Parallel TBCC engine fuel supply system and control method thereof

Abstract

The invention belongs to the technical field of parallel TBCC engine fuel oil supply scheme design, and particularly relates to a parallel TBCC engine fuel oil supply system and a control method thereof. A thrust augmentation fuel oil pump and a stamping fuel oil pump are integrally designed, and a set of stamping fuel oil pump and a stamping air turbine for driving the stamping fuel oil pump are omitted; the number of accessories of the parallel TBCC engine fuel supply system is reduced, the complexity and weight of the system are reduced, and the problem of thrust resistance balance when the flight Mach number is 2-3.5 can be well solved.

Description

Technical Field

[0001] The present application belongs to the technical field of parallel TBCC engine fuel supply scheme design, and specifically relates to a parallel TBCC engine fuel supply system and a control method thereof. Background Art

[0002] The parallel TBCC engine is composed of a turbine engine and a ramjet engine in parallel. It has the advantages of a wide operating speed range, large comprehensive specific impulse, low operating and maintenance costs, and good reusability. It is an ideal power for future hypersonic aircraft.

[0003] In a typical mission scenario, the parallel TBCC engine needs to go through the process of turbine engine working alone - turbine engine and ramjet working together - ramjet engine working alone. The fuel system needs to realize fuel supply to the TBCC engine under all working conditions.

[0004] At present, in the parallel TBCC engine fuel supply system, the turbine engine and ramjet engine adopt their own independent fuel supply system solutions. The turbine engine provides power by itself, and drives the main fuel pump and afterburner fuel pump to supply fuel to the main combustion chamber and afterburner combustion chamber of the turbine engine respectively through the engine accessory casing. The ramjet engine drives the ram air turbine from the rear air intake, driving the ram fuel pump to supply fuel to the ramjet engine. Figure 1 As shown, this technical solution has the following defects:

[0005] 1) The fuel pump has excessive fuel supply capacity, and the system is complex and heavy;

[0006] 2) When the flight Mach number is 2-3.5, the turbine engine and the ramjet engine work together. There is a situation where the ramjet engine cannot provide air with sufficient pressure to drive the ramjet fuel pump to supply fuel to the ramjet engine. It is necessary to bleed air from the turbine engine to drive the ramjet fuel pump, but this will cause the thrust of the parallel TBCC engine to decrease, exacerbating the thrust-drag balance problem.

[0007] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0008] The purpose of the present application is to provide a parallel TBCC engine fuel supply system and a control method thereof to overcome or alleviate at least one of the known technical deficiencies.

[0009] The technical solution of this application is:

[0010] On the one hand, a parallel TBCC engine fuel supply system is provided, including an engine accessory case, a main fuel pump, an aircraft accessory case, a ram air turbine, and an afterburner / ram fuel pump;

[0011] The main fuel pump is used to supply fuel to the main combustion chamber of the turbine engine, and the afterburner / ramjet fuel pump is used to supply fuel to the afterburner combustion chamber of the turbine engine and the ramjet engine;

[0012] The engine accessory case is connected to the turbine engine, and the main fuel pump is connected to the engine accessory case. The engine accessory case can extract power from the turbine engine to drive the main fuel pump to work;

[0013] The aircraft accessory casing is connected to the engine accessory casing through a clutch, and the afterburner / ram fuel pump is connected to the aircraft accessory casing. When the clutch is connected, the aircraft accessory casing can extract power from the engine accessory casing to drive the afterburner / ram fuel pump to work;

[0014] The ram air turbine is connected to the aircraft accessory casing and can draw high-pressure gas from the ramjet engine intake to work, drive the aircraft accessory casing, and then drive the afterburner / ramjet fuel pump to work.

[0015] According to at least one embodiment of the present application, the above-mentioned parallel TBCC engine fuel supply system control has:

[0016] The turbine engine is in fuel supply mode, the clutch is connected, the engine accessory case extracts power from the turbine engine to drive the main fuel pump to supply fuel to the main combustion chamber of the turbine engine, and the aircraft accessory case extracts power from the engine accessory case to drive the afterburner / ramjet fuel pump to supply fuel to the afterburner combustion chamber of the turbine engine;

[0017] The turbine engine and ramjet engine work together in the fuel supply mode, the clutch is connected, the engine accessory casing extracts power from the turbine engine to drive the main fuel pump to supply fuel to the main combustion chamber of the turbine engine, and the aircraft accessory casing extracts power from the engine accessory casing to drive the afterburner / ramjet fuel pump to supply fuel to the afterburner combustion chamber of the turbine engine and the ramjet engine;

[0018] In the ramjet engine working fuel supply mode, the clutch is disengaged, and the ram air turbine draws high-pressure gas from the ramjet engine intake to work, driving the aircraft accessory casing, and then driving the afterburner / ramjet fuel pump to work and supply fuel to the ramjet engine.

[0019] On the other hand, a parallel TBCC engine fuel supply system control method is provided, which is used to control the parallel TBCC engine fuel supply system, comprising:

[0020] When the turbine engine is working alone, the parallel TBCC engine fuel supply system is set to be in the turbine engine working fuel supply mode;

[0021] When the turbine engine and the ramjet engine work together, the parallel TBCC engine fuel supply system is set to be in the turbine engine and the ramjet engine work together fuel supply mode;

[0022] When the ramjet engine works alone, the parallel TBCC engine fuel supply system is set in the ramjet engine working fuel supply mode.

[0023] According to at least one embodiment of the present application, in the above-mentioned parallel TBCC engine fuel supply system control method, when the flight Mach number is 0-2, the turbine engine works alone.

[0024] According to at least one embodiment of the present application, in the above-mentioned parallel TBCC engine fuel supply system control method, when the flight Mach number is 2-3.5, the turbine engine and the ramjet engine work together.

[0025] According to at least one embodiment of the present application, in the above-mentioned parallel TBCC engine fuel supply system control method, when the flight Mach number is 3.5-5, the ramjet engine works alone.

[0027] This application has at least the following beneficial technical effects:

[0028] Provided are a parallel TBCC engine fuel supply system and a control method thereof, wherein an afterburner fuel pump and a ram fuel pump are designed in an integrated manner, thereby eliminating a set of ram fuel pumps and a ram air turbine for driving the ram fuel pumps, reducing the number of accessories of the parallel TBCC engine fuel supply system, reducing the complexity and weight of the system, and being able to effectively overcome the thrust-drag balance problem when the flight Mach number is 2-3.5. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a schematic diagram of the existing parallel TBCC engine fuel supply system;

[0030] Figure 2 It is a schematic diagram of a parallel TBCC engine fuel supply system provided in an embodiment of the present application.

[0031] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and cannot be understood as limitations on this patent. DETAILED DESCRIPTION

[0032] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not 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 accompanying drawings, and other related parts can refer to the general design.

[0033] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0034] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection 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. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0035] In practice, the maximum fuel flow demand of the afterburner of a turbine engine occurs in the state of a large Mach number of 0 km / h. When the turbine engine and the ramjet engine work together, the total fuel flow demand of the afterburner and the ramjet engine is close to the fuel flow of the afterburner in the state of a large Mach number of 0 km / h. That is, the fuel flow that can be supplied by an afterburner fuel pump can meet the common fuel supply demand of the afterburner and the ramjet engine. The existing parallel TBCC engine fuel supply system has a surplus of a ramjet fuel pump and a ram air turbine driving the ramjet fuel pump. The afterburner fuel pump and the ramjet fuel pump can be designed as an integrated whole, reducing the number of accessories of the parallel TBCC engine fuel supply system, thereby reducing the complexity and weight of the system, and being able to overcome the thrust-drag balance problem when the flight Mach number is 2-3.5. Based on this, an embodiment of the present application provides a parallel TBCC engine fuel supply system, such as Figure 2 As shown, it includes the engine accessory case, main fuel pump, aircraft accessory case, ram air turbine, and afterburner / ram fuel pump.

[0036] The main fuel pump is used to supply fuel to the main combustion chamber of the turbine engine, and the afterburner / ramjet fuel pump is used to supply fuel to the afterburner combustion chamber of the turbine engine and the ramjet engine.

[0037] The engine accessory casing is connected to the turbine engine, and the main fuel pump is connected to the engine accessory casing. The engine accessory casing can extract power from the turbine engine to drive the main fuel pump to work, and stop working when the turbine engine is shut down.

[0038] The aircraft accessory casing is connected to the engine accessory casing through a clutch, and the afterburner / ram fuel pump is connected to the aircraft accessory casing. When the clutch is connected, the aircraft accessory casing can extract power from the engine accessory casing to drive the afterburner / ram fuel pump to work.

[0039] The ram air turbine is connected to the aircraft accessory casing and can draw high-pressure gas from the ramjet engine intake to work, drive the aircraft accessory casing, and then drive the afterburner / ramjet fuel pump to work.

[0040] The parallel TBCC engine fuel supply system has:

[0041] The turbine engine is in fuel supply mode, the clutch is connected, the engine accessory case extracts power from the turbine engine to drive the main fuel pump to supply fuel to the main combustion chamber of the turbine engine, and the aircraft accessory case extracts power from the engine accessory case to drive the afterburner / ramjet fuel pump to supply fuel to the afterburner combustion chamber of the turbine engine;

[0042] The turbine engine and ramjet engine work together in the fuel supply mode, the clutch is connected, the engine accessory casing extracts power from the turbine engine to drive the main fuel pump to supply fuel to the main combustion chamber of the turbine engine, and the aircraft accessory casing extracts power from the engine accessory casing to drive the afterburner / ramjet fuel pump to supply fuel to the afterburner combustion chamber of the turbine engine and the ramjet engine;

[0043] In the ramjet engine working fuel supply mode, the clutch is disengaged, and the ram air turbine draws high-pressure gas from the ramjet engine intake to work, driving the aircraft accessory casing, and then driving the afterburner / ramjet fuel pump to work and supply fuel to the ramjet engine.

[0044] A parallel TBCC engine fuel supply system control method is used to control the parallel TBCC engine fuel supply system disclosed in the above embodiment, comprising:

[0045] When the turbine engine is working alone, the parallel TBCC engine fuel supply system is set to be in the turbine engine working fuel supply mode;

[0046] When the turbine engine and the ramjet engine work together, the parallel TBCC engine fuel supply system is set to be in the turbine engine and the ramjet engine work together fuel supply mode;

[0047] When the ramjet engine works alone, the parallel TBCC engine fuel supply system is set in the ramjet engine working fuel supply mode.

[0048] Usually, when the flight Mach number is 0-2, the turbine engine works alone; when the flight Mach number is 2-3.5, the turbine engine and the ramjet engine work together; when the flight Mach number is 3.5-5, the ramjet engine works alone.

[0049] In the parallel TBCC engine fuel supply system and control method thereof disclosed in the above-mentioned embodiment, the afterburner fuel pump and the ram fuel pump are designed to be integrated, thereby eliminating a set of ram fuel pumps and a ram air turbine driving the ram fuel pump, reducing the number of accessories of the parallel TBCC engine fuel supply system, reducing the complexity and weight of the system, and being able to effectively overcome the thrust-drag balance problem when the flight Mach number is 2-3.5.

[0050] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles 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 scope of protection of the present application.

Claims

1. A parallel TBCC engine fuel supply system, characterized in that: Includes engine accessory casing, main fuel pump, aircraft accessory casing, ram air turbine, afterburner / ram fuel pump; The main fuel pump is used to supply fuel to the main combustion chamber of the turbine engine, and the afterburner / ramjet fuel pump is used to supply fuel to the afterburner combustion chamber of the turbine engine and the ramjet engine; The engine accessory case is connected to the turbine engine, and the main fuel pump is connected to the engine accessory case. The engine accessory case can extract power from the turbine engine to drive the main fuel pump to work; The aircraft accessory casing is connected to the engine accessory casing through a clutch, and the afterburner / ram fuel pump is connected to the aircraft accessory casing. When the clutch is connected, the aircraft accessory casing can extract power from the engine accessory casing to drive the afterburner / ram fuel pump to work; The ram air turbine is connected to the aircraft accessory casing and can draw high-pressure gas from the ramjet engine intake to work, drive the aircraft accessory casing, and then drive the afterburner / ramjet fuel pump to work.

2. The parallel TBCC engine fuel supply system according to claim 1, characterized in that: have: The turbine engine is in fuel supply mode, the clutch is connected, the engine accessory case extracts power from the turbine engine to drive the main fuel pump to supply fuel to the main combustion chamber of the turbine engine, and the aircraft accessory case extracts power from the engine accessory case to drive the afterburner / ramjet fuel pump to supply fuel to the afterburner combustion chamber of the turbine engine; The turbine engine and ramjet engine work together in the fuel supply mode, the clutch is connected, the engine accessory casing extracts power from the turbine engine to drive the main fuel pump to supply fuel to the main combustion chamber of the turbine engine, and the aircraft accessory casing extracts power from the engine accessory casing to drive the afterburner / ramjet fuel pump to supply fuel to the afterburner combustion chamber of the turbine engine and the ramjet engine; In the ramjet engine working fuel supply mode, the clutch is disengaged, and the ram air turbine draws high-pressure gas from the ramjet engine intake to work, driving the aircraft accessory casing, and then driving the afterburner / ramjet fuel pump to work and supply fuel to the ramjet engine.

3. A method for controlling a parallel TBCC engine fuel supply system, for controlling the parallel TBCC engine fuel supply system of claim 2, comprising: When the turbine engine is working alone, the parallel TBCC engine fuel supply system is set to be in the turbine engine working fuel supply mode; When the turbine engine and the ramjet engine work together, the parallel TBCC engine fuel supply system is set to be in the turbine engine and the ramjet engine work together fuel supply mode; When the ramjet engine works alone, the parallel TBCC engine fuel supply system is set in the ramjet engine working fuel supply mode.

4. The parallel TBCC engine fuel supply system control method according to claim 3, characterized in that: When the flight Mach number is 0-2, the turbine engine works alone.

5. The parallel TBCC engine fuel supply system control method according to claim 3, characterized in that: When the flight Mach number is 2-3.5, the turbine engine and ramjet engine work together.

6. The parallel TBCC engine fuel supply system control method according to claim 3, characterized in that: When the flight Mach number is 3.5-5, the ramjet engine works alone.

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