A parallel TBCC engine fuel supply system and control method thereof

Abstract

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 control method thereof. The invention integrates an afterburner fuel pump and a ram fuel pump into an integrated design, thereby eliminating a ram fuel pump and a ram air turbine that drives the ram fuel pump. This reduces the number of accessories in the parallel TBCC engine fuel supply system, reduces the system complexity and weight, and effectively overcomes the thrust-drag balance problem at a flight Mach number of 2-3.5.

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 source for future hypersonic aircraft.

[0003] In a typical mission scenario, the parallel TBCC engine needs to go through the process of the turbine engine working alone - the turbine engine and the ramjet working together - and the ramjet working alone. The fuel system needs to realize the fuel supply of 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 of the turbine engine respectively through the engine accessory casing. The ramjet engine drives the ram air turbine by bleed air from the rear of the air inlet, which drives 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 this 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 technical deficiencies of the known ones.

[0009] The technical solution of this application is:

[0010] In one aspect, a parallel TBCC engine fuel supply system is provided, comprising an engine accessory case, a main fuel pump, an aircraft accessory case, a ram air turbine, and an afterburner / ramjet 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 via 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.

[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 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 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] Another aspect provides a method for controlling a parallel TBCC engine fuel supply system, for controlling 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 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 the turbine engine and ramjet engine working together fuel supply mode;

[0022] When the ramjet engine works alone, the parallel TBCC engine fuel supply system is set to be 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.

[0026] This application has at least the following beneficial technical effects:

[0027] Provided are a parallel TBCC engine fuel supply system and a control method thereof. An afterburner fuel pump and a ram fuel pump are integrated into a design, eliminating a ram fuel pump and a ram air turbine for driving the ram fuel pump. This reduces the number of accessories in the parallel TBCC engine fuel supply system, lowering the system's complexity and weight. This effectively overcomes the thrust-drag balance problem at a flight Mach number of 2-3.5. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a schematic diagram of the existing parallel TBCC engine fuel supply system;

[0029] Figure 2 Schematic diagram of the parallel TBCC engine fuel supply system provided in an embodiment of the present application.

[0030] 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 should not be understood as limitations on this patent. DETAILED DESCRIPTION

[0031] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0032] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application 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 means 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.

[0033] In addition, it should be noted that, unless otherwise clearly stipulated 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.

[0034] 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 kilometers. 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 kilometers, that is, the fuel flow that can be supplied by one 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 redundant set of ramjet fuel pumps and a ram air turbine that drives 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, the 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 / ramjet fuel pump.

[0035] 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.

[0036] 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.

[0037] 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.

[0038] 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.

[0039] Parallel TBCC engine fuel supply system, with:

[0040] 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;

[0041] The turbine engine and ramjet engine work together in the 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 and the ramjet engine;

[0042] 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.

[0043] 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:

[0044] When the turbine engine is working alone, the parallel TBCC engine fuel supply system is set to the turbine engine working fuel supply mode;

[0045] When the turbine engine and the ramjet engine work together, the parallel TBCC engine fuel supply system is set to the turbine engine and ramjet engine working together fuel supply mode;

[0046] When the ramjet engine works alone, the parallel TBCC engine fuel supply system is set to be in the ramjet engine working fuel supply mode.

[0047] 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 ramjet engine work together; when the flight Mach number is 3.5-5, the ramjet engine works alone.

[0048] In the parallel TBCC engine fuel supply system and control method disclosed in the above-mentioned embodiments, the afterburner fuel pump and ram fuel pump are integrated into a design, eliminating a ram fuel pump and the ram air turbine that drives the ram fuel pump. This reduces the number of accessories in the parallel TBCC engine fuel supply system, reducing the system's complexity and weight, and effectively overcoming the thrust-drag balance problem at a flight Mach number of 2-3.5.

[0049] 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 replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A parallel TBCC engine fuel supply system, characterized in that: Including engine accessory case, main fuel pump, aircraft accessory case, ram air turbine, afterburner / ramjet 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 via 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.

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 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 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 operating 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 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 the turbine engine and ramjet engine working together fuel supply mode; When the ramjet engine works alone, the parallel TBCC engine fuel supply system is set to be 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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