CN116293808A - Full-cyclone grading combustion chamber - Google Patents
Full-cyclone grading combustion chamber Download PDFInfo
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- CN116293808A CN116293808A CN202310177261.XA CN202310177261A CN116293808A CN 116293808 A CN116293808 A CN 116293808A CN 202310177261 A CN202310177261 A CN 202310177261A CN 116293808 A CN116293808 A CN 116293808A
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 115
- 239000000446 fuel Substances 0.000 claims description 21
- 238000002156 mixing Methods 0.000 claims description 14
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 claims description 14
- 238000011144 upstream manufacturing Methods 0.000 claims description 12
- 239000000203 mixture Substances 0.000 claims description 9
- 238000000889 atomisation Methods 0.000 claims description 8
- 238000002347 injection Methods 0.000 claims description 8
- 239000007924 injection Substances 0.000 claims description 8
- 230000003068 static effect Effects 0.000 claims description 4
- 238000001704 evaporation Methods 0.000 claims description 3
- 230000008020 evaporation Effects 0.000 claims description 3
- 238000005507 spraying Methods 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 238000011084 recovery Methods 0.000 abstract description 3
- 230000002093 peripheral effect Effects 0.000 abstract description 2
- 238000013316 zoning Methods 0.000 abstract 2
- 239000003921 oil Substances 0.000 description 26
- 238000001816 cooling Methods 0.000 description 10
- 238000013461 design Methods 0.000 description 10
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- 230000001419 dependent effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
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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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M5/00—Casings; Linings; Walls
- F23M5/08—Cooling thereof; Tube walls
- F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
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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
- F23R3/002—Wall structures
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
- Spray-Type Burners (AREA)
Abstract
The invention discloses a full-cyclone staged combustion chamber, which adopts the ideas of staged oil supply and zoned combustion and combines the advantages of the physical zoning of a conventional afterburner and the pneumatic zoning of a cyclone. The invention uses the peripheral strong cyclone auxiliary cyclone to form a class, and ignition and duty combustion both occur at the class; and meanwhile, the central weak-swirl main swirlers are used for improving the residence time of the main combustion stage and carrying out the main combustion stage combustion, and the swirling directions of the swirlers are reasonably arranged to promote the high-speed propagation of flame. The invention achieves balance among widening ignition boundary, improving combustion efficiency and controlling flow resistance loss, ensures smaller flow resistance loss of the combustion chamber, and is especially suitable for high-through-flow inlets and medium and small aeroengines needing to improve total pressure recovery coefficient.
Description
Technical Field
The invention relates to the technical field of aviation gas turbine combustion with a new concept, in particular to a full-cyclone classification combustion chamber.
Background
The national defense military requirements lead to the flight heights and flight Mach numbers of various military aircrafts to be larger and larger. At present, the Mach number of the front inlet of a diffuser of various advanced afterburners and sub-combustion ram combustors is more than 0.4, and the turbulent flame propagation speed of aviation kerosene is greatly exceeded; meanwhile, when working near the left boundary of the flight envelope, the combustor inlet is often in a negative pressure condition, the air density is low, the chemical reaction rate is slow, and the fuel atomization blending performance is poor. These severe inlet conditions present challenges to wide-boundary ignition, flame stabilization, and efficient combustion of the combustion chamber. One common solution is to apply the concept of zoned oil supply and staged combustion in the design of the combustion chamber, namely, adopting various zoned modes to form a relatively independent class in the combustion chamber, manufacturing a low-speed backflow flow field suitable for flame stabilization in the class, and pertinently arranging independent oil supply nozzles for oil supply, ignition and combustion. The area outside the class serves as the main combustion stage, and the stable ignition is completely dependent on the diffusion of the flame of the class.
In the existing afterburner and sub-combustion stamping combustor, the physical structure is adopted for grading, namely, independent duty space is divided by means of a physical wall surface. Based on the grading thought, a plurality of duty flame stabilizers such as a blunt body type flame stabilizer, a concave cavity type flame stabilizer and the like are generated; in decades of research and application, the ignition performance, operating margin and combustion efficiency of these flame holders have been demonstrated. In order to prevent the flame from being blown out by the high-speed incoming flow, the air inlet speed and the air inlet flow rate of the class are not high, and the corresponding oil supply flow rate is also low, which means that most of the temperature rise of the combustion chamber still needs to be provided by the main combustion stage. However, physical staging requires a larger duty cycle area to ensure flame holding, which wastes limited combustor space and reduces the mixing residence time and combustion efficiency of the main stage. In addition, with the increasing of the incoming flow speed of the inlet of the forced/punched combustion chamber, the larger windward area brought by the physical wall surface also leads to the severe increase of the total pressure loss, and reduces the thrust of the engine. The above two drawbacks are particularly pronounced in medium and small aircraft engines with limited internal space.
Disclosure of Invention
The invention aims to solve the technical problem of providing a full-cyclone staged combustion chamber aiming at the defects related to the background technology.
The invention adopts the following technical scheme for solving the technical problems:
a full-cyclone staged combustion chamber comprises an air inlet pipe, a casing, a flame tube, a mounting plate, a main cyclone, N auxiliary cyclones, a corrugated heat shield and a high-energy electric nozzle, wherein N is a natural number greater than or equal to 3;
the casing is a hollow cylinder with two open ends;
one end of the air inlet pipe positioned at the downstream is hermetically and fixedly connected with one end of the casing at the upstream and is used for guiding air into the combustion chamber;
the flame tube is coaxially arranged in the casing, M connecting blocks are circumferentially arranged on the outer wall of the flame tube, and M is a natural number greater than or equal to 3; one end of each connecting block is fixedly connected with the outer wall of the flame tube, and the other end of each connecting block is fixedly connected with the inner wall of the casing;
the mounting disc is in a circular ring shape, and the outer wall of the mounting disc is hermetically and fixedly connected with one end of the flame tube, which is positioned at the upstream;
the main cyclone adopts secondary cyclone, is arranged in the center of the mounting plate, and the secondary outer ring of the main cyclone is coaxially and fixedly connected with the inner wall of the mounting plate;
n mounting holes are uniformly formed in the mounting plate around the circumference of the main cyclone, and the N auxiliary cyclones are arranged in the N mounting holes in a one-to-one correspondence manner;
the corrugated heat shield is arranged in the casing, and one end of the corrugated heat shield, which is positioned at the upstream, is coaxially and fixedly connected with one end of the flame tube, which is positioned at the downstream;
p oil injection rods which extend into the air inlet pipe from the outside are uniformly arranged in the circumferential direction of the air inlet pipe and are used for inputting oil for a main combustion stage, wherein P is a natural number which is more than or equal to 3;
the auxiliary cyclone adopts single-stage cyclone, a through hole is formed in the central body along the axis of the auxiliary cyclone, and a nozzle for spraying class-I fuel towards the combustion chamber is arranged in the through hole of the central body; the nozzles at the centers of the N auxiliary cyclones are communicated with the outside through oil pipelines penetrating through the casing and used for supplying oil to an input class;
the main cyclone is used for enabling a uniform oil-gas mixture formed by the atomization evaporation of the main fuel level fuel injected by the fuel injection rod and the full mixing of air to be divided into inner and outer two-stage cyclone flows with opposite rotation directions, so that the mixing capability of the inner and outer-stage airflow is enhanced, and the atomization capability of the main fuel level fuel and the uniformity of oil-gas mixing are improved;
the auxiliary cyclone is used for forming closed backflow, so as to provide an on-duty flow field for stable ignition and efficient combustion;
the high-energy electric nozzle sequentially penetrates through the casing and the flame tube and stretches into the combustion chamber behind the auxiliary cyclone for ignition.
As a further optimization scheme of the full-cyclone staged combustion chamber, the outer ring of the auxiliary cyclone is elliptical, so that the straight line where the center of the ellipse and the center of the mounting plate are located is L1, the straight line where the major axis of the ellipse is located is L2, and then L1 is perpendicular to L2.
As a further optimization scheme of the full-cyclone stage combustion chamber, the cross section of the air inlet pipe gradually expands from the upstream to the downstream, so that the speed is reduced and the static pressure is increased when air is introduced into the combustion chamber.
As a further optimization scheme of the full-cyclone stage combustion chamber, a nozzle in a through hole of a central body of the auxiliary cyclone is a small centrifugal nozzle.
Compared with the prior art, the technical scheme provided by the invention has the following technical effects:
1. the invention discloses a full-cyclone staged combustion chamber which adopts a design idea of zoned oil supply and staged combustion. In the two stages, the duty stage adopts a plurality of auxiliary cyclones with strong rotational flow, and a resident symmetrical backflow area can be formed by matching the peripheral physical wall surface of the flame tube and the air inlet jet flow of the flame tube diversion hole. The recirculation zone is relatively independent in structure and is not affected by the high-speed main flow. Meanwhile, a centrifugal nozzle which has good atomization performance and is matched with the oil mist cone and the flow field is assembled. Therefore, the valve class can successfully ignite under severe inlet conditions and form a stable ignition source, so that the main combustion stage mixed gas is continuously ignited.
2. In the two stages, the main combustion stage adopts a main cyclone with two-stage weak cyclone, the two-stage cyclone direction of the main cyclone is opposite, and a turbulent flow shear layer formed between the two-stage cyclone can promote the oil-gas mixing of the main combustion stage and the rapid propagation of flame in the radial and circumferential directions. The weak swirl can also increase the residence time of the fuel to a certain extent, thereby improving the combustion efficiency.
3. From the aspect of flow resistance control, the class-level auxiliary cyclone has high swirl strength but small windward area, and the main combustion-level main cyclone has large windward area but low swirl strength, so that the inner and outer two stages cannot generate excessively high flow resistance loss, and the thrust loss is reduced under high-speed incoming flow.
4. The design adopts a flame tube with a straight wall surface and a transverse corrugated heat shield; according to the structural characteristics of the wall surface and the near-wall surface flow field, the multi-inclined-hole air film cooling, the straight-hole evaporative cooling and other forms are adopted, so that the wall surface is prevented from being ablated, the structural strength of the combustion chamber is improved, and the service life of the combustion chamber is prolonged.
5. The outer ring of the auxiliary cyclone adopts an ellipse, so that an on-duty reflux zone formed behind the auxiliary cyclone can be greatly expanded in the direction of the major axis of the ellipse, the flame linkage capacity among the auxiliary cyclones in the circumferential direction is effectively improved, the purpose of circumferential flame linkage can be achieved by using fewer elliptical auxiliary cyclones, and the weight and complexity of the overall structure of the combustion chamber are reduced.
Drawings
Fig. 1 is a schematic structural view of the present invention.
FIG. 2 is a schematic view of the intake pipe and the outer casing in half-section.
FIG. 3 is a schematic view of the main cyclone structure in the present invention.
FIG. 4 is a schematic view of a secondary cyclone and a duty nozzle of the present invention partially cut away.
FIG. 5 is a schematic view of a flame tube in partial cutaway according to the present invention.
FIG. 6 is a schematic view of the present invention showing the longitudinal section, flow and combustion process of the secondary cyclone.
In the figure, a 1-air inlet pipe, a 2-casing, a 3-main cyclone, a 4-auxiliary cyclone, a 5-flame tube, a 6-corrugated heat shield, a 7-high-energy electric nozzle, an 8-oil injection rod, a 9-on-duty oil delivery pipe elbow part, a 10-on-duty nozzle, a 11-on-duty oil delivery pipe straight pipe part, a 12-main cyclone center cone, a 13-main cyclone primary blade, a 14-main cyclone secondary blade, a 15-flame tube cooling hole, a 16-flame tube front-row diversion hole, a 17-flame tube rear-row diversion hole, a 18-connecting block, a 19-high-energy electric nozzle mounting hole, a 20-inner duct, a 21-outer duct, a 22-on-duty strong cyclone backflow, a 23-diversion hole air inlet jet, a 24-on-duty oil mist cone, a 25-on-duty combustion zone, a 26-main combustion stage oil-gas mixture, a 27-main combustion stage weak cyclone, a 28-main combustion stage weak cyclone, a 29-main combustion stage combustion zone, a 30-flame tube cooling air inlet and a 31-corrugated heat shield cooling air inlet.
Description of the embodiments
The technical scheme of the invention is further described in detail below with reference to the accompanying drawings:
this invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, the components are exaggerated for clarity.
It will be understood that, although the terms first, second, third, etc. may be used herein to describe various elements, components and/or sections, these elements, components and/or sections should not be limited by these terms. These terms are only used to distinguish one element, component, and/or section from another. Accordingly, a first element, component, and/or section discussed below could be termed a second element, component, or section without departing from the teachings of the present invention.
As shown in fig. 1 and 2, the invention discloses a full-cyclone stage combustion chamber, which comprises an air inlet pipe, a casing, a flame tube, a mounting plate, a main cyclone, N auxiliary cyclones, a corrugated heat shield and a high-energy electric nozzle, wherein N is a natural number greater than or equal to 3;
the casing is a hollow cylinder with two open ends;
one end of the air inlet pipe positioned at the downstream is hermetically and fixedly connected with one end of the casing at the upstream and is used for guiding air into the combustion chamber;
the flame tube is coaxially arranged in the casing, M connecting blocks are circumferentially arranged on the outer wall of the flame tube, and M is a natural number greater than or equal to 3; one end of each connecting block is fixedly connected with the outer wall of the flame tube, and the other end of each connecting block is fixedly connected with the inner wall of the casing;
as shown in fig. 3, the mounting plate is in a circular ring shape, and the outer wall of the mounting plate is tightly and fixedly connected with one end of the flame tube positioned at the upstream;
the main cyclone adopts secondary cyclone, is arranged in the center of the mounting plate, and the secondary outer ring of the main cyclone is coaxially and fixedly connected with the inner wall of the mounting plate;
n mounting holes are uniformly formed in the mounting plate around the circumference of the main cyclone, and the N auxiliary cyclones are arranged in the N mounting holes in a one-to-one correspondence manner;
the corrugated heat shield is arranged in the casing, and one end of the corrugated heat shield, which is positioned at the upstream, is coaxially and fixedly connected with one end of the flame tube, which is positioned at the downstream;
p oil injection rods which extend into the air inlet pipe from the outside are uniformly arranged in the circumferential direction of the air inlet pipe and are used for inputting oil for a main combustion stage, wherein P is a natural number which is more than or equal to 3;
the auxiliary cyclone adopts single-stage cyclone, a through hole is formed in the central body along the axis of the auxiliary cyclone, and a nozzle for spraying class-I fuel towards the combustion chamber is arranged in the through hole of the central body; the nozzles at the centers of the N auxiliary cyclones are communicated with the outside through oil delivery pipes passing through the casing and are used for supplying oil to an input class, as shown in fig. 4;
the main cyclone is used for enabling a uniform oil-gas mixture formed by the atomization evaporation of the main fuel level fuel injected by the fuel injection rod and the full mixing of air to be divided into inner and outer two-stage cyclone flows with opposite rotation directions, so that the mixing capability of the inner and outer-stage airflow is enhanced, and the atomization capability of the main fuel level fuel and the uniformity of oil-gas mixing are improved;
the auxiliary cyclone is used for forming closed backflow, so as to provide an on-duty flow field for stable ignition and efficient combustion;
the high-energy electric nozzle sequentially penetrates through the casing and the flame tube and stretches into the combustion chamber behind the auxiliary cyclone for ignition.
As a further optimization scheme of the full-cyclone staged combustion chamber, the outer ring of the auxiliary cyclone is elliptical, so that the straight line where the center of the ellipse and the center of the mounting plate are located is L1, the straight line where the major axis of the ellipse is located is L2, and then L1 is perpendicular to L2.
As a further optimization scheme of the full-cyclone stage combustion chamber, the cross section of the air inlet pipe gradually expands from the upstream to the downstream, so that the speed is reduced and the static pressure is increased when air is introduced into the combustion chamber.
As a further optimization scheme of the full-cyclone stage combustion chamber, a nozzle in a through hole of a central body of the auxiliary cyclone is a small centrifugal nozzle.
Each auxiliary cyclone corresponds to an oil supply way. The fuel oil is fed into the rear of the auxiliary cyclone through a duty nozzle arranged in the center of the auxiliary cyclone to form a duty oil mist cone, two high-energy electric nozzles are symmetrically arranged in the circumferential direction of the combustion chamber, the high-energy electric nozzles extend into the flame tube, and the front end of the high-energy electric nozzles discharges and ignites a duty oil-gas mixture in duty strong cyclone backflow.
The main cyclone in the center of the flame tube is two-stage cyclone, which can be divided into a main cyclone center cone, a main cyclone primary blade and a main cyclone secondary blade from inside to outside. The formed oil-gas mixture flows through the main cyclone, and is separated into a main combustion stage primary weak cyclone and a main combustion stage secondary weak cyclone by a main cyclone primary blade and a main cyclone secondary blade. The oil-gas mixture in the main combustion stage is ignited by the duty-stage flame and is subjected to main combustion stage combustion.
As shown in fig. 5, a plurality of rows of cooling holes are formed in the wall surfaces of the flame tube and the corrugated heat shield. The wall cooling holes of the flame tube wall adopt a multi-inclined hole form and the wall cooling holes of the corrugated heat shield adopt a straight hole form. The cold air flow flowing through the outer duct flows into the inner duct from the cooling hole, forms an air film near the wall surfaces of the flame tube and the corrugated heat shield, and protects the wall surface structure.
Referring to fig. 6, the working principle of the full cyclone staged combustion chamber of the invention is as follows:
1. the incoming flow flows into the casing through the air inlet channel, the air flow area is increased in the process, the flow speed is reduced, and the static pressure is increased, so that the total pressure recovery coefficient and the combustion efficiency are improved. One part of the inflow air flowing into the casing enters the outer duct, and the other part enters the inner duct.
2. In the air entering the internal channel, a small part of air enters the rear class through the auxiliary cyclone, and forms a cyclone under the guiding action of the auxiliary cyclone. The front part of the swirl is limited by the auxiliary swirler, the upper part of the swirl is limited by the physical wall surface of the flame tube, and the rear part of the swirl is blocked by the air inlet jet flow of the diversion hole formed by the front diversion hole of the flame tube and the rear diversion hole of the flame tube. This combination of aerodynamic and physical restriction limits the over-extension of the airflow, creating a streamline closed, symmetrical and stable duty-class strong swirl reflux in the class. The backflow is relatively independent, and is little influenced by time variation or distortion of incoming flow of the main combustion stage, so that stable duty combustion can be maintained under extreme inlet conditions such as low pressure, high speed and the like. Meanwhile, as the strong rotational flow reflux quantity is large, the on-duty stage can realize good flame stability without excessively large volume, and the size of the auxiliary cyclone can be designed smaller, so that the windward area of the on-duty stage can be reduced, and the flow resistance loss is reduced.
3. And a small amount of fuel oil flows through the on-duty oil delivery pipe and the on-duty oil supply nozzle in sequence, enters the rear of the auxiliary cyclone and forms an oil mist cone, the cone-shaped oil mist structure is suitable for strong on-duty cyclone backflow, fuel oil droplets are rapidly atomized and evaporated and mixed with air, and are ignited under the discharge of the high-energy electric nozzle, and stable on-duty flame is formed in the backflow. Meanwhile, as the duty stage strong cyclone backflow behind different auxiliary cyclones gradually expands in the circumferential direction, duty stage flames can naturally spread in the circumferential direction and ignite oil-gas mixtures behind all auxiliary cyclones.
4. In the air entering the internal channel, most of the air flows through the main cyclone; because the oil injection rod is arranged at a certain distance in front of the main cyclone, the main combustion grade fuel oil is injected into the air, the fuel oil droplets are atomized, evaporated and fully mixed with the air, and the formed uniform oil-gas mixture is separated into the main combustion grade primary weak cyclone and the main combustion grade secondary weak cyclone by the main cyclone primary blade and the main cyclone secondary blade. The burnt high-temperature mixed gas of the class with the value is diffused in the radial direction, the primary secondary weak swirling flow at the outer side is firstly ignited, and the primary weak swirling flow at the primary combustion stage is continuously ignited inwards to form a primary combustion zone. The two rotational flow intensities are weaker, so that the flow resistance loss of the main combustion stage can be reduced; the weak swirl itself also increases the fuel residence time to some extent. In addition, the primary weak rotational flow of the primary combustion stage and the secondary weak rotational flow of the primary combustion stage are opposite in rotational direction, a strong turbulence shear layer is formed at the junction of the primary rotational flow and the secondary weak rotational flow of the primary combustion stage, and high vortex quantity and high turbulence in the shear layer promote oil-gas mixing and radial and circumferential diffusion of flame, so that the combustion efficiency of the primary combustion stage is improved.
5. In the combustion process of the combustion chamber, cold air flowing through the outer duct flows into the inner duct from the cooling holes formed in the flame tube and the corrugated heat shield to form an air film and protect the wall surface structure.
Unlike traditional forced/punched combustor, the present invention has pneumatic grading thought, i.e. the area on duty and the main combustion area are divided by the swirl airflow with different rotation directions. In the classification thought, the swirl strength can be controlled by adjusting the swirl number of the cyclone, so that the balance between flame stability and total pressure loss is achieved; even a variable structure can be designed, and the working conditions such as different inlet speeds, residual air coefficients and the like can be reasonably adapted.
In order to solve the inherent problem of physical classification, the invention designs a full-cyclone type classification combustion chamber, and introduces the pneumatic classification function of a cyclone into the design of the afterburner/ram combustion chamber. Considering that the afterburner/ram combustor reference section velocity is much greater than that of the main combustor and that severe inlet distortion and inlet time variation often occur, flame holding is difficult if pneumatic staging is relied solely on, and physical structures are also partially employed in the design to enhance the independence and stability of class-specific combustion. In the scheme of the combustion chamber, a strong cyclone auxiliary cyclone on the periphery is used for forming a class, and ignition and duty combustion both occur at the class; and meanwhile, the central weak-swirl main swirlers are used for improving the residence time of the main combustion stage and carrying out the main combustion stage combustion, and the swirling directions of the swirlers are reasonably arranged to promote the high-speed propagation of flame. The combustion organization thought combines the advantages of pneumatic classification and physical classification, and achieves balance among widening ignition boundary, improving combustion efficiency and controlling flow resistance loss.
The invention relates to a full-cyclone stage combustor, which is a novel combustor structural design and combustion organization scheme and is suitable for inlet conditions with high inflow speed and low total inlet pressure, such as an afterburner and a scramjet combustor. The combustor adopts the ideas of graded oil supply and zone combustion, and combines the advantages of the physical zone of the conventional afterburner and the pneumatic zone of the cyclone. The main combustion stage and the value shift use a cyclone structure. The class-on-duty is realized through the cyclone with strong cyclone, and the physical wall surface and the outer duct air inlet jet flow are matched to form stable class-on-duty reflux, so that the class-on-duty flow field is not influenced by the main flow, and the ignition and combustion stability under the extreme inlet condition can be effectively improved. The rotational flows in the valve class and the main combustion stage can exchange energy and substances through the shear layers among the rotational flows so as to promote oil-gas mixing and achieve the purposes of fast flame transfer and high-efficiency combustion. Meanwhile, as the duty stage under the strong cyclone design combines the pneumatic classification characteristic of the cyclone, the flame stabilization can be realized under the condition of smaller physical windward area; the main combustion stage under the weak rotational flow design can reduce the flow resistance loss caused by the high-speed main flow, and the two points ensure that the flow resistance loss of the combustion chamber is smaller, so that the design is particularly suitable for a high-through flow inlet and a medium-and-small aeroengine with the need of improving the total pressure recovery coefficient.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
While the foregoing is directed to embodiments of the present invention, other and further details of the invention may be had by the present invention, it should be understood that the foregoing description is merely illustrative of the present invention and that no limitations are intended to the scope of the invention, except insofar as modifications, equivalents, improvements or modifications are within the spirit and principles of the invention.
Claims (4)
1. The full-cyclone grading combustion chamber is characterized by comprising an air inlet pipe, a casing, a flame tube, a mounting disc, a main cyclone, N auxiliary cyclones, a corrugated heat shield and a high-energy electric nozzle, wherein N is a natural number greater than or equal to 3;
the casing is a hollow cylinder with two open ends;
one end of the air inlet pipe positioned at the downstream is hermetically and fixedly connected with one end of the casing at the upstream and is used for guiding air into the combustion chamber;
the flame tube is coaxially arranged in the casing, M connecting blocks are circumferentially arranged on the outer wall of the flame tube, and M is a natural number greater than or equal to 3; one end of each connecting block is fixedly connected with the outer wall of the flame tube, and the other end of each connecting block is fixedly connected with the inner wall of the casing;
the mounting disc is in a circular ring shape, and the outer wall of the mounting disc is hermetically and fixedly connected with one end of the flame tube, which is positioned at the upstream;
the main cyclone adopts secondary cyclone, is arranged in the center of the mounting plate, and the secondary outer ring of the main cyclone is coaxially and fixedly connected with the inner wall of the mounting plate;
n mounting holes are uniformly formed in the mounting plate around the circumference of the main cyclone, and the N auxiliary cyclones are arranged in the N mounting holes in a one-to-one correspondence manner;
the corrugated heat shield is arranged in the casing, and one end of the corrugated heat shield, which is positioned at the upstream, is coaxially and fixedly connected with one end of the flame tube, which is positioned at the downstream;
p oil injection rods which extend into the air inlet pipe from the outside are uniformly arranged in the circumferential direction of the air inlet pipe and are used for inputting oil for a main combustion stage, wherein P is a natural number which is more than or equal to 3;
the auxiliary cyclone adopts single-stage cyclone, a through hole is formed in the central body along the axis of the auxiliary cyclone, and a nozzle for spraying class-I fuel towards the combustion chamber is arranged in the through hole of the central body; the nozzles at the centers of the N auxiliary cyclones are communicated with the outside through oil pipelines penetrating through the casing and used for supplying oil to an input class;
the main cyclone is used for enabling a uniform oil-gas mixture formed by the atomization evaporation of the main fuel level fuel injected by the fuel injection rod and the full mixing of air to be divided into inner and outer two-stage cyclone flows with opposite rotation directions, so that the mixing capability of the inner and outer-stage airflow is enhanced, and the atomization capability of the main fuel level fuel and the uniformity of oil-gas mixing are improved;
the auxiliary cyclone is used for forming closed backflow, so as to provide an on-duty flow field for stable ignition and efficient combustion;
the high-energy electric nozzle sequentially penetrates through the casing and the flame tube and stretches into the combustion chamber behind the auxiliary cyclone for ignition.
2. The full cyclone stage combustor according to claim 1, wherein the outer ring of the secondary cyclone is elliptical, such that a straight line between the center of the ellipse and the center of the mounting plate is L1, and a straight line between the major axis of the ellipse is L2, such that L1 is perpendicular to L2.
3. The full swirl staged combustion chamber of claim 1 wherein the cross section of the air inlet duct gradually expands from upstream to downstream such that air is introduced into the combustion chamber at a reduced velocity and with an increased static pressure.
4. The full swirl staged combustion chamber of claim 1 wherein the nozzle in the central body throughbore of the secondary swirler is a small centrifugal nozzle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310177261.XA CN116293808A (en) | 2023-02-28 | 2023-02-28 | Full-cyclone grading combustion chamber |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310177261.XA CN116293808A (en) | 2023-02-28 | 2023-02-28 | Full-cyclone grading combustion chamber |
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| Publication Number | Publication Date |
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| CN116293808A true CN116293808A (en) | 2023-06-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202310177261.XA Pending CN116293808A (en) | 2023-02-28 | 2023-02-28 | Full-cyclone grading combustion chamber |
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| Country | Link |
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| CN (1) | CN116293808A (en) |
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