Airplane fuel supply tank

Abstract

The invention belongs to the technical field of aviation mechanical control, and relates to an aircraft fuel supply tank which comprises a main fuel tank and a partition frame using an aircraft body, a fuel supply tank front wall plate and a fuel supply tank rear wall plate are formed in the main fuel tank, the left wall plate and the right wall plate of the fuel supply tank are formed through the side walls of the main fuel tank, and a top plate is arranged at the top of the fuel supply tank to form an independent fuel supply tank body. The oil supply tank is divided into a left oil supply tank and a right oil supply tank, the left oil supply tank is communicated with the right oil supply tank, the left oil supply tank is communicated with the jet pump, one-way valves are arranged on the tops of the left oil supply tank and the right oil supply tank, and one-way valves are arranged on front wall plates and rear wall plates of the oil supply tanks. During design, the gravity center of the aircraft can be adjusted by setting the position of the oil supply tank; the fuel oil utilization rate of the long and flat oil tank is increased through the arrangement of the jet pump; the influence of fuel bubbles brought into the fuel tank after the jet pump is exposed out of the fuel surface is eliminated, and the working stability of an engine is improved; the function of oil supply in the airplane negative overload state is achieved; due to the oil transportation redundancy design after an injection power source is lost, the safety of the aircraft is guaranteed.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation machinery control and relates to an aircraft fuel supply tank. Background Art

[0002] The aircraft fuel tank has the function of storing fuel and supplying fuel to the engine, and needs to meet the fuel consumption requirements of the aircraft under negative overload conditions.

[0003] For the long flat fuel tank of the aircraft, when the oil level in the fuel supply tank in the long flat fuel tank is low and the long flat fuel tank is connected to the fuel supply tank, the fuel supply tank cannot be full of oil and cannot perform negative overload fuel supply, resulting in the aircraft being unable to perform negative overload flight. In order to keep the fuel supply tank full of oil, the fuel supply tank is generally filled with oil by injection. During the oil transfer process, when the oil suction port of the injection pump is exposed to the oil surface, bubbles will be generated and enter the fuel supply tank. The bubbles will enter the oil supply circuit along the fuel supply pump and then enter the engine, affecting the normal operation of the engine.

[0004] Since the long flat fuel tank is connected to the fuel supply tank, when the induced oil transfer power is lost, the fuel in the fuel supply tank will flow into the long flat fuel tank, causing oil cross-contamination and reducing the available fuel in the fuel supply tank.

[0005] At present, during the aircraft design phase, the fuel tank layout is determined in the overall design stage. Since the center of gravity change exceeds the requirements, when the fuel tank layout needs to be changed later, the overall layout also needs to be adjusted accordingly. The adjustment workload is huge, time-consuming and labor-intensive. Summary of the invention

[0006] Purpose of the present invention:

[0007] The present invention provides an aircraft fuel supply tank to solve the problems that a fuel supply tank in a long flat fuel tank of an aircraft cannot be always kept in a full fuel state when the oil level is low, how to eliminate bubbles entering the fuel tank, how to prevent oil leakage in the fuel tank after power is lost, and how to adjust the center of gravity of the aircraft, so that the fuel tank can be kept in a full fuel state to the maximum extent possible and meet the fuel supply requirements of the engine.

[0008] The technical solution of the present invention:

[0009] An aircraft fuel supply tank comprises a main fuel tank, a bulkhead of an aircraft body is used to form front and rear wall panels of the fuel supply tank in the main fuel tank, left and right wall panels of the fuel supply tank are formed by utilizing the side walls of the main fuel tank, a top plate is arranged on the top of the fuel supply tank to form an independent fuel supply tank body, a partition is arranged in the fuel supply tank to separate the fuel supply tank into left and right parts, the left and right fuel supply tanks are connected, the left fuel supply tank is connected to an ejector pump, one-way valves are arranged on the tops of the left and right fuel supply tanks, and one-way valves are arranged on the front and rear wall panels of the fuel supply tanks.

[0010] Furthermore, the main oil tank is a long flat oil tank.

[0011] Furthermore, the size and position of the fuel supply tank are adjusted according to the center of gravity requirements of the aircraft.

[0012] Furthermore, during the fuel supply tank design process, bulkheads and side walls at different positions of the fuselage are selected for design based on the aircraft center of gravity requirements, and the aircraft fuel tank layout does not need to be readjusted.

[0013] Furthermore, the left and right fuel supply tanks are connected via a connecting conduit.

[0014] Furthermore, the amount of oil delivered by the ejector pump to the oil supply tank is greater than the amount of oil flowing out of the oil supply tank.

[0015] Furthermore, a one-way valve is arranged on the wall plate formed by the partition frame between the fuel supply tank and the main fuel tank, and the fuel in the main fuel tank can enter the fuel supply tank through the one-way valve.

[0016] Furthermore, ventilation one-way valves are arranged on the top of the left and right fuel supply tanks, and bubbles in the fuel in the left fuel tank can overflow through the ventilation one-way valve, and excess fuel in the left and right fuel tanks can flow out through the ventilation one-way valves.

[0017] Beneficial effects of the present invention:

[0018] The fuel supply tank of the present invention can adjust the center of gravity of the aircraft by setting the position of the fuel supply tank during design; the arrangement of the ejector pump increases the fuel utilization rate of the long flat fuel tank; the influence of fuel bubbles brought into the fuel tank by the ejector pump after it is exposed to the oil surface is eliminated, thereby improving the working stability of the engine; the function of supplying fuel to the aircraft in a negative overload state is realized; and the fuel delivery margin design after the jet power source is lost ensures the safety of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a structural principle diagram of the oil tank of the present invention;

[0020] Figure 2 yes Figure 1 View along direction A;

[0021] Among them, 1. main fuel tank, 2. priming pump, 3. one-way valve, 4. connecting duct, 5. ventilation one-way valve, 6. left fuel supply tank, 7. right fuel supply tank. DETAILED DESCRIPTION

[0022] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without the need for some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is by no means limited to any specific settings and methods proposed below, but covers any improvements, replacements and modifications of structures, methods, devices without departing from the spirit of the present invention. In the accompanying drawings and the following description, known structures and technologies are not shown to avoid unnecessary ambiguity in the present invention.

[0023] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other, and the embodiments can refer to and quote each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0024] An embodiment of the present invention is:

[0025] The present invention provides an aircraft fuel supply tank to solve the problems that a fuel supply tank in a long flat fuel tank of an aircraft cannot be always kept in a full fuel state when the oil level is low, how to eliminate bubbles entering the fuel tank, how to prevent oil leakage in the fuel tank after power is lost, and how to adjust the center of gravity of the aircraft, so that the fuel tank can be kept in a full fuel state to the maximum extent possible and meet the fuel supply requirements of the engine.

[0026] like Figure 1-2 As shown, the present invention provides a composition and working principle of an aircraft fuel supply tank.

[0027] The fuel supply tank is partitioned by the body structure, separated in the middle of the main fuel tank, and partitioned in the middle of the fuel supply tank to separate the left and right fuel supply tanks.

[0028] Specifically: a body partition frame is used to form front and rear wall panels of the fuel supply tank in the main fuel tank, the left and right wall panels of the fuel supply tank are formed by utilizing the side walls of the main fuel tank, a top plate is provided on the top of the fuel supply tank to form an independent fuel supply tank body, and a partition is provided in the fuel supply tank to separate the left and right fuel supply tanks.

[0029] The size and position of the fuel tank can be adjusted according to the center of gravity requirements of the aircraft. That is, during the design process, the bulkheads and side walls at different positions of the fuselage are selected for design according to the center of gravity requirements of the aircraft, and the layout of the aircraft fuel tank does not need to be readjusted, saving manpower and material resources.

[0030] The left and right fuel supply tanks are connected via a connecting conduit.

[0031] The priming pump introduces the fuel in the main fuel tank into the left fuel tank, and the fuel in the left fuel tank flows into the right fuel tank through the bottom connecting conduit. The fuel bubbles brought by the priming pump in the main fuel tank after the fuel tank is exhausted float in the left fuel tank and overflow out of the fuel tank through the ventilation valve installed on the top of the left fuel tank, and will not enter the right fuel tank. Since the fuel delivery of the priming pump is greater than the fuel supply out of the fuel tank, the fuel tank will always be full of fuel, and the excess fuel will flow out through the ventilation valve on the top of the fuel tank. When the aircraft is in a negative overload state, the ventilation valve on the top of the fuel tank will close to prevent the fuel from flowing out of the valve, ensuring the fuel supply of the aircraft under the negative overload state. A one-way valve is set on the bulkhead between the fuel tank and the main fuel tank. When the priming pump loses its power source, the fuel in the main tank can enter the fuel tank through the one-way valve to maintain the fuel supply capacity and prevent the fuel in the fuel tank from flowing out.

[0032] The present invention can adjust the center of gravity of the aircraft by setting the position of the fuel supply tank; the arrangement of the ejector pump increases the fuel utilization rate of the long flat fuel tank; the influence of the fuel bubbles brought into the fuel tank by the ejector pump after it is exposed to the oil surface is eliminated, thereby improving the working stability of the engine; the function of supplying fuel to the aircraft in a negative overload state is realized; and the invention has an oil delivery margin design after the jet power source is lost, thereby ensuring the safety of the aircraft.

[0033] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the field can easily think of various equivalent modifications or substitutions within the technical scope disclosed by the present invention, and these modifications or substitutions should all be covered within the protection scope of the present invention.

Claims

1. An aircraft fuel supply tank, comprising a main fuel tank, characterized in that: A partition frame of the machine body is used to form front and rear wall panels of the fuel supply tank in the main fuel tank. The left and right wall panels of the fuel supply tank are formed by utilizing the side walls of the main fuel tank. A top plate is arranged on the top of the fuel supply tank to form an independent fuel supply tank body. A partition is arranged in the fuel supply tank to separate the left and right fuel supply tanks into two parts. The left and right fuel supply tanks are connected. The left fuel supply tank is connected to the ejection pump. One-way valves are arranged on the tops of the left and right fuel supply tanks. One-way valves are arranged on the front and rear wall panels of the fuel supply tanks.

2. The aircraft fuel supply tank according to claim 1, characterized in that: The main oil tank is a long flat oil tank.

3. The aircraft fuel supply tank according to claim 1, characterized in that: The size and position of the fuel supply tank are adjusted according to the center of gravity requirements of the aircraft.

4. The aircraft fuel supply tank according to claim 3, characterized in that: During the fuel supply tank design process, the bulkheads and side walls at different positions of the fuselage are selected for design based on the aircraft center of gravity requirements, and the aircraft fuel tank layout does not need to be readjusted.

5. The aircraft fuel supply tank according to claim 1, characterized in that: The left and right fuel supply tanks are connected via a connecting conduit.

6. The aircraft fuel supply tank according to claim 3, characterized in that: The amount of oil delivered by the priming pump to the oil supply tank is greater than the amount of oil flowing out of the oil supply tank.

7. The aircraft fuel supply tank according to claim 1, characterized in that: A one-way valve is arranged on the wall plate formed by the partition frame between the fuel supply tank and the main fuel tank, and the fuel in the main fuel tank can enter the fuel supply tank through the one-way valve.

8. The aircraft fuel supply tank according to claim 1, characterized in that: A ventilation one-way valve is arranged on the top of the left and right fuel supply tanks. Bubbles in the fuel in the left fuel tank can overflow through the ventilation one-way valve, and excess fuel in the left and right fuel tanks can flow out through the ventilation one-way valve.

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