A fuel supply system and method for a wide-speed range ramjet engine driven by a cracking oil and gas turbine

Abstract

This invention belongs to the field of ramjet technology and provides a wide-speed range ramjet fuel supply system and method driven by a pyrolysis oil-gas turbine. The system comprises a fuel tank, a centrifugal pump, a motor, an oil-gas turbine, a battery, an electromagnetic control module, fuel lines, a pyrolysis fuel vapor line, a combustion chamber, and a regenerative cooling channel on the outer wall of the combustion chamber. Through the connection between the centrifugal pump, the regenerative cooling channel, and the oil-gas turbine, the system utilizes the cracking of hydrocarbon fuel into small-molecule pyrolysis kerosene vapor to drive the turbine rotor to produce work. The motor then assists in starting the ramjet, thereby resolving the power generation challenges of the ramjet mode and alleviating thermal protection issues.

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 vehicles generally refer to aircraft that fly at speeds exceeding five times the speed of sound. They are a new type of aircraft capable of large airspace, supersonic speeds, long distances, and high precision. These include hypersonic ballistic missiles, space planes, hypersonic reconnaissance aircraft, hypersonic transport aircraft, and reusable space-to-ground shuttles. Scramjets allow incoming air to enter the combustion chamber at supersonic speeds for combustion. Therefore, combined engines based on scramjets are the optimal power source for achieving hypersonic flight. Because scramjets must operate at a certain speed to start and cannot independently complete the entire process from takeoff to hypersonic flight, several combined cycle embodiments based on scramjets have emerged. Among these, turbo-ramjet combined cycle engines integrate the structural structure and operating processes of both turbine and ramjets, leveraging the strengths of each engine within its respective operating range. This makes them ideal power sources for hypersonic aircraft. For hypersonic aircraft capable of long-duration and long-distance flight, the effective management and utilization of onboard energy significantly impacts 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 scramjet engines is greater than that of rocket engines.

[0003] However, because ramjets lack rotating parts, they cannot extract energy through traditional shaft work methods. Furthermore, as the flight Mach number increases, the total temperature, total pressure, and velocity of the airflow within the scramjet combustion chamber continuously increase during extended operation, placing significant aerodynamic and combustion heat loads on the combustion chamber structure. Summary of the Invention

[0004] In order to overcome the deficiencies of the prior art, the present invention aims 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 regenerative cooling channel on the outer wall of the combustion chamber; the electromagnetic control module comprises: a first solenoid valve, a second solenoid valve, and a third solenoid 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 via the fuel line; the fuel tank is connected to the centrifugal pump via the fuel line; 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 channel can utilize the heat of the combustion chamber to crack the received hydrocarbon fuel into small-molecule cracked kerosene vapor, and transmit the small-molecule cracked kerosene vapor to the oil-gas turbine.

[0009] Preferably, the oil-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 from 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 it reaches the design opening value of the third solenoid valve, and then the linear increase of the opening of the third solenoid valve is stopped;

[0016] When the output power of the oil-gas turbine reaches the pump boost power requirement, the battery is shut down.

[0017] Preferably, it also includes:

[0018] During the acceleration phase, the opening of the first solenoid valve is linearly increased, and the opening of the third solenoid valve is gradually reduced until the third solenoid valve is closed, at which point the reduction in 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 linearly decrease.

[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 between a centrifugal pump, a regenerative cooling channel and the oil and gas turbine, the system solves the power extraction problem of the ramjet mode and alleviates the thermal protection problem, and realizes the use of hydrocarbon fuel to crack into small molecule cracking kerosene vapor to drive the turbine rotor to perform work. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or technical embodiments in the prior art, the following briefly introduces the drawings required for use in the embodiments. 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 any creative labor.

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

[0023] Figure 2 A schematic flow chart of a wide-speed range ramjet engine fuel supply method 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-Cracked oil and gas pipeline, 9-Regeneration cooling channel. DETAILED DESCRIPTION

[0026] The following will clearly and completely describe the technical embodiments of the present invention in conjunction with the accompanying drawings 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 making creative efforts 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 power extraction problem of 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 according to 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 regenerative cooling channel 9 on the outer wall of the combustion chamber; the electromagnetic control module 6 includes: 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 via the fuel line 7; the fuel tank 1 is connected to the centrifugal pump 2 via the fuel line 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. The motor 3 drives the centrifugal pump 2 to pressurize the hydrocarbon fuel input from the fuel tank 1;

[0035] Step 200: In the initial stage, linearly increase the openings of the first solenoid valve 601 and the third solenoid valve 603, and keep the second solenoid valve 602 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-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, at which point the reduction in 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 linearly decrease.

[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 under different flight Mach numbers.

[0044] Specifically, during the ramjet engine startup process, the fuel supply embodiment keeps the diverter valve in front of the regenerative cooling channel 9 closed, opens the diverter valve and the return valve after the pump, and the fuel pressurized by the centrifugal pump 2 is injected into the combustion chamber through the fuel line 7. The battery 5 drives the centrifugal pump 2 to work via the motor 3. After a period of time, the combustion chamber wall temperature reaches the fuel cracking requirement, and the diverter valve in front of the regenerative cooling channel 9 is opened, allowing the fuel pressurized by the centrifugal pump 2 to pass through the regenerative cooling channel 9, changing from liquid to high-temperature, high-pressure cracked mixed oil and gas. The fuel 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 perform work, thereby meeting the energy requirements of the centrifugal pump 2 during the startup process. The calculation input of the ramjet engine fuel supply embodiment for a wide speed range during the ramjet engine startup 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 Maximum pump 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 this example, at the final steady-state state during the startup process, the pump power was 113.42 kW, the cracking oil and gas turbine 4 was 143.83 kW, and the motor 3 was operating in generator mode, charging the battery. During the startup process, the battery, acting as the sole energy source, provided energy to the turbopump for a total of 2.2 seconds.

[0048] Furthermore, during the acceleration of the ramjet engine from flight Mach 5 to flight Mach 6, the opening of the diverter valve in front of the regenerative cooling channel 9 decreases linearly from 0.78 to 0.56, the opening of the post-pump diverter valve 603 decreases linearly from 0.05 to 0, and the opening of the post-pump return valve increases linearly from 0.68 to 0.81. During this process, the fuel pressurized by the centrifugal pump 2 passes through the regenerative cooling channel 9, transforming from a liquid state into a high-temperature, high-pressure cracked oil and gas mixture. This mixture then 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 produce work and meet the energy requirements of the centrifugal pump 2 during acceleration. The calculation inputs for the wide-speed range ramjet engine fuel supply embodiment during the ramjet engine acceleration process are shown in Table 2 below.

[0049] Table 2

[0050]

[0051] According to calculations in this embodiment, at the final steady-state state during the startup process, the pump power is 113.42 kW. The power of the cracking oil and gas turbine 4 decreases from 127.68 kW to 91.9 kW. The motor 3 switches from generator mode to motor mode, and the overall system switches from battery charging to battery discharging. The gas flow rate of the cracking oil and gas turbine 4 decreases from 1.96 kg / s to 1.41 kg / 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 achieve the use of hydrocarbon fuel cracking into small molecule cracked kerosene vapor to drive the turbine rotor to perform work, and uses a motor to assist in driving the ramjet engine to start, thereby solving the power extraction problem of the ramjet mode and alleviating 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] This document uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only intended to help understand the method and core concept of the present invention. At the same time, those skilled in the art will find that the specific implementation methods and application scopes may vary based on the concept of the present invention. In summary, the contents of this specification should not be construed 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 line, a cracked fuel vapor line, a combustion chamber, and a regenerative cooling channel on the outer wall of the combustion chamber; the electromagnetic control module includes: a first solenoid valve, a second solenoid valve, and a third solenoid 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 via the fuel line; the fuel tank is connected to the centrifugal pump via the fuel line; 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 channel can utilize the heat of the combustion chamber to crack the received hydrocarbon fuel into small-molecule cracked kerosene vapor, and transmit the small-molecule cracked kerosene vapor to the oil-gas turbine.

2. The wide-speed range ramjet 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 fuel supply method for a wide-speed range ramjet engine driven by a cracking oil and gas turbine, characterized in that: The method applied to the wide-speed range ramjet fuel supply system driven by a cracking oil and gas turbine as described in claim 1 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 from 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 it reaches the design opening value of the third solenoid valve, and then the linear increase of the opening of the third solenoid valve is stopped; When the output power of the oil-gas turbine reaches the pump boost power requirement, the battery is shut down.

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 linearly increased, and the opening of the third solenoid valve is gradually reduced until the third solenoid valve is closed, at which point the reduction in 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 linearly decrease.

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