Aviation fuel tank

Abstract

The invention discloses an aviation fuel tank, and relates to the technical field of aviation product fuel equipment, the aviation fuel tank comprises a fuel tank main body, a front end cover and a rear end cover are respectively welded at two ends of the fuel tank main body, an oil injection port, an exhaust port and a pressurized gas inlet are respectively arranged at the upper end of the fuel tank main body, and the oil injection port and the pressurized gas inlet are distributed at two sides of the exhaust port; an oil discharging port is welded to the bottom end of the fuel tank body, an insertion type filter installation connector is arranged on the surface of the front end cover, and a plurality of insertion type filter fixing installation holes are formed in the peripheral side of the insertion type filter installation connector. According to the aviation fuel tank, the plug-in type filter installation connector is reserved in the fuel tank, a fuel filter can be rapidly installed, and the aviation fuel tank adopts a mature manufacturing process, is low in cost and convenient to install, can be manufactured into various complex structures and is high in adaptability.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation product fuel equipment, and in particular to an aviation fuel tank. Background Art

[0002] Aviation fuel tanks are containers installed in aircraft cabins for storing fuel, used to supply fuel to engines, and also as a medium for pressure regulation of control systems. Fuel tanks are relatively closed systems, and are usually equipped with three or more outlets, including fuel filling ports, fuel outlets, and vents. To prevent impurities from entering the aircraft fuel system from the fuel inside and during the filling process, causing abnormalities in combustion, control, and other operations, threatening flight safety, a fuel filter must be installed after the fuel tank outlet. At present, aircraft design is developing in the direction of lightweight, miniaturization, clustering, and low cost. Accordingly, the manufacturing and installation of fuel supply system components and finished parts must also have the characteristics of light weight, low cost, and rapid mass production.

[0003] At present, the fuel tank and fuel filter of aviation products are fixedly installed separately, and oil pipelines and related connectors need to be installed in between. This method has many installation processes, occupies a large space, is costly, and is not conducive to weight control. For this reason, we propose an aviation fuel tank. Summary of the invention

[0004] The main purpose of the present invention is to provide an aviation fuel tank to solve the problems raised in the background technology.

[0005] To achieve the above-mentioned purpose, the technical solution adopted by the present invention is: an aviation fuel tank, including a fuel tank body, a front end cover and a rear end cover are respectively welded at both ends of the fuel tank body, a fuel filling port, an exhaust port and a pressurized gas inlet are respectively arranged at the upper end of the fuel tank body, the fuel filling port and the pressurized gas inlet are distributed on both sides of the exhaust port, an oil drain port is welded at the bottom end of the fuel tank body, a plug-in filter installation interface is arranged on the surface of the front end cover, and a plurality of plug-in filter fixing installation holes are arranged on the outer peripheral side of the plug-in filter installation interface.

[0006] Preferably, fixing brackets are welded to the bottom ends of the front cover and the rear cover to support and fix the fuel tank body.

[0007] Preferably, the oil filling port, exhaust port and pressurized gas inlet all protrude from the fuel tank body, and the output ends of the oil filling port, exhaust port and pressurized gas inlet are welded to the fuel tank body, which is convenient for oil filling, exhaust and pressurized gas injection and easy to operate.

[0008] Preferably, the number of the fuel filling port, the exhaust port, the pressurized gas inlet port and the fuel drain port disposed on the surface of the fuel tank body includes but is not limited to one group, so as to improve the utilization efficiency of the aviation fuel tank.

[0009] Preferably, the interface diameter of the plug-in filter installation interface is adapted to the socket size of the plug-in fuel filter, so as to facilitate quick plug-in.

[0010] Preferably, the fixing forms at the interface of the plug-in filter installation interface include but are not limited to clamps, screws, expansion tubes and clamps, and the fixing methods are diverse and the fixing strength is enhanced.

[0011] The present invention has the following beneficial effects:

[0012] The aviation fuel tank of the present invention can be directly assembled with the fuel filter, and the operation is quick. At the same time, the raw materials used are low in cost, and various complex configurations can be quickly made. The manufacturing process is simple, the cycle is short, and the weight is light, which meets the requirements of low weight, low cost, and rapid mass production. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is the overall structural diagram of the aviation fuel tank of the present invention;

[0014] Figure 2 It is a schematic diagram of the side structure of the aviation fuel tank of the present invention.

[0015] In the figure: 1. Fuel tank body; 2. Front cover; 3. Rear cover; 4. Fuel filling port; 5. Exhaust port; 6. Pressurized gas inlet; 7. Oil drain port; 8. Plug-in filter installation interface; 9. Fixed bracket; 10. Plug-in filter fixing installation hole. DETAILED DESCRIPTION

[0016] In order to make the above-mentioned purpose, features and advantages of the present invention more obvious and easy to understand, the specific embodiments of the present invention are described in detail below in conjunction with the accompanying drawings. In the following description, many specific details are set forth so as to fully understand the present invention. However, the present invention can be implemented in many other ways different from those described herein, and those skilled in the art can make similar improvements without violating the connotation of the present invention, so the present invention is not limited by the specific embodiments disclosed below. In the description of the present invention, it should be understood that the orientation or position relationship indicated by the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like is based on the orientation or position relationship shown in the accompanying drawings, only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present invention.

[0017] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0018] Please refer to Figure 1-Figure 2 As shown, the present invention is an aviation fuel tank, comprising a fuel tank body 1, a front end cover 2 and a rear end cover 3 are welded at both ends of the fuel tank body 1, and a fuel filling port 4, an exhaust port 5 and a pressurized gas inlet 6 are respectively arranged at the upper end of the fuel tank body 1, and the fuel filling port 4 and the pressurized gas inlet 6 are distributed on both sides of the exhaust port 5. Fuel can be directly added to the fuel tank body 1 through the fuel filling port 4, and the internal pressure of the fuel tank is adjusted through the exhaust port 5 and the pressurized gas inlet 6 during the refueling and fuel supply process, wherein the pressurized gas inlet 6 is connected to an external pressurizing device to introduce pressurized gas into the fuel tank. Gas is discharged from the exhaust port 5 to balance the internal pressure of the fuel tank. A drain port 7 is welded at the bottom of the fuel tank body 1 to guide the fuel out. A plug-in filter installation interface 8 is provided on the surface of the front cover 2 to install a plug-in fuel filter, thereby reducing the connection between the fuel tank and the aircraft structure. A plurality of plug-in filter fixing installation holes 10 are provided on the outer peripheral side of the plug-in filter installation interface 8 to assist in fixing the plug-in fuel filter. A fixing bracket 9 is welded at the bottom of the front cover 2 and the rear cover 3 to support and fix the fuel tank body 1.

[0019] The fuel filling port 4, the exhaust port 5 and the pressurized gas inlet 6 are all protruding from the fuel tank body 1, and the output ends of the fuel filling port 4, the exhaust port 5 and the pressurized gas inlet 6 are all welded to the fuel tank body 1, which is convenient for filling, exhausting and injecting pressurized gas, and has strong operational stability; the number of the fuel filling port 4, the exhaust port 5, the pressurized gas inlet 6 and the fuel drain port 7 arranged on the surface of the fuel tank body 1 includes but is not limited to one group, which improves the fuel filling efficiency, internal pressure regulation efficiency and fuel drain efficiency of the fuel tank;

[0020] The interface diameter of the plug-in filter mounting interface 8 is adapted to the socket size of the plug-in fuel filter. At the same time, the plug-in filter mounting interface 8 does not limit the filter interface size and can be plugged in and adapted to plug-in filters of different sizes, with strong controllability and improved efficiency. The interface fixing forms of the plug-in filter mounting interface 8 include but are not limited to clamps, screws, expansion tubes and clamps, etc., and the installation is easy.

[0021] The present invention discloses an aviation fuel tank, wherein a fuel tank body 1 is connected with a front end cover 2 and a rear end cover 3 by welding, a fuel filling port 4, an exhaust port 5, a pressurized gas inlet 6, etc. are welded on the upper side of the fuel tank body 1, fuel can be directly filled through the fuel filling port 4, and the internal pressure of the fuel tank is adjusted through the exhaust port 5 and the pressurized gas inlet 6 during the refueling and fuel supply process, a fuel drain port 7 is welded below the fuel tank body 1 for fuel output, a plug-in filter installation interface 8 is welded on the surface of the front end cover 2, a plug-in fuel filter can be installed, and the connection between the fuel tank and the aircraft structure is reduced, and a fixing bracket 9 is welded at the bottom end of each of the front end cover 2 and the rear end cover 3, and after the fuel tank is placed in the fuel tank compartment in the aircraft body, it can be fastened to the fuel tank compartment by using a fixing belt.

[0022] At the same time, the fuel tank of the present invention uses stainless steel plate as the main raw material, and is quickly formed by sheet metal and welding technology according to a specific fuel tank configuration, which is light in weight, low in manufacturing cost, and simple in process;

[0023] In addition, the present invention does not limit the number of fixing holes of the fuel filter interface, and the mounting holes can be set according to the actual needs of the fuel filter. The present invention does not limit the size of the filter mounting interface to adapt to the installation of filters of different sizes. At the same time, the present invention does not limit the fixing form at the filter interface, and can adopt a variety of fastening methods such as clamps, screws, expansion tubes and clamps, which have strong operational adaptability when fixed. In addition, the present invention does not limit the number of openings of the fuel tank body 1 to meet the use of fuel tanks of different sizes or adjust the filling and discharge efficiency of the fuel tank.

[0024] The aviation fuel tank of the present invention can assemble a fuel filter with the fuel tank, thereby reducing the connection between the fuel tank and the aircraft. At the same time, the fuel tank has a simple structure, and the materials and processing technology are relatively common, which is conducive to reducing costs, controlling quality, and rapid mass production.

[0025] In the description of this specification, the description with reference to the terms "one embodiment", "example", "specific example", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0026] The preferred embodiments of the present invention disclosed above are only used to help explain the present invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to only specific implementation methods. Obviously, many modifications and changes can be made according to the content of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well. The present invention is limited only by the claims and their full scope and equivalents.

Claims

1. An aviation fuel tank, comprising a fuel tank body (1), Features: The two ends of the fuel tank body (1) are respectively welded with a front cover (2) and a rear cover (3); the upper end of the fuel tank body (1) is respectively provided with a fuel filling port (4), an exhaust port (5) and a pressurized gas inlet (6); the fuel filling port (4) and the pressurized gas inlet (6) are distributed on both sides of the exhaust port (5); the bottom end of the fuel tank body (1) is welded with a fuel drain port (7); the surface of the front cover (2) is provided with an insert filter installation interface (8); and the outer peripheral side of the insert filter installation interface (8) is provided with a plurality of insert filter fixing installation holes (10).

2. An aviation fuel tank according to claim 1, Features: The bottom ends of the front cover (2) and the rear cover (3) are both welded with a fixing bracket (9).

3. An aviation fuel tank according to claim 1, Features: The fuel filling port (4), the exhaust port (5) and the pressurized gas inlet (6) all protrude from the fuel tank body (1), and the output ends of the fuel filling port (4), the exhaust port (5) and the pressurized gas inlet (6) are all welded to the fuel tank body (1).

4. An aviation fuel tank according to claim 1, Features: The number of the fuel filling port (4), the exhaust port (5), the pressurized gas inlet (6) and the fuel drain port (7) provided on the surface of the fuel tank body (1) includes, but is not limited to, one group.

5. An aviation fuel tank according to claim 1, Features: The interface diameter of the plug-in filter installation interface (8) is adapted to the socket size of the plug-in fuel filter.

6. An aviation fuel tank according to claim 1, Features: The fixing forms at the interface of the plug-in filter installation interface (8) include but are not limited to clamps, screws, expansion tubes and clamps.

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