CN112455702B

CN112455702B - Fuel supply system and aircraft

Info

Publication number: CN112455702B
Application number: CN202110132939.3A
Authority: CN
Inventors: 彭小波; 郑立伟; 施发树
Original assignee: Beijing Interstellar Glory Technology Co Ltd; Beijing Star Glory Space Technology Co Ltd
Current assignee: Beijing Interstellar Glory Technology Co Ltd; Beijing Star Glory Space Technology Co Ltd
Priority date: 2021-02-01
Filing date: 2021-02-01
Publication date: 2021-05-28
Anticipated expiration: 2041-02-01
Also published as: CN112455702A

Abstract

The invention provides a fuel supply system and an aircraft, belonging to the technical field of aircraft fuel supply, wherein the fuel supply system comprises: a central tank and at least two side tanks respectively communicating with the central tank; the outlet of the central storage tank is suitable for being communicated with an oil inlet of an engine of an aircraft, an air inlet channel is communicated with each side storage tank, pressure gas is suitable for being introduced into the side storage tanks through the air inlet channels, and fuel oil in the side storage tanks is converged towards the inside of the central storage tank through the pressure gas; the fuel supply system of the invention converges the fuel in the plurality of side tanks into the central tank when supplying fuel, and supplies fuel to the engine through the central tank, namely, the fuel in the side tanks is consumed firstly, so that the fuel in the central tank is kept in a full state, thereby being capable of keeping the gravity center of the aircraft to change little or not to change basically during the fuel supply process.

Description

Fuel supply system and aircraft

Technical Field

The invention relates to the technical field of aircraft fuel supply, in particular to a fuel supply system and an aircraft.

Background

In an existing aircraft (e.g., an airplane), a plurality of independent fuel tanks are generally provided, and each fuel tank can supply fuel to the aircraft simultaneously.

The weight of each fuel tank directly affects the center of gravity of the aircraft, and uneven fuel supply of each fuel tank causes different weights of each fuel tank, so that the center of gravity of the aircraft shifts, and the aircraft risks being unpredictable.

Disclosure of Invention

Therefore, the technical problem to be solved by the present invention is to overcome the defect that the center of gravity of the aircraft is easily shifted when a plurality of fuel tanks are used for supplying fuel to the aircraft simultaneously in the fuel supply system in the prior art, so as to provide a fuel supply system capable of keeping the center of gravity of the aircraft substantially unchanged.

The invention also provides an aircraft with the fuel supply system.

In order to solve the above technical problem, the present invention provides a fuel supply system, including: a central tank and at least two side tanks respectively communicating with the central tank;

the outlet of the central storage tank is suitable for being communicated with an oil inlet of an engine of an aircraft, each side storage tank is communicated with an air inlet channel, the air inlet channels are suitable for introducing pressure gas into the side storage tanks, and the pressure gas enables fuel oil in the side storage tanks to converge towards the central storage tank.

Optionally, the side tank comprises: the front storage tank, the central storage tank and the rear storage tank are sequentially arranged along the front-rear direction.

Optionally, the central tank and the side tanks are communicated by a transfer pipe, one end of the transfer pipe is communicated with the bottom outlet of the side tank, and the other end of the transfer pipe is communicated with the top inlet of the central tank.

Optionally, a plurality of the side tanks communicate with an intake passage, one end of which is adapted to communicate with the rear end of an engine low pressure compressor or fan of the aircraft.

Optionally, a pressure reducer is provided on the intake passage.

Optionally, an anti-negative-overload tank is arranged below the central storage tank, and the anti-negative-overload tank is communicated with an oil inlet of the engine through a first oil supply pipeline.

Optionally, the central tank communicates with the first oil supply line via a second oil supply line having a one-way valve communicating towards the first oil supply line.

Optionally, the top of the negative overload resistant box is provided with an air release valve.

Optionally, the outlet end of the anti-negative overload tank is provided with an electric valve.

The invention also provides an aircraft comprising a fuel supply system according to any one of the preceding claims.

The technical scheme of the invention has the following advantages:

1. the fuel supply system provided by the invention converges the fuel in the plurality of side storage tanks into the central storage tank when supplying fuel, and supplies fuel to the engine through the central storage tank, namely, the fuel in the side storage tanks is consumed firstly, so that the fuel in the central storage tank is kept in a full state, and the change of the gravity center of the aircraft is kept very small or basically unchanged in the fuel supply process.

2. According to the fuel supply system provided by the invention, the pressure gas is introduced from the engine to the side storage tank, so that the use of a gas cylinder is reduced, the load is reduced, and the system structure is simpler.

3. The fuel supply system provided by the invention can ensure that the aircraft can continuously supply fuel towards the engine under different flight conditions through the negative overload resisting box at the final stage of fuel supply.

4. The invention provides an aircraft having a fuel supply system as described in any one of the preceding claims and thus having the advantages as described in any one of the preceding claims.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.

FIG. 1 is a schematic diagram of one embodiment of a fuel supply system of the present invention.

Description of reference numerals:

1. a front storage tank; 2. a central storage tank; 3. a rear storage tank; 4. a first delivery conduit; 5. a second delivery conduit; 6. an air intake passage; 7. an engine; 8. a pressure reducer; 9. a negative overload resistant box; 10. a first oil supply line; 11. an electrically operated valve; 12. a second oil supply line; 13. a one-way valve; 14. an air release valve.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. 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.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

Example 1

The present embodiment provides a specific implementation of a fuel supply system, as shown in fig. 1, including: a front tank 1, a central tank 2 and a rear tank 3 arranged in this order in the fore-and-aft direction of the aircraft. The central storage tank 2 is respectively communicated with the front storage tank 1 and the rear storage tank 3 through conveying pipelines, wherein the front storage tank 1 is communicated with the middle storage tank through a first conveying pipeline 4, and the rear storage tank 3 is communicated with the central storage tank 2 through a second conveying pipeline 5. In addition, as an alternative embodiment, the front tank 1 and the rear tank 3 may be replaced with other side tanks.

As shown in fig. 1, one end of the first transfer pipe 4 communicates with the bottom outlet of the front tank 1, and the other end of the first transfer pipe 4 communicates with the top inlet of the central tank 2. One end of the second conveying pipeline 5 is communicated with the bottom outlet of the rear storage tank 3, and the other end of the second conveying pipeline 5 is communicated with the top inlet of the central storage tank 2. An air inlet channel 6 is communicated with the front storage tank 1 and the rear storage tank 3, pressure gas is suitable to be introduced into the side storage tank through the air inlet channel 6, and the fuel oil in the side storage tank is converged towards the center storage tank 2 through the pressure gas. So that when fuel is supplied, the fuel in the front tank 1 and the rear tank 3 is consumed first, keeping the central tank 2 full, and thus maintaining the centre of gravity of the aircraft stable.

As shown in fig. 1, the intake passages 6 of the front tank 1 and the rear tank 3 are communicated to equalize the gas pressures for driving the fuel in the front tank 1 and the rear tank 3, so that the fuel in the front tank 1 and the rear tank 3 is automatically balanced, and the use of an active regulation system is reduced. One end of the air inlet channel 6 is communicated with a low-pressure compressor of an engine 7 of the aircraft. In addition, as an alternative embodiment, the air intake passage 6 may also be in communication with a blast of air introduced at the rear end of the fan, for supplying pressurized air to the front tank 1 and the rear tank 3. The gas temperature at the position of the engine 7 is low, and the temperature requirement of the supercharged gas can be met.

The air inlet channel 6 is provided with a pressure reducer 8 which is used for controlling the pressure of air entering the front storage tank 1 and the rear storage tank 3 so as to meet the requirement of the inlet pressure of the fuel pump.

It should be noted that: the low pressure compressor is the first compressor to compress the gas stream to a low exit pressure in a two or three spool gas turbine engine 7. The engine 7 includes, from front to rear: the device comprises an air inlet channel, a fan, a low-pressure compressor, a medium-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine, a tail pipe and a spray pipe. The fan is connected with the low-pressure compressor and the low-pressure turbine. The power of the rotation of the fan: the air compressed by the compressor is combusted in the combustion chamber to generate gas, the gas is expanded in the turbine, and the heat energy is converted into mechanical energy to drive the turbine to rotate so as to drive the fan to rotate and generate thrust.

As shown in fig. 1, an anti-negative-overload tank 9 is provided below the central tank 2, and the anti-negative-overload tank 9 communicates with an oil inlet of the engine 7 through a first oil supply line 10. At the outlet end of the anti-negative-overload tank 9, an electric valve 11 is provided on the first fuel supply line 10, and the electric valve 11 may be embodied as a solenoid valve, and fuel can be supplied to the engine 7 by opening the solenoid valve.

As shown in fig. 1, the outlet of the central tank 2 communicates with an oil inlet of an engine 7 of the aircraft, and in particular, the central tank 2 communicates with the first oil supply line 10 through a second oil supply line 12, and the second oil supply line 12 is provided with a check valve 13 that opens toward the first oil supply line 10. When the fuel in the central storage tank 2 is sufficient, the fuel can be directly supplied to the engine 7 through the central storage tank 2; when the fuel in the central reservoir 2 is insufficient, or when the aircraft is in maneuver (e.g. high attitude flight) and the engine 7 is in transition (e.g. deceleration) operation, the electric valve 11 of the anti-negative-overload tank 9 is opened, and fuel can be supplied to the engine 7 through the anti-negative-overload tank 9.

The top of the anti-negative overload box 9 is provided with an air release valve 14, and when the pressure of bubbles generated in the anti-negative overload box 9 is large, the air can be discharged through the air release valve 14. The volume V of the anti-negative overload tank 9 can be designed as required, specifically, determined according to the negative overload working time t, the fuel flow q and the fuel density ρ, and V = t.q/ρ.

The fuel filling process of the fuel supply system provided by the embodiment is as follows: when a plurality of storage tanks are refueled on the ground, the central storage tank 2 is refueled respectively to the front storage tank 1, the rear storage tank 3 and the anti-negative-overload tank 9, and air is discharged through the lead-out passage.

The fuel supply system provided by the embodiment has the advantages of simple structure and clear principle, does not need any maintenance after being installed, and is suitable for the negative overload fuel supply requirement of an aircraft.

Example 2

This embodiment provides a specific implementation of an aircraft, including: an engine 7 and the fuel supply system described in embodiment 1, wherein a fuel supply line of the fuel supply system is communicated with a fuel inlet of the engine 7.

It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are intended to be within the scope of the invention.

Claims

1. A fuel supply system, comprising: the device comprises a central storage tank (2) and at least two side storage tanks which are respectively communicated with the central storage tank (2), wherein the central storage tank (2) and the side storage tanks are respectively communicated through a conveying pipeline, one end of the conveying pipeline is communicated with a bottom outlet of each side storage tank, and the other end of the conveying pipeline is communicated with a top inlet of the central storage tank (2);

the outlet of the central storage tank (2) is suitable for being communicated with an oil inlet of an engine (7) of an aircraft, a negative overload resisting tank (9) is arranged below the central storage tank (2), and the negative overload resisting tank (9) is communicated with the oil inlet of the engine (7) through a first oil supply pipeline (10); the top of the negative overload resistant box (9) is provided with an air escape valve (14);

the outlet end of the anti-negative overload tank (9) is provided with an electric valve (11) on the first oil supply pipeline (10), the central storage tank (2) is communicated with the first oil supply pipeline (10) through a second oil supply pipeline (12) after the electric valve (11), and the second oil supply pipeline (12) is provided with a one-way valve (13) communicated towards the first oil supply pipeline (10);

each side storage tank is communicated with an air inlet channel (6), pressure gas is suitable to be introduced into the side storage tanks through the air inlet channels (6), and the fuel oil in the side storage tanks is converged towards the center storage tank (2) through the pressure gas.

2. The fuel supply system according to claim 1, wherein the side tank comprises: the front storage tank (1), the central storage tank (2) and the rear storage tank (3) are sequentially arranged along the front-rear direction.

3. A fuel supply system according to claim 1, characterized in that a plurality of said side tanks have their intake passages (6) communicating, one end of said intake passages (6) being adapted to communicate with the rear end of a low-pressure compressor or fan of an engine (7) of an aircraft.

4. A fuel supply system according to claim 3, characterized in that a pressure reducer (8) is provided on the intake passage (6).

5. An aircraft comprising a fuel supply system as claimed in any one of claims 1 to 4.