CN111259488A - Oil transportation and heat management integrated system for controlling temperature rise of fuel oil of high-speed aircraft - Google Patents
Oil transportation and heat management integrated system for controlling temperature rise of fuel oil of high-speed aircraft Download PDFInfo
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- CN111259488A CN111259488A CN202010020340.6A CN202010020340A CN111259488A CN 111259488 A CN111259488 A CN 111259488A CN 202010020340 A CN202010020340 A CN 202010020340A CN 111259488 A CN111259488 A CN 111259488A
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
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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 oil tank pressurized gas enters the main oil tank from the air inlet pipe and provides pressure for fuel oil in the main oil tank, so that the fuel oil is conveyed to the built-in oil tank from the main oil tank through the first oil pipe and then conveyed to the oil pump through the second oil pipe, and finally the fuel oil supplies fuel oil to the engine through the oil pump. By applying the technical scheme of the invention, the built-in fuel tank is arranged in the main fuel tank, so that the temperature of fuel at the tail section of the flight of the high-speed aircraft in long-term flight can be effectively reduced, and the effects of reducing the cavitation risk of the fuel pump, reducing the pressurization pressure of the fuel tank, reducing the design difficulty of oil passing equipment, increasing the available fuel heat sink of an engine and the like can be achieved. The invention can be applied to high-speed aircrafts such as high-speed airplanes and space airplanes.
Description
Technical Field
The invention relates to the technical field of fuel delivery and thermal management of high-speed aircrafts, in particular to a fuel delivery and thermal management integrated system for controlling the temperature rise of fuel of a high-speed aircraft.
Background
The existing fuel oil cabin body of the high-speed aircraft is not only used for storing fuel oil, but also plays a role in bearing the aircraft. Due to the fact that the flying speed is high, the pneumatic heating phenomenon is serious, and the temperature of fuel oil in the cabin is continuously increased after the aircraft flies for a long time; especially, the fuel quantity is reduced and the fuel temperature rise is accelerated at the tail section of the flight. The increased fuel temperature can cause cavitation at the pump inlet, and can increase the risk of over-temperature failure of the oil through valve. For high speed aircraft that use fuel for active engine cooling, the increased fuel temperature also increases the risk of engine wall over-temperature.
In order to control the temperature of fuel before being delivered to an engine pump by a fuel system during long-endurance flight not to exceed a design temperature, the existing high-speed aircraft reduces heat flow input into a cabin by enhancing the thermal protection of a fuel cabin, but the fuel loading space of the aircraft is reduced, the range is reduced, and extra weight and cost are added.
Disclosure of Invention
The invention provides an oil delivery 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 of a fuel pump of the high-speed aircraft, over-temperature failure of an oil passing valve and over-temperature of the wall surface of an engine in the prior art on the premise of not reducing the loading space of the fuel oil.
In order to solve the technical problem, 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 connected with the built-in oil tank; the built-in oil tank, the first oil pipe and the support frame are arranged inside the main oil tank, the support 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, oil tank pressurized gas enters the main oil tank from the air inlet pipe and provides pressure for fuel oil in the main oil tank, so that the fuel oil is conveyed to the built-in oil tank from the main oil tank through the first oil pipe and then conveyed to the oil pump through the second oil pipe, and finally the fuel oil supplies fuel oil 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 a predetermined distance away from the bottom of the main oil tank, the other end of the first oil pipe is located at the top of the built-in oil tank, and the height of the support frame is greater than the predetermined distance.
Preferably, a gap is formed 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 insulation layer disposed on an outer wall or an inner wall of the main tank.
Preferably, the system further comprises a second insulation layer arranged on the outer wall or the inner wall of the built-in oil tank.
Preferably, the system further comprises a high-reflectivity coating, and when the second heat insulation layer is arranged on the outer wall of the built-in oil tank, 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, 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 applying the technical scheme of the invention, the built-in fuel tank is arranged in the main fuel tank, so that the temperature of fuel at the tail section of the flight of the high-speed aircraft in long-term flight can be effectively reduced, and the effects of reducing the cavitation risk of the fuel pump, reducing the pressurization pressure of the fuel tank, reducing the design difficulty of oil passing equipment, increasing the available fuel heat sink of an engine and the like can be achieved. The invention can be applied to high-speed aircrafts such as high-speed airplanes and space airplanes.
Drawings
The accompanying drawings, which are included to provide a further understanding of the 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 obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 is a schematic structural diagram illustrating an integrated fuel delivery and thermal management system for controlling temperature rise of fuel of a high-speed aircraft according to an embodiment of the invention;
FIG. 2 is a schematic diagram illustrating a temperature rise profile of fuel provided in accordance with an embodiment of the present invention;
fig. 3 is a flow chart illustrating a method for designing a fuel delivery thermal management system for controlling temperature rise of fuel 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 inside; 4. A first oil pipe;
5. a second oil pipe; 6. A support frame; 7. An air inlet pipe.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. 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. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. 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.
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 according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
Fig. 1 shows a schematic structural diagram of an integrated fuel delivery and thermal management system for controlling temperature rise of fuel of a high-speed aircraft according to an embodiment of the invention. As shown in fig. 1, the invention provides an oil transportation and thermal 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 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 intake pipe 7 set up in the top of main oil tank 1, the oil tank pressurized gas follow intake pipe 7 gets into main oil tank 1 for fuel in the main oil tank 1 provides pressure, makes the fuel follow main oil tank 1 via first oil pipe 4 carry to built-in oil tank 3, via again the second oil pipe 5 carry to oil pump 2, the fuel passes through oil pump 2 supplies fuel for the engine at last.
The built-in fuel tank is arranged in the main fuel tank, so that the temperature of fuel at the tail section of the flight of the high-speed aircraft in long-term flight can be effectively reduced, and the effects of reducing the cavitation risk of the fuel pump, reducing the pressurization pressure of the fuel tank, reducing the design difficulty of fuel passing equipment, increasing the available fuel heat sink of the engine and the like can be achieved. The invention can be applied to high-speed aircrafts such as high-speed airplanes and space airplanes.
According to an 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 fuel tank is designed into a jacketed fuel tank. On one hand, an interlayer is formed between the built-in oil tank and the main oil tank, and the heat insulation effect is achieved; on the other hand, the requirement that no structural collision occurs during flight is met. 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, the fuel is more and the temperature rise of the fuel is less. 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 any more, so that the heat transfer quantity of the outer surface of the high-speed aircraft to the fuel can be effectively reduced, the temperature rise rate of the fuel is reduced, the temperature of the fuel at the tail end of flight is restrained, and the effect is shown in fig. 2. In general, the clearance between the outer wall of the built-in oil tank 3 and the inner wall of the main oil tank 1 is not less than 30 mm.
According to an embodiment of the present invention, one end of the first oil pipe 4 is located at the bottom of the main oil tank 1 and is spaced from the bottom of the main oil tank 1 by a predetermined distance, 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 support 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 effectively reduce the heat conduction of the main fuel tank 1 to the built-in fuel tank 3. Because the contact area of the support frame 6 is limited, and the support frame 6 is provided with a heat bridge blocking structure, the heat conduction of 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, and can resist high temperature and perform a bearing function. The tank wall of the built-in oil tank 3 is not used as a main bearing structure of the aircraft, the internal and external pressure difference is small, and light materials, such as aluminum alloy materials, can be selected.
For better control of the temperature of the end of the fuel, the system further comprises a first heat insulation layer which is arranged on the outer wall or the inner wall of the main fuel tank 1. The system also comprises a second heat insulation layer which is arranged on the outer wall or the inner wall of the built-in oil tank 3. The system also comprises a high-reflectivity coating, and when the second heat-insulating 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-insulating 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 welded structure, and before welding, a pipeline and a built-in oil tank 3 in the main oil tank 1 are installed.
Fig. 3 is a flow chart illustrating a method for designing a fuel delivery thermal management system for controlling temperature rise of fuel 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 a fuel delivery thermal management system for controlling temperature rise of fuel of a high speed aircraft, wherein the method comprises:
s1, establishing a main oil tank heat transfer model without a built-in oil tank based on the main oil tank structure model;
s2, determining the fuel consumption at the target fuel temperature based on the fuel temperature rise curve of the main fuel tank heat transfer model without the built-in fuel tank;
s3, determining the initial volume of the built-in oil tank based on the fuel consumption at the fuel target temperature;
s4, establishing a main oil tank heat transfer model with a built-in oil tank based on the main oil tank structure model and the built-in oil tank initial volume;
and S5, determining the final volume of the built-in oil tank based on the highest temperature of the fuel temperature rise curve of the main oil tank heat transfer model with the built-in oil tank, the target temperature of the fuel and the initial volume of the built-in oil tank.
The fuel temperature rise curve of the heat transfer model in the flight fuel supply process is obtained by analyzing along the flight track by using a three-dimensional CFD method or a heat transfer engineering analysis method.
According to an embodiment of the present invention, the 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 temperature of the fuel, and the initial volume of the built-in fuel tank includes:
s51, comparing the highest temperature of the fuel oil temperature rise curve of the main fuel tank heat transfer model with the built-in fuel tank with the 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 main fuel tank heat transfer model with the built-in fuel tank is smaller than or equal to the target fuel temperature, correcting the highest temperature, and determining the initial volume of the built-in fuel tank as the final volume of the built-in fuel tank;
and 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 the 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 an embodiment of the present invention, the step of modifying the initial volume of the internal fuel tank in S54 includes: and increasing the initial volume of the built-in oil tank. For example, the initial volume of the internal fuel tank can be determined by:
V＝V0-V1/n；
in the formula: v is the initial volume of the built-in oil tank, V0Is the volume of the main oil tank, V1Predominantly/nThe volume of the oil tank and the interlayer of the built-in oil tank, n is the volume coefficient, V1The fuel consumption at the target fuel temperature.
Wherein the initial volume of the built-in oil tank is increased by increasing the value of the volume coefficient n.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship 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 of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A fuel delivery and heat management integrated system for controlling the temperature rise of fuel oil of a high-speed aircraft is characterized by comprising a main fuel tank (1), a built-in fuel 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), oil tank pressurization gas enters the main oil tank (1) from the air inlet pipe (7), pressure is provided for fuel oil in the main oil tank (1), the fuel oil is conveyed to the built-in oil tank (3) from the main oil tank (1) through the first oil pipe (4), then conveyed to the oil pump (2) through the second oil pipe (5), and finally the fuel oil is supplied to an engine through the oil pump (2).
2. The integrated fuel delivery and heat management system for controlling the temperature rise of fuel of a high-speed aircraft according to claim 1, wherein one end of the first fuel pipe (4) is positioned at the bottom of the main fuel tank (1) and is separated from the bottom of the main fuel tank (1) by a preset distance, the other end of the first fuel pipe is positioned at the top of the built-in fuel tank (3), and the height of the support frame (6) is larger than the preset distance.
3. The integrated fuel delivery and heat management system for controlling the temperature rise of the fuel of the high-speed aircraft as claimed in claim 2, wherein a gap is formed between the outer wall of the built-in fuel tank (3) and the inner wall of the main fuel tank (1).
4. The integrated fuel delivery and heat management system for controlling the temperature rise of fuel oil of a high-speed aircraft according to claim 1, wherein the wall of the main fuel tank (1) is made of high-temperature-resistant metal material.
5. The integrated oil delivery and heat management system for controlling the temperature rise of the fuel oil of the high-speed aircraft as claimed in claim 1, wherein the wall of the built-in oil tank (3) is made of aluminum alloy.
6. The integrated fuel delivery and heat management system for controlling the temperature rise of fuel of a high-speed aircraft according to claim 1, further comprising a first heat insulation layer arranged on the outer wall or the inner wall of the main fuel tank (1).
7. The integrated fuel delivery and heat management system for controlling the temperature rise of fuel of a high-speed aircraft according to claim 1, further comprising a second thermal insulation layer, wherein the second thermal insulation layer is arranged on the outer wall or the inner wall of the built-in fuel tank (3).
8. The integrated fuel delivery and heat management system for controlling the temperature rise of fuel oil of a high-speed aircraft according to claim 7, further comprising a high-reflectivity coating, wherein when the second heat insulation layer is arranged on the outer wall of the built-in fuel 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).
9. The integrated oil delivery and heat management system for controlling the temperature rise of the fuel oil of the high-speed aircraft as claimed in claim 1, wherein the support frame (6) is provided with a heat bridge blocking structure.
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| Application Number | Priority Date | Filing Date | Title |
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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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| CN112278298A (en) * | 2020-10-20 | 2021-01-29 | 北京机电工程研究所 | Bionic aircraft oil tank |
| CN113353286A (en) * | 2021-06-11 | 2021-09-07 | 南京航空航天大学 | Thermal analysis method for multi-compartment oil tank of helicopter |
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| 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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| Publication number | Publication date |
|---|---|
| CN111259488B (en) | 2023-07-11 |
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