CN111259488B - Oil transportation and thermal management integrated system for controlling temperature rise of fuel oil of high-speed aircraft - Google Patents
Oil transportation and thermal management integrated system for controlling temperature rise of fuel oil of high-speed aircraft Download PDFInfo
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- CN111259488B CN111259488B CN202010020340.6A CN202010020340A CN111259488B CN 111259488 B CN111259488 B CN 111259488B CN 202010020340 A CN202010020340 A CN 202010020340A CN 111259488 B CN111259488 B CN 111259488B
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Abstract
The invention provides an oil transportation and heat management integrated system for controlling the temperature rise of fuel oil of a high-speed aircraft, which comprises a main oil tank, a built-in oil tank, an oil pump, a first oil pipe, a second oil pipe, a support frame and an air inlet pipe, wherein the main oil tank is arranged in the main oil tank; the pressurized gas of the oil tank enters the main oil tank from the air inlet pipe to provide pressure for the fuel in the main oil tank, so that the fuel is conveyed from the main oil tank to the built-in oil tank through the first oil pipe, is conveyed to the oil pump through the second oil pipe, and finally, the fuel supplies fuel to the engine through the oil pump. By adopting the technical scheme, the built-in oil tank is arranged in the main oil tank, so that the temperature of fuel oil at the last flight section of the high-speed aircraft in long voyage can be effectively reduced, and the effects of reducing cavitation risk of the fuel pump, reducing the pressurizing pressure of the fuel tank, reducing the design difficulty of oil passing equipment, increasing available fuel oil heat sink of an engine and the like can be achieved. The invention can be applied to high-speed aircrafts such as high-speed aircrafts, aerospace aircrafts and the like.
Description
Technical Field
The invention relates to the technical field of high-speed aircraft fuel oil transportation and thermal management, in particular to an oil transportation and thermal management integrated system for controlling the temperature rise of high-speed aircraft fuel oil.
Background
The existing high-speed aircraft fuel tank body is not only used for storing fuel, but also plays a role in bearing the aircraft. Because of higher flying speed, the pneumatic heating phenomenon is serious, and the temperature of fuel in the cabin is continuously increased after long-endurance flying; especially, at the end of the flight, the fuel quantity is reduced, and the temperature rise of the fuel is accelerated. The rising temperature of the fuel can lead to easier cavitation at the pump inlet and increase the risk of overtemperature failure of the oil valve. For high speed aircraft that use fuel for engine active cooling, elevated fuel temperatures also increase the risk of excessive engine wall temperatures.
In order to control the temperature of the fuel before the long-endurance fuel system is delivered to the engine pump to not exceed the design temperature, existing high-speed aircraft reduce the heat flow input into the tank by enhancing the fuel tank thermal protection, but this results in reduced aircraft fuel loading space and thus reduced range, and additional weight and cost.
Disclosure of Invention
The invention provides an oil transportation and heat management integrated system for controlling the temperature rise of fuel oil of a high-speed aircraft, which can solve the technical problems of cavitation, overtemperature failure of an oil passing valve and overtemperature of an engine wall surface of a fuel pump of the high-speed aircraft in the prior art on the premise of not reducing the loading space of the fuel oil.
In order to solve the technical problems, the invention provides an oil transportation and heat management integrated system for controlling the temperature rise of fuel oil of a high-speed aircraft, which comprises a main oil tank, a built-in oil tank, an oil pump, a first oil pipe, a second oil pipe, a support frame and an air inlet pipe; the built-in oil tank, the first oil pipe and the supporting frame are arranged in the main oil tank, the supporting frame is arranged between the bottom of the main oil tank and the bottom of the built-in oil tank and is used for supporting the built-in oil tank, the main oil tank is communicated with the built-in oil tank through the first oil pipe, and the built-in oil tank is connected with the oil pump through the second oil pipe; the air inlet pipe is arranged at the top of the main oil tank, the pressurized gas of the oil tank enters the main oil tank from the air inlet pipe to provide pressure for the fuel in the main oil tank, so that the fuel is conveyed from the main oil tank to the built-in oil tank through the first oil pipe and then conveyed to the oil pump through the second oil pipe, and finally the fuel is supplied to the engine through the oil pump.
Preferably, one end of the first oil pipe is located at the bottom of the main oil tank and is spaced from the bottom of the main oil tank by a predetermined distance, the other end of the first oil pipe is located at the top of the built-in oil tank, and the height of the supporting frame is greater than the predetermined distance.
Preferably, a gap is arranged between the outer wall of the built-in oil tank and the inner wall of the main oil tank.
Preferably, the wall of the main oil tank is made of high-temperature-resistant metal material.
Preferably, the wall of the built-in oil tank is made of aluminum alloy materials.
Preferably, the system further comprises a first thermal insulation layer arranged on the outer wall or the inner wall of the main oil tank.
Preferably, the system further comprises a second thermal insulation layer, and the second thermal insulation layer is arranged on the outer wall or the inner wall of the built-in oil tank.
Preferably, the system further comprises a high-reflectivity coating layer, and when the second heat insulation layer is arranged on the outer wall of the built-in oil tank, the high-reflectivity coating layer is arranged on the outer side of the second heat insulation layer; when the second heat insulation layer is arranged on the inner wall of the built-in oil tank, the high-reflectivity coating is arranged on the outer wall of the built-in oil tank.
Preferably, the support frame is provided with a thermal bridge blocking structure.
By adopting the technical scheme, the built-in oil tank is arranged in the main oil tank, so that the temperature of fuel oil at the last flight section of the high-speed aircraft in long voyage can be effectively reduced, and the effects of reducing cavitation risk of the fuel pump, reducing the pressurizing pressure of the fuel tank, reducing the design difficulty of oil passing equipment, increasing available fuel oil heat sink of an engine and the like can be achieved. The invention can be applied to high-speed aircrafts such as high-speed aircrafts, aerospace aircrafts and the like.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is evident that the drawings in the following description are only some embodiments of the present invention and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
FIG. 1 is a schematic diagram of an integrated thermal management system for controlling the temperature rise of fuel oil of a high-speed aircraft according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a fuel temperature rise profile provided in accordance with an embodiment of the present invention;
fig. 3 is a schematic flow chart of a design method of an oil transportation thermal management system for controlling the temperature rise of fuel oil of a high-speed aircraft according to an embodiment of the invention.
Description of the reference numerals
1. A main oil tank; 2. An oil pump; 3. An oil tank is arranged in the tank; 4. A first oil pipe;
5. a second oil pipe; 6. A support frame; 7. And an air inlet pipe.
Detailed Description
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments in accordance with the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
Fig. 1 shows a schematic structural diagram of an integrated thermal management system for controlling the temperature rise of fuel oil of a high-speed aircraft according to an embodiment of the present invention. As shown in fig. 1, the invention provides an oil transportation and heat management integrated system for controlling the temperature rise of fuel oil of a high-speed aircraft, which comprises a main oil tank 1, a built-in oil tank 3, an oil pump 2, a first oil pipe 4, a second oil pipe 5, a support frame 6 and an air inlet pipe 7; the built-in oil tank 3, the first oil pipe 4 and the supporting frame 6 are arranged inside the main oil tank 1, the supporting frame 6 is arranged between the bottom of the main oil tank 1 and the bottom of the built-in oil tank 3 and is used for supporting the built-in oil tank 3, the main oil tank 1 is communicated with the built-in oil tank 3 through the first oil pipe 4, and the built-in oil tank 3 is connected with the oil pump 2 through the second oil pipe 5; the air inlet pipe 7 is arranged at the top of the main oil tank 1, the oil tank pressurized gas enters the main oil tank 1 from the air inlet pipe 7 to provide pressure for fuel in the main oil tank 1, so that the fuel is conveyed from the main oil tank 1 to the built-in oil tank 3 through the first oil pipe 4, is conveyed to the oil pump 2 through the second oil pipe 5, and finally the fuel is supplied to the engine through the oil pump 2.
According to the invention, the built-in oil tank is arranged in the main oil tank, so that the temperature of fuel oil at the last flight section of the high-speed aircraft in long voyage can be effectively reduced, and the effects of reducing cavitation risk of the fuel pump, reducing the pressurizing pressure of the fuel tank, reducing the design difficulty of oil passing equipment, increasing the available fuel oil heat sink of an engine and the like can be achieved. The invention can be applied to high-speed aircrafts such as high-speed aircrafts, aerospace aircrafts and the like.
According to one embodiment of the invention, a gap is arranged between the outer wall of the built-in oil tank 3 and the inner wall of the main oil tank 1, and the whole oil tank is designed into a jacketed oil tank. On one hand, an interlayer is formed between the built-in oil tank and the main oil tank, so that the heat insulation effect is achieved; on the other hand, the method can not generate structural collision in the flying process. The flow sequence of the fuel oil is 'main fuel tank-built-in fuel tank-engine'. When flying, the fuel in the main fuel tank 1 is consumed first, and in the process, more fuel and smaller temperature rise of the fuel are obtained. After the fuel in the main fuel tank 1 is exhausted, the fuel to be supplied to the engine is not contacted with the wall of the main fuel tank 1, so that the heat transfer quantity of the fuel on the outer surface of the high-speed aircraft can be effectively reduced, the temperature rise rate of the fuel is reduced, and the temperature of the fuel at the tail end of the flight is inhibited, and the effect is shown in figure 2. Typically, the gap between the outer wall of the built-in fuel tank 3 and the inner wall of the main fuel tank 1 is not less than 30mm.
According to one embodiment of the invention, one end of the first oil pipe 4 is located at the bottom of the main oil tank 1 and at a predetermined distance from the bottom of the main oil tank 1, and the other end is located at the top of the built-in oil tank 3, so that the main oil tank 1 and the built-in oil tank 3 constitute a series oil tank. The height of the supporting frame 6 is larger than the preset distance so as to meet the requirement that the residual fuel at the bottom of the main fuel tank 1 cannot contact the built-in fuel tank 3, and heat conduction from the main fuel tank 1 to the built-in fuel tank 3 can be effectively reduced. Because the contact area of the supporting frame 6 is limited, and the supporting frame 6 is provided with a thermal bridge blocking structure, the heat conduction from the main oil tank 1 to the built-in oil tank 3 can be further isolated.
According to an embodiment of the present invention, the wall of the main oil tank 1 is made of a high temperature resistant metal material, such as a titanium alloy material or a composite material, which can resist high temperature and can also play a bearing role. The wall of the built-in oil tank 3 is not used as a main bearing structure of the aircraft, the pressure difference between the inside and the outside is small, and light materials, such as aluminum alloy materials, can be selected.
For better control of the fuel end temperature, the system further comprises a first insulation layer, which is arranged on the outer or inner wall of the main tank 1. The system further comprises a second insulation layer arranged on the outer wall or the inner wall of the built-in oil tank 3. The system further comprises a high-reflectivity coating, wherein when the second heat insulation layer is arranged on the outer wall of the built-in oil tank 3, the high-reflectivity coating is arranged on the outer side of the second heat insulation layer; when the second heat insulation layer is arranged on the inner wall of the built-in oil tank 3, the high-reflectivity coating is arranged on the outer wall of the built-in oil tank 3.
The wall of the main oil tank 1 is of a welding structure, and a pipeline inside the main oil tank 1 and the built-in oil tank 3 are installed before welding.
Fig. 3 is a schematic flow chart of a design method of an oil transportation thermal management system for controlling the temperature rise of fuel oil of a high-speed aircraft according to an embodiment of the invention. As shown in fig. 3, the present invention provides a design method of an oil transportation thermal management system for controlling temperature rise of fuel oil of a high-speed aircraft, which comprises:
s1, establishing a main oil tank heat transfer model without a built-in oil tank based on a main oil tank structure model;
s2, determining the fuel consumption when the target temperature of the fuel is the target temperature based on a fuel temperature rise curve of a main fuel tank heat transfer model without a built-in fuel tank;
s3, determining the initial volume of the built-in oil tank based on the fuel consumption at the target temperature of the fuel;
s4, based on the main oil tank structure model and the initial volume of the built-in oil tank, establishing a main oil tank heat transfer model of the built-in oil tank;
s5, determining the final volume of the built-in oil tank based on the highest temperature of the fuel temperature rise curve of the heat transfer model of the main oil tank with the built-in oil tank, the target temperature of the fuel and the initial volume of the built-in oil tank.
According to the invention, a three-dimensional CFD method or a heat transfer engineering analysis method is utilized to analyze and obtain a fuel oil temperature rise curve of a heat transfer model in the process of supplying fuel in a flight along a flight track.
According to one embodiment of the present invention, determining the final volume of the built-in fuel tank in S5 based on the maximum temperature of the fuel temperature rise curve of the main fuel tank heat transfer model with the built-in fuel tank, the target fuel temperature, and the initial volume of the built-in fuel tank comprises:
s51, comparing the highest temperature of a fuel temperature rise curve of a main fuel tank heat transfer model with a built-in fuel tank with a target fuel temperature;
s52, judging whether to correct the initial volume of the built-in oil tank according to the comparison result;
s53, if the highest temperature of the fuel temperature rise curve of the heat transfer model of the main fuel tank with the built-in fuel tank is less than or equal to the target fuel temperature, determining the initial volume of the built-in fuel tank as the final volume of the built-in fuel tank without correction;
s54, if the highest temperature of the fuel temperature rise curve of the main fuel tank heat transfer model with the built-in fuel tank is higher than the target fuel temperature, correcting the initial volume of the built-in fuel tank, establishing a corrected main fuel tank heat transfer model with the built-in fuel tank, and determining the corrected volume of the built-in fuel tank as the final volume of the built-in fuel tank until the highest temperature of the fuel temperature rise curve of the corrected main fuel tank heat transfer model with the built-in fuel tank is lower than or equal to the target fuel temperature.
According to one embodiment of the present invention, the correcting of the initial volume of the built-in tank in S54 includes: the initial volume of the built-in oil tank is increased. For example, the initial volume of the built-in fuel tank may be determined by:
V＝V 0 -V 1 /n；
wherein: v is the initial volume of the built-in oil tank, V 0 Is the main oil tank volume, V 1 N is the volume of the interlayer between the main oil tank and the built-in oil tank, n is the volume coefficient, V 1 Is the fuel consumption at the target temperature of the fuel.
Wherein the initial volume of the built-in tank is increased by increasing the value of the volume coefficient n.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present invention.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The integrated oil transportation and heat management system for controlling the temperature rise of the fuel oil of the high-speed aircraft is characterized by comprising a main oil tank (1), a built-in oil tank (3), an oil pump (2), a first oil pipe (4), a second oil pipe (5), a support frame (6) and an air inlet pipe (7); the built-in oil tank (3), the first oil pipe (4) and the support frame (6) are arranged inside the main oil tank (1), the support frame (6) is arranged between the bottom of the main oil tank (1) and the bottom of the built-in oil tank (3) and is used for supporting the built-in oil tank (3), the main oil tank (1) is communicated with the built-in oil tank (3) through the first oil pipe (4), and the built-in oil tank (3) is connected with the oil pump (2) through the second oil pipe (5); the air inlet pipe (7) is arranged at the top of the main oil tank (1), pressurized gas of the oil tank enters the main oil tank (1) from the air inlet pipe (7) to provide pressure for fuel in the main oil tank (1), so that the fuel is conveyed from the main oil tank (1) to the built-in oil tank (3) through the first oil pipe (4), is conveyed to the oil pump (2) through the second oil pipe (5), and finally the fuel supplies fuel to an engine through the oil pump (2); one end of the first oil pipe (4) is located at the bottom of the main oil tank (1) and is away from the bottom of the main oil tank (1) by a preset distance, the other end of the first oil pipe is located at the top of the built-in oil tank (3), and the height of the supporting frame (6) is larger than the preset distance.
2. An integrated system for thermal management of fuel delivery for controlling the temperature rise of a high-speed aircraft according to claim 1, characterized in that a gap is provided between the external wall of said internal tank (3) and the internal wall of said main tank (1).
3. An integrated system for thermal management of fuel delivery for controlling the temperature rise of a high-speed aircraft according to claim 1, characterized in that the walls of the main tank (1) are made of refractory metal material.
4. An integrated system for thermal management of fuel delivery for controlling the temperature rise of a high-speed aircraft according to claim 1, characterized in that the walls of said internal tank (3) are made of aluminium alloy material.
5. An integrated thermal management system for the transportation of fuel in high speed aircraft according to claim 1, characterized in that it further comprises a first insulating layer, which is provided on the external or internal wall of the main tank (1).
6. An integrated thermal management system for the transportation of oil for controlling the temperature rise of the fuel of a high-speed aircraft according to claim 1, characterized in that it further comprises a second insulating layer, which is provided on the external or internal wall of said built-in tank (3).
7. An integrated thermal management system for oil delivery for controlling the temperature rise of a high-speed aircraft fuel according to claim 6, characterized in that it further comprises a high-reflectivity coating, said coating being arranged outside said second thermal insulation layer when said second thermal insulation layer is arranged on the external wall of said internal tank (3); when the second heat insulation layer is arranged on the inner wall of the built-in oil tank (3), the high-reflectivity coating is arranged on the outer wall of the built-in oil tank (3).
8. An integrated system for thermal management of oil delivery for controlling the temperature rise of a high-speed aircraft fuel according to claim 1, characterized in that said support frame (6) is provided with a thermal bridge blocking structure.
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| CN202010020340.6A CN111259488B (en) | 2020-01-09 | 2020-01-09 | Oil transportation and thermal management integrated system for controlling temperature rise of fuel oil of high-speed aircraft |
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| CN202010020340.6A CN111259488B (en) | 2020-01-09 | 2020-01-09 | Oil transportation and thermal management integrated system for controlling temperature rise of fuel oil of high-speed aircraft |
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| CN112278298B (en) * | 2020-10-20 | 2022-07-08 | 北京机电工程研究所 | Bionic aircraft fuel tank |
| CN113353286B (en) * | 2021-06-11 | 2022-06-17 | 南京航空航天大学 | Thermal analysis method for multi-compartment oil tank of helicopter |
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