Parallel combination engine starting and fuel oil supply system cross-linking structure and control method

Abstract

The invention particularly relates to a parallel combination engine starting and fuel oil supply system cross-linking structure and a control method, and the parallel combination engine starting and fuel oil supply system cross-linking structure comprises an air turbine, an aircraft accessory cartridge receiver, an engine transmission system and a stamping fuel oil pump; an air turbine shaft is connected with an aircraft accessory casing, a starting clutch is arranged between the air turbine shaft and the aircraft accessory casing, the aircraft accessory casing is connected with an engine transmission system, and the engine transmission system is connected with a turbine engine; an air turbine shaft is connected with a ramjet fuel pump, an oil supply clutch is arranged between the air turbine shaft and the ramjet fuel pump, and the ramjet fuel pump is used for The air turbine is connected with an airplane auxiliary power system through an air entraining pipeline; an auxiliary air entraining valve is arranged on the air entraining pipeline; the air turbine is connected with the turbine engine fan rear flow channel through an air entraining pipeline, and a fan air entraining valve is arranged on the air entraining pipeline. The air turbine is connected with the stamping air inlet channel through an air entraining pipeline, and a stamping air entraining valve is arranged on the air entraining pipeline.

Description

Technical Field

[0001] This application belongs to the technical field of the design of the starting and fuel supply of a parallel combined engine, and specifically relates to a cross-linked structure and a control method for the starting and fuel supply system of a parallel combined engine. Background Art

[0002] Currently, a combined engine is usually adopted to achieve the wide airspace and wide speed range flight of an aircraft. The parallel combined engine is composed of a turbine engine and a ramjet engine. Among them, the turbine engine requires a starting system to realize the starting function of the turbine engine, and the ramjet engine requires a fuel supply system to realize the continuous and stable supply of fuel.

[0003] At present, most of the starting systems of turbine engines supply air to the turbine starter by the aircraft auxiliary power system, and then the turbine starter provides shaft power to the turbine engine through the aircraft accessory gearbox and the engine transmission system to drive the turbine engine to start, as Figure 1 shown. Most of the fuel supply systems of ramjet engines draw air from the ramjet inlet to drive the ram air turbine pump, and then the ram air turbine pump drives the ram fuel pump to supply fuel to the ramjet engine, as Figure 2 shown.

[0004] The starting system of the turbine engine and the fuel supply system of the ramjet engine are independent of each other, and there is a redundancy of components with the same function, resulting in a large number of components and heavy weight of the parallel combined engine, and great difficulty in thermal protection under high Mach number working conditions.

[0005] In view of the existence of the above technical defects, this application is proposed. Summary of the Invention

[0006] The purpose of this application is to provide a cross-linked structure and a control method for the starting and fuel supply system of a parallel combined engine, to integrally design the functions of the accessory system of the parallel combined engine, reduce the redundancy of components with the same function in the starting system of the turbine engine and the fuel supply system of the ramjet engine, reduce the number and weight of components, and reduce the difficulty of thermal protection under high Mach number working conditions.

[0007] The technical solution of this application is as follows:

[0008] On the one hand, a cross-linked structure for the starting and fuel supply system of a parallel combined engine is provided, including an air turbine, an aircraft accessory gearbox, an engine transmission system, and a ram fuel pump;

[0009] The air turbine shaft is connected to the aircraft accessory gearbox, and a starting clutch is arranged therebetween. The aircraft accessory gearbox shaft is connected to the engine transmission system, and the engine transmission system shaft is connected to the turbine engine;

[0010] The air turbine shaft is connected to the ramjet fuel pump, and a fuel supply clutch is arranged therebetween. The ramjet fuel pump is used to supply fuel to the ramjet engine;

[0011] The air turbine is connected to the aircraft auxiliary power system through an air duct. An auxiliary air intake valve is arranged on the air duct;

[0012] The air turbine is connected to the rear flow path of the turbine engine fan through an air duct. A fan air intake valve is arranged on the air duct;

[0013] The air turbine is connected to the ramjet inlet through an air duct. A ramjet air intake valve is arranged on the air duct.

[0014] According to at least one embodiment of the present application, in the cross-linked structure of the parallel combined engine starting and fuel supply system described above, the starting clutch and the fuel supply clutch are connected to the aircraft control system, and the starting clutch and the fuel supply clutch can be controlled to engage and disengage through the aircraft control system.

[0015] According to at least one embodiment of the present application, in the cross-linked structure of the parallel combined engine starting and fuel supply system described above, the auxiliary air intake valve, the fan air intake valve, and the ramjet air intake valve are connected to the aircraft control system, and the auxiliary air intake valve, the fan air intake valve, and the ramjet air intake valve can be controlled to open and close through the aircraft control system.

[0016] According to at least one embodiment of the present application, the cross-linked structure of the parallel combined engine starting and fuel supply system described above has:

[0017] Turbine engine starting working state: the starting clutch is engaged, the fuel supply clutch is disengaged, the auxiliary air intake valve is open, the fan air intake valve and the ramjet air intake valve are closed. The aircraft auxiliary power system provides high-temperature and high-pressure gas to the air turbine through the air duct. The air turbine expands and does work, and outputs shaft power to the turbine engine through the aircraft accessory gearbox and the engine transmission system, driving the connected turbine engine to start;

[0018] Turbine engine single and powerless working state: the starting clutch and the fuel supply clutch are disengaged, and the auxiliary air intake valve, the fan air intake valve, and the ramjet air intake valve are closed;

[0019] Turbine-ramjet combined working state: the starting clutch is disengaged, the fuel supply clutch is engaged, the auxiliary air intake valve is closed, the fan air intake valve is open, the ramjet air intake valve is closed. The rear flow path of the turbine engine fan provides high-temperature and high-pressure gas to the air turbine through the air duct. The air turbine expands and does work, and outputs shaft power to the ramjet fuel pump, driving the ramjet fuel pump to supply fuel to the ramjet engine;

[0020] Ramjet engine operating alone: The starting clutch is disengaged, the fuel supply clutch is engaged, the auxiliary air bleed valve is closed, the fan air bleed valve is closed, the ram air bleed valve is open, and the ram inlet duct supplies high-temperature and high-pressure gas to the air turbine through the air duct. The air turbine expands and does work, outputting shaft power to the ram fuel pump, driving the ram fuel pump, and supplying fuel to the ramjet engine.

[0021] On the other hand, a control method for the cross-linked structure of the parallel combined engine starting and fuel supply system is provided, which is used to control the above-mentioned cross-linked structure of the parallel combined engine starting and fuel supply system, including:

[0022] When starting the turbofan engine on the ground, set the cross-linked structure of the parallel combined engine starting and fuel supply system to be in the working state of starting the turbofan engine;

[0023] When the turbofan engine operates alone, set the cross-linked structure of the parallel combined engine starting and fuel supply system to be in the state of the turbofan engine operating alone and without power;

[0024] When the turbofan engine and the ramjet engine work together, set the cross-linked structure of the parallel combined engine starting and fuel supply system to be in the working state of the turbofan-ramjet engine working together;

[0025] When the ramjet engine operates alone, set the cross-linked structure of the parallel combined engine starting and fuel supply system to be in the working state of the ramjet engine operating alone;

[0026] When performing a powerless glide, set the cross-linked structure of the parallel combined engine starting and fuel supply system to be in the state of the turbofan engine operating alone and without power;

[0027] When starting the turbofan engine in the air, set the cross-linked structure of the parallel combined engine starting and fuel supply system to be in the working state of starting the turbofan engine.

[0028] The present application has at least the following beneficial technical effects:

[0029] A cross-linked structure and a control method for the parallel combined engine starting and fuel supply system are provided. The functional integration design of the parallel combined engine accessory system is carried out, the air turbine is shared, the redundancy of the accessory functions of the turbofan engine starting system and the ramjet engine fuel supply system is reduced, the number and weight of the accessories are reduced, and the difficulty of thermal protection under high Mach number conditions is reduced. Moreover, only by controlling a limited number of clutches and valves, it is possible to control the switching between the working state of starting the turbofan engine, the state of the turbofan engine operating alone and without power, the state of the turbofan-ramjet engine working together, and the state of the ramjet engine operating alone, so as to adapt to various working states of the parallel combined engine. Description of the Drawings

[0030] Figure 1 is a schematic diagram of an existing parallel combined engine turboengine starting system;

[0031] Figure 2 is a schematic diagram of an existing parallel combined engine ramjet fuel supply system;

[0032] Figure 3 is a schematic diagram of the cross - linked structure of the starting and fuel supply systems of a parallel combined engine provided in an embodiment of the present application;

[0033] Figure 4 is a schematic diagram of the cross - linked structure of the starting and fuel supply systems of a parallel combined engine provided in an embodiment of the present application in the working state of starting the turboengine;

[0034] Figure 5 is a schematic diagram of the cross - linked structure of the starting and fuel supply systems of a parallel combined engine provided in an embodiment of the present application in the working state of the turboengine alone and without power;

[0035] Figure 6 is a schematic diagram of the cross - linked structure of the starting and fuel supply systems of a parallel combined engine provided in an embodiment of the present application in the co - working state of the turbo - ramjet engine;

[0036] Figure 7 is a schematic diagram of the cross - linked structure of the starting and fuel supply systems of a parallel combined engine provided in an embodiment of the present application in the working state of the ramjet engine alone;

[0037] Wherein:

[0038] 1 - air turbine; 2 - aircraft accessory gearbox; 3 - engine drive system; 4 - ramjet fuel pump; 5 - starting clutch; 6 - turboengine; 7 - fuel supply clutch; 8 - aircraft auxiliary power system; 9 - auxiliary bleed air valve; 10 - fan bleed air valve; 11 - ramjet inlet; 12 - ramjet bleed air valve.

[0039] For better illustration of this embodiment, some contents in the drawings are omitted, enlarged or reduced, which are only for illustrative purposes and should not be construed as a limitation to the present application. Detailed implementation manners

[0040] To make the technical solutions and their advantages of the present application clearer, the technical solutions of the present application will be further described clearly and completely below with reference to the drawings. It can be understood that the specific embodiments described herein are only partial embodiments of the present application, which are only used to explain the present application rather than to limit the present application. It should be noted that for the convenience of description, only the parts related to the present application are shown in the drawings, and other related parts can refer to the general design.

[0041] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the ordinary meanings understood by those of ordinary skill in the art to which this application pertains. The term "including" used in the description of this application means that the concept appearing before this word encompasses the concepts listed after this word and their equivalents, without excluding other related concepts.

[0042] In addition, the terms indicating directions used in the description of this application are only used to represent relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise clearly specified and limited, the terms such as "installed" and "connected" used in the description of this application should be understood in a broad sense. For example, "connected" can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand their specific meanings in this application according to the specific circumstances.

[0043] A cross - linked structure for a parallel - combined engine starting and fuel supply system includes an air turbine 1, an aircraft accessory gearbox 2, an engine drive system 3, and a ram - air fuel pump 4, as Figure 3 shown.

[0044] The shaft of the air turbine 1 is connected to the aircraft accessory gearbox 2, and a starting clutch 5 is arranged therebetween. The shaft of the aircraft accessory gearbox 2 is connected to the engine drive system 3, and the shaft of the engine drive system 3 is connected to the turbine engine 6, as Figure 3 shown.

[0045] The shaft of the air turbine 1 is connected to the ram - air fuel pump 4, and an oil supply clutch 7 is arranged therebetween. The ram - air fuel pump 4 supplies fuel to the ramjet engine.

[0046] The air turbine 1 is connected to the aircraft auxiliary power system 8 through an air intake pipe, and an auxiliary air intake valve 9 is arranged on this air intake pipe.

[0047] The air turbine 1 is connected to the rear flow path of the fan of the turbine engine 6 through an air intake pipe, and a fan air intake valve 10 is arranged on this air intake pipe.

[0048] The air turbine 1 is connected to the ram air inlet 11 through an air intake pipe, and a ram air intake valve 12 is arranged on this air intake pipe.

[0049] The starting clutch 5 and the oil supply clutch 7 are connected to the aircraft control system and can be controlled to engage and disengage by the aircraft control system.

[0050] The auxiliary bleed air valve 9, the fan bleed air valve 10, and the ram air bleed valve 12 are connected to the aircraft control system, and the auxiliary bleed air valve 9, the fan bleed air valve 10, and the ram air bleed valve 12 can be controlled by the aircraft control system to open and close.

[0051] The parallel combined engine starting and fuel supply system cross-linking structure has a turbojet engine starting operating state, a turbojet engine alone and powerless operating state, a turbofan-ramjet combined operating state, and a ramjet engine alone operating state.

[0052] In the turbojet engine starting operating state, the starting clutch 5 is engaged, the fuel supply clutch 7 is disengaged, the auxiliary bleed air valve 9 is opened, and the fan bleed air valve 10 and the ram air bleed valve 12 are closed. At this time, the aircraft auxiliary power system 8 supplies high-temperature and high-pressure gas to the air turbine 1 through the air duct. The air turbine 1 expands and does work, and outputs shaft power to the connected turbojet engine 6 through the aircraft accessory gearbox 2 and the engine drive system 3 to drive the connected turbojet engine 6 to start, as Figure 4 shown, which is applicable to the ground and in-air starting of the turbojet engine 6.

[0053] In the turbojet engine alone and powerless operating state, the starting clutch 5 and the fuel supply clutch 7 are disengaged, and the auxiliary bleed air valve 9, the fan bleed air valve 10, and the ram air bleed valve 12 are closed, as Figure 5 shown, which is applicable to the single operation of the turbojet engine 6 and the powerless gliding.

[0054] In the turbofan-ramjet combined operating state, the starting clutch 5 is disengaged, the fuel supply clutch 7 is engaged, the auxiliary bleed air valve 9 is closed, the fan bleed air valve 10 is opened, and the ram air bleed valve 12 is closed. At this time, the flow path behind the fan of the turbojet engine 6 supplies high-temperature and high-pressure gas to the air turbine 1 through the air duct. The air turbine 1 expands and does work, and outputs shaft power to the ram fuel pump 4 to drive the ram fuel pump 4 to supply fuel for the ramjet engine, as Figure 6 shown, which is applicable to the combined operation of the turbojet engine 6 and the ramjet engine.

[0055] In the ramjet engine alone operating state, the starting clutch 5 is disengaged, the fuel supply clutch 7 is engaged, the auxiliary bleed air valve 9 is closed, the fan bleed air valve 10 is closed, and the ram air bleed valve 12 is opened. At this time, the ram air inlet 11 supplies high-temperature and high-pressure gas to the air turbine 1 through the air duct. The air turbine 1 expands and does work, and outputs shaft power to the ram fuel pump 4 to drive the ram fuel pump 4 to supply fuel for the ramjet engine, as Figure 7 shown, which is applicable to the single operation of the ramjet engine.

[0056] The cross-linked structure of the parallel combined engine starting and fuel supply system disclosed in the above embodiments integrates the functions of the parallel combined engine accessory system, shares the air turbine 1, reduces the redundancy of the functions of the accessory of the turbine engine starting system and the ramjet engine fuel supply system, reduces the number and weight of the accessories, and reduces the difficulty of thermal protection under high Mach number conditions. Moreover, by only controlling a limited number of clutches and valves, it is possible to control the switching between the turbine engine starting working state, the turbine engine alone and powerless working state, the turbo-ramjet combined working state, and the ramjet engine alone working state, so as to adapt to various working states of the parallel combined engine.

[0057] The cross-linked structure of the parallel combined engine starting and fuel supply system disclosed in the above embodiments can be controlled with reference to the following methods:

[0058] When starting the turbine engine 6 on the ground, set the cross-linked structure of the parallel combined engine starting and fuel supply system to the turbine engine starting working state, corresponding to the situation of the aircraft starting on the ground.

[0059] When the turbine engine 6 works alone, set the cross-linked structure of the parallel combined engine starting and fuel supply system to the turbine engine alone and powerless working state, corresponding to the situation of the aircraft flying at low altitude and low Mach number and changing to high altitude and high Mach number.

[0060] When the turbine engine 6 and the ramjet engine work together, set the cross-linked structure of the parallel combined engine starting and fuel supply system to the turbo-ramjet combined working state, corresponding to the situation of the aircraft taking off, landing and flying at low altitude and low Mach number.

[0061] When the ramjet engine works alone, set the cross-linked structure of the parallel combined engine starting and fuel supply system to the ramjet engine alone working state, corresponding to the situation of the aircraft flying at high altitude and high Mach number and changing.

[0062] When making a powerless glide, set the cross-linked structure of the parallel combined engine starting and fuel supply system to the turbine engine alone and powerless working state, corresponding to the situation of the aircraft making a powerless glide at the end of the flight mission.

[0063] When starting the turbine engine 6 in the air, set the cross-linked structure of the parallel combined engine starting and fuel supply system to the turbine engine starting working state, corresponding to the situation of the aircraft descending to a certain altitude and Mach number and making an in-air restart.

[0064] For the control method of the cross-linked structure of the parallel combined engine starting and fuel supply system disclosed in the above embodiments, which is used to control the cross-linked structure of the parallel combined engine starting and fuel supply system disclosed in the above embodiments, the description is relatively simple. For specific relevant parts, reference can be made to the relevant descriptions in the part of the cross-linked structure of the parallel combined engine starting and fuel supply system. The technical effects can also be referred to the technical effects of the relevant parts of the cross-linked structure of the parallel combined engine starting and fuel supply system, which will not be elaborated here.

[0065] So far, the technical solutions of the present application have been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present application.

Claims

1. A cross-linked structure of a parallel combined engine starting and fuel supply system, characterized in that, It includes an air turbine (1), an aircraft accessory case (2), an engine drive system (3), and a ram fuel pump (4); The shaft of the air turbine (1) is connected to the aircraft accessory case (2), and a starting clutch (5) is arranged therebetween. The shaft of the aircraft accessory case (2) is connected to the engine drive system (3), and the shaft of the engine drive system (3) is connected to the turbofan engine (6); The shaft of the air turbine (1) is connected to the ram fuel pump (4), and an oil supply clutch (7) is arranged therebetween. The ram fuel pump (4) is used to supply fuel to the ramjet engine; The air turbine (1) is connected to the aircraft auxiliary power system (8) through an air duct, and an auxiliary air intake valve (9) is arranged on this air duct; The air turbine (1) is connected to the rear flow path of the fan of the turbofan engine (6) through an air duct, and a fan air intake valve (10) is arranged on this air duct; The air turbine (1) is connected to the ram air intake duct (11) through an air duct, and a ram air intake valve (12) is arranged on this air duct.

2. The cross-linked structure of the parallel combined engine starting and fuel supply system according to claim 1, characterized in that The starting clutch (5) and the oil supply clutch (7) are connected to the aircraft control system, and the engagement and disengagement of the starting clutch (5) and the oil supply clutch (7) can be controlled through the aircraft control system.

3. The cross-linked structure of the parallel combined engine starting and fuel supply system according to claim 2, characterized in that The auxiliary air intake valve (9), the fan air intake valve (10), and the ram air intake valve (12) are connected to the aircraft control system, and the opening and closing of the auxiliary air intake valve (9), the fan air intake valve (10), and the ram air intake valve (12) can be controlled through the aircraft control system.

4. The cross-linking structure of the parallel combined engine starting and fuel supply system according to claim 3, wherein It has: Turbofan engine starting working state: The starting clutch (5) is engaged, the oil supply clutch (7) is disengaged, the auxiliary air intake valve (9) is opened, the fan air intake valve (10) and the ram air intake valve (12) are closed. The aircraft auxiliary power system (8) supplies high-temperature and high-pressure gas to the air turbine (1) through the air duct. The air turbine (1) expands and does work, and outputs shaft power to the turbofan engine (6) through the aircraft accessory case (2) and the engine drive system (3), driving the turbofan engine (6) to start; Turbofan engine single and powerless working state: The starting clutch (5) and the oil supply clutch (7) are disengaged, and the auxiliary air intake valve (9), the fan air intake valve (10), and the ram air intake valve (12) are closed; Turboramjet combined working state: The starting clutch (5) is disengaged, the oil supply clutch (7) is engaged, the auxiliary air intake valve (9) is closed, the fan air intake valve (10) is opened, the ram air intake valve (12) is closed. The rear flow path of the fan of the turbofan engine (6) supplies high-temperature and high-pressure gas to the air turbine (1) through the air duct. The air turbine (1) expands and does work, outputs shaft power to the ram fuel pump (4), drives the ram fuel pump (4), and supplies fuel to the ramjet engine; Ramjet engine in independent operation state: The starting clutch (5) is disengaged, the fuel supply clutch (7) is engaged, the auxiliary bleed air valve (9) is closed, the fan bleed air valve (10) is closed, the ram bleed air valve (12) is open, and the ram air intake (11) supplies high-temperature and high-pressure gas to the air turbine (1) through the air duct. The air turbine (1) expands and does work, outputs shaft power to the ram fuel pump (4), drives the ram fuel pump (4), and supplies fuel to the ramjet engine.

5. A control method for the cross-linked structure of a parallel combined engine starting and fuel supply system, which is used to control the cross-linked structure of the parallel combined engine starting and fuel supply system described in claim 4, characterized in that, Including: When starting the turbofan engine (6) on the ground, set the cross-linked structure of the parallel combined engine starting and fuel supply system to the turbofan engine starting operation state; When the turbofan engine (6) operates independently, set the cross-linked structure of the parallel combined engine starting and fuel supply system to the turbofan engine independent and powerless operation state; When the turbofan engine (6) and the ramjet engine operate together, set the cross-linked structure of the parallel combined engine starting and fuel supply system to the turbofan-ramjet combined operation state; When the ramjet engine operates independently, set the cross-linked structure of the parallel combined engine starting and fuel supply system to the ramjet engine independent operation state; When performing a powerless glide, set the cross-linked structure of the parallel combined engine starting and fuel supply system to the turbofan engine independent and powerless operation state; When starting the turbofan engine (6) in the air, set the cross-linked structure of the parallel combined engine starting and fuel supply system to the turbofan engine starting operation state.

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