas to be cooled are lower than the specified temperature value; The unit cooling heat is 1 / 10 of the difference between the highest temperature in all temperature zones and the specified temperature.

2. The cooling method for aircraft hot surfaces according to claim 1, characterized in that: At least one group of adjacent zones rotates synchronously with the nozzles of the current cooling zone.

3. The cooling method for aircraft hot surfaces according to claim 1, characterized in that: The nozzles in the current cooling area spray cold air in a 270-degree rotation direction.

4. The cooling method for aircraft hot surfaces according to claim 1, characterized in that: When the nozzles of the first adjacent area and the nozzles of the second adjacent area spray toward the current cooling area, the inclination angles of the two are different; The spray paths of the nozzles of the current cooling zone, the first adjacent zone, and the second adjacent zone do not intersect within a specified height from the hot surface of the aircraft.

5. The cooling method for aircraft hot surfaces according to claim 1, characterized in that: All nozzles spray cold air intermittently in pulses and continuously according to the unit spraying time.

6. The method for cooling aircraft hot surfaces according to claim 5, characterized in that: The ratio of the spraying time of the nozzles of the first adjacent area and the second adjacent area toward the designated cooling area to the unit spraying time is the ratio of the difference between the temperature of the designated cooling area and the designated temperature to the designated temperature.

7. A cooling device for hot surfaces of an aircraft, characterized in that The cooling method for the hot surface of an aircraft as claimed in claim 1 comprises a base plate arranged on the hot surface of the aircraft, the base plate is evenly provided with impact holes, and the base plate is provided with nozzles passing through the impact holes; the nozzles are connected to the central control unit through a connecting part, and the central control unit is provided with a microcontroller for controlling each nozzle to rotate and spray cold air according to a preset strategy.

8. A cooling device for hot surfaces of an aircraft, characterized in that The cooling method for the hot surface of an aircraft as claimed in claim 1 comprises a bottom plate arranged on the opposite side of the hot surface of the aircraft, the bottom plate is evenly provided with impact holes, and the bottom plate is provided with nozzles passing through the impact holes; the nozzles are connected to the central control unit through a connecting part, and the central control unit is provided with a microcontroller for controlling each nozzle to rotate and spray cold air according to a preset strategy.

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