CN114526497A - Double-necking combined spiral-flow type center-grading high-temperature-rise combustion chamber - Google Patents
Double-necking combined spiral-flow type center-grading high-temperature-rise combustion chamber Download PDFInfo
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- CN114526497A CN114526497A CN202210019050.9A CN202210019050A CN114526497A CN 114526497 A CN114526497 A CN 114526497A CN 202210019050 A CN202210019050 A CN 202210019050A CN 114526497 A CN114526497 A CN 114526497A
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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
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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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
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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
- F23R3/26—Controlling the air flow
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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
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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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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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The utility model provides a hierarchical high temperature rise combustion chamber in two throat combination spiral-flow type center, including diffuser, interior machine casket, outer machine casket, flame tube, cap cover, splash guard, fuel nozzle and flame stabilizer, wherein: the inner casing and the outer casing are connected with the tail end of the diffuser, the fuel nozzle is used for conveying fuel oil to the flame tube, and the flame stabilizer is sleeved on the outer side of the nozzle shell at the downstream end of the fuel nozzle and is coaxially arranged with the nozzle shell; the flame stabilizer comprises a primary cyclone, a secondary cyclone and a tertiary cyclone which are sequentially sleeved, wherein the outlet end face of the downstream of the primary cyclone is connected with an inner reducing port, the outlet end face of the downstream of the secondary cyclone is connected with an outer reducing port, and the outlet end face of the downstream of the tertiary cyclone is connected with a variable cross-section ring; the flame tube comprises a flame tube inner ring and a flame tube outer ring. The multi-path classification and echelon utilization of the air are utilized, the stability of reliable ignition and combustion under low working conditions can be considered, and efficient smokeless combustion can be avoided under high working conditions.
Description
Technical Field
The disclosure relates to the technical field of aero-engines or gas turbines, in particular to a dual-throat Combined cyclone type center-Staged High Temperature rising combustion chamber (Secondary-nozzle Combined-fan Internally-Staged High Temperature Rise Combustor).
Background
In order to meet the requirement of high maneuverability of modern fighters, high-performance aircraft engines with high thrust-weight ratios are required to be developed, and high cycle parameters are required to be continuously pursued for the aircraft engines. Along with the increase of the thrust-weight ratio target of the aircraft engine from 8-10 to 16-20, the total pressure increase ratio target of the engine is increased to more than 40, the outlet temperature target of the combustion chamber is also increased from 1650K to 2150K, and even aimed at 2400K. The temperature rise of the combustion chamber is increased from 850K to 1150K or even 1400K. At present, the development of high-temperature combustion chambers of various large aircraft engine mechanisms is vigorously carried out.
At present, the biggest problem faced by the high-temperature combustion chamber technology is how to solve the contradiction between ignition, low working condition stability and smokeless high-efficiency combustion under high working conditions. To ensure good ignition and low operating stability of the engine, both conventional and high temperature rise combustors require the same low lean blow out limit. On the premise of ensuring the low lean burn flameout limit, under a large working condition, the conventional combustion chamber has low temperature rise and low total oil-gas ratio, so that the conventional tissue combustion technology can ensure high combustion efficiency and no smoke generation, namely the head air intake is controlled to be between 10 and 25 percent, and the residual gas coefficient of a main combustion area is still over 1.0; and for the high temperature rise combustion chamber, the total oil-gas ratio is greatly increased, if the design is carried out according to the flow distribution scheme of the original combustion chamber, the residual gas coefficient of the main combustion area of the combustion chamber under the working condition is less than 1, incomplete combustion and serious carbon deposition are inevitably caused, and even the smoke generation phenomenon is generated. Thus, much of the prior research has led to the recognition that as temperature increases, conventional combustor technology has failed to ensure efficient, smokeless combustion of the combustor.
Disclosure of Invention
In view of the above problem, the present disclosure provides a double-throat combined cyclone type center-staged high temperature rising combustion chamber capable of giving consideration to high-efficiency smokeless combustion under high operating conditions.
The utility model provides a hierarchical high temperature rise combustion chamber in two throat combination spiral-flow type center, including diffuser, interior machine casket, outer machine casket, flame tube, cap cover, splash guard, fuel nozzle and flame stabilizer, wherein: the inner casing and the outer casing are connected with the tail end of the diffuser, the fuel nozzle is used for conveying fuel oil to the flame tube, and the flame stabilizer is sleeved on the outer side of the nozzle shell at the downstream end of the fuel nozzle and is coaxially arranged with the nozzle shell; the flame stabilizer comprises a primary cyclone, a secondary cyclone and a tertiary cyclone which are sequentially sleeved, wherein the outlet end face of the downstream of the primary cyclone is connected with an inner reducing port, the outlet end face of the downstream of the secondary cyclone is connected with an outer reducing port, and the outlet end face of the downstream of the tertiary cyclone is connected with a variable cross-section ring; the flame tube comprises a flame tube inner ring and a flame tube outer ring, the middle parts of the flame tube inner ring and the flame tube outer ring are respectively provided with a main combustion hole, a mixing hole and a cooling hole, one ends of the flame tube inner ring and the flame tube outer ring close to the flame stabilizer are respectively connected with a cap, and the other ends of the flame tube inner ring and the flame tube outer ring form a flame tube outlet; the splash guard for sealing the flame tube is respectively lapped between the variable cross-section circular ring and the inner ring of the flame tube and between the variable cross-section circular ring and the outer ring of the flame tube, and the splash guard is provided with a cooling hole.
Optionally, the high temperature lift combustor further comprises: and the electric nozzle is used for igniting the flame tube, is arranged on the outer casing and respectively penetrates through the outer casing and the outer ring of the flame tube.
Optionally, the fuel nozzle is a liquid fuel nozzle or a gas fuel nozzle, wherein the structure of the liquid fuel nozzle includes a pressure atomization mode, a pneumatic atomization mode or a combination structure of different atomization modes.
Optionally, the nozzle orifice center of the fuel nozzle is located on the center line of the high temperature rise combustion chamber, and the fuel nozzle is a dual fuel channel fuel nozzle or a single fuel channel fuel nozzle.
Optionally, the primary cyclone and the secondary cyclone are axial-flow cyclones, the tertiary cyclone is a radial-flow cyclone, and the primary cyclone, the secondary cyclone and the tertiary cyclone are each independently of the other in a vane-type or chamfered hole-type structure.
Optionally, the primary swirler is flush with the outlet end face of the jet housing, and the outlet end faces downstream of the primary swirler and the secondary swirler are flush.
Optionally, the swirl number of the primary cyclone is 0.45-0.75, the swirl number of the secondary cyclone is 0.9-1.4, and the swirl number of the tertiary cyclone is 1.1-1.6.
Optionally, the contraction half angle α of the inner necking is between 15 ° and 23 °, the contraction half angle β of the outer necking is between 15 ° and 23 °, the variable cross-section annular ring is flared, and the expansion half angle γ of the meridian plane is between 25 ° and 35 °.
Optionally, the axial length of the external throat is 5mm to 10mm longer than the axial length of the internal throat.
Optionally, the cooling hole structures on the inner liner, the outer liner, and the splash plate are each independently configured as dense, chamfered holes or film slots.
Compared with the prior art, the double-throat combined spiral-flow type center-grading high-temperature-rise combustor provided by the disclosure at least has the following beneficial effects:
the invention adopts an organization combustion strategy of air classification and combustion zone. The air is divided into four stages in the head flow passage, so that the interaction of layered and zoned shearing, mixing and the like with the fuel in the flame tube is realized. The air in the nozzle air flow channel is beneficial to promoting the atomization of fuel oil and the mixing with liquid drops, and the carbon deposition at the head of the flame tube under high working conditions is reduced; the primary swirler realizes the shearing mixing of the rotating air and the liquid fog, further accelerates the fuel atomization and the mixing with the air, and improves the mixing uniformity of the fuel/air; the secondary swirler utilizes highly rotating turbulent air to achieve deeper shear mixing with fuel at an axially downstream location; the purpose of the tertiary swirler is, on the one hand, to create a recirculation zone within the liner to stabilize combustion and, on the other hand, to entrain the central fuel/air mixture and the high temperature flue gases downstream to achieve high efficiency and low emissions of combustion.
The invention is provided with an inner necking structure and an outer necking structure while air classification is arranged, and aims to consider the stability of reliable ignition and combustion under low working conditions and consider high-efficiency smokeless combustion under high working conditions. The arrangement of the inner reducing opening and the outer reducing opening enables graded air to be utilized in a gradient manner along the axial direction, the fuel flow is extremely low under low working conditions, and the air quantity near the fuel (in the inner area of the inner reducing opening) is small due to the inner reducing opening, so that reliable ignition and stable combustion under the low working conditions are ensured; under high working conditions, the fuel flow is large, the air amount in the inner area of the inner reducer is not enough to completely combust the fuel, the air at the outlet of the secondary swirler is further supplemented to combust, and simultaneously the air of the tertiary swirler is further supplemented in sequence, so that high-efficiency and smoke-free combustion under high working conditions is realized.
Compared with the prior art, the invention realizes multi-path classification and echelon utilization of air through structure optimization and innovation, not only can apply the aerodynamic characteristic of strong rotation shearing turbulence to carry out auxiliary crushing on liquid fuel, accelerate the mixing of the fuel and the air and improve the combustion performance; meanwhile, the fuel stratified combustion is realized by applying the echelon air intake concept, the stability of reliable ignition and combustion under low working conditions can be considered, and the efficient smokeless combustion can be realized under high working conditions.
Drawings
The above and other objects, features and advantages of the present disclosure will become more apparent from the following description of embodiments of the present disclosure with reference to the accompanying drawings, in which:
FIG. 1 schematically illustrates a block diagram of a dual-throat combined cyclonic center staged high temperature lift combustor in accordance with an embodiment of the present disclosure;
FIG. 2 schematically illustrates a three-dimensional cross-sectional view of a dual-throat combination cyclonic center staged high temperature lift combustor, according to an embodiment of the present disclosure;
FIG. 3 schematically illustrates a close-up view of a flame holder, according to an embodiment of the disclosure;
fig. 4 schematically shows a structure view of an air flow passage according to an embodiment of the present disclosure.
[ description of reference ]
1-a diffuser; 2-inner case; 3-an outer casing; 4-inner ring of flame tube; 5-outer ring of flame tube; 6-a cap; 7-a splash shield; 8-a fuel nozzle; 9-a spout housing; 10-flame stabilizer; 11-a primary cyclone; 12-a secondary cyclone; 13-a tertiary cyclone; 14-inner necking; 15-necking out; 16-a variable cross-section ring; 17-electric nozzle; 21-a diffuser flow channel; 22-inner thigh flow channel; 23-outer thigh flow channel; 24-a head flow channel; 25-nozzle air flow path; 26-a primary cyclone runner; 27-secondary swirler flow channel; 28-tertiary swirler flow passage; 29-cooling holes; 30-a flame tube; 31-main burning hole; 32-a mixing hole; 33-flame tube outlet.
Detailed Description
For the purpose of promoting a better understanding of the objects, aspects and advantages of the present disclosure, reference is made to the following detailed description taken in conjunction with the accompanying drawings. It is to be understood that the described embodiments are only a few, and not all, of the disclosed embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, or components.
In the present disclosure, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integral; can be mechanically connected, electrically connected or can communicate with each other; either directly or indirectly through intervening media, either internally or in any other suitable relationship. The specific meaning of the above terms in the present disclosure can be understood by those of ordinary skill in the art as appropriate.
All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art unless otherwise defined. It is noted that the terms used herein should be interpreted as having a meaning that is consistent with the context of this specification and should not be interpreted in an idealized or overly formal sense.
FIG. 1 schematically illustrates a block diagram of a dual-throat combined cyclonic center staged high temperature lift combustor in accordance with an embodiment of the present disclosure. FIG. 2 schematically illustrates a three-dimensional cross-sectional view of a dual-throat combination cyclonic center staged high temperature lift combustor, according to an embodiment of the present disclosure.
With reference to fig. 1 to 2, an embodiment of the present disclosure provides a dual-throat combined cyclone type center-staged high temperature rising combustor, which includes a diffuser 1, an inner casing 2, an outer casing 3, a flame tube 30, a cap 6, a splash plate 7, a fuel nozzle 8, and a flame stabilizer 10. Wherein, the inner casing 2 and the outer casing 3 are connected with the tail end of the diffuser 1. The fuel nozzle 8 is used for delivering fuel oil to the flame tube 30, and the flame holder 10 is sleeved outside the spout shell 9 at the downstream end of the fuel nozzle 8 and is arranged coaxially with the spout shell 9.
Further, with continued reference to fig. 1, the high temperature combustion chamber may further include an electric nozzle 17 for igniting the liner 30, the electric nozzle 17 being disposed on the outer casing 3 and penetrating through the outer casing 3 and the liner outer ring 5, respectively.
FIG. 3 schematically illustrates a close-up view of a flame holder, according to an embodiment of the disclosure.
As shown in fig. 3, the flame holder 10 includes a primary cyclone 11, a secondary cyclone 12 and a tertiary cyclone 13, which are sequentially sleeved, an inner reducing port 14 is connected to an outlet end surface of the downstream of the primary cyclone 11, an outer reducing port 15 is connected to an outlet end surface of the downstream of the secondary cyclone 12, and a variable cross-section ring 16 is connected to an outlet end surface of the downstream of the tertiary cyclone 13. Specifically, the primary cyclone 11 is sleeved outside the nozzle casing 9, the secondary cyclone 12 is sleeved outside the primary cyclone 11, and the tertiary cyclone 13 is sleeved outside the secondary cyclone 12.
Further, the primary swirler 11 is flush with the outlet end surface of the jet casing 9, and the primary swirler 11 and the outlet end surface downstream of the secondary swirler 12 are flush.
Further, the primary cyclone 11 and the secondary cyclone 12 are axial flow cyclones, the tertiary cyclone 13 is a radial flow cyclone, and the primary cyclone 11, the secondary cyclone 12 and the tertiary cyclone 13 are respectively and independently of a blade type or a chamfered hole type structure. The swirl number of the primary cyclone 11 is 0.45-0.75, the swirl number of the secondary cyclone 12 is 0.9-1.4, and the swirl number of the tertiary cyclone 13 is 1.1-1.6.
Through this disclosed embodiment, the structure of interior throat 14 and outer throat 15 sets up aim at, compromises the stability of the reliable ignition of low operating mode and burning on the one hand, and high efficiency does not have the smoldering burning when on the other hand compromises the high operating mode. The arrangement of the inner reducing opening 14 and the outer reducing opening 15 enables graded air to be utilized in a gradient mode along the axial direction, the fuel flow is extremely low under low working conditions, and the air quantity near the fuel (in the inner area of the inner reducing opening) is small due to the inner reducing opening, so that reliable ignition and stable combustion under the low working conditions are guaranteed; under high working conditions, the fuel flow is large, the air amount in the inner area of the inner reducer is not enough to completely combust the fuel, the air at the outlet of the secondary cyclone 12 is further supplemented to combust, and simultaneously the air of the tertiary cyclone 13 is further supplemented in sequence, so that high-efficiency and smoke-free combustion under high working conditions is realized.
With continued reference to fig. 3, preferably, the half-angle α of contraction of the inner throat 14 is between 15 ° and 23 °, the half-angle β of contraction of the outer throat 15 is between 15 ° and 23 °, the variable cross-section ring 16 is flared, and the half-angle γ of expansion of the meridian plane is between 25 ° and 35 °.
Further, the axial length of the outer constriction 15 is 5mm to 10mm longer than the axial length of the inner constriction 14.
Fig. 4 schematically shows a structure view of an air flow passage according to an embodiment of the present disclosure.
As shown in fig. 4, in the embodiment of the present disclosure, the flame tube 30 includes a flame tube inner ring 4 and a flame tube outer ring 5, the middle portions of the flame tube inner ring 4 and the flame tube outer ring 5 are respectively provided with a main combustion hole 31, a mixing hole 32 and a cooling hole 29, one ends of the flame tube inner ring 4 and the flame tube outer ring 5 close to the flame stabilizer 10 are respectively connected to the cap 6, and the other ends of the flame tube inner ring 4 and the flame tube outer ring 5 form a flame tube outlet 33; the splash guard 7 for sealing the flame tube 30 is respectively lapped between the variable cross-section circular ring 16 and the inner flame tube ring 4 and between the variable cross-section circular ring 16 and the outer flame tube ring 5, and the splash guard 7 is also provided with cooling holes 29.
Based on the above disclosure, a diffuser flow passage 21 is formed inside the diffuser 1, an inner flow passage 22 is formed between the inner casing 2 and the inner ring 4 of the liner, an outer flow passage 23 is formed between the outer casing 3 and the outer ring 5 of the liner, and air flowing in from the diffuser flow passage 21 simultaneously flows into the inner flow passage 22, the outer flow passage 23 and the head flow passage 24. In the flame holder 10, the insides of the primary cyclone 11, the secondary cyclone 12 and the tertiary cyclone 13 form a primary cyclone flow passage 26, a secondary cyclone flow passage 27 and a tertiary cyclone flow passage 28, respectively. In addition, a nozzle air flow passage 25 communicating with the outside air is formed inside the fuel nozzle 8.
Therefore, as can be seen from fig. 1 to 4 and the above disclosure, the operating principle of the dual-throat combined cyclone type center staged high temperature lift combustor provided by the present embodiment lies in: the air flows into the inner flow channel 22, the outer flow channel 23 and the head flow channel 24 after passing through the diffuser flow channel 21, wherein:
(1) the air flowing into the inner thigh runner 22 flows into the flame tube 30 through the main combustion hole 31, the mixing hole 32 and the cooling hole 29 on the flame tube inner ring 4;
(2) the air flowing into the outer flow channel 23 flows into the flame tube 30 through the main combustion holes 31, the mixing holes 32 and the cooling holes 29 on the outer ring 5 of the flame tube;
(3) the air flowing into the head flow passage 24 flows into the combustor basket 30 through the nozzle air flow passage 25, the primary swirler flow passage 26, the secondary swirler flow passage 27, the tertiary swirler flow passage 28, and the cooling holes 29 in the splash plate 7.
Meanwhile, the fuel oil enters the combustor basket 30 through the fuel nozzle 8, is mixed with air and is combusted after the electric torch 17 is ignited, and then high-temperature gas is discharged from the combustor basket outlet 33.
Analysis it can be seen that the present disclosure employs an organized combustion strategy of air staging and combustion zones. The air is divided into four stages in the head flow passage, so that the interaction of layered and partitioned shearing, mixing and the like with the fuel in the flame tube is realized. The air in the nozzle air flow passage is beneficial to promoting the atomization of fuel oil and the mixing with liquid drops, and the carbon deposition at the head of the flame tube under high working conditions is reduced; the primary swirler realizes the shearing mixing of the rotating air and the liquid fog, further accelerates the fuel atomization and the mixing with the air, and improves the mixing uniformity of the fuel/air; the secondary swirler utilizes highly rotating turbulent air to achieve deeper shear mixing with fuel at an axially downstream location; the purpose of the tertiary swirler is, on the one hand, to create a recirculation zone within the liner to stabilize combustion and, on the other hand, to entrain the central fuel/air mixture and the high temperature flue gases downstream to achieve high efficiency and low emissions of combustion.
Further, the air inflow of the nozzle air channel 25 accounts for 1% -3% of the total air inflow of the combustion chamber, the air inflow of the primary swirler channel 26 accounts for 4% -10% of the total air inflow of the combustion chamber, the air inflow of the secondary swirler channel 27 accounts for 4% -10% of the total air inflow of the combustion chamber, and the air inflow of the tertiary swirler channel 28 accounts for 10% -18% of the total air inflow of the combustion chamber. It can be understood that the specific air intake amount is closely related to the fuel-air ratio of the state of the design point of the combustion chamber, and the adjustment of the air intake amount can be carried out by a person skilled in the art according to the actual requirement, and is not limited herein.
Further, the fuel nozzles 8 are liquid fuel nozzles or gas fuel nozzles. If a liquid fuel nozzle is adopted, the structure of the liquid fuel nozzle may include a pressure atomization mode, a pneumatic atomization mode or a combined structure of different atomization modes. For example, in some embodiments, the combination structure may include other combinations of pressure atomization and pneumatic atomization, and other combinations of atomization, such as at least two of evaporation tube atomization and air-assisted atomization, are also included in the scope of the present disclosure.
Further, the nozzle hole center of the fuel nozzle 8 is located on the center line of the high temperature rise combustion chamber, and the fuel nozzle 8 is a dual fuel channel fuel nozzle or a single fuel channel fuel nozzle.
Further, the cooling hole 29 structures on the inner liner ring 4, the outer liner ring 5 and the splash plate 7 are each independently provided as dense chamfered holes or film slots.
Furthermore, the air inflow of the main combustion hole 31 accounts for 15% -30% of the total air inflow of the combustion chamber, and the air inflow of the blending hole 32 accounts for 0% -15% of the total air inflow of the combustion chamber. The specific air inflow is closely related to the state oil-gas ratio of the combustion chamber at the design point, and the skilled person can adjust the air inflow according to the actual requirement without limitation.
To sum up, the double-throat combined spiral-flow type center-staged high-temperature-rise combustion chamber provided by the embodiment of the disclosure realizes multi-path staging and echelon utilization of air through structural optimization and innovation, and not only can be used for assisting in crushing liquid fuel by applying the pneumatic characteristic of strong rotary shearing turbulence, accelerating the mixing of the fuel and the air, and improving the combustion performance; meanwhile, the fuel stratified combustion is realized by applying the echelon air intake concept, the stability of reliable ignition and combustion under low working conditions can be considered, and the efficient smokeless combustion can be realized under high working conditions.
In the description of the present disclosure, it is to be understood that the terms "upper", "lower", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are only for convenience in describing the present disclosure and simplifying the description, and do not indicate or imply that the referred devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present disclosure. Throughout the drawings, like elements are represented by like or similar reference numerals. Conventional structures or constructions will be omitted when they may obscure the understanding of the present disclosure. And the shapes, sizes and positional relationships of the components in the drawings do not reflect the actual sizes, proportions and actual positional relationships.
Similarly, in the above description of exemplary embodiments of the disclosure, various features of the disclosure are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure and aiding in the understanding of one or more of the various disclosed aspects. Reference to the description of the terms "other embodiments," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the disclosure. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The above-mentioned embodiments are intended to illustrate the objects, aspects and advantages of the present disclosure in further detail, and it should be understood that the above-mentioned embodiments are only illustrative of the present disclosure and are not intended to limit the present disclosure, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present disclosure should be included in the scope of the present disclosure.
Claims (10)
1. The utility model provides a hierarchical high temperature of two throat combination spiral-flow type center rises combustion chamber which characterized in that, includes diffuser (1), interior casket (2), outer casket (3), flame tube (30), cap (6), splash guard (7), fuel nozzle (8) and flame stabilizer (10), wherein:
the inner casing (2) and the outer casing (3) are connected with the tail end of the diffuser (1), the fuel nozzle (8) is used for conveying fuel oil to the flame tube (30), and the flame holder (10) is sleeved on the outer side of the nozzle shell (9) at the downstream end of the fuel nozzle (8) and is coaxially arranged with the nozzle shell (9);
the flame stabilizer (10) comprises a primary cyclone (11), a secondary cyclone (12) and a tertiary cyclone (13) which are sequentially sleeved, wherein the outlet end face of the downstream of the primary cyclone (11) is connected with an inner reducing port (14), the outlet end face of the downstream of the secondary cyclone (12) is connected with an outer reducing port (15), and the outlet end face of the downstream of the tertiary cyclone (13) is connected with a variable cross-section ring (16);
the flame tube (30) comprises a flame tube inner ring (4) and a flame tube outer ring (5), the middle parts of the flame tube inner ring (4) and the flame tube outer ring (5) are respectively provided with a main combustion hole (31), a mixing hole (32) and a cooling hole (29), one ends of the flame tube inner ring (4) and the flame tube outer ring (5) close to the flame stabilizer (10) are respectively connected with the cap cover (6), and the other ends of the flame tube inner ring (4) and the flame tube outer ring (5) form a flame tube outlet (33); splash plates (7) for sealing the flame tube (30) are respectively lapped between the variable cross-section circular ring (16) and the inner ring (4) of the flame tube and between the variable cross-section circular ring (16) and the outer ring (5) of the flame tube, and cooling holes (29) are also formed in the splash plates (7).
2. The dual-throat combined cyclonic center staged high temperature lift combustor as claimed in claim 1, further comprising:
the electric nozzle (17) is used for igniting the flame tube (30), and the electric nozzle (17) is arranged on the outer casing (3) and penetrates through the outer casing (3) and the outer ring (5) of the flame tube respectively.
3. The dual-throat combined cyclone type center-staged high temperature rising combustion chamber as claimed in claim 1, wherein the fuel nozzle (8) is a liquid fuel nozzle or a gas fuel nozzle, and the structure of the liquid fuel nozzle comprises a pressure atomization mode, a pneumatic atomization mode or a combined structure of different atomization modes.
4. The dual-throat combined cyclone type center-staged high temperature rising combustion chamber as claimed in claim 1, wherein the nozzle center of the fuel nozzle (8) is located on the center line of the high temperature rising combustion chamber, and the fuel nozzle (8) is a dual fuel channel fuel nozzle or a single fuel channel fuel nozzle.
5. The dual-throat combined cyclonic center-staged high temperature lift combustor as claimed in claim 1, wherein the primary cyclone (11) and the secondary cyclone (12) are axial flow cyclones, the tertiary cyclone (13) is a radial flow cyclone, and the primary cyclone (11), the secondary cyclone (12) and the tertiary cyclone (13) are each independently of the other of a vane-type or a chamfered-hole-type structure.
6. The dual-throat combined cyclone type center-staged high temperature rising combustor as claimed in claim 1, wherein the primary cyclone (11) is flush with an outlet end surface of the nozzle housing (9), and the primary cyclone (11) and an outlet end surface downstream of the secondary cyclone (12) are flush.
7. The dual-throat combined cyclone type center-staged high temperature rising combustor as claimed in claim 1, wherein the cyclone number of the primary cyclone (11) is 0.45-0.75, the cyclone number of the secondary cyclone (12) is 0.9-1.4, and the cyclone number of the tertiary cyclone (13) is 1.1-1.6.
8. The dual-throat combined cyclone type center-staged high temperature rising combustor as claimed in claim 1, wherein the contraction half angle α of the inner throat (14) is between 15 ° and 23 °, the contraction half angle β of the outer throat (15) is between 15 ° and 23 °, the variable cross-section ring (16) is flared and the expansion half angle γ of the meridian plane is between 25 ° and 35 °.
9. The dual-throat combined cyclonic center staged high temperature lift combustor of claim 1, wherein the axial length of the outer throat (15) is 5mm to 10mm longer than the axial length of the inner throat (14).
10. The dual-throat combined cyclone type center staged high temperature lift combustor as claimed in claim 1, wherein the cooling hole (29) structures on the inner liner ring (4), the outer liner ring (5) and the splash plate (7) are each independently arranged as dense chamfer holes or film slots.
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| CN115270319B (en) * | 2022-06-21 | 2023-08-25 | 哈尔滨工程大学 | Automatic design modeling method for combustion chamber of gas turbine |
| CN115355540A (en) * | 2022-08-05 | 2022-11-18 | 中国航发沈阳发动机研究所 | Three-cyclone main combustion chamber of aero-engine |
| CN117610235A (en) * | 2023-10-26 | 2024-02-27 | 中国石油大学(北京) | Method and system for predicting rotational flow shrinkage expansion type multielement liquid phase atomization evaporation characteristic parameters |
| CN117610235B (en) * | 2023-10-26 | 2024-06-11 | 中国石油大学(北京) | Method and system for predicting rotational flow shrinkage expansion type multielement liquid phase atomization evaporation characteristic parameters |
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