A four-engine aircraft interactive bleed air system and its usage method

Abstract

This invention relates to the field of aircraft bleed air system technology, and particularly to an interactive bleed air system for a four-engine aircraft and its usage method. The interactive bleed air system includes, symmetrically arranged with respect to the fuselage, a right isolation valve (41), a right first bleed air interactive pipe (31), a right second bleed air interactive pipe (51), a right first one-way valve (11), a right second one-way valve (21), a right third one-way valve (61), and a right fourth one-way valve (71); and a left isolation valve (42), a left first bleed air interactive pipe (32), a left second bleed air interactive pipe (52), a left first one-way valve (12), a left second one-way valve (22), a left third one-way valve (62), and a left fourth one-way valve (72). The interactive bleed air system architecture of the present invention can directly improve the utilization of engine bleed air source under leakage failure, effectively solving the prominent safety problem caused by insufficient available bleed air volume after turboprop aircraft lose part of the bleed air source. In addition to the conventional bleed air main pipeline, the bleed air interactive pipeline and one-way valve are simple in structure and light in weight.

Description

Technical Field

[0001] This invention relates to the field of aircraft bleed air system technology, and in particular to an interactive bleed air system for a four-engine aircraft and its usage method. Background Technology

[0002] When a leak occurs in the bleed air duct of a four-engine aircraft, the corresponding side duct system and the corresponding bleed air source must be shut off to avoid the area safety risks caused by the bleed air leak. The conventional bleed air system architecture is to use cross valves to isolate independent left and right bleed air manifolds. The two bleed air manifolds correspond to the bleed air of the two engines respectively. If a leak occurs in one engine's bleed air system or on any part of one side's bleed air manifold, isolating the corresponding side's bleed air manifold will not affect the other side. However, the bleed air system of the engine that is not directly leaking will be passively shut down, thus directly reducing the engine's available bleed air volume by half. For turboprop aircraft with very limited available bleed air volume, the significant reduction in available bleed air volume will directly lead to reduced redundancy and performance degradation of the air conditioning system. For hot air anti-icing systems with high air consumption, it will reduce anti-icing capability and aircraft safety.

[0003] This invention proposes an interactive bleed air system for four-engine aircraft and its usage method, which can effectively solve the contradiction between the large bleed air demand of four-engine aircraft, especially turboprop aircraft, and the small amount of bleed air available in the engine. Summary of the Invention

[0004] The purpose of this invention is to address the limitations and shortcomings of existing conventional bleed air systems for four-engine aircraft by providing an interactive bleed air system and its usage method for four-engine aircraft, which effectively improves the utilization efficiency of bleed air energy from each engine on board.

[0005] The technical solution adopted in this invention is:

[0006] To achieve the above objectives, according to a first aspect of the present invention, a four-engine aircraft interactive bleed air system is provided, characterized in that the interactive bleed air system of the present invention is used in an aircraft symmetrically arranged with respect to the fuselage on the left and right sides: a left inner engine, a left outer engine, a left air conditioning system, a left anti-icing system, a right inner engine, a right outer engine, a right air conditioning system, and a right anti-icing system; the left inner engine, left outer engine, left air conditioning system, left anti-icing system, and the right inner engine, right outer engine, right air conditioning system, and right anti-icing system are respectively connected by a main pipeline and their respective branch pipelines;

[0007] The interactive air intake system includes a right isolation valve 41, a right first air intake interactive pipeline 31, a right second air intake interactive pipeline 51, a right first one-way valve 11, a right second one-way valve 21, a right third one-way valve 61, and a right fourth one-way valve 71, which are symmetrically arranged on the left and right sides of the fuselage.

[0008] Left partition valve 42, left first bleed air interaction pipeline 32, left second bleed air interaction pipeline 52, left first one-way valve 12, left second one-way valve 22, left third one-way valve 62, left fourth one-way valve 72;

[0009] One end of the right first bleed air interaction pipe 31 is connected to the right air conditioning system branch pipe, and the other end is connected to the main pipe. The connection position is set between the right inner engine, the right outer engine and the main pipe connection position; so as to realize that the right air conditioning system branch pipe is connected in parallel with the inner and outer bleed air main pipe sections. When the inner bleed air main pipe section leaks and cuts off the bleed air, the bleed air of the right outer engine is supplied to the right air conditioning system through the outer bleed air main pipe section and the right first bleed air interaction pipe 31.

[0010] One end of the right second bleed air interaction pipe 51 is connected to the right inner engine and main pipe connection position, and the other end is connected to the right anti-icing system branch pipe; so as to realize that the right anti-icing system branch pipe is connected in parallel with the inner and outer bleed air main pipe sections. When the outer bleed air main pipe section leaks and cuts off the bleed air, the bleed air of the right inner engine is supplied to the right air conditioning system through the inner bleed air main pipe section and the right second bleed air interaction pipe 51.

[0011] The right first one-way valve 11 is installed on the right air conditioning system branch pipe, located between the main pipe and the right first bleed air interaction pipe 31 and the right air conditioning system branch pipe; when the engine bleed air is supplied to the right air conditioning system through the right first bleed air interaction pipe 31, it prevents the bleed air from flowing back into the isolated inner bleed air main pipe section.

[0012] The right second one-way valve 21 is installed on the right first bleed air interaction pipe 31; when the engine bleed air supplies air to the right air conditioning system through the inner bleed air main pipe section, it prevents the bleed air from flowing back to the isolated outer bleed air main pipe section.

[0013] The right isolation valve 41 is installed on the main pipeline, located between the right first bleed air interaction pipeline 31 and the right second bleed air interaction pipeline 51; so as to realize the isolation valve to split the bleed air main pipe into two independent and separable parts, isolate the two generators and each downstream gas system, and avoid the complete failure of the bleed air system due to leakage; the isolation valve splits the bleed air main pipe into two independent and separable parts, isolate the two generators and each downstream gas system, and avoid the complete failure of the bleed air system due to leakage;

[0014] The right third one-way valve 61 is located on the main pipeline between the right outer engine and the right second bleed air interaction pipeline 51; when the engine bleed air supplies air to the right anti-icing system through the inner bleed air main pipeline and the right second bleed air interaction pipeline 51, it prevents the bleed air from flowing back to the isolated outer bleed air main pipeline.

[0015] The right fourth one-way valve 71 is installed on the right second bleed air interaction pipe 51; when the engine bleed air is supplied to the right anti-icing system through the outer bleed air main pipe section, it prevents the bleed air from flowing back into the isolated inner bleed air main pipe section.

[0016] In one possible embodiment, the connection relationship and position of the left partition valve 42, the left first bleed air interaction pipe 32, the left second bleed air interaction pipe 52, the left first one-way valve 12, the left second one-way valve 22, the left third one-way valve 62, and the left fourth one-way valve 72 are symmetrical to the right side.

[0017] In one possible embodiment, on the main pipeline, cross valves 8 are symmetrically positioned at the following locations: left inner engine, left outer engine, left air conditioning system, left anti-icing system, and right inner engine, right outer engine, right air conditioning system, and right anti-icing system. The section between the right partition valve 41 and left partition valve 42 on the left and right sides of the main pipeline and the cross valves 8 forms the inner bleed air main pipeline section; the section between the right partition valve 41 and the left anti-icing system, and the section between the left partition valve 42 and the right anti-icing system forms the outer bleed air main pipeline section.

[0018] According to a second aspect of the present invention, a method of using a four-engine aircraft interactive bleed air system is provided, wherein the above-described four-engine aircraft interactive bleed air system is characterized in that...

[0019] Under normal conditions, the cross valve 8 is closed to isolate the left and right main air intake pipes from each other; the right isolation valve 41 and the left isolation valve 42 are opened to connect the two main air intake pipe sections of the main air intake pipe, and the air intake is supplied to the downstream air conditioning system or anti-icing system by opening / closing the valves of the corresponding branches on the left and right sides.

[0020] When a leak occurs in the inner bleed air main section on either side, close the corresponding isolation valve 41 or 42 and the corresponding inner bleed air valve to cut off the leaking bleed air pipeline section. The external bleed air can be supplied to the downstream air conditioning system through the outer bleed air main section and the bleed air interaction pipeline 31 or 32. The air supply to the anti-icing system is not affected. At the same time, the one-way valve 11 or 12 on the inner bleed air main section and the one-way valve 71 or 72 on the bleed air interaction pipeline 51 or 52 prevent the external bleed air from entering the leaking inner bleed air main section.

[0021] When a leak occurs in any of the outer bleed air main pipe sections, the corresponding isolation valve 41 or 42 and the corresponding external bleed air valve are closed to cut off the leaking bleed air pipe section. The internal bleed air can be supplied to the downstream anti-icing system through the inner bleed air main pipe section and the bleed air interaction pipe 31 or 32. The air supply to the air conditioning system is not affected. At the same time, the one-way valve 61 or 62 on the outer bleed air main pipe section and the one-way valve 21 or 22 on the bleed air interaction pipe 31 or 32 prevent the internal bleed air from entering the leaking outer bleed air main pipe section.

[0022] When a leak occurs in the outer section of the bleed air main pipeline on one side, or when leaks occur in the outer sections of the bleed air main pipelines on both sides, the cross valve 8 is opened to connect the unleashed bleed air main pipeline sections while the corresponding isolation valve is closed, so as to make full use of the limited engine bleed air resources to supply the downstream system.

[0023] In one possible embodiment, an alarm will be issued when a leak is detected in the left and / or right bleed main pipe section.

[0024] In one possible embodiment, the right partition door 41 and the left partition door 42 can be controlled manually or automatically.

[0025] In one possible embodiment, each branch of the left inner engine, left outer engine, left air conditioning system, left anti-icing system, right inner engine, right outer engine, right air conditioning system, and right anti-icing system is also equipped with a partition valve.

[0026] According to a third aspect of the present invention, a four-engine aircraft is characterized by comprising the above-described four-engine aircraft interactive bleed air system.

[0027] Advantages of the present invention: The interactive bleed air system architecture of the present invention can directly improve the utilization of the engine bleed air source under leakage failure, effectively solve the prominent safety problem caused by insufficient available bleed air volume after turboprop aircraft lose part of the bleed air source. In addition to the conventional bleed air main pipeline, the bleed air interactive pipeline and one-way valve are simple in structure and light in weight. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the architecture of a four-engine aircraft interactive bleed air system according to the present invention.

[0029] in:

[0030] 11-Right first one-way valve; 12-Left first one-way valve; 21-Right second one-way valve; 22-Left second one-way valve; 31-Right first bleed air exchange pipeline; 32-Left first bleed air exchange pipeline; 41-Right isolation valve; 42-Left isolation valve; 51-Right second bleed air exchange pipeline; 52-Left second bleed air exchange pipeline; 61-Right third one-way valve; 62-Left third one-way valve; 71-Right fourth one-way valve; 72-Left fourth one-way valve. Detailed Implementation

[0031] The present invention will be further described below with reference to the accompanying drawings.

[0032] like Figure 1As shown, a four-engine aircraft interactive bleed air system is characterized in that the interactive bleed air system of the present invention is used in an aircraft with a left inner engine, a left outer engine, a left air conditioning system, a left anti-icing system, a right inner engine, a right outer engine, a right air conditioning system, and a right anti-icing system symmetrically arranged relative to the fuselage; the left inner engine, left outer engine, left air conditioning system, left anti-icing system and the right inner engine, right outer engine, right air conditioning system, and right anti-icing system are respectively connected through main pipelines and their respective branch pipelines;

[0033] The interactive air intake system includes a right isolation valve 41, a right first air intake interactive pipeline 31, a right second air intake interactive pipeline 51, a right first one-way valve 11, a right second one-way valve 21, a right third one-way valve 61, and a right fourth one-way valve 71, which are symmetrically arranged on the left and right sides of the fuselage.

[0034] Left partition valve 42, left first bleed air interaction pipeline 32, left second bleed air interaction pipeline 52, left first one-way valve 12, left second one-way valve 22, left third one-way valve 62, left fourth one-way valve 72;

[0035] One end of the right first bleed air interaction pipe 31 is connected to the right air conditioning system branch pipe, and the other end is connected to the main pipe. The connection position is set between the right inner engine, the right outer engine and the main pipe connection position; so as to realize that the right air conditioning system branch pipe is connected in parallel with the inner and outer bleed air main pipe sections. When the inner bleed air main pipe section leaks and cuts off the bleed air, the bleed air of the right outer engine is supplied to the right air conditioning system through the outer bleed air main pipe section and the right first bleed air interaction pipe 31.

[0036] One end of the right second bleed air interaction pipe 51 is connected to the right inner engine and main pipe connection position, and the other end is connected to the right anti-icing system branch pipe; so as to realize that the right anti-icing system branch pipe is connected in parallel with the inner and outer bleed air main pipe sections. When the outer bleed air main pipe section leaks and cuts off the bleed air, the bleed air of the right inner engine is supplied to the right air conditioning system through the inner bleed air main pipe section and the right second bleed air interaction pipe 51.

[0037] The right first one-way valve 11 is installed on the right air conditioning system branch pipe, located between the main pipe and the right first bleed air interaction pipe 31 and the right air conditioning system branch pipe; when the engine bleed air is supplied to the right air conditioning system through the right first bleed air interaction pipe 31, it prevents the bleed air from flowing back into the isolated inner bleed air main pipe section.

[0038] The right second one-way valve 21 is installed on the right first bleed air interaction pipe 31; when the engine bleed air supplies air to the right air conditioning system through the inner bleed air main pipe section, it prevents the bleed air from flowing back to the isolated outer bleed air main pipe section.

[0039] The right isolation valve 41 is installed on the main pipeline, located between the right first bleed air interaction pipeline 31 and the right second bleed air interaction pipeline 51; so as to realize the isolation valve to split the bleed air main pipe into two independent and separable parts, isolate the two generators and each downstream gas system, and avoid the complete failure of the bleed air system due to leakage; the isolation valve splits the bleed air main pipe into two independent and separable parts, isolate the two generators and each downstream gas system, and avoid the complete failure of the bleed air system due to leakage;

[0040] The right third one-way valve 61 is located on the main pipeline between the right outer engine and the right second bleed air interaction pipeline 51; when the engine bleed air supplies air to the right anti-icing system through the inner bleed air main pipeline and the right second bleed air interaction pipeline 51, it prevents the bleed air from flowing back to the isolated outer bleed air main pipeline.

[0041] The right fourth one-way valve 71 is installed on the right second bleed air interaction pipe 51; when the engine bleed air is supplied to the right anti-icing system through the outer bleed air main pipe section, the bleed air is prevented from flowing back to the isolated inner bleed air main pipe section.

[0042] The connection relationship and position setting of the left partition valve 42, the left first air venting interaction pipe 32, the left second air venting interaction pipe 52, the left first one-way valve 12, the left second one-way valve 22, the left third one-way valve 62, and the left fourth one-way valve 72 are symmetrical to the right side;

[0043] On the main pipeline, cross valves 8 are symmetrically positioned with the left inner engine, left outer engine, left air conditioning system, and left anti-icing system, and the right inner engine, right outer engine, right air conditioning system, and right anti-icing system. The inner bleed air main pipeline is located between the right partition valve 41 and the left partition valve 42 on both sides of the main pipeline and the cross valves 8; the outer bleed air main pipeline is located between the right partition valve 41 and the left anti-icing system, and between the left partition valve 42 and the right anti-icing system.

[0044] According to a second aspect of the present invention, a method of using a four-engine aircraft interactive bleed air system is provided, wherein the above-described four-engine aircraft interactive bleed air system is characterized in that...

[0045] Under normal conditions, the cross valve 8 is closed to isolate the left and right main air intake pipes from each other; the right isolation valve 41 and the left isolation valve 42 are opened to connect the two main air intake pipe sections of the main air intake pipe, and the air intake is supplied to the downstream air conditioning system or anti-icing system by opening / closing the valves of the corresponding branches on the left and right sides.

[0046] When a leak occurs in the inner bleed air main section on either side, close the corresponding isolation valve 41 or 42 and the corresponding inner bleed air valve to cut off the leaking bleed air pipeline section. The external bleed air can be supplied to the downstream air conditioning system through the outer bleed air main section and the bleed air interaction pipeline 31 or 32. The air supply to the anti-icing system is not affected. At the same time, the one-way valve 11 or 12 on the inner bleed air main section and the one-way valve 71 or 72 on the bleed air interaction pipeline 51 or 52 prevent the external bleed air from entering the leaking inner bleed air main section.

[0047] When a leak occurs in any of the outer bleed air main pipe sections, close the corresponding isolation valve 41 or 42 and the corresponding external bleed air valve to cut off the leaking bleed air pipe section. The internal bleed air can be supplied to the downstream anti-icing system through the left bleed air main pipe section and the bleed air interaction pipe 5. The air supply to the air conditioning system is not affected. At the same time, the one-way valve 61 or 62 on the outer bleed air main pipe section and the one-way valve 21 or 22 on the bleed air interaction pipe 31 or 32 prevent the internal bleed air from entering the leaking outer bleed air main pipe section.

[0048] When a leak occurs in the outer section of the bleed air main pipeline on one side, or when leaks occur in the outer sections of the bleed air main pipelines on both sides, the cross valve 8 is opened to connect the unleashed bleed air main pipeline sections while the corresponding isolation valve is closed, so as to make full use of the limited engine bleed air resources to supply the downstream system.

[0049] An alarm will be triggered if a leak is detected in the left and / or right bleed air mains.

[0050] The right partition door 41 and the left partition door 42 can be controlled manually or automatically.

[0051] Each branch of the left inner engine, left outer engine, left air conditioning system, left anti-icing system, right inner engine, right outer engine, right air conditioning system, and right anti-icing system is also equipped with a partition door;

[0052] According to a third aspect of the present invention, a four-engine aircraft is characterized by comprising the above-described four-engine aircraft interactive bleed air system.

[0053] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications are also considered to be within the scope of protection of the present invention.

Claims

1. A four-engine aircraft interactive bleed air system, characterized in that, For an aircraft symmetrically arranged with respect to the fuselage, the left inner engine, left outer engine, left air conditioning system, left anti-icing system, right inner engine, right outer engine, right air conditioning system, and right anti-icing system are connected by main pipelines and their respective branch pipelines. The interactive air intake system includes a right isolation valve (41), a right first air intake interactive pipeline (31), a right second air intake interactive pipeline (51), a right first one-way valve (11), a right second one-way valve (21), a right third one-way valve (61), and a right fourth one-way valve (71) symmetrically arranged relative to the fuselage. Left partition valve (42), left first bleed air interaction pipeline (32), left second bleed air interaction pipeline (52), left first one-way valve (12), left second one-way valve (22), left third one-way valve (62), left fourth one-way valve (72); One end of the right first bleed air interaction pipe (31) is connected to the right air conditioning system branch pipe, and the other end is connected to the main pipe. The connection position is located between the left inner engine, the left outer engine and the main pipe connection position. One end of the right second bleed air interaction pipeline (51) is connected to the right inner engine and main pipeline connection position, and the other end is connected to the right anti-icing system branch pipeline; The right first one-way valve (11) is installed on the right air conditioning system branch pipe, located between the main pipe and the right first air venting interaction pipe (31) and the right air conditioning system branch pipe; The right second one-way valve (21) is disposed on the right first air intake interaction pipe (31); The right partition valve (41) is located on the main pipeline, between the right first bleed air interaction pipeline (31) and the right second bleed air interaction pipeline (51); The right third one-way valve (61) is located on the main pipeline, between the right external engine and the right second bleed air interaction pipeline (51); The right fourth one-way valve (71) is located on the right second air intake interaction pipe (51).

2. The four-engine aircraft interactive bleed air system according to claim 1, characterized in that, The connection relationship and position setting of the left partition valve (42), the left first bleed air interaction pipeline (32), the left second bleed air interaction pipeline (52), the left first one-way valve (12), the left second one-way valve (22), the left third one-way valve (62), and the left fourth one-way valve (72) are symmetrical to the right side.

3. The four-engine aircraft interactive bleed air system according to claim 2, characterized in that, On the main pipeline, cross valves (8) are symmetrically positioned at the following locations: left inner engine, left outer engine, left air conditioning system, left anti-icing system, right inner engine, right outer engine, right air conditioning system, right anti-icing system.

4. A method of using a four-engine aircraft interactive bleed air system, employing the four-engine aircraft interactive bleed air system described in any one of claims 1-3, characterized in that, Under normal conditions, the cross valve (8) is closed to isolate the main air intake pipes on the left and right sides from each other; the right isolation valve (41) and the left isolation valve (42) are opened to connect the two main air intake pipe sections of the main air intake pipe, and the air intake system or anti-icing system is supplied with air by opening / closing the valves of the corresponding branches on the left and right sides. When a leak occurs in the inner bleed main pipe section on any side, close the corresponding right isolation valve (41) or left isolation valve (42) and the corresponding inner bleed valve to cut off the leaking bleed pipe section. The external bleed air can be supplied to the downstream air conditioning system through the outer bleed main pipe section and the bleed interaction pipe (31) or (32). The anti-icing system's gas supply is not affected. At the same time, the right first one-way valve (11) or left first one-way valve (12) on the inner bleed main pipe section and the right fourth one-way valve (71) or left fourth one-way valve (72) on the right second bleed interaction pipe (51) or left second bleed interaction pipe (52) prevent the external bleed air from entering the leaking inner bleed main pipe section. When a leak occurs in any of the outer bleed main pipe sections, close the corresponding right isolation valve (41) or left isolation valve (42) and the corresponding external bleed valve to cut off the leaking bleed pipe section. The internal bleed air can be supplied to the downstream anti-icing system through the inner bleed main pipe section and the right first bleed interaction pipe (31) or left first bleed interaction pipe (32). The air supply to the air conditioning system is not affected. At the same time, the right third one-way valve (61) or left third one-way valve (62) on the outer bleed main pipe section and the right second one-way valve (21) or left second one-way valve (22) on the right first bleed interaction pipe (31) or left first bleed interaction pipe (32) prevent the internal bleed air from entering the leaking outer bleed main pipe section. At the same time, when a leak occurs in the outer section of the bleed air main pipeline on one side, or when a leak occurs in the outer sections of the bleed air main pipelines on both sides, while closing the corresponding right isolation valve (41) or left isolation valve (42), the cross valve (8) is opened to connect the various bleed air main pipelines that have not leaked, so as to make full use of the limited engine bleed air resources to provide them to the downstream system.

5. The method of using a four-engine aircraft interactive bleed air system according to claim 4, characterized in that, The system will issue an alarm if a leak occurs in the left and / or right bleed air mains.

6. The method of using a four-engine aircraft interactive bleed air system according to claim 4, characterized in that, The right partition door (41) and the left partition door (42) can be controlled manually or automatically.

7. The method of using a four-engine aircraft interactive bleed air system according to claim 4, characterized in that, Each branch of the left inner engine, left outer engine, left air conditioning system, left anti-icing system, right inner engine, right outer engine, right air conditioning system, and right anti-icing system is also equipped with a partition valve.

8. A four-engine aircraft, characterized in that, Includes a four-engine aircraft interactive bleed air system as described in any one of claims 1-3.

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