Fuel supply system and method for wide-speed-range ramjet driven by cracking oil-gas turbine

Abstract

The invention belongs to the technical field of ramjet engines, and provides a fuel supply system and method for a wide-speed-range ramjet engine driven by a cracking oil-gas turbine. Comprising an oil tank, a centrifugal pump, a motor, an oil-gas turbine, a storage battery, an electromagnetic control module, a fuel oil pipeline, a cracking fuel oil steam pipeline, a combustion chamber and a regeneration cooling channel on the outer wall surface of the combustion chamber. Through the connection relation of the centrifugal pump, the regenerative cooling channel and the oil-gas turbine, hydrocarbon fuel is cracked into micromolecule cracked kerosene steam to push the turbine rotor to do work, the motor assists in driving the ramjet engine to start, the power taking problem of a ramjet mode is solved, and meanwhile the thermal protection problem is relieved.

Description

Technical Field

[0001] The present invention relates to the technical field of ramjet engines, and in particular to a fuel supply system and method for a wide-speed range ramjet engine driven by a cracking oil and gas turbine. Background Art

[0002] Hypersonic aircraft generally refers to aircraft with a flight speed exceeding 5 times the speed of sound. It is a new type of aircraft with large airspace, supersonic speed, long distance and high precision. It includes hypersonic ballistics, space planes, hypersonic reconnaissance aircraft, hypersonic transport aircraft and reusable space-to-earth aircraft. Scramjet engines can make the incoming air enter the combustion chamber at supersonic speed for combustion. Therefore, the combined engine based on the scramjet engine is the best power embodiment for realizing hypersonic flight. Since the scramjet engine must be started at a certain speed and cannot independently complete the whole process from takeoff to hypersonic flight, some combined cycle embodiments based on the scramjet engine have emerged. Among them, the turbine-ramjet combined cycle engine realizes the structural integration of the two power forms of turbine engine and ramjet engine and the organic combination of the working process, so that the turbine engine and ramjet engine can each play their advantages in the area suitable for their own work, which is the ideal power for hypersonic aircraft. For hypersonic aircraft that fly for a long time and long distance, the effective management and utilization of airborne energy will have a great impact on the aircraft. Scramjet engines obtain large amounts of oxygen during flight and do not need to carry oxidizers, which means that when consuming the same mass of propellant, the thrust generated by a scramjet engine is greater than that of a rocket engine.

[0003] However, since ramjets have no rotating parts, they cannot extract energy through the traditional method of extracting shaft work. In addition, as the flight Mach number increases, the total temperature, total pressure and speed of the airflow in the combustion chamber of the scramjet engine that works for a long time will continue to increase, causing the combustion chamber structure to bear huge aerodynamic and combustion heat loads. Summary of the invention

[0004] In order to overcome the deficiencies of the prior art, the object of the present invention is to provide a wide-speed range ramjet engine fuel supply system and method driven by a cracking oil and gas turbine, so as to solve the power extraction problem of the ramjet mode.

[0005] To achieve the above object, the present invention provides the following embodiments:

[0006] A wide-speed range ramjet fuel supply system driven by a cracking oil and gas turbine comprises: a fuel tank, a centrifugal pump, a motor, an oil and gas turbine, a battery, an electromagnetic control module, a fuel pipeline, a cracking fuel vapor pipeline, a combustion chamber and a regeneration cooling channel on the outer wall of the combustion chamber; the electromagnetic control module comprises: a first electromagnetic valve, a second electromagnetic valve and a third electromagnetic valve;

[0007] The outlet of the centrifugal pump is connected to the first solenoid valve, the second solenoid valve and the third solenoid valve respectively; the first solenoid valve is connected to the fuel tank through the fuel pipeline; the fuel tank is connected to the centrifugal pump through the fuel pipeline; the centrifugal pump, the motor and the oil-gas turbine are connected in sequence; the motor is also connected to the battery; the second solenoid valve is connected to the regenerative cooling channel; the third solenoid valve is connected to the nozzle inlet of the combustion chamber; the outlet and inlet of the oil-gas turbine are connected to the combustion chamber and the regenerative cooling channel respectively;

[0008] The regenerative cooling passage can utilize the heat of the combustion chamber to crack the received hydrocarbon fuel into small-molecule cracked kerosene vapor, and transport the small-molecule cracked kerosene vapor to the oil-gas turbine.

[0009] Preferably, the oil and gas turbine, the centrifugal pump and the motor are connected in a coaxial manner.

[0010] Preferably, a method for supplying fuel to a wide-speed range ramjet engine driven by a cracking oil and gas turbine comprises:

[0011] In the initial stage, the motor is started, and the battery is used to provide the motor with a power supply with a stable voltage and a linearly increasing current, and the motor drives the centrifugal pump to pressurize the hydrocarbon fuel input into the tank;

[0012] In the initial stage, the openings of the first solenoid valve and the third solenoid valve are linearly increased, and the second solenoid valve is kept in a closed state;

[0013] When the output current of the battery reaches the maximum safe current, the second stage is entered;

[0014] In the second stage, the opening of the first solenoid valve is fixed, and the opening of the second solenoid valve increases linearly;

[0015] In the second stage, the opening of the third solenoid valve keeps increasing linearly until the opening design value of the third solenoid valve is reached, and then the linear increase of the opening of the third solenoid valve is stopped;

[0016] When the output power of the oil and gas turbine reaches the pump boost power requirement, the battery is turned off.

[0017] Preferably, it also includes:

[0018] During the acceleration phase, the opening of the first solenoid valve is increased linearly, and the opening of the third solenoid valve is gradually reduced until the third solenoid valve is closed and the reduction of the opening of the third solenoid valve is stopped. The opening of the second solenoid valve is controlled to first increase to 0.93 and then decrease linearly.

[0019] The present invention discloses the following technical effects:

[0020] The present invention provides a wide-speed range ramjet engine fuel supply system and method driven by a cracking oil and gas turbine. Through the connection relationship between a centrifugal pump, a regenerative cooling channel and an oil and gas turbine, the power extraction problem of the ramjet mode is solved and the thermal protection problem is alleviated, and the use of hydrocarbon fuel cracking into small molecule cracking kerosene vapor to drive the turbine rotor to do work is realized. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical embodiments in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0022] Figure 1 A schematic diagram of a module of a wide-speed range ramjet fuel supply system provided by an embodiment of the present invention;

[0023] Figure 2 A schematic flow chart of a method for supplying fuel to a ramjet engine over a wide speed range provided by an embodiment of the present invention.

[0024] Description of reference numerals:

[0025] 1-fuel tank, 2-centrifugal pump, 3-motor, 4-oil and gas turbine, 5-battery, 6-electromagnetic control module, 601-first solenoid valve, 602-second solenoid valve, 603-third solenoid valve, 7-fuel pipeline, 8-cracking oil and gas pipeline, 9-regeneration cooling channel. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical embodiments in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0027] The purpose of the present invention is to provide a wide-speed range ramjet engine fuel supply system and method driven by a cracking oil and gas turbine, so as to solve the problem of power extraction in the ramjet mode.

[0028] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0029] Figure 1 A schematic diagram of a wide speed range ramjet engine fuel supply system module provided by an embodiment of the present invention is shown in FIG. Figure 1 As shown, the present invention provides a wide-speed range ramjet fuel supply system driven by a cracking oil and gas turbine, comprising: a fuel tank 1, a centrifugal pump 2, a motor 3, an oil and gas turbine 4, a battery 5, an electromagnetic control module 6, a fuel pipeline 7, a cracking fuel vapor pipeline, a combustion chamber and a regeneration cooling channel 9 on the outer wall of the combustion chamber; the electromagnetic control module 6 comprises: a first electromagnetic valve 601, a second electromagnetic valve 602 and a third electromagnetic valve 603;

[0030] The outlet of the centrifugal pump 2 is connected to the first solenoid valve 601, the second solenoid valve 602 and the third solenoid valve 603 respectively; the first solenoid valve 601 is connected to the fuel tank 1 through the fuel pipeline 7; the fuel tank 1 is connected to the centrifugal pump 2 through the fuel pipeline 7; the centrifugal pump 2, the motor 3 and the oil-gas turbine 4 are connected in sequence; the motor 3 is also connected to the battery 5; the second solenoid valve 602 is connected to the regenerative cooling channel 9; the third solenoid valve 603 is connected to the nozzle inlet of the combustion chamber; the outlet and inlet of the oil-gas turbine 4 are connected to the combustion chamber and the regenerative cooling channel 9 respectively;

[0031] The regenerative cooling channel 9 can utilize the heat of the combustion chamber to crack the received hydrocarbon fuel into small-molecule cracked kerosene vapor, and transport the small-molecule cracked kerosene vapor to the oil-gas turbine 4 .

[0032] Preferably, the oil-gas turbine 4, the centrifugal pump 2 and the motor 3 are connected in a coaxial manner.

[0033] refer to Figure 2 , a fuel supply method for a wide speed range ramjet engine driven by a cracking oil and gas turbine 4, comprising:

[0034] Step 100: In the initial stage, the motor 3 is started, and the battery 5 is used to provide the motor 3 with a power supply with a stable voltage and a linearly increasing current, and the motor 3 drives the centrifugal pump 2 to pressurize the hydrocarbon fuel input into the fuel tank 1;

[0035] Step 200: In the initial stage, the openings of the first solenoid valve 601 and the third solenoid valve 603 are linearly increased, and the second solenoid valve 602 is kept in a closed state;

[0036] Step 300: When the output current of the battery 5 reaches the maximum safe current, the second stage is entered;

[0037] Step 400: In the second stage, the opening of the first solenoid valve 601 is fixed, and the opening of the second solenoid valve 602 increases linearly;

[0038] Step 500: In the second stage, the opening of the third solenoid valve 603 keeps increasing linearly until the opening design value of the third solenoid valve 603 is reached, and then the linear increase of the opening of the third solenoid valve 603 is stopped;

[0039] Step 600: When the output power of the oil and gas turbine 4 reaches the pump boost power requirement, the battery 5 is turned off.

[0040] Furthermore, it also includes:

[0041] During the acceleration phase, the opening of the first solenoid valve 601 is linearly increased, and the opening of the third solenoid valve 603 is gradually reduced until the third solenoid valve 603 is closed and the reduction of the opening of the third solenoid valve is stopped. The opening of the second solenoid valve 602 is controlled to first increase to 0.93 and then decrease linearly.

[0042] Preferably, this embodiment utilizes the high temperature of the outer wall of the combustion chamber in the ramjet mode to allow the hydrocarbon fuel to flow through the regeneration cooling channel 9 and crack into small molecule cracked kerosene vapor, which can enter the turbine to drive the rotor to do work.

[0043] Furthermore, the fuel supply system can meet the fuel supply demand during the starting process of the ramjet engine; the fuel supply system can meet the fuel supply demand of the ramjet engine at different flight Mach numbers.

[0044] Specifically, during the starting process of the ramjet engine, the fuel supply embodiment keeps the diverter valve in front of the regeneration cooling channel 9 closed, opens the diverter valve and the reflux valve behind the pump, and the fuel pressurized by the centrifugal pump 2 is injected into the combustion chamber through the fuel pipeline 7, and the battery 5 drives the centrifugal pump 2 to work through the motor 3. After a period of time, the wall temperature of the combustion chamber reaches the fuel cracking requirement, and the diverter valve in front of the regeneration cooling channel 9 is opened, so that the fuel pressurized by the centrifugal pump 2 passes through the regeneration cooling channel 9, and changes from liquid to high-temperature and high-pressure cracked mixed oil and gas, and enters the cracking oil and gas turbine 4 through the cracking oil and gas pipeline 8, driving the cracking oil and gas turbine 4 to work, and meeting the energy demand of the centrifugal pump 2 during the starting process. The calculation input of the ramjet engine fuel supply embodiment for a wide speed range during the ramjet engine starting process is shown in Table 1 below.

[0045] Table 1

[0046] Parameter name Parameter Unit Value Flight Mach number 2.4 Flight altitude km 14.82 Pump maximum flow kg / s 7 Mode conversion time s 10 Maximum safe current A 600 Battery discharge voltage V 48 Pump inlet pressure MPa 0.1 Pump inlet temperature K 300 Pump pressure rise MPa 5.9

[0047] According to the calculation of this embodiment, the pump power is 113.42kW in the final stable state of the starting process, the cracking oil and gas turbine 4 power is 143.83kW, and the motor 3 mode is the power generation mode to charge the battery. During the starting process, the battery alone serves as an energy source to provide energy to the turbine pump for a total time of 2.2s.

[0048] Furthermore, in the fuel supply embodiment, during the acceleration of the ramjet engine from the flight Mach number Ma5 to the flight Mach number Ma6, the opening of the diverter valve in front of the regeneration cooling channel 9 is linearly reduced from 0.78 to 0.56, the opening of the diverter valve 603 after the pump is linearly reduced from 0.05 to 0, and the opening of the return valve after the pump is linearly increased from 0.68 to 0.81. In this process, the fuel pressurized by the centrifugal pump 2 passes through the regeneration cooling channel 9, and changes from liquid to high-temperature and high-pressure cracked mixed oil and gas, and enters the cracked oil and gas turbine 4 through the cracked oil and gas pipeline 8, driving the cracked oil and gas turbine 4 to work, thereby meeting the energy demand of the centrifugal pump 2 during the acceleration process. The calculation input of the ramjet engine fuel supply embodiment for a wide speed range during the acceleration process of the ramjet engine is shown in Table 2 below.

[0049] Table 2

[0050]

[0051] According to the calculation of this embodiment, the pump power is 113.42kW in the final stable state of the starting process, the power of the cracking oil and gas turbine 4 is reduced from 127.68kW to 91.9kW, the motor 3 mode is changed from the power generation mode to the motor mode, and the overall system is changed from the battery charging state to the battery discharging state. The gas flow rate of the cracking oil and gas turbine 4 is changed from 1.96kg / s to 1.41kg / s.

[0052] The beneficial effects of the present invention are as follows:

[0053] The present invention utilizes the connection between a centrifugal pump, a regenerative cooling channel and an oil-gas turbine to realize the use of hydrocarbon fuel to crack into small molecule cracked kerosene vapor to drive the turbine rotor to do work, and uses a motor to assist in driving the ramjet engine to start, so as to solve the power extraction problem of the ramjet mode and alleviate the thermal protection problem.

[0054] The various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.

[0055] The principles and implementation methods of the present invention are described in this article using specific examples. The description of the above embodiments is only used to help understand the method and core idea of ​​the present invention. At the same time, for those skilled in the art, according to the idea of ​​the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. A fuel supply system for a wide speed range ramjet engine driven by a cracking oil and gas turbine, characterized in that: include: A fuel tank, a centrifugal pump, a motor, an oil and gas turbine, a battery, an electromagnetic control module, a fuel pipeline, a cracked fuel vapor pipeline, a combustion chamber, and a regeneration cooling channel on the outer wall of the combustion chamber; the electromagnetic control module includes: a first electromagnetic valve, a second electromagnetic valve, and a third electromagnetic valve; The outlet of the centrifugal pump is connected to the first solenoid valve, the second solenoid valve and the third solenoid valve respectively; the first solenoid valve is connected to the fuel tank through the fuel pipeline; the fuel tank is connected to the centrifugal pump through the fuel pipeline; the centrifugal pump, the motor and the oil-gas turbine are connected in sequence; the motor is also connected to the battery; the second solenoid valve is connected to the regenerative cooling channel; the third solenoid valve is connected to the nozzle inlet of the combustion chamber; the outlet and inlet of the oil-gas turbine are connected to the combustion chamber and the regenerative cooling channel respectively; The regenerative cooling passage can utilize the heat of the combustion chamber to crack the received hydrocarbon fuel into small-molecule cracked kerosene vapor, and transport the small-molecule cracked kerosene vapor to the oil-gas turbine.

2. A wide speed range ramjet engine fuel supply system driven by a cracking oil and gas turbine according to claim 1, characterized in that: The oil-gas turbine, the centrifugal pump and the motor are connected in a coaxial manner.

3. A method for supplying fuel to a wide-speed range ramjet engine driven by a cracking oil and gas turbine, characterized in that: Applied to a wide-speed range ramjet fuel supply system driven by a cracking oil and gas turbine as described in claim 1, the method comprises: In the initial stage, the motor is started, and the battery is used to provide the motor with a power supply with a stable voltage and a linearly increasing current, and the motor drives the centrifugal pump to pressurize the hydrocarbon fuel input into the tank; In the initial stage, the openings of the first solenoid valve and the third solenoid valve are linearly increased, and the second solenoid valve is kept in a closed state; When the output current of the battery reaches the maximum safe current, the second stage is entered; In the second stage, the opening of the first solenoid valve is fixed, and the opening of the second solenoid valve increases linearly; In the second stage, the opening of the third solenoid valve keeps increasing linearly until the opening design value of the third solenoid valve is reached, and then the linear increase of the opening of the third solenoid valve is stopped; When the output power of the oil and gas turbine reaches the pump boost power requirement, the battery is turned off.

4. The method for supplying fuel to a wide speed range ramjet engine driven by a cracking oil and gas turbine according to claim 3, characterized in that: Also includes: During the acceleration phase, the opening of the first solenoid valve is increased linearly, and the opening of the third solenoid valve is gradually reduced until the third solenoid valve is closed and the reduction of the opening of the third solenoid valve is stopped. The opening of the second solenoid valve is controlled to first increase to 0.93 and then decrease linearly.

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