JPH0893555A - Ram combustion device - Google Patents

Abstract

PURPOSE: To prevent generation of the blowoff phenomenon of flame by achieving high combustion efficiency within the wide flight Mach range while holding pressure loss to the low level, and preventing the inside of a main combustor- type flame stabilizer from being made into the fuel excessive rich state, in a ram combustion device. CONSTITUTION: A ram combustion device is provided with a main combustor- type flame stabilizer 10 arranged inside a combustor duct 2, and for performing combustion of fuel, a sub combustion chamber 22 arranged in the center position on the front end of the main combustor-type flame stabilizer, an upstream opening 10e arranged between the sub combustion chamber and the peripheral wall of the main combustor-type flame stabilizer, and for partially taking the air flow into the main combustor-type flame stabilizer, and a second combustion nozzle 24 for supplying fuel between the peripheral wall of the main combustor- type flame stabilizer and the peripheral wall of the sub-combustion chamber.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a ram combustion device,
In particular, the present invention relates to a technique for operating a ramjet engine with high combustion efficiency in a wide flight Mach number range.

[0002]

BACKGROUND OF THE INVENTION Ramjet engines do not have an air compressor like turbojet engines,
The air flowing at high speed into the combustor duct is compressed using ram pressure, and the structure is simple, and
It is considered that the combustion efficiency can be improved as the navigation speed of the airframe increases, and for example, application to supersonic aircraft and space shuttles with navigation speeds of Mach number 2.5 to 5 has been studied.

FIG. 9 shows a schematic structure of a ramjet engine. Reference numeral 1 is a diffuser, 2 is a combustor duct, 3 is a combustion chamber, 4 is a jet nozzle, and 5 is a combustion device (ram combustion device). . Then, as the combustion device 5, those shown in FIGS. 10 and 11 have been proposed.

In the combustion apparatus 5 shown in FIG. 10, a plurality of fuel nozzles 6 are arranged inside a cylindrical combustor duct 2, and an annular frame holder (flame holder) 7 is provided at a position downstream of each fuel nozzle 6. And the spark plug 8 is arranged in the vicinity of the frame holder 7, and the fuel nozzle 6 and the frame holder 7 are provided on the inner surface of the combustor duct 2 with a plurality of cantilever beams arranged at intervals in the circumferential direction. It is supported by a support beam 9. Then, the fuel is injected from the plurality of ejection holes 6a of the fuel nozzle 6 into the air flow G indicated by the arrow to form a mixed flow, and the spark plug 8
At the same time, the mixed flow is ignited, and the V-shaped cross section of the frame holder 7 causes a low flow velocity region with a large amount of turbulence in the subsequent flow to perform flame holding for maintaining the combustion state.

In the combustion apparatus 5 of the example shown in FIG. 10, when air is compressed by an appropriate ram pressure as in the case of high Mach, the mixed flow of air and fuel becomes a low speed region behind the frame holder 7. Based on this, in addition to maintaining the combustion state, the mixing and stirring of air and fuel is promoted, and high combustion efficiency can be obtained.

On the other hand, in the combustion apparatus 5 of the example shown in FIG. 11, a hollow hemispherical main combustor type flame stabilizer 10 is arranged in the combustion chamber 3 of the cylindrical combustor duct 2, and the main combustor type flame stabilizer is provided. The main combustor type flame stabilizer is configured so that the gutta type flame stabilizers 11 are circumferentially spaced on the downstream side outer periphery of the chamber 10 and the fuel nozzle 12 is connected to the main combustor type flame stabilizer 10. The portions of 10 and the gutta-type flame stabilizer 11 are supported by a plurality of cantilever-shaped support beams 9. Then, when the fuel supply system 13 is operated, fuel is injected from the fuel nozzle 12 to be ignited by the spark plug 8 and, while performing flame holding based on the shape of the main combustor type flame stabilizer 10, while maintaining the gutta type flame holding flame. The V-shaped cross section of the vessel 11 is used to generate a low flow velocity region with a large amount of turbulence to achieve complete combustion by mixing the combustion flame and air.

[0007]

However, in the case where the combustion device 5 has the structure of the example of FIG. 10, the ram pressure is used to utilize the ram pressure of the combustor duct 2 in the navigation state in which the Mach number is small or in the subsonic navigation state. Since the internal air flow cannot be compressed sufficiently and the temperature of the air rises insufficiently, it is likely that the combustion efficiency is lowered and the ignitability of the fuel is adversely affected. Further, in the case where the combustion device 5 has the structure of the example in FIG. 11, in the supersonic navigation state in which the Mach number is large, the amount of fuel supplied from the fuel nozzle 12 increases and It is conceivable that the increase in the amount of air introduced from the air introduction hole 10a cannot be followed, the inside of the main combustor type flame stabilizer 10 becomes in a fuel rich state, and the combustion efficiency decreases.

The present invention has been made in view of these problems and has the following objects. To achieve high combustion efficiency in a wide flight Mach number range while keeping pressure loss at a low level. To reduce NOx in the high Mach flight range. Preventing the inside of the main combustor type flame stabilizer from becoming rich in fuel and preventing a decrease in combustion efficiency.

[0009]

As a ram combustion device, a main combustor type flame stabilizer disposed inside a combustor duct for combusting a supplied fuel and a front end of the main combustor type flame stabilizer are provided. A sub-combustion chamber that is arranged at the central position and has an opening downstream and is supplied with fuel from the first fuel nozzle; and a part of the air flow that is arranged at the upstream end of the sub-combustion chamber And a second fuel nozzle disposed near the upstream opening for supplying fuel between the peripheral wall of the main combustor type flame stabilizer and the peripheral wall of the auxiliary combustion chamber. Adopted. Instead of the upstream opening, a configuration is adopted in which a swirler that generates a swirling flow is generated between the auxiliary combustion chamber and the peripheral wall of the main combustor type flame stabilizer, and fuel is supplied to the inside of the swirler around the swirler. A second fuel nozzle is provided. At the downstream end of the peripheral wall of the sub-combustion chamber, a flare portion that is spread in the downstream direction or a lobe mixer that guides the internal and external fluids in both radial directions and mixes them is arranged. As the lobe mixer, a lobe mixer having a corrugated peripheral wall in cross-sectional shape and having a corrugated height gradually increasing in both radial directions as it goes downstream is adopted. A premix chamber for diluting and mixing the fuel with air is formed between the peripheral wall of the main combustor type flame stabilizer and the peripheral wall of the auxiliary combustion chamber. The second fuel nozzle is provided with an annular fuel header that guides the fuel in the circumferential direction and fuel injection holes that connect the fuel header and the swirler at a plurality of points. The fuel ejection holes are arranged at the swirler position or at the downstream position of the swirler. A plurality of gutta-type flame stabilizers are arranged at a downstream position in the peripheral wall of the main-combustor-type flame stabilizer at intervals in the circumferential direction, and a main-combustor-type flame stabilizer is provided at an upstream position of the gutta-type flame stabilizer. An airflow inlet that penetrates the peripheral wall of the vessel is arranged.

[0010]

The fuel is supplied from the first fuel nozzle to the auxiliary combustion chamber and ignited. By separating the auxiliary combustion chamber by its peripheral wall, the internal fuel concentration is maintained and flame holding is performed. When the fuel is supplied from the second fuel nozzle between the peripheral wall of the main combustor type flame stabilizer and the peripheral wall of the auxiliary combustion chamber, the fuel merges with a part of the air flow taken from the upstream opening, and And the air are mixed, the mixed flow is supplied to the inside of the main combustor type flame stabilizer, and is ignited by the flame of the auxiliary combustion chamber, so that the combustion range is expanded. If a swirler is arranged between the sub-combustion chamber and the peripheral wall of the main combustor type flame stabilizer, a swirling force is applied to the air flow passing through the swirler, and the mixed flow of fuel and air flow becomes a swirl state. Is supplied to the inside of the main combustor type flame stabilizer to promote combustion. When the flare part is arranged in the auxiliary combustion chamber, the flame inside the auxiliary combustion chamber gradually expands inside the main combustor type flame stabilizer, and the lobe mixer is arranged at the downstream end of the peripheral wall of the auxiliary combustion chamber. In this case, the mixing property of the internal and external fluids in the auxiliary combustion chamber is promoted based on the shape in which the height of the waveform gradually increases. Between the peripheral wall of the main combustor type flame stabilizer and the peripheral wall of the auxiliary combustion chamber, a pre-mixing chamber is formed together with the addition of the flare portion, and fuel and air are mixed. In the second fuel nozzle, the fuel is guided in the circumferential direction at the fuel header portion, and the fuel is ejected from the fuel ejection holes at a plurality of locations to the inside of the swirler or a position downstream thereof, thereby causing a swirling mixed flow. Then, the mixture is promoted by being sent to the premix chamber. The swirling mixed flow formed by the swirler is spread inside the main combustor type flame stabilizer, and is mixed with the air taken in from the airflow inlet in the entire area of the main combustor type flame stabilizer. Burned,
Further, it is led to a complete combustion state by mixing with the internal air flow of the combustor duct. The flame-holding action due to these combined functions is caused by the shapes of the main combustion chamber-type flame stabilizer and the gutta-type flame-maintainer inside the sub-combustion chamber, the part of the low velocity region due to the vortex generated downstream of the sub-combustion chamber. It is carried out at a plurality of places in the low flow velocity region based on.

[0011]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A first embodiment of a ram combustion device according to the present invention will be described below with reference to FIGS. In each drawing, reference numeral 20 is a ram combustion device, 21 is a first fuel nozzle, 22 is a secondary combustion chamber, 23 is a swirler, and 24 is a second
Fuel nozzle, 25 is a premixing chamber, 26 is a fuel control means,
Reference numeral 27 is a fuel control unit, 28 is a fuel supply means for ignition, and 29 is a fuel supply means for main combustion.

In the ram combustion device 20, a plurality of main combustor types are arranged, for example, in a state of being supported by the support beam 9 on the inner wall of the combustor duct 2 and spaced apart in the circumferential direction of the combustor duct 2. A flame stabilizer 10, a plurality of gutter type flame stabilizers 11 arranged circumferentially at a position near the downstream opening of the main combustor type flame stabilizer 10, and a main combustor type flame stabilizer 10 The first fuel nozzle 21 arranged at the front end (upstream wall) of the main fuel and supplying fuel to the central position, and the first fuel nozzle 21 arranged at the central position of the front end of the main combustor type flame stabilizer 10 and having an opening at the downstream side. The auxiliary combustion chamber 22 to which fuel is supplied from the nozzle 21, and the auxiliary combustion chamber 22 and the peripheral wall 10b in the vicinity of the upstream end of the main combustor type flame stabilizer 10 are arranged in a penetrating state in the upstream and downstream directions and the air flow. A swirl for introducing a part of G into the main combustor type flame stabilizer 10 to generate a swirling flow. 23, a second fuel nozzle 24 arranged around the swirler 23 and supplying fuel into the swirler 23, between the peripheral wall 10b of the main combustor type flame stabilizer 10 and the peripheral wall 22a of the auxiliary combustion chamber 22. Premix chamber 25 formed in
And a fuel control means 26 connected to the first fuel nozzle 21 and the second fuel nozzle 24.

As shown in FIGS. 1 and 3, the main combustor type flame stabilizer 10 has a guide portion 10c, for example, in an annular shape, at a position slightly upstream from the gutta type flame stabilizer 11.
Are arranged integrally with the peripheral wall 10b and project outward in the radial direction, and a plurality of airflow inlets 10d penetrating the peripheral wall 10b are arranged at the inner position of the guide portion 10c. At the downstream end of the peripheral wall 10b, a skirt-shaped wall 10f that is widened in the downstream direction along the longitudinal direction of the plurality of gutta-type flame stabilizers 11 is integrally arranged.

The auxiliary combustion chamber 22 is formed in a cylindrical shape, and is attached to the front end of the main combustor type flame stabilizer 10 in a state where the upstream side is closed and the downstream side is opened. , The tip of the first fuel nozzle 21 is placed inside. Inside the auxiliary combustion chamber 22, an ignition plug 8 is arranged as shown in FIG. 1, and the peripheral wall 22 of the auxiliary combustion chamber 22 is disposed.
The a is extended to a state in which it projects further downstream than the swirler 23, and the flare portion 22b, which is widened in the downstream direction, is integrally connected to the downstream end of the peripheral wall 22a.

The second fuel nozzle 24 has a fuel supply pipe 24a for supplying the fuel from the main combustion fuel supply means 29 to the main combustor type flame stabilizer 10, and the fuel supply pipe 24a.
An annular fuel header 24b that is connected to and is disposed on the peripheral wall 10b around the swirler 23 to guide the fuel in the circumferential direction,
As shown in FIGS. 1 and 2, the fuel header 24b and the twist blades 23a of the swirler 23 are connected to each other at a plurality of points, and a fuel injection hole 24c for blowing the fuel in parallel is provided.

The premixing chamber 25 is located downstream of the swirler 23, and the peripheral wall 1 of the main combustor type flame stabilizer 10 is located in the premixing chamber 25.
0b, the peripheral wall 22a of the auxiliary combustion chamber 22, and the flare portion 22b.

In the fuel control means 26, the fuel supply amount required for ignition or maintaining the flight Mach number is calculated, and the fuel is distributed to the first fuel nozzle 21 and the second fuel nozzle 24. A fuel control unit 27 for setting the ratio according to the Mach number in the ignition mode and the flight mode,
Ignition fuel supply means 28 arranged in an intervening state between the first fuel nozzle 21 and the second fuel nozzle 24 and supplying fuel according to a fuel distribution ratio in accordance with a command from the fuel control unit 27.
And a main combustion fuel supply means 29.

The ram combustion device 2 configured as described above
At 0, when the ignition mode is selected, the fuel is supplied only to the first fuel nozzle 21 and burned. That is, the fuel control unit 27 calculates the fuel supply amount necessary for ignition, and the ignition fuel supply unit 2
By injecting fuel from the first fuel nozzle 21 by the operation of 8, the fuel concentration in the main combustor flame stabilizer 10, particularly in the internal atmosphere of the auxiliary combustion chamber 22, is optimized.
By operating the spark plug 8, the fuel supplied into the auxiliary combustion chamber 22 is ignited, and the combustion state is continued. At this time, if the flare portion 22b is arranged, the flame inside the auxiliary combustion chamber 22 gradually spreads inside the main combustor type flame stabilizer 10 as it goes downstream.

When the flight mode is selected, combustion is performed with the fuel supply to the first fuel nozzle 21 and the fuel supply to the second fuel nozzle 24 added. When the fuel is supplied from the second fuel nozzle 24 to the inside of the swirler 23 at a plurality of locations in parallel, the fuel is supplied in parallel to the auxiliary combustion chamber 22 formed near the inner center of the main combustor flame stabilizer 10. Ignition is performed by the flame downstream of the peripheral wall 22a, and the flame is guided by the flare portion 22b to expand the combustion range. Further, the peripheral wall 1 of the main combustor type flame stabilizer 10 is further expanded.
By passing from 0b through the skirt-shaped wall 10f,
The combustion flame F spreads throughout the combustion chamber 3.

At this time, the fuel control unit 27 causes the air insertion amount of the combustor duct 2 corresponding to the flight Mach number, the air intake amount into the main combustor type flame stabilizer 10 by the swirler 23, and the air flow introduction port. The amount of fuel supplied to the first fuel nozzle 21 and the second fuel nozzle 24, which takes into consideration conditions such as the amount of air taken in from 10d, is calculated, and the combustion flame F is guided so as to lead to a complete combustion state.

Since the airflow velocity inside the combustor duct 2 changes as the flight Mach number increases, the amount of air taken into the inside of the main combustor type flame stabilizer 10 via the swirler 23 and the airflow inlet 10d are changed. Via main combustor type flame stabilizer 1
The amount of air taken into the inside of 0 is the combustor duct 2
Changes in a state almost proportional to the insertion amount of the air flow G. Therefore, it becomes possible to adjust the relationship between the fuel supply amount and the air supply amount inside the main combustor type flame stabilizer 10 and the air-fuel ratio to the optimum state, and the inside of the main combustor type flame stabilizer 10 can be adjusted. Suppress the occurrence of fuel rich condition.

The air taken into the main combustor type flame stabilizer 10 via the swirler 23 takes in a part of the air flow G as shown in FIG. , A swirling vortex A is generated as indicated by a chain line arrow, and the fuel from the first fuel nozzle 21 and the second fuel nozzle 24 is entrained to promote the mixing of the fuel and the air.

The fuel supplied to the main combustor type flame stabilizer 10 is the first fuel nozzle 21 and the second fuel nozzle 2.
4, the fuel is supplied to the central portion of the main combustor type flame stabilizer 10 by the first fuel nozzle 21, and the fuel is supplied in a swirling flow state via the swirler 23. Therefore, the fuel that has passed through the swirler 23 is sent to the central portion of the main combustor type flame stabilizer 10 by the vortex B shown by the broken line generated in the center of the swirling vortex A, and mixing is promoted. As described above, in the main combustor type flame stabilizer 10, the fuel is directly merged with the swirling vortex A to be in a premixed state,
Next, mixing is promoted by stirring the swirling vortex A with the vortex B, and further air is merged from the airflow inlet 10d to improve the mixing property.

On the other hand, since the peripheral wall 22a separates the sub-combustion chamber 22 and the premixing chamber 25, the first fuel nozzle 2
The combustion flame of the fuel injected from No. 1 is not affected by the swirling vortex A at least in the area inside the premixing chamber 25, and the combustion is stably performed even when the air amount changes due to the change in the flight Mach number. Be done.

The flame holding of each part will be described. The flame holding action due to the inside of the auxiliary combustion chamber 22 being isolated from the surroundings, and the flame holding action due to the low flow velocity region based on the vortex B generated downstream of the auxiliary combustion chamber 22. The flame holding action by the low flow velocity region based on the vortex generated by the shapes of the downstream edge portions of the main combustor type flame stabilizer 10 and the gutta type flame stabilizer 11 is performed. And
Combustion flame F in a completely combusted state is obtained by mixing the above-mentioned fuel and air.

[Combustion Test Example] FIG. 5 shows the improved model (first embodiment of the ram combustion apparatus) shown in FIGS. 1 to 4 and FIG.
It shows the results of carrying out a combustion test on one comparative model. However, the combustion efficiency was measured by exhaust gas sampling, and exhaust gas sampling was performed 7D downstream of the ram combustor. (D = combustor duct diameter) The test results show that in the improved model (examples of FIGS. 1 to 4),
At an equivalence ratio of 0.3, which is a target equivalence ratio (equivalence ratio corresponding to a flight Mach number of 3), the combustion efficiency was increased by 5% as compared with the comparative model (of the example of FIG. 11). Further, flat characteristics were obtained at an equivalence ratio of 0.2 to 0.3. The combustion efficiency of the comparative model shows the maximum value near the equivalence ratio of 0.2, and then decreases as the equivalence ratio increases. The improved model increases the combustion efficiency by increasing the amount of air in the main combustor type flame stabilizer. Can be prevented and the swirling flow due to the swirler and the second
It is shown that the mixing of fuel and air is promoted by the multiple fuel injection holes (multiple nozzles) of the fuel nozzle (main nozzle), and good combustion is performed as compared with the comparative model. Conceivable. In the future, further improvement of combustion efficiency can be expected by optimizing the fuel distribution to the second fuel nozzle and the air flow distribution.

Next, a second embodiment of the ram combustion device according to the present invention will be described with reference to FIG. In the second embodiment, the fuel header 24 of the second fuel nozzle 24
b and the fuel ejection hole 24c are arranged at the downstream position of the swirler 23. In this example, the fuel is the fuel injection hole 24c.
Is mixed into the premixing chamber 25 by the swirling flow of the air sent out from the swirler 23. Since the other parts are the same as those in the first embodiment, the description thereof will be omitted.

FIGS. 7 and 8 show another embodiment of the auxiliary combustion chamber 22 of the ram combustion device according to the present invention, in which the flare portion 22b is provided at the downstream end of the auxiliary combustion chamber 22. Lobe mixer 30 for guiding internal and external fluids in both radial directions for mixing
Are to be arranged. The lobe mixer 30 has a corrugated peripheral wall that is continuous in the circumferential direction, and as shown in FIG. 8, the height of the corrugation is set to gradually increase in both radial directions as it goes downstream. When such a lobe mixer 30 is arranged, as shown in FIG. 7, the fluid flowing outside the peripheral wall 22a of the auxiliary combustion chamber 22 is guided in the radial inward direction as shown by the dashed arrow in FIG. On the other hand, the fuel injected into the sub-combustion chamber 22 is guided radially outward, and the vortex B is generated, so that the fuel is mixed and diluted near the downstream end of the sub-combustion chamber 22. Is promoted.

[Other Embodiments] In the ram combustion device according to the present invention, the following technique is adopted in addition to each embodiment. a) Adjusting the opening amount of the upstream opening 10e of the swirler 23 according to the opening area. b) Improving the mixing property by adding an inner / outer flow insertion means such as a slit or a hole to a part of the flare portion 22b of the auxiliary combustion chamber 22. c) Skirt-shaped wall 10f in the main combustor type flame stabilizer 10
Change the shape of.

[0030]

The ram combustion apparatus according to the present invention has the following excellent effects. (1) A main combustor type flame stabilizer, a sub-combustion chamber arranged at a central position of the main combustor type flame stabilizer, an upstream opening arranged in the sub-combustion chamber for taking in a part of the airflow therein, By adopting the configuration including the second fuel nozzle for supplying fuel between the peripheral wall of the combustor type flame stabilizer and the peripheral wall of the auxiliary combustion chamber, the flight Mach number is increased inside the main combustor type flame stabilizer. Accordingly, combustion can be generated, and high combustion efficiency can be achieved in a wide flight Mach number range. (2) By placing a swirler between the sub-combustion chamber and the peripheral wall of the main combustor type flame stabilizer, the mixed fluid of air and fuel introduced is introduced into the main combustor type flame stabilizer as a swirling flow. As a result, the mixing property of the fuel can be improved. (3) A sub-combustion chamber arranged at the central position of the main combustor type flame stabilizer and a swirler arranged between the sub-combustion chamber and the peripheral wall of the main combustor type flame stabilizer are provided. The pressure loss can be maintained at a low level even if the air flow therethrough is introduced into the main combustor type flame stabilizer. (4) By arranging the flare portion that is expanded downstream in the downstream side of the sub-combustion chamber, the flame inside the sub-combustion chamber is guided to the outside and spread throughout the main combustor flame stabilizer. The mixability of the internal and external fluids in the auxiliary combustion chamber can be enhanced. (5) By disposing the lobe mixer at the downstream end portion of the peripheral wall of the auxiliary combustion chamber, the internal and external fluids of the auxiliary combustion chamber can be rapidly mixed near the downstream end portion of the peripheral wall, and combustion efficiency can be improved. (6) By arranging the premixing chamber between the peripheral wall of the main combustor type flame stabilizer and the peripheral wall of the auxiliary combustion chamber, mixing of air and fuel can be promoted. (7) By guiding the fuel in the circumferential direction by the annular fuel header and supplying it to the swirler from the fuel injection holes at a plurality of locations, the fuel is sent in parallel to each location of the swirl flow, and the swirl flow promotes mixing promotion. The combustion efficiency can be realized. (8) Inside the sub-combustion chamber, the low flow velocity region part due to the vortex generated downstream thereof, and the low flow velocity region part due to the vortex generated by the shapes of the main combustor type flame holder and the gutta type flame stabilizer By performing the flame, it is possible to obtain a high flame holding property and prevent the occurrence of the flame blowout phenomenon. (9) A plurality of gutta-type flame stabilizers should be arranged downstream of the main-combustor-type flame stabilizer, and an airflow inlet that penetrates the peripheral wall of the main-combustor-type flame stabilizer should be arranged. As a result, improvement in combustion efficiency can be achieved.

[Brief description of drawings]

FIG. 1 is a front sectional view including a block diagram showing a first embodiment of a ram combustion device according to the present invention.

FIG. 2 is a cross-sectional view near the swirler in FIG.

FIG. 3 is a cross-sectional view of the vicinity of the airflow introducing port in FIG.

FIG. 4 is a right side view of the vicinity of the gutta-type flame stabilizer in FIG.

FIG. 5 is a relationship curve diagram between an equivalence ratio and combustion efficiency, which shows the results of a combustion test performed on the improved model comparison model.

FIG. 6 is a front sectional view showing a second embodiment of the ram combustion device according to the present invention.

FIG. 7 is a front sectional view showing another embodiment of the auxiliary combustion chamber of the ram combustion device according to the present invention.

FIG. 8 is a perspective view of a lobe mixer portion showing another embodiment of the auxiliary combustion chamber of the ram combustion device according to the present invention.

FIG. 9 is a front sectional view showing a schematic structure of a ramjet engine.

FIG. 10 is a front cross-sectional view showing a conventional structure example of a ram combustion device.

FIG. 11 is a front sectional view showing another example of the conventional structure of the ram combustion device.

[Explanation of symbols]

 2 Combustor duct 3 Combustion chamber 8 Spark plug 9 Support beam 10 Main combustor type flame stabilizer 10a Air introduction hole 10b Peripheral wall 10c Guide part 10d Air flow introduction port 10e Upstream opening 10f Skirt wall 11 Gutta flame stabilizer 20 Ram burn Device 21 First fuel nozzle 22 Secondary combustion chamber 22a Circumferential wall 22b Flare portion 23 Swirler 23a Twist blade 24 Second fuel nozzle 24b Fuel header 24c Fuel injection hole 25 Premixing chamber 26 Fuel control means 27 Fuel control portion 28 Ignition fuel Supply means 29 Fuel supply means for main combustion 30 Lobe mixer G Airflow A Swirling vortex B Vortex F Combustion flame

Claims (9)

[Claims] 1. A ram combustion device mounted inside a combustor duct of a ramjet engine, wherein the main combustor type flame holding is arranged inside the combustor duct (2) and burns the supplied fuel. (10) and a sub-combustion chamber (2) which is arranged at the central position of the front end of the main combustor type flame stabilizer and has an opening downstream and is supplied with fuel from a first fuel nozzle (21).
2) and an upstream opening (10e) arranged at the upstream end of the auxiliary combustion chamber to take in a part of the air flow into the main combustor type flame stabilizer.
And a second fuel nozzle (24) arranged near the upstream opening and supplying fuel between the peripheral wall of the main combustor type flame stabilizer and the peripheral wall (22a) of the auxiliary combustion chamber. A characteristic ram combustion device. 2. A ram combustion device mounted inside a combustor duct of a ramjet engine, wherein the main combustor type flame holding is arranged inside the combustor duct (2) and burns the supplied fuel. (10) and a sub-combustion chamber (2) which is arranged at the central position of the front end of the main combustor type flame stabilizer and has an opening downstream and is supplied with fuel from a first fuel nozzle (21).
2) and the peripheral wall (10) of the auxiliary combustion chamber and the main combustor type flame stabilizer.
a swirler (23) that creates a swirling flow with b),
A ram combustion device comprising a second fuel nozzle (24) disposed around the swirler and supplying fuel to the inside of the swirler. 3. A flare portion (22b) spread in the downstream direction at the downstream end of the peripheral wall (22a) of the auxiliary combustion chamber (22).
The ram combustion device according to claim 1 or 2, characterized in that: 4. A lobe mixer (30) arranged at the downstream end of the peripheral wall (22a) of the auxiliary combustion chamber (22) for guiding the internal and external fluids in both radial directions for mixing. The ram combustion device according to 2. 5. A peripheral wall (10) of a main combustor type flame stabilizer (10).
A premixing chamber (25) is formed between b) and the peripheral wall (22a) of the auxiliary combustion chamber (22).
The ram combustion device according to 2, 3, or 4. 6. An annular fuel header (24b) for guiding fuel to the second fuel nozzle (24) in the circumferential direction, and a peripheral wall (10b) of the fuel header and the main combustor type flame stabilizer (10). The ram combustion device according to claim 1, 2, 3, 4, or 5, further comprising: a fuel ejection hole (24c) that connects the interior of the fuel cell at a plurality of points. 7. The fuel injection hole (24c) has a swirler (2).
3. It is arranged at the position of 3), 2.
The ram combustion device according to 4, 5, or 6. 8. The fuel injection hole (24c) has a swirler (2).
3. It is arranged at the downstream position of 3),
The ram combustion device according to 3, 4, 5 or 6. 9. A peripheral wall (10) of a main combustor type flame stabilizer (10).
At the downstream position in b), a plurality of gutter-type flame stabilizers (1
1) are arranged at intervals in the circumferential direction, and an air flow inlet (10d) is arranged at a position upstream of the gutta type flame stabilizer through the peripheral wall of the main combustor type flame stabilizer. The ram combustion device according to claim 1, 2, 3, 4, 5, 6, 7 or 8.