KR101126861B1 - Combined cycle engine for hypersonic air-breathing and it's engine mode - Google Patents

Abstract

The present invention relates to a supersonic air-suction combined cycle engine device and an engine mode thereof, which take off at ground altitude and standstill in an atmosphere region and are driven to a high altitude of 30 km and a hypersonic area up to Mach 8. A center body for receiving fuel to generate propulsion of the rocket; A cowl body formed in a hollow can shape to surround the center body in the center; A rocket engine installed at the rear of the center body to suck air through the rocket ejection; A combustor installed on an inner surface of the cowl body to mix and combust air and fuel introduced through an inlet; A nozzle for obtaining thrust through combustion of the combustor; An injector installed at the rear of the injector and used in a flame maintenance situation; And a connecting pylon positioned at a rear portion of the center body and connected to the cowl body, wherein the engine mode of the apparatus is based on an operating environment of an aircraft, such as an ejector jet engine mode, a ramjet engine mode, and a scramjet engine mode. Act as a propulsion engine.

Ultrasonic, Air-Suction, Combined Cycle Engine, Rocket, Ejector Jet, Ramjet Engine, Scramjet Engine

Description

Combined cycle engine for hypersonic air-breathing and it's engine mode

The present invention relates to a hypersonic air intake hybrid cycle engine, and more particularly, to a supersonic air intake hybrid cycle engine which is a propulsion engine system capable of driving from the ground altitude, standstill to high altitude, and the hypersonic region of the atmosphere region. will be.

In general, a single propulsion system capable of flying a given speed range (Mach 0-8) is a rocket propulsion engine.

In addition, there are ramjet engines which cannot be started from the stationary state but can be driven in the Mach 2 or higher region and scramjet engines which can be driven in the Mach 5 or higher region.

However, the rocket propulsion engine, the ramjet engine and the scramjet engine have some problems as follows.

First, rocket propulsion engines must be loaded with oxidants because they cannot capture oxidants in the atmosphere. Because oxidants and fuels are stored in a liquefied state, they are stored under high pressure. Therefore, for safety, the system becomes huge, and the non-thrust and efficiency are lower than those of the ramjet engine and the scramjet engine which can be driven in a similar area. In addition, depending on the complexity of the system, the production cost is high, but it is basically used only once, so it cannot be reused.

Secondly, the ramjet engine operates on Mach numbers 2-6 using the ram effect of high-speed flight. The high speed air passes through a number of gradient shock waves and one weak vertical shock wave at the engine inlet, and the flow rate is reduced to subsonic velocity, which causes compression at the diffuser at the combustor, increasing the temperature and pressure. The characteristic of Ramjet engine is that combustion occurs at subsonic speed, and after combustion, air is expanded in the contraction-expansion nozzle to generate thrust. But Mach number 0 can't thrust. In the Mach 6 and above area, thermal dissociation occurs at the inlet of the combustor, resulting in a sharp drop in efficiency.

Third, unlike the ramjet engine, the scramjet engine generates thrust using only the expansion nozzle because the entire internal flow including the combustion chamber is supersonic. However, like the ramjet engine, it is impossible to operate in a stationary state.

An object of the present invention for solving the above problems is to achieve a supersonic flight in the atmosphere by combining a rocket engine, a ramjet engine and a scramjet engine appropriately, not only to reduce the weight of the system but also to stop the flight It is to provide a hypersonic air-sucking combined cycle engine device and its engine mode which are remarkably advantageous compared to the existing rocket propulsion system, such as flexibility in risk.

According to an embodiment of the present invention, an ultrasonic air suction type combined cycle engine apparatus for driving up to an altitude and a hypersonic region in an atmosphere region according to an embodiment of the present invention for achieving the above object is supplied with fuel and provided with a rocket. A center body generating a driving force of the; A cowl body formed in a hollow can shape to surround the center body in the center; A rocket engine installed at the rear of the center body to suck air through the rocket ejection; A combustor configured to configure a plurality of fuel injectors on an inner surface of the cowl body to mix and combust air and fuel introduced through an inlet; A nozzle for obtaining thrust through combustion of the combustor; An injector, which is installed in the center shape and the cowl body which is the rear of the injector, is used in a flame maintaining situation; And a connection pylon positioned at a rear portion of the center body and connected to the cowl body.

According to an embodiment of the present invention, the hypersonic air-suction combined cycle engine mode for driving the ground altitude and the high altitude and the hypersonic region even in the atmospheric region according to the embodiment of the present invention may vary from the ground take-off state to the Mach 3 depending on the operating environment of the vehicle. An ejector jet engine mode which is operated in the region and obtains thrust by burning by inhaling air using a rocket; A ramjet engine mode operating in the region from Mach 3 to Mach 6, in which combustion occurs in subsonic state using compressed air obtained with a Ram effect; And a scramjet engine mode operated in a region from Mach 6 to Mach 8, in which combustion occurs in a supersonic state.

The ultrasonic air suction type combined cycle engine device and its engine mode according to the present invention as described above have the following effects.

first. Unlike conventional hybrid engines with two or more combustors, a multi-cycle engine system operating from the standstill to Mach 8 using a single flow path and combustor from outside, with a control system and fuel injection system with two or more combustors While it is difficult to pursue the system weight reduction due to the dualization of the system, in the case of a single flow path type multiple cycle engine, the system weight reduction can be achieved.

second. Ultrasonic air-suction propulsion engines capable of driving over a range of ground altitudes, 30 km altitude at standstill, and a broad range of Mach 8, with operating altitudes and long ranges suitable for atmospheric missions. It is very likely to be selected as the propulsion system for single stage to orbit (SSTO) and two stage to orbit (TSTO) vehicles, and does not significantly affect the requirements of the propellant while the aircraft is rising. It is possible to repeat the use of cross-range flight without using the engine and select the alternative landing base even if some engines stop working when it is raised. Have

It will be described below with reference to the accompanying drawings, preferred embodiments of the ultrasonic air-suction combined cycle engine device and the engine mode thereof according to the present invention.

1 is a cross-sectional view showing a supersonic air suction type combined cycle engine apparatus according to the present invention, Figure 2 is a front cross-sectional view of the ultrasonic air suction type combined cycle engine apparatus according to the present invention, Figure 3 is carried out by the apparatus of the present invention 4 is a cross-sectional view showing the vehicle driving fluid and the injection path display, Figure 4 is a cross-sectional view showing the vehicle behavior and fuel injection mode when the ejector jet engine mode by the device of the present invention, Figure 5 is a ramjet by the device of the present invention FIG. 6 is a cross-sectional view illustrating a vehicle behavior and a fuel injection form when the engine mode is operated. FIG. 6 is a cross-sectional view illustrating a vehicle behavior and a fuel injection form when the scramjet engine mode is operated by the apparatus of the present invention.

1 and 2, according to an embodiment of the present invention, the supersonic air suction type combined cycle engine apparatus for driving up to the high altitude and the hypersonic region of the atmosphere region even in a ground altitude and a stationary state may include a center body ( 10), cowl body 20, rocket engine 30, combustor, nozzle 40, flame gun 50 and the connecting pylon (60).

The center body 10 is a portion for generating the propulsion force of the rocket by receiving the fuel, the configuration of the front, rear, inner surface of each part is as follows.

That is, the front of the center body 10 has an axially symmetrical inlet shape, and serves as a diffuser at subsonic speed so as to smoothly suck the flow, and the amount of air trapped in the supersonic region.

In addition, the rocket nozzle is disposed at the rear of the center body 10 so as to face the inlet of the combustion chamber at the center of the engine, and the rocket engine 30 ejects the air in the ejector jet engine mode of the ultrasonic air suction type combined cycle engine. It is installed for the purpose of sucking through.

A fuel and an oxidant tank (not shown) and a rocket combustion chamber (not shown) of the rocket engine 30 are positioned inside the center body 10, so that the fuel and the oxidant may regenerate and cool the center body 10. To protect the center body 10 from aerodynamic heating.

The cowl body 20 is formed in a hollow can shape to surround the center body 10 in the center.

The front of the cowl body 20 has a cut-off shape so that a shock shock (Blunt shock or bow shock) does not occur at the leading edge in the supersonic mode.

Inside the cowl body 20, a fuel tank (not shown) and various facilities (not shown) for injecting fuel are embedded in the fuel injector 45 for fuel injection described below.

The rocket engine 30 is installed at the rear of the center body 10 to serve to suck air through the rocket ejection.

That is, the rocket engine 30 is installed to suck air through the rocket ejection in the ejector jet engine mode of the ultrasonic air suction type combined cycle engine apparatus of the present invention.

The combustor is installed to configure a plurality of fuel injectors 45 on the inner surface of the cowl body 20 to serve to mix and burn the air and fuel introduced through the inlet.

As described above, the fuel injector 45 of the combustor located on the inner surface of the cowl body 20 may be largely divided into three parts.

That is, the fuel injector 45 of the combustor may include a combustor introduction portion where the first injector 45-1 is located, a combustor parallel portion where the second injector 45-2 is located, and a third injector 45-3. It can be divided into three parts located combustor extension.

The nozzle 40 is for obtaining thrust through combustion of the combustor, and is located on the inner surface of the cowl body 20.

The nozzle 40 basically takes an enlarged nozzle shape and in order to form a nozzle throat, fuel injection is performed at the nozzle inlet to form a thermal throat.

The flame prosthesis 50 is installed in the shape of a cavity in the center body 10 and the cowl body 20, which are the rear of the first injector 45-1, and is used in a flame holding situation.

That is, in the case of the combustor introduction portion in which the first injector 45-1 is located, the supersonic combustion 50 is positioned not only in the cowl body 20 but also in the center body 10 so that the supersonic combustion as in the scramjet engine mode is performed. It is to keep the flame at ease.

The connection pylon 60 is located at the rear of the center body 10 and serves to connect with the cowl body 20.

As shown in FIG. 2, the connecting pylon 60 connecting the cowl body 20 and the center body 10 is located at an extension part of the rear part rather than the front part of the center body 10 in which the suction port is located. And 4 locations in total in the radial direction.

The ultrasonic air suction type combined cycle engine apparatus according to the present invention is preferably made in a circular shape in consideration of structural safety and convenience of internal component arrangement.

The engine mode for the ultrasonic air suction type combined cycle engine apparatus according to the present invention as described above will be described with reference to FIGS. 3 to 6.

The ultrasonic air-suction combined cycle engine is an engine aiming to reach an altitude of about 30 km and a flying Mach number 8 starting at sea level and static.

The engine described above is according to the operating mode of the vehicle, that is, the flight Mach number, the ejector jet engine mode (see FIGS. 3 and 4), the ramjet engine mode (see FIG. 5), and the scramjet engine mode (see FIG. 6). Is made of.

The engine apparatus according to the present invention is an ejector jet engine mode operating in the area from the ground take-off state to the Mach 3 according to the flying Mach number, a ramjet engine mode operating in the area from Mach 3 to Mach 6, and Mach 6 to the Mach 6 It operates in three of the scramjet engine modes operating in areas up to eight.

The four first fuel injectors 45-1, the second fuel injectors 45-2, the third fuel injectors 45-3, and the third fuel injector may be switched between the ejector jet engine mode, the ramjet engine mode, and the scramjet engine mode. 4 is implemented according to the injection method of the fuel by the fuel injector 45-4.

The above three engine modes are markedly distinguished according to the operation modes of the respective fuel injectors 45-1 to 45-4, which are as follows.

In the ejector jet engine mode, as shown in FIG. 4, the thrust is obtained by inhaling air by using an ejection effect using the rocket engine 30 as a working fluid.

At this time, the fuel is injected to the fourth injector 45-4 to generate thermal suffocation to implement thermal suffocation of the nozzle (thermal throat 45-5, see FIG. 1).

In the ramjet engine mode, as shown in FIG. 5, the air sucked at supersonic speed reaches the combustor via a subsonic diffusion in which combustion occurs in a subsonic state by using a vertical shock wave and compressed air obtained by a ram effect. Thrust by combustion and expansion.

Here, the second injector 45-2 and the third injector 45-3 inject fuel for main combustion, and thermal suffocation with the fourth injector 45-4 similarly to the ejector jet engine mode. To generate thermal suffocation (45-5, see FIG. 1).

In the scramjet engine mode, as shown in FIG. 6, ignition occurs in the first injector 45-1 for proper supersonic combustion.

Further, in order to prevent thermal suffocation, additional combustion is generated in the third injector 45-3, which is an expansion section.

However, in the scramjet mode as described above, unlike the ejector jet engine mode and the ramjet engine mode, thermal suffocation using the fourth injector 45-4 is not implemented.

That is, the switch from the ramjet engine mode to the scramjet engine mode occurs by terminating the thermal throat by terminating the fourth injector 45-4 located in the nozzle 40 part.

In addition, the flame is maintained in the scramjet engine mode by installing the cavity 4 having a cavity shape behind the first fuel injector.

Therefore, the ultrasonic air-suction combined cycle engine apparatus according to the present invention is an ejector jet engine mode (mach 0 to 3), a ramjet engine mode, using a small rocket in sequence at an altitude of 30 km at an altitude, at a standstill, and a flight area of Mach 8. (Mach 3-6) and Scramble Jet engine modes (Mach 6-8) can be implemented in a single flow path (intake, combustor, nozzle), allowing ultra-sonic flight at ultra-light weight compared to conventional rockets. will be.

Although the above has been illustrated and described with respect to the preferred embodiments of the present invention, the present invention is not limited to the above-described embodiments, but in the art to which the present invention pertains without departing from the spirit of the invention as claimed in the claims. Various modifications can be made by those skilled in the art, and such changes will fall within the scope of the claims set forth.

1 is a cross-sectional view showing an ultrasonic air suction type combined cycle engine apparatus according to the present invention.

Figure 2 is a front sectional view of the ultrasonic air suction type combined cycle engine apparatus according to the present invention.

3 is a cross-sectional view showing the vehicle drive fluid and injection path representations implemented by the apparatus of the present invention.

4 is a cross-sectional view showing the vehicle behavior and fuel injection mode when the ejector jet engine mode is operated by the apparatus of the present invention.

5 is a cross-sectional view showing the vehicle behavior and fuel injection mode when the ramjet engine mode is operated by the apparatus of the present invention.

Figure 6 is a cross-sectional view showing the vehicle behavior and fuel injection mode when the operation of the scramjet engine mode by the apparatus of the present invention.

* Brief description of symbols for the main parts of the drawings *

10: center body 20: cowl body

30: rocket engine 40: nozzle

45: fuel injector 45-1: first injector

45-2: second injector 45-3: third injector

45-4: fourth injector 50: flame retardant

60: connection pylon

Claims (12)

In the supersonic air suction type combined cycle engine device which is driven to the high altitude and the supersonic area even in the ground altitude and the stationary state of the atmosphere region, A center body 10 receiving fuel and generating propulsion force of the rocket; A cowl body 20 formed in a hollow can shape to surround the center body 10 in the center; A rocket engine (30) installed at the rear of the center body (10) to suck air through the rocket ejection; A combustor configured to install a plurality of fuel injectors 45 on an inner surface of the cowl body 20 to mix and combust air and fuel introduced through an inlet; A nozzle 40 for obtaining thrust through combustion of the combustor; An inflammator 50 installed in the center body 10 and the cowl body 20 which are the rear of the injector in a shape of a cavity and used in a flame holding situation; And Included in the rear of the center body 10, the connection pylon 60 connected to the cowl body 20; including, The front of the center body 10 takes the role of a diffuser at subsonic speed so as to smoothly suck the flow, and in the supersonic region has an axisymmetric inlet shape so that the air trapping amount is constant, the rear of the center body 10 is a rocket nozzle It is arranged to face the inlet of the combustion chamber in the center of the engine, and the supersonic air suction type combined cycle engine device, characterized in that the fuel and oxidant tank of the rocket engine 2 and the rocket combustion chamber are located inside the center body (10). . delete The method of claim 1, The front of the cowl body 20 has a cut-off shape so that a shock shock (Blunt shock or bow shock) does not occur at the leading edge in the supersonic mode, and the cowl body 20 Ultrasonic air suction type combined cycle engine device, characterized in that provided with a fuel tank and various facilities for injecting fuel to the fuel injection injector. The method of claim 1, The fuel injector 45 of the combustor includes a combustor introduction portion in which the first injector 45-1 is located, a combustor parallel portion in which the second injector 45-2 is located, and a combustor in which the third injector 45-3 is located. Ultrasonic air suction type combined cycle engine device characterized by being divided into three parts of the extension 5. The method of claim 4, Ultrasonic speed, characterized in that the center body 10 and the cowl body 20 of the combustor introduction portion where the first injector (45-1) is located is provided with a flame gun (50) for maintaining the flame during supersonic combustion Air-suction combined cycle engine unit. The method of claim 1, The connection pylon (60) is a supersonic air suction type combined cycle engine device, characterized in that installed in four places in the radial direction. The method of claim 1, The supersonic air suction type combined cycle engine device, characterized in that the engine is formed in a circular shape. The supersonic air suction type hybrid cycle engine mode of driving the ground altitude and the high altitude and the supersonic area in the atmosphere region using the hypersonic air suction type hybrid cycle engine device according to any one of claims 1 to 3 Depending on the operating environment of the aircraft, An ejector jet engine mode operated in the area from the ground take-off state to Mach 3 and burning by inhaling air using a rocket to obtain thrust; A ramjet engine mode operating in the region from Mach 3 to Mach 6, in which combustion occurs in subsonic state using compressed air obtained with a Ram effect; And It operates in the area from Mach 6 to Mach 8 and consists of a scramjet engine mode in which combustion occurs at supersonic speed, Four first fuel injectors 45-1, second fuel injectors 45-2, and third fuel injectors 45-3 are used to switch between the ejector jet engine mode, the ramjet engine mode, and the scramjet engine mode. And a fourth fuel injector 45-4, wherein the supersonic air suction type combined cycle engine mode is used. delete The method of claim 8, The supersonic air suction type combined cycle engine mode, characterized in that the flame is maintained in the scramjet engine mode by installing a cavity having a cavity shape behind the first fuel injector. The method of claim 8, In the ejector jet engine mode and the ramjet engine mode, the supersonic air suction type combined cycle, characterized in that the thermal throat occurs by injecting fuel from the fourth injector (45-4) located in the nozzle 40 parts. Engine mode. The method of claim 8, The switching from the ramjet engine mode to the scramjet engine mode may occur by terminating a fourth thermal injector by terminating the fourth injector 45-4 located in the nozzle 40 part. Combined cycle engine mode.

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