阅读说明：本技术 一种适用于飞机的储油系统以及该系统的应急放油方法 (Oil storage system suitable for airplane and emergency oil discharge method of system ) 是由 朱德轩 龚昊 张霄宇 徐铭浩 葛锐 卞刚 于 2020-07-07 设计创作，主要内容包括：本发明涉及一种适用于飞机的储油系统以及该系统的应急放油方法。根据本发明将中央翼油箱和机翼油箱物理隔离的隔离壁的特定高度上设有机翼油箱应急放油隔离阀,在需要进行应急放油的情况下,燃油可以借助重力作用自动从该机翼油箱应急放油隔离阀流入中央翼油箱；此外,机翼油箱应急放油隔离阀还可以用作自动平衡燃油在中央翼油箱、机翼油箱的分配量。(The invention relates to an oil storage system suitable for an airplane and an emergency oil discharge method of the system. According to the invention, the wing oil tank emergency oil drainage isolation valve is arranged at a specific height of the isolation wall which physically isolates the central wing oil tank from the wing oil tank, and fuel oil can automatically flow into the central wing oil tank from the wing oil tank emergency oil drainage isolation valve under the action of gravity under the condition of emergency oil drainage; in addition, the wing oil tank emergency oil discharge isolation valve can also be used for automatically balancing the distribution amount of fuel oil in the central wing oil tank and the wing oil tank.)

1. An oil storage system adapted for use in an aircraft, the oil storage system comprising:

a center wing tank located within a fuselage of the aircraft;

the wing oil tanks are arranged in the wings of the airplane, are respectively positioned on two sides of the central wing oil tank, and are respectively physically isolated from the central wing oil tank through isolation walls; and

an emergency bleed line communicable with the center wing tank through a center wing tank emergency bleed isolation valve and configured to enable fuel within the center wing tank to be discharged out of the aircraft when the center wing tank bleed isolation valve is open,

wherein the partition wall is provided with a wing oil tank emergency oil drainage isolation valve which is in a normally closed position and is configured such that when the wing oil tank emergency oil drainage isolation valve is opened, at least part of the fuel oil of the wing oil tank can flow into the central wing oil tank under the action of gravity.

2. The fuel storage system of claim 1, wherein the height of the wing tank emergency drain isolation valve is set such that when the fuel level in the wing fuel is level with the wing tank emergency drain isolation valve, the amount of fuel in the wing tank is not less than the reserve fuel amount.

3. The fuel storage system according to claim 1 or 2, wherein the aircraft is provided with a fuel supply line connecting an on-wing engine and the center wing fuel tank, the fuel storage system further comprising at least one first fuel supply pump located at the bottom of the center wing fuel tank for pumping fuel to the emergency relief line or the fuel supply line.

4. The fuel storage system of claim 3, wherein said fuel supply line further includes at least a second fuel supply pump for pressurizing fuel in said fuel supply line, said second fuel supply pump being located on a line downstream of said first fuel supply pump.

5. The oil storage system of claim 1, wherein the wing tank emergency oil drain isolation valve is provided with two driving motors capable of independently driving the wing tank emergency oil drain isolation valve to act respectively.

6. The oil storage system of claim 1, wherein an outlet end of the emergency relief pipeline is provided with a shut-off valve.

7. The oil storage system of claim 1, wherein the wing tank emergency drain isolation valve is a one-way valve.

8. The oil storage system of claim 1, further comprising a control and calculation unit configured for calculating, controlling an emergency relief amount of the oil storage system.

9. An emergency oil drain method for an oil storage system according to any one of claims 1-8, characterized in that the emergency oil drain method comprises the steps of:

inputting the target weight of the airplane after oil drainage is finished on an input interface of a control and calculation unit of the oil storage system;

the control and calculation unit calculates the emergency oil discharge amount W _ Jettison;

when the calculated emergency oil discharge amount W _ Jettison is smaller than the oil storage amount of the central wing oil tank, the emergency oil discharge isolation valves of the wing oil tanks are kept in a closed state, and the emergency oil discharge isolation valves of the central wing oil tank and a cut-off valve in an emergency oil discharge pipeline are opened;

and when the calculated emergency oil drainage quantity W _ Jettison exceeds the oil storage quantity of the central wing oil tank, opening the emergency oil drainage isolation valve of the wing oil tank, the emergency oil drainage isolation valve of the central wing and a cut-off valve in an oil drainage pipeline.

10. The emergency oil drain method of claim 9, wherein the center wing tank emergency oil drain isolation valve and the shut-off valve are opened when the calculated emergency oil drain amount exceeds the center wing tank oil storage amount, and the wing tank emergency oil drain isolation valve is opened when the center wing tank oil storage amount reaches a preset value, wherein the preset value is a minimum fuel amount of the center wing tank.

11. The emergency oil drain method according to claim 9 or 10, wherein the emergency oil drain amount W _ Jettison is:

W_Jettison＝W_Aircraft-W_Target-W_Engine，

wherein W _ Aircraft is the total weight of the Aircraft at the current position; w _ Target is the Target gross weight of the aircraft, and W _ Engine is the amount of fuel consumed by the aircraft to fly from the current location to the Target aircraft location.

12. An aircraft, characterized in that the aircraft has an oil storage system according to any one of claims 1-8.

Technical Field

The invention relates to a fuel management system of a civil transport aircraft, in particular to an oil storage system suitable for an aircraft and an emergency oil discharge method of the system.

Background

An emergency oil discharge system is usually arranged on a large civil aircraft, so that rapid aerial oil discharge can be realized in an aerial emergency, and the aircraft can have enough re-flight climbing capacity specified in the items 25.119 and 25.121(d) even under extreme conditions that the aircraft breaks down when taking off, and the like, so that the requirement on climbing capacity during emergency return landing is met.

The design of the emergency oil drainage system can be basically divided into two categories: independent design and high integration design. Both types of oil drainage to the centre wing tanks is achieved by means of an override/transfer pump located in the centre wing tank, the difference between them being the way in which the wing tanks are drained.

The independent emergency oil discharge system is provided with a special emergency oil discharge pump arranged in each wing oil tank. In the case of oil drainage, the override pump in the central wing oil tank and the emergency oil drainage pump in the wing oil tank are respectively used for pumping fuel of the central wing oil tank and the wing oil tank so as to reduce the total weight of the airplane. However, the addition of a conventional type emergency oil drain pump and the associated accessory equipment such as the required mating brackets, power supply control and the like can add at least 15Kg of aircraft load. Obviously, this would result in unnecessary fuel consumption for the aircraft.

The high-integration emergency oil discharge system is not provided with an independent emergency oil discharge pump, in the system, an emergency oil discharge pipeline and an oil supply pipeline in a wing oil tank are shared pipelines, and the required pump oil pressure of the emergency oil discharge pipeline is provided by the oil supply pump on the oil supply pipeline. For this type of oil drain system, there are the following problems:

1) because the oil supply pipeline and the emergency oil discharge pipeline are partially shared, the oil supply system and the emergency oil discharge system need to ensure that oil discharge and oil supply performances can be balanced under various failure modes, so that the matching difficulty of the oil supply system and the emergency oil discharge system can be increased;

2) because the wing oil tank supply pump is usually arranged at the lowest point of the oil collecting tank, emergency oil drainage of the wing oil tank cannot be interrupted, and the risk of excessive oil drainage exists.

Disclosure of Invention

In view of the above-mentioned situation of the fuel system according to the prior art, it is an object of the present invention to provide a fuel storage system which is simple to operate and does not require the provision of an emergency relief pump for the wing fuel tank.

This object is achieved by the following form of the invention of an oil storage system. The oil storage system suitable for the airplane comprises a central wing oil tank, a wing oil tank and an emergency oil discharge pipeline. Wherein the center wing fuel tank is located within a fuselage of the aircraft. The wing oil tanks are arranged in the wings of the airplane, are respectively positioned at two sides of the central wing oil tank and are respectively physically isolated from the central wing oil tank through isolation walls. The emergency drain line is capable of communicating with the center wing tank through a center wing tank drain isolation valve and is configured to enable fuel within the center wing tank to be discharged out of the aircraft when the center wing tank drain isolation valve is open.

Wherein the partition wall is provided with a wing oil tank emergency oil drainage isolation valve which is in a normally closed position and is configured such that when the wing oil tank emergency oil drainage isolation valve is opened, at least part of the fuel oil of the wing oil tank can flow into the central wing oil tank under the action of gravity.

The invention utilizes the characteristic that the wing oil tank is higher than the central wing oil tank, and sets the emergency oil drainage isolation valve of the wing oil tank at the specific height of the isolation wall between the central wing oil tank and the wing oil tank. Under the condition that emergency oil drainage is needed, an operator can open the emergency oil drainage isolation valve of the wing oil tank to enable fuel oil to automatically flow into the central wing oil tank; furthermore, according to the distribution condition of the fuel oil in the wing fuel tank and the central wing fuel tank, an operator can also adaptively set the opening time of the emergency fuel drain valve of the wing fuel tank, so that the fuel oil of the airplane is relatively uniformly dispersed in each fuel tank in the flying process, and the flying of the airplane is facilitated.

According to a preferred embodiment of the invention, the height of the wing tank emergency drain isolation valve is set such that when the fuel level in the wing fuel is level with the wing tank emergency drain isolation valve, the amount of fuel in the wing tank is not less than the reserve fuel amount. After the emergency oil drain isolation valve of the wing oil tank is set to the height, the oil storage system can ensure that enough airplane can be ensured to land on a standby airport under any accident condition.

According to a preferred embodiment of the invention, the aircraft is provided with a fuel supply line connecting the engines on the wings and the centre wing tank, and the fuel storage system further comprises at least one first fuel supply pump located at the bottom of the centre wing tank for pressure-feeding fuel to the emergency relief line or the fuel supply line. The first oil supply pump arranged near the inlet of the pipeline system in the central wing oil tank does not bring troubles in the aspect of cross-linking to the design of an oil supply pipeline and an emergency oil drain pipeline, and can provide fuel oil with certain pressure for the two pipeline systems at the same time.

According to a preferred embodiment of the present invention, the fuel supply line further includes at least one second fuel supply pump for pressurizing fuel in the fuel supply line, and the second fuel supply pump is located on a downstream line of the first fuel supply pump.

According to a preferred embodiment of the invention, the wing oil tank emergency oil drainage isolation valve is provided with two driving motors which can respectively and independently drive the wing oil tank emergency oil drainage isolation valve to act. The emergency oil drain isolation valve of the wing oil tank adopts a double-motor design, so that the situation that the isolation valve is blocked at an opening position due to motor faults can be avoided, and the fuel oil jumping between unexpected oil tanks is avoided.

According to a preferred embodiment of the invention, the outlet end of the emergency relief pipeline is provided with a shut-off valve.

According to a preferred embodiment of the invention, the wing oil tank emergency oil drain isolation valve is a one-way valve.

According to a preferred embodiment of the invention, the oil storage system further comprises a control and calculation unit configured for calculating, controlling the emergency relief amount of the oil storage system.

The invention further relates to an aircraft with any one of the oil storage systems and an emergency oil discharge method for any one of the oil storage systems. The emergency oil drainage method comprises the following steps:

inputting the target weight of the airplane after oil drainage is finished on an input interface of a control and calculation unit of the oil storage system;

the control and calculation unit calculates the emergency oil discharge amount W _ Jettison;

when the calculated emergency oil discharge amount W _ Jettison is smaller than the oil storage amount of the central wing oil tank, the emergency oil discharge isolation valves of the wing oil tanks are kept in a closed state, and the emergency oil discharge isolation valves of the central wing oil tank and a cut-off valve in an emergency oil discharge pipeline are opened;

and when the calculated emergency oil drainage quantity W _ Jettison exceeds the oil storage quantity of the central wing oil tank, opening the emergency oil drainage isolation valve of the wing oil tank, the emergency oil drainage isolation valve of the central wing and a cut-off valve in an oil drainage pipeline.

According to a preferred embodiment of the invention, the centre wing tank emergency drain isolation valve and the shut-off valve are opened when the calculated emergency drain volume exceeds the reserve volume of the centre wing tank, and the wing tank emergency drain isolation valve is opened when the reserve volume of the centre wing tank reaches a preset value, wherein the preset value is the minimum fuel volume of the centre wing tank.

According to a preferred embodiment of the present invention, the emergency oil release amount W _ Jettison is:

W_Jettison＝W_Aircraft-W_Target-W_Engine，

wherein W _ Aircraft is the total weight of the Aircraft at the current position; w _ Target is the Target gross weight of the aircraft, and W _ Engine is the amount of fuel consumed by the aircraft to fly from the current location to the Target aircraft location.

On the basis of the common general knowledge in the field, the preferred embodiments can be combined randomly to obtain the preferred examples of the invention.

The oil storage system of the aircraft has the following advantages:

1. the wing oil tank is not provided with an independent or shared emergency oil discharge system, so that the weight increase or the complex cross-linking with an oil supply system is avoided. When the emergency oil drainage is carried out, the emergency oil drainage isolation valve of the wing oil tank is opened, so that fuel oil in the wing oil tank flows into the central wing oil tank under the action of gravity, and the oil drainage is facilitated.

2. The emergency oil drainage isolation valve is installed at a proper height, so that the situation that the emergency oil drainage cannot be stopped is ensured, the wing oil tank can retain enough fuel oil to safely land, and the risk of excessive oil drainage is avoided.

3. The system can carry out emergency oil discharge system intelligent management according to the total fuel quantity, fuel distribution and target oil discharge quantity on the aircraft, and reduces oil discharge time on the premise of avoiding excessive pressure bearing of the central wing oil tank.

Drawings

For a better understanding of the above and other objects, features, advantages and functions of the present invention, reference should be made to the preferred embodiments illustrated in the accompanying drawings. Like reference numerals in the drawings refer to like parts. It will be appreciated by persons skilled in the art that the drawings are intended to illustrate preferred embodiments of the invention without any limiting effect on the scope of the invention, and that the various components in the drawings are not drawn to scale.

FIG. 1 is a block diagram of an oil storage system according to a preferred embodiment of the present invention;

FIG. 2 is an enlarged schematic view of the left half of the reservoir system;

fig. 3 is a flow chart of an emergency oil discharge control of the oil storage system shown in fig. 1.

Description of reference numerals:

center wing tank: 10; wing oil tank: 12. 12';

a partition wall: 11; emergent oil drain isolating valve of wing oil tank: 13;

an oil discharge pipeline: 14; emergent oil drain isolating valve of central wing oil tank: 15;

an oil supply pipeline: 16; a first oil supply pump: 17;

an engine: 18; a second oil supply pump: 19;

emergency oil nozzle release: 20; emergent oil drain trip valve: 21;

a one-way valve: 22; oil supply cutoff: 23.

Detailed Description

The inventive concept of the present invention will be described in detail below with reference to the accompanying drawings. What has been described herein is merely a preferred embodiment in accordance with the present invention and other ways of practicing the invention will occur to those skilled in the art and are within the scope of the invention. In the following detailed description, directional terms, such as "upper", "lower", "inner", "outer", "longitudinal", "lateral", and the like, are used with reference to the orientation depicted in the accompanying drawings. Components of embodiments of the present invention can be positioned in a number of different orientations and the directional terminology is used for purposes of illustration and is in no way limiting.

Referring to fig. 1, an oil storage system according to a preferred embodiment of the present invention is shown generally from the top of an aircraft down. The oil storage system for the airplane comprises a central wing oil tank 10, wing oil tanks 12 and 12', an emergency oil discharge pipeline 14 and the like. Wherein the centre-wing tank 10 is located in the fuselage of the aircraft, in particular in the direction of the height of the aircraft, in the bottom position of the aircraft; in the length direction of the airplane, the airplane wing positioning device is positioned in parallel with wings on two sides of the airplane. The wing fuel tanks 12, 12' are arranged in the wings of the aircraft, are respectively positioned at the left side and the right side of the central wing fuel tank 10, and are respectively physically separated from the central wing fuel tank 10 through a separation wall 11.

With reference to fig. 2, fig. 2 shows the left-hand side structure of the oil reservoir substantially in the flight direction of the aircraft. As shown in fig. 2, the wing tanks 12, 12' are located higher on the aircraft than the central wing tank 10. And a normally closed wing oil tank emergency oil discharge isolating valve 13 is arranged on the isolating wall 11. The wing tank emergency drain isolation valves 13 are one-way valves that allow fuel to flow from the wing tanks 12, 12' into the center wing tank 10 in one direction. The wing tank emergency drain isolation valves 13 are configured such that with them open, at least some of the fuel in the wing tanks 12, 12' is able to flow by gravity into the centre wing tank 10. That is, the wing tank emergency drain isolation valve 13 is offset from the bottom of the dividing wall 11. In one embodiment, the amount of fuel in the wing tanks 12, 12 'is approximately 30%, 40%, etc. of the maximum load of the wing tanks 12, 12' when the fuel level is at the level of the wing tank emergency bleed isolation valve 13.

More preferably, the height of the wing tank emergency drain isolation valve 13 is set such that the amount of fuel in the wing tank 12, 12 'is not less than the reserve fuel amount when the fuel level in the wing fuel 12, 12' is level with the wing tank emergency drain isolation valve 13. The reserve fuel amount may be understood as the amount of fuel required for the aircraft to fly from the current location to the reserve airport when the target airport does not satisfy the reserve landing condition. After the emergency oil drain isolation valve 13 of the wing oil tank is set to the height, the oil storage system can ensure that fuel oil enough to ensure that the airplane lands on a standby airport can be stored under any accident condition.

It should be noted that the wing oil tank emergency oil drain isolation valve 13 disposed on the isolation wall 11 is an "emergency oil drain isolation valve", but the function of the valve is not only reflected in "emergency oil drain". In fact, according to the distribution of the fuel in the wing fuel tanks 12, 12' and the center wing fuel tank 10, the flight crew can also adaptively set the opening time and the opening duration of the wing fuel tank emergency oil drain isolation valve 13, so that the fuel of the airplane is relatively uniformly dispersed in each fuel tank during the flight process to facilitate the flight of the airplane.

With further reference to fig. 1, the emergency drain line 14 can be in communication with the center wing tank 10 through a center wing tank drain isolation valve 15. In the embodiment of FIG. 1, the emergency bleed line 14 communicates with both an emergency bleed nipple 20 on the left wing and an emergency bleed nipple 20 on the right wing. The inlet of the emergency relief line 14 is approximately in the middle of the center wing tank 10. Preferably, the center wing tank drain isolation valve 15 is set to 2. It will be appreciated that when all 2 centre wing tank emergency drain isolation valves 15 are open, fuel will be drained out of the aircraft more quickly. In addition, after 2 central wing oil tank emergency oil drain isolation valves 15 are arranged, the aircraft can drain oil by using another central wing oil tank emergency oil drain isolation valve 15 when the 1 central wing oil tank emergency oil drain isolation valve 15 breaks down.

For safety, the oil discharge line 14 is further provided with an emergency oil discharge cut-off valve 21 at a position adjacent to the emergency oil discharge nipple. The emergency oil drain cut valve 21 is preferably a one-way valve.

With further reference to fig. 1, the centre wing tank 10 is provided with 2 first supply pumps 17 in its bottom position, which first supply pumps 17 are Override pumps (Override pumps) which simultaneously function as emergency relief pumps (Jettison pumps). The first supply pump 17 pressurizes the fuel to a higher pressure and pumps the pressurized fuel to a supply line 16 communicating with the center wing tank 10 and the left wing engine 18, and a supply line 16 communicating with the center wing tank 10 and the right wing engine 18 to supply the engine 18 with power fuel. The first supply pump 17 is also used to pump fuel to the emergency drain line 14 when the centre wing tank emergency drain isolation valve 15 is opened.

The oil supply line 16 to the left wing engine 18 and the oil supply line 16 to the right wing engine 18 may be coupled by a crossover oil supply valve 24.

Downstream of the first feed pump 17, the feed line 16 is also provided with a second feed pump 19 which can be used to power the fuel in the feed line 16. Preferably, there are two second feed pumps 19, and the outlets of the two second feed pumps 19 are connected to the check valve 22 and then to the main line of the feed line 16. The second oil supply pump 19 is provided at a bottom position of the wing tanks 12, 12'.

According to the invention, the fuel in the centre wing tanks 10 can be pumped by the first supply pump 17 preferentially and the fuel in the wing tanks 12, 12' can be pumped by the second supply pump 19 after the fuel in the centre wing tanks 10 has been pumped to a lower content.

The supply line 16 is preferably provided with a fuel cut-off valve 23 at a position adjacent to the engine 18 so that the fuel cut-off valve 23 can be used to prevent fuel from flowing out when maintenance of the engine 18 is required.

In a preferred embodiment, the wing oil tank emergency oil discharge isolation valve 13 is provided with two driving motors which can respectively and independently drive the wing oil tank emergency oil discharge isolation valve 13 to act. The emergency oil drain isolation valve 13 of the wing oil tank adopts a double-motor design, so that the situation that the isolation valve 13 is blocked at an opening position due to motor faults can be avoided, and the fuel oil movement between unexpected oil tanks is avoided.

For the oil storage system, the required oil discharge amount can be automatically released in a mode as shown in fig. 3. Specifically, the emergency oil drainage method can be realized through the following steps:

inputting the Target weight W _ Target of the airplane after oil drainage is finished on an input interface of a control and calculation unit of the oil storage system;

the control and calculation unit calculates emergency oil discharge amount W _ Jettison, wherein the emergency oil discharge amount W _ Jettison is as follows:

W_Jettison＝W_Aircraft-W_Target-W_Engine，

wherein W _ Aircraft is the total weight of the Aircraft at the current position; w _ Target is the Target total weight of the airplane, and W _ Engine is the fuel quantity consumed by the airplane flying from the current position to the Target airplane site;

when the calculated emergency oil discharge amount W _ Jettison is smaller than the oil storage amount of the central wing oil tank 10, the wing oil tank emergency oil discharge isolation valves 13 are kept in a closed state, and the central wing oil tank emergency oil discharge isolation valves 15 and the cut-off valves in the emergency oil discharge pipelines 14 are opened;

when the calculated emergency oil discharge amount W _ Jettison exceeds the oil storage amount of the central wing oil tank 10, the wing oil tank emergency oil discharge isolation valves 13, the central wing emergency oil discharge isolation valves 15 and the cut-off valves 21 in the oil discharge pipelines 14 are opened.

Preferably, when the calculated emergency oil drain exceeds the oil storage capacity of the center wing oil tanks 10, the center wing oil tank emergency oil drain isolation valve 15 and the cut-off valve 21 are first opened, and the wing oil tank emergency oil drain isolation valves 13 are opened when the oil storage capacity of the center wing oil tanks 10 reaches a preset value, wherein the preset value is the minimum fuel oil amount of the center wing oil tanks 10. It is understood that the minimum fuel amount of the center wing tank 10 indicates a fuel amount for ensuring that the first feed pump 17 can be always submerged in fuel for safe operation in various attitudes where the aircraft is flying normally.

The scope of the invention is limited only by the claims. Persons of ordinary skill in the art, having benefit of the teachings of the present invention, will readily appreciate that alternative structures to the structures disclosed herein are possible alternative embodiments, and that combinations of the disclosed embodiments may be made to create new embodiments, which also fall within the scope of the appended claims.