Aircraft fuel oil cooling system
A cooling system, aircraft technology, applied in the direction of the fuel tank of the power plant, etc., to achieve the effect of reducing the weight and resistance of the aircraft
Active Publication Date: 2018-06-01
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology
[0005] The object of the present invention is to provide a kind of aircraft fuel cooling system, to solve at least one problem that existing aircraft fuel cooling system exists
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[0026] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...
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The invention relates to the technical field of fuel oil heat management, in particular to an aircraft fuel oil cooling system. The aircraft fuel oil cooling system is used for cooling to-be-cooled fuel oil which absorbs heat and then is pre-returned to an oil supply tank. The aircraft fuel oil cooling system includes an aircraft wing oil tank, at least one nozzle and an oil transport pipe; the to-be-cooled fuel oil is injected into the aircraft wing oil tank through an oil inlet pipe, the nozzles are arranged on the oil inlet pipe and are used for ejecting the to-be-cooled fuel oil to an upper skin of the aircraft wing oil tank according to a preset ejection direction and preset ejection flow, an oil inlet of the oil transport pipe is formed in the position, close to an upper skin of theaircraft wing oil tank, of the interior of the aircraft wing oil tank, and the oil transport pipe is used for transporting the to-be-cooled fuel oil which is sequentially cooled by the upper skin andthe lower skin to the oil supply tank. According to the aircraft fuel oil cooling system, air heat sink is adopted to cool high-temperature fuel oil, it is unnecessary to form a punching opening in anaircraft to introduce punching air, and resistance is reduced when the aircraft flies.
Description
technical field [0001] The invention relates to the technical field of fuel thermal management, in particular to an aircraft fuel cooling system. Background technique [0002] With the improvement of the overall performance of the aircraft, the number and power of on-board electronic equipment continue to increase, and the heat generated by the system naturally increases accordingly. In addition, in order to meet the stealth requirements of the aircraft, the number and area of stamping openings on the exterior of the fuselage are limited, and the amount of ram air that can be used is limited. Therefore, fuel is bound to become the main cold source to cool other equipment and systems of the aircraft (such as hydraulic oil, lubricating oil, coolant, etc.). The heat-absorbed fuel returns to the fuel supply tank, causing the temperature of the fuel in the fuel supply tank to rise, potentially reaching or exceeding the inlet temperature limit to the engine. [0003] From the ...
Claims
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IPC IPC(8): B64D37/02B64D37/06
CPCB64D37/02B64D37/06
Inventor 王亚盟赵营李群金钊单玉伟
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA