CN114183773A - Combustion chamber capable of generating multiple rotary detonation waves - Google Patents
Combustion chamber capable of generating multiple rotary detonation waves Download PDFInfo
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- 238000005474 detonation Methods 0.000 title claims abstract description 91
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 37
- 239000000446 fuel Substances 0.000 claims abstract description 39
- 238000002347 injection Methods 0.000 claims abstract description 12
- 239000007924 injection Substances 0.000 claims abstract description 12
- 238000003466 welding Methods 0.000 claims abstract description 4
- 230000000087 stabilizing effect Effects 0.000 claims description 13
- 238000007789 sealing Methods 0.000 claims description 10
- 230000008901 benefit Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 238000002474 experimental method Methods 0.000 description 4
- 239000007789 gas Substances 0.000 description 3
- 238000002156 mixing Methods 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 239000002828 fuel tank Substances 0.000 description 2
- 239000011261 inert gas Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 230000000644 propagated effect Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009841 combustion method Methods 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000001902 propagating effect Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 239000000376 reactant Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000012916 structural analysis Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/58—Cyclone or vortex type combustion chambers
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
The invention provides a combustion chamber capable of generating a plurality of rotary detonation waves, which comprises an end cover, an air pipe, a central column and a shell, wherein a fuel input port and an air input port are distributed on the end cover, an air injection port and an air connecting port are distributed on the air pipe, the air injection port is connected with the air input port on the end cover in a welding mode, cylindrical holes are distributed on the central column, the end cover is connected with the central column by screws, an igniter placing port and a pressure sensor placing port are distributed on the shell, the end cover and the shell are connected by hexagonal bolts, and a detonation ring cavity is formed between the central column and the shell. The propelling performance of the rotary detonation engine can be effectively improved, and the detonation stability is enhanced.
Description
Technical Field
The invention relates to a combustion chamber capable of generating a plurality of rotary detonation waves, and belongs to the research field of air-breathing engines.
Background
Conventional aerospace aircraft engines, such as turbojet engines, turbine engines, and ramjet engines, all use combustion in an approximately isobaric manner. Over the last hundred years, it has become very difficult to significantly improve the thermal efficiency of these engines. Because the detonation is similar to the constant volume combustion, the volume of the fuel gas is hardly expanded in the combustion process, and the chemical energy is almost completely converted into internal energy, so the entropy increase is small, and the thermal efficiency is higher than that of the traditional aerospace engine. Detonation is the only combustion mode which can promote the total pressure so as to improve the working capacity. The engine using the detonation combustion method is called a detonation engine, and the detonation engine can be classified into an oblique detonation engine, a pulse detonation engine, and a rotary detonation engine according to the propagation method of a detonation wave. Compared with other two detonation engines, the rotary detonation engine is expected to become a new choice for the future hypersonic propulsion due to the advantages of one-time ignition sustainable propagation, wide working range and the like. In this engine, the combustion chamber is generally of annular configuration, with the direction of flow of the reactants being perpendicular to the direction of rotation of the detonation waves. When the detonation wave rotates, the combustible mixture formed by the fuel and the oxidant is continuously filled into the combustion chamber from the head, a triangular unburnt propellant is formed in the detonation wave front for the detonation wave to combust, and the generated high-temperature and high-pressure detonation product expands along the axial direction of the combustion chamber and is accelerated and discharged through the spray pipe to generate thrust.
In recent years, researchers at home and abroad invent a plurality of novel experimental devices of the rotary detonation engine, and attempt to realize the stable propagation of the rotary detonation engine. Like the CN104792534A patent, the diameter of the oxygen at the inlet of the annular combustion chamber is 1mm, and the quantity reaches one hundred, so that the fuel and the oxygen are mixed more uniformly, and the possibility of continuous rotary detonation phenomenon in the annular pipeline is improved. Like CN213480276U patent, each fuel nozzle is provided with a plurality of inert gas nozzles at two sides, and the contact surface area of premixed fuel and high-temperature products is reduced by feeding premixed fuel and inert gas in a layered manner, thereby reducing the proportion of fuel explosion and combustion and improving the thermal efficiency. Like in the CN110715323A patent, the liquid fuel channel is adjacent to the outer body of the combustion chamber and is coaxially arranged with the combustion chamber to realize the wall surface cooling and the fuel preheating of the combustion chamber, prevent the outer wall surface of the combustion chamber from deforming due to overhigh thermal stress, and effectively improve the atomization effect of the fuel at the same time, thereby enhancing the intensity of detonation waves.
At present, how to improve the thrust stability of an engine is one of urgent problems to be solved in the research of a rotary detonation engine, and the experimental results of the documents of Lingwei, Zhongyuan, Linshiyong, Liushijie, H _2/Air continuous rotary detonation engine thrust test thrust [ J ] in a (-II double) wave mode propulsion technology, 2015,36(05):641-649 indicate that the vibration frequency of the rotary detonation engine in the working stage is basically consistent with the propagation frequency of the rotary detonation wave, the increase of the rotary detonation wave number can enable the pressure distribution of a combustion chamber to be more uniform, and the thrust of the engine to be more stable. In the Bykovskii F A, Zhdan S A, Vedenikov E F. continuous propagation [ J ] Journal of pulsation and power 2006,22(6):1204 and 1216 ] experiments, it is found that the number of wave heads is in direct proportion to the size of the combustion chamber, because the detonation wave propagation needs sufficient blended fuel to be maintained, and therefore, as the size of the combustion chamber increases, more combustible mixture is filled into the combustion chamber in the detonation wave propagation process, and further, a plurality of detonation waves which are stably propagated in the same direction can be generated.
Disclosure of Invention
Based on the above analysis, the present invention provides a combustion chamber capable of generating a plurality of rotating detonation waves, which can effectively improve the propulsion performance of a rotating detonation engine and enhance the detonation stability.
The scheme for realizing the purpose is that the combustion chamber capable of generating a plurality of rotary detonation waves comprises an end cover, an air pipe, a central column and a shell, wherein a fuel input port, an air input port, a bolt through hole, a screw through hole and a low-frequency pressure sensor placing port are distributed on the end cover, an air injection port and an air connecting port are distributed on the air pipe, a cylindrical hole and a screw through hole are distributed on the central column, an igniter placing port is distributed on the shell, a bolt through hole, a high-frequency pressure sensor placing port and a low-frequency pressure sensor placing port are distributed on the shell.
Furthermore, the end cover is a cylinder with steps, a fuel input port and two low-frequency pressure sensor placing ports are distributed on the inner side of the end cover, and three air input ports are distributed on the outer side of the end cover at equal intervals of 120 degrees along the circumferential direction.
Furthermore, the air pipe is an arc-shaped pipeline, two ends of the air pipe are of a closed structure, an air connecting port is distributed on the outer side of the air pipe, three air injection ports are distributed on the inner side of the air pipe at intervals of 120 degrees along the circumferential direction and are respectively connected with the air input ports on the end covers in a welding mode.
Furthermore, the bottom end of the central column is of a groove structure, the groove parts are connected with the end cover through screws and sealed through O-shaped sealing rings, the inner hollow cavity is a fuel pressure stabilizing chamber, the outer hollow cavity is an air pressure stabilizing chamber, 450 cylindrical holes with the diameter of 0.8mm are distributed on the central column at equal intervals along the circumferential direction, fuel is axially injected through the cylindrical holes, the other end of the central column is of a hollow cylindrical structure, and a detonation ring cavity is formed between the hollow cylinder and the shell.
Furthermore, the inner side of the bottom end of the shell is of a hollow wedge-shaped structure, a convergence expansion annular seam is formed in a gap between the shell and the bottom of the center column, air is jetted from the convergence expansion annular seam in the radial direction and flows into the detonation annular cavity after being orthogonally mixed with fuel axially jetted from a cylindrical hole in the center column, a placing opening of an igniter, four high-frequency pressure sensor placing openings and two low-frequency pressure sensor placing openings are distributed in the outer wall surface of the shell, the end cover is connected with the shell through a hexagon bolt, and an O-shaped sealing ring is adopted to ensure the sealing performance of the engine.
The invention relates to a combustion chamber capable of generating a plurality of rotary detonation waves, which has the following beneficial effects compared with the prior art: on the basis of ensuring light weight and compact structure of the rotary detonation engine, the combustion chamber adopts a coaxial circular ring cavity structure, the outer diameter of the detonation ring cavity is 220mm, the inner diameter of the detonation ring cavity is 100mm, and the detonation ring cavity can form a plurality of co-propagating rotary detonation waves in a stable stage after ignition, so that the propelling performance of the rotary detonation engine can be effectively improved, and the detonation stability is enhanced.
Drawings
The invention may be better understood by referring to the following description in conjunction with the accompanying drawings, in which like reference numerals are used throughout the figures to indicate like or similar parts. The accompanying drawings, which are incorporated in and form a part of this specification, illustrate preferred embodiments of the present invention and, together with the detailed description, serve to further explain the principles and advantages of the invention. Wherein:
FIG. 1 is a two-dimensional front sectional view of a rotary detonation combustor.
FIG. 2 is a two-dimensional top view of an air tube and end cap of a rotary detonation engine.
FIG. 3 is a three-dimensional schematic view of a housing of a rotary detonation engine.
FIG. 4 is a plot of pressure versus time plotted against data collected by a high frequency pressure sensor.
The device comprises a 1-end cover, a 2-low-frequency pressure sensor placing port, a 3-fuel inlet, a 4-air inlet, a 5-fuel pressure stabilizing chamber, a 6-air pressure stabilizing chamber, a 7-air pipe, an 8-air injection port, a 9-air connecting port, a 10-bolt through hole, a 11-bolt through hole, a 12-center column, a 13-cylindrical hole, a 14-hexagon bolt, a 15-bolt, a 16-O-shaped sealing ring, a 17-shell, an 18-high-frequency pressure sensor placing port and a 19-igniter placing port.
Skilled artisans appreciate that elements in the figures are illustrated for simplicity and clarity and have not necessarily been drawn to scale. For example, the dimensions of some of the elements in the figures may be exaggerated relative to other elements to help improve the understanding of the embodiments of the present invention.
Detailed Description
The invention will now be described in more detail by way of example with reference to the accompanying drawings in which:
in order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to specific embodiments and the accompanying drawings.
As shown in fig. 1-2, the rotary detonation combustor is composed of an end cover (1), an air pipe (7), a center post (12) and a shell (17), and is made of 45 steel, and the rusting rate is slowed down through bluing treatment. The end cover is provided with a fuel inlet (3), an air inlet (4), a bolt through hole (10), a screw through hole (11) and a low-frequency pressure sensor placing port (2), an air injection port (8) and an air connecting port (9) are distributed on an air pipe (7), a cylindrical hole (13) and the screw through hole (11) are distributed on a center post, an igniter placing port (19) is distributed on the shell, and the bolt through hole (10), a high-frequency pressure sensor placing port (18) and the low-frequency pressure sensor placing port (2) are distributed on the shell.
As shown in fig. 1-2, the end cover (1) is a cylinder with a diameter of 374mm and steps, and a fuel inlet (3) is distributed at the center of the inner side of the end cover (1) and is connected with a fuel tank through a pipeline. Two low-frequency pressure sensor placing ports (2-1) and (2-2) are radially distributed along the inner side of the end cover (1) and are respectively 110mm and 147.5mm away from the center of the end cover (1). Three air input ports (4) are distributed on the outer side of the end cover (1) at equal intervals of 120 degrees along the circumferential direction.
As shown in figure 2, the air tube (7) is an arc-shaped tube with an outer diameter of 20mm, an inner diameter of 14mm and a radian of 260 degrees, and the wall thickness of the tube is 3 mm. Two ends of the air pipe (7) are closed, and an air connecting port (9) for connecting an air tank is distributed on the outer side of the air pipe. Three air injection ports (8) are distributed on the inner side at intervals of 120 degrees along the circumferential direction, are respectively connected with the air input ports (4) on the end cover (1) in a welding mode, and the three air injection ports (8) are adopted to mainly ensure that air can be uniformly distributed in the combustion chamber.
As shown in fig. 1, the bottom end of the central column (12) is of a groove structure, the groove part is connected with the end cover through a screw (15) and sealed by an O-shaped sealing ring (16), the inner hollow cavity is a fuel pressure stabilizing chamber (5) for storing fuel, and the outer hollow cavity is an air pressure stabilizing chamber (6) for storing air. In the experiment, the pressure of the fuel pressure stabilizing chamber (5) and the pressure of the air pressure stabilizing chamber (6) are measured by two low-frequency pressure sensors arranged on the end cover (1) and used for judging the filling state of fuel and air in the pressure stabilizing chamber. 450 cylindrical holes (13) with the diameter of 0.8mm are distributed in the central column (12) at equal intervals along the circumferential direction, and fuel is injected axially through the cylindrical holes (13). The other end of the center post (12) is a hollow cylinder structure with the axial length of 152.8mm, the outer diameter of 100mm and the inner diameter of 80mm, the structure can reduce the weight of a combustion chamber and improve the thrust performance of an engine, a detonation ring cavity is formed between the hollow cylinder and the shell (17), the outer diameter of the detonation ring cavity is 220mm, the inner diameter of the detonation ring cavity is 100mm, and the processes of fuel and air mixing, rotary detonation, exhaust and the like all occur in the ring cavity.
As shown in figures 1 and 3, the inner side of the bottom end of the shell (17) is of a hollow wedge-shaped structure, the wedge angle is about 15 degrees, the structure can concentrate mixed gas on the inner side of the detonation ring cavity, detonation waves are propagated along the inner side of the detonation ring cavity after ignition, and the temperature and the pressure of the outer wall surface of the combustion chamber are reduced. A convergent-divergent annular gap is formed between the shell (17) and the bottom of the central column (12), the width of the narrowest part of the annular gap is 1mm, air is jetted from the convergent-divergent annular gap in the radial direction, and flows into a detonation annular cavity after being orthogonally mixed with fuel axially jetted from a cylindrical hole (13) in the central column (12), and factors such as mixing quality, flow loss, process and the like are comprehensively considered in orthogonal mixing design. An igniter placing port (19), four high-frequency pressure sensor placing ports (18) and two low-frequency pressure sensor placing ports (2) are distributed on the outer wall surface of the shell (17), the high-frequency pressure sensor placing ports (18-2) and (18-3) are located at the same azimuth angle, the axial distance is 30mm, the high-frequency pressure sensor placing ports (18-1), (18-2) and (18-4) are sequentially circumferentially spaced by 90 degrees, and the placing position of the high-frequency pressure sensor placing port (18) can finish the collection of high-frequency signals such as detonation waves and the like in the experimental process and determine the propagation direction of the detonation waves. The included angle between the low-frequency pressure sensor (2-3) and the low-frequency pressure sensor (2-4) is 90 degrees, and the low-frequency pressure sensor is used for collecting the pressure of the detonation cavity. The end cover (1) and the shell (17) are connected by adopting a hexagon bolt (14), the rotary detonation engine is restrained and fastened, and the sealing performance of the engine is ensured by adopting an O-shaped sealing ring (16).
The operation of the embodiment of the present invention will be described below to facilitate understanding of the advantages of the present invention.
Before the experiment begins, an air connecting port on an air pipe is connected with an air tank, a fuel input port is connected with a fuel tank by using a pipeline provided with an electromagnetic valve, a pre-detonation pipe is tangentially welded at an igniter placing port on the outer wall surface of a shell, low-frequency and high-frequency pressure sensors are respectively placed in pressure sensor placing ports on a combustion chamber and connected to signal acquisition equipment, and the electromagnetic valve on the air input pipeline and the fuel input pipeline is connected to a control system.
In the experiment, the electromagnetic valves of air and fuel are sequentially opened at 0 moment, the fuel enters a fuel pressure stabilizing chamber from a fuel inlet in the center of an end cover, and is axially jetted through cylindrical holes distributed on the center column in the circumferential direction, the air enters the air pressure stabilizing chamber through three air injection ports on an air pipe and an air inlet on the end cover in sequence, and finally the air is radially jetted from a convergent expansion circumferential seam. Air and fuel are orthogonally mixed in the annular seam and then flow into the detonation annular cavity, combustible mixed gas in the detonation annular cavity at the moment of 50ms is completely filled to ignite and finish ignition at the moment of 100ms, high-temperature and high-pressure energy enters the detonation annular cavity through the pre-detonation tube after ignition, and mixed gas is combusted to realize detonation and propagation of detonation waves. Fuel input is cut off at time t by the control system, and air input is cut off at time t +2 s. The air is finally cut off to ensure that the residual detonation products are purged clean and to cool the combustion chamber.
FIG. 4 is a pressure time-varying curve plotted according to data collected by the high-frequency pressure sensor, and since the high-frequency pressure sensor placement ports (18-1) and (18-2) are located at the downstream position of the combustion chamber and are closer to the detonation wave position, the measured pressure peak value is higher, and the pressure fluctuation range is larger. Taking the pressure change over time curve measured at the high frequency pressure sensor placement port (18-1) as an example, the average time interval between two pressure peaks is about 85 μ s. According to the CEA (chemical Equisrium with application) software, the detonation velocity of C-J (Chapman-Jouquet) is about 1975m/s, and the propagation period of the detonation wave under the size of the combustion chamber is calculated to be about 159 mu s, so that the existence of two rotating detonation waves in the combustion chamber can be determined.
From the above structural analysis and experimental measurement results, it can be known that the detonation combustor according to the embodiment of the present invention can provide the following technical advantages, on the basis of ensuring the light weight and compact structure of the rotary detonation engine, the combustor adopts a coaxial circular ring cavity structure, the outer diameter of the detonation ring cavity is 220mm, the inner diameter is 100mm, after ignition, the detonation ring cavity can form a plurality of rotary detonation waves propagating in the same direction at a stable stage, so that the propulsion performance of the rotary detonation engine can be effectively improved, and the detonation stability can be enhanced.
While the invention has been described with respect to a limited number of embodiments, those skilled in the art, having benefit of this description, will appreciate that other embodiments can be devised which do not depart from the scope of the invention as described herein. Furthermore, it should be noted that the language used in the specification has been principally selected for readability and instructional purposes, and may not have been selected to delineate or circumscribe the inventive subject matter. Accordingly, many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the appended claims. The present invention has been disclosed in an illustrative rather than a restrictive sense, and the scope of the present invention is defined by the appended claims.
Claims (5)
1. A combustor capable of generating a plurality of rotating detonation waves, characterized by: the fuel injection port and the air connecting port are distributed on the air pipe, the cylindrical hole and the screw through hole are distributed on the central column, the igniter placing port is distributed on the shell, and the bolt through hole, the high-frequency pressure sensor placing port and the low-frequency pressure sensor placing port are distributed on the bolt through hole.
2. The combustion chamber capable of generating multiple rotating detonation waves of claim 1, wherein: the end cover is a cylinder with steps, a fuel input port and two low-frequency pressure sensor placing ports are distributed on the inner side of the end cover, and three air input ports are distributed on the outer side of the end cover at equal intervals of 120 degrees along the circumferential direction.
3. The combustion chamber capable of generating multiple rotating detonation waves of claim 1, wherein: the air pipe is an arc-shaped pipeline, two ends of the air pipe are of closed structures, an air connecting port is distributed on the outer side of the air pipe, three air injection ports are distributed on the inner side of the air pipe at intervals of 120 degrees along the circumferential direction, and the three air injection ports are respectively connected with the air input ports on the end covers in a welding mode.
4. The combustion chamber capable of generating multiple rotating detonation waves of claim 1, wherein: the bottom end of the central column is of a groove structure, the groove part and the end cover are connected through screws and sealed through O-shaped sealing rings, the inner hollow cavity is a fuel pressure stabilizing chamber, the outer hollow cavity is an air pressure stabilizing chamber, 450 cylindrical holes with the diameter of 0.8mm are distributed on the central column at equal intervals along the circumferential direction, fuel is axially injected through the cylindrical holes, the other end of the central column is of a hollow cylinder structure, and a detonation ring cavity is formed between the hollow cylinder and the shell.
5. The combustion chamber capable of generating multiple rotating detonation waves of claim 1, wherein: the inner side of the bottom end of the shell is of a hollow wedge-shaped structure, a convergence expansion annular seam is formed between the shell and the bottom of the center column in a gap mode, air is jetted radially from the convergence expansion annular seam, and flows into the detonation annular cavity after being orthogonally mixed with fuel jetted axially from the cylindrical hole in the center column, a placing opening of an igniter, four high-frequency pressure sensor placing openings and two low-frequency pressure sensor placing openings are distributed in the outer wall surface of the shell, the end cover and the shell are connected through hexagon bolts, and an O-shaped sealing ring is adopted to ensure the sealing performance of the engine.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116025484A (en) * | 2023-02-28 | 2023-04-28 | 北京大学 | Continuous detonation solid rocket engine system based on solid powder |
| CN117663193A (en) * | 2024-01-31 | 2024-03-08 | 西安交通大学 | Quick compressor combustion chamber pressure stabilizing device and method |
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