CN115127126A - Annular combustion chamber and staged fuel nozzle and method for suppressing oscillatory combustion - Google Patents
Annular combustion chamber and staged fuel nozzle and method for suppressing oscillatory combustion Download PDFInfo
- Publication number
- CN115127126A CN115127126A CN202110332566.4A CN202110332566A CN115127126A CN 115127126 A CN115127126 A CN 115127126A CN 202110332566 A CN202110332566 A CN 202110332566A CN 115127126 A CN115127126 A CN 115127126A
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- China
- Prior art keywords
- combustion
- stage
- main
- fuel spray
- annular
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/52—Toroidal combustion chambers
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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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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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
Abstract
The annular combustion chamber staged fuel nozzle comprises a pre-combustion stage and a main combustion stage, wherein the main combustion stage comprises a plurality of main combustion stage fuel spray rods, and the axial lengths of the main combustion stage fuel spray rods are provided with a plurality of specifications, so that the flight time of fuel in the main combustion stage fuel spray rods with different specifications from the injection position to the flame peak surface is inconsistent, and the effect of eliminating and inhibiting oscillatory combustion is achieved. An annular combustor and a method of suppressing oscillating combustion in an annular combustor are also provided.
Description
Technical Field
The invention relates to a staged fuel nozzle.
Background
In order to reduce the engine pollution emission, especially the NOx emission, most low-emission combustors adopt a lean premixed combustion organization mode, and the typical characteristic is that a staged combustion mode is adopted. The fuel oil grading nozzle is a fuel oil nozzle which divides fuel oil entering a combustion chamber into two or more stages, the fuel oil grading nozzle is respectively mixed with air entering from a main combustion stage swirl passage and a pre-combustion stage swirl passage of the grading nozzle to form a main combustion stage fuel air mixture and a pre-combustion stage fuel air mixture, and the main combustion stage fuel air mixture and the pre-combustion stage fuel air mixture are combusted in different areas at the downstream of the grading nozzle in a zoning mode, so that pollution emission of an aeroengine or a gas turbine is reduced.
Generally, a fuel classifying nozzle is generally divided into a main combustion stage (also called a premixing nozzle) and a pre-combustion stage (also called a Pilot nozzle), wherein the main combustion stage adopts a premixing combustion mode, and the pre-combustion stage adopts a diffusion combustion mode, so that the flame combustion temperature can be effectively reduced, and the NOx emission of a combustion chamber can be reduced. However, premixed combustion is prone to cause combustion oscillation, the combustion oscillation is an oscillation process of mutual coupling of combustion heat release pulsation and pressure pulsation in combustion chambers of aircraft engines and gas turbines, and when the oscillation is intensified, phenomena such as engine hardware damage, unstable thrust, even explosion and the like can be caused.
To suppress the problem of combustion oscillations, chinese patent CN203671658 discloses a combustion chamber in which combustion instabilities can be suppressed by providing at least two sets of differently sized head structures. However, further experiments have found that the combustion chamber with two sets of head structures of different sizes cannot effectively inhibit combustion in various combustion environments; in addition, the design of the head structures with different sizes is time-consuming and inefficient in actual manufacturing.
Disclosure of Invention
The invention aims to provide a grading fuel nozzle of an annular combustion chamber, which can effectively avoid combustion oscillation of the annular combustion chamber under various working conditions, and has simple design and easy manufacture.
The annular combustion chamber staged fuel nozzle comprises a pre-combustion stage and a main combustion stage, wherein the main combustion stage comprises a plurality of main combustion stage fuel spray rods, and the axial lengths of the plurality of main combustion stage fuel spray rods are provided with a plurality of specifications.
In one or more embodiments, the primary fuel stage fuel spray bars having different axial length specifications are arranged circumferentially adjacent to one another.
In one or more embodiments, the fuel injection rods of the main combustion stage are arranged circumferentially adjacent to each other in sequence according to increase or decrease of axial length.
In one or more embodiments, the primary fuel stage fuel spray bars of different axial length specifications are randomly arranged circumferentially.
In one or more embodiments, the fuel injection rods of the main combustion stage having the same axial length specification are circumferentially adjacently distributed to form groups, and a plurality of the groups are circumferentially distributed.
In one or more embodiments, the number of primary fuel stage fuel spray bars is an integer multiple of the number of axial length specification types.
In one or more embodiments, the primary fuel stage fuel spray bars of different axial length specifications are not evenly distributed circumferentially.
It is another object of the present invention to provide an annular combustor that uses the above annular combustor staging fuel nozzle.
Still another object of the present invention is to provide a method for suppressing the oscillating combustion in an annular combustion chamber, which employs main fuel-grade fuel spray bars with different axial lengths, so that the flight times of different fuel spray positions reaching the flame front are not uniformly distributed, thereby avoiding the occurrence of combustion oscillation.
The annular combustion chamber grading fuel nozzle is easy to manufacture by arranging the main combustion level fuel spray rods with different axial length specifications in the circumferential direction, meanwhile, the distance from a part of the main combustion level fuel spray rods to the downstream axial extension of a combustion chamber is longer, and the distance from a part of the main combustion level fuel spray rods to the downstream axial extension of the combustion chamber is shorter, so that the distances from main combustion level fuel spray points at the tail ends of the main combustion level fuel spray rods to the main combustion level channel outlet are different, the flying time of fuel in the spray rods with different specifications reaching the flame peak surface from the spray position is unevenly distributed, the flying time of most fuel spray points under any operation working condition of an engine is not in the 1/4 phase difference range of oscillation frequency, and therefore oscillation combustion is effectively eliminated and inhibited.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a schematic illustration of the structure of an aircraft engine;
FIG. 2 is a schematic view of the structure of an annular combustor;
FIG. 3 is a schematic illustration of the structure of a staged fuel nozzle for an annular combustor;
FIG. 4 is a schematic illustration of a first embodiment of an annular combustor stage fuel nozzle;
FIG. 5 is a schematic illustration of a second embodiment of an annular combustor stage fuel nozzle;
FIG. 6 is a schematic illustration of a third embodiment of an annular combustor stage fuel nozzle;
FIG. 7 is a schematic view of a third embodiment of an annular combustor stage fuel nozzle in another orientation.
Description of symbol mark
1 Low pressure compressor
2 high-pressure compressor
3 annular combustion chamber
4 high-pressure turbine
5 Low-pressure turbine
300 diffuser
302 combustion chamber outer casing
304 combustion chamber inner casing
306 flame tube outer ring
308 inner ring of flame tube
310 annular combustion chamber staged fuel nozzle
340 high pressure turbine vane
312 main fuel stage oil way
316 main combustion stage
318 precombustion stage
320 main combustion stage oil collecting ring cavity
324 primary stage direct spray
328 outer swirler of main combustion stage
330 inner swirler of main combustion stage
350 main combustion grade fuel spray rod
351 main combustion level fuel oil injection point
352 precombustion stage fuel nozzle
350A, 350B, 350C, 350D, 350E axial length specification
360 groups
Detailed Description
The present invention is further described in the following description with reference to specific embodiments and the accompanying drawings, wherein the details are set forth in order to provide a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms different from those described herein, and it will be readily appreciated by those skilled in the art that the present invention can be implemented in many different forms without departing from the spirit and scope of the invention. It is noted that these and other figures which follow are merely exemplary and not drawn to scale and should not be considered as limiting the scope of the invention as it is actually claimed.
The aircraft engine shown in fig. 1 comprises a low-pressure compressor 1, a high-pressure compressor 2, an annular combustion chamber 3, a high-pressure turbine 4 and a low-pressure turbine 5. Air is compressed by the low-pressure compressor 1 and then enters the high-pressure compressor 2, the high-pressure air enters the annular combustion chamber 3 to be combusted with fuel, high-temperature high-pressure gas formed after combustion enters the high-pressure turbine 4 and the low-pressure turbine 5, and the high-pressure compressor 2 and the low-pressure compressor 1 are respectively driven by the turbine to do work.
Fig. 2 shows an enlarged view of the annular combustion chamber 3. The annular combustor 3 includes a diffuser 300, an outer combustor casing 302, an inner combustor casing 304, an outer liner ring 306, an inner liner ring 308, and an annular combustor staging fuel nozzle 310. The plurality of annular combustion chamber staged fuel nozzles 310 are uniformly arranged along the circumferential direction of the single-ring cavity structure of the annular combustion chamber 3, for example, the number of the annular combustion chamber staged fuel nozzles 310 is 10-60, the annular combustion chamber staged fuel nozzles are circumferentially distributed in the single-ring cavity, and air incoming flow enters the flame tube through the annular combustion chamber staged fuel nozzles 310 after passing through the diffuser 300.
The annular combustor staging fuel nozzle 310 employs a center staging configuration. As shown in FIG. 3, the annular combustor staging fuel nozzle 310 includes a main combustion stage 316 and a pre-combustion stage 318, the main combustion stage 316 being disposed coaxially with the pre-combustion stage 318, the pre-combustion stage 318 being centrally located, the main combustion stage 316 being disposed peripherally to the pre-combustion stage 318.
The main combustion stage oil path 312 is connected with the main combustion stage oil collecting annular cavity 320, fuel oil in the main combustion stage oil collecting annular cavity 320 is sprayed to the main combustion stage premixing pre-evaporation channel through a main combustion stage fuel oil spraying point 351 at the end part of a main combustion stage fuel oil spraying rod 350 on the main combustion stage oil collecting annular cavity 320 to form a main combustion stage direct spraying mist 324, and the main combustion stage direct spraying mist is crushed and atomized under the shearing action of two rotational flows of a main combustion stage outer side cyclone 328 and a main combustion stage inner side cyclone 330 to form a main combustion stage pneumatic atomized oil mist which is mixed with air to form a uniform oil-gas mixture, so that premixing pre-evaporation combustion is realized.
As shown in connection with FIG. 4, the main stage 316 includes a plurality of main stage fuel spray bars 350, the plurality of main stage fuel spray bars 350 disposed around the pre-combustion stage fuel nozzle ports 352. The axial length of the plurality of main combustion stage fuel spray bars 350 has a plurality of specifications, and the oscillating combustion of the annular combustion chamber can be effectively inhibited. As shown in fig. 4 for the first embodiment of the annular combustor staging fuel nozzle, the main stage fuel spray bars 350 have 2 different axial length specifications 350A, 350B, and the main stage fuel spray bars 350 having different axial length specifications 350A, 350B are arranged circumferentially adjacent to each other. Through designing into different axial length with main fuel grade fuel spray lance 350 to change the flight time of fuel injection position to the flame frontal, make the flight time uneven distribution that different fuel injection positions reachd the flame frontal, can effectively restrain the oscillatory combustion. Meanwhile, only the finished product main combustion grade fuel spray rods with different axial dimension specifications need to be installed on the main combustion grade oil collecting ring cavity in the manufacturing and production process of the nozzle, assembly can be completed, excessive steps do not need to be consumed, and production efficiency is effectively improved.
One arrangement of the main stage fuel spray bars 350 is circumferentially adjacent main stage fuel spray bars 350 having different axial length specifications. In a second embodiment as shown in fig. 5, main stage fuel spray bars 350 have 5 different axial length specifications 350A, 350B, 350C, 350D, 350E, with 5 different axial length main stage fuel spray bars 350 being circumferentially adjacent. By providing 5 axial length types of main stage fuel spray bars 350, the time of flight for the fuel injected by the fuel spray points to reach the flame front in the circumferential direction is almost completely inconsistent, and the use of spray bars of multiple axial length specifications further enhances this difference, thereby further suppressing the oscillatory combustion.
The main combustion stage fuel spray bars 350 can be sequentially and circumferentially arranged adjacently according to the increase or decrease of the axial length, or the main combustion stage fuel spray bars 350 with different axial length specifications are randomly and circumferentially arranged. For example, in fig. 5, the axial lengths of the main stage fuel spray bars 350A, 350B, 350C, 350D, 350E decrease in order, and the main stage fuel spray bars 350A, 350B, 350C, 350D, 350E are arranged in order with increasing axial lengths. For another example, the axial length distribution of the main combustion stage fuel spray bars 350A, 350B, 350C, 350D and 350E is random, so that the distances from the main combustion stage fuel spray points 351 on each circumferentially distributed adjacent main combustion stage fuel spray bar 350 to the main combustion stage channel outlet are different, the oscillatory combustion is effectively inhibited, and the stability and the safety of the engine during operation are improved.
The number of the main combustion stage fuel spray bars 350 is preferably integral multiple of the number of the axial length specification types, so that regular arrangement of the main combustion stage fuel spray bars 350 with different axial length specifications is realized. For example, in the second embodiment shown in fig. 5, the main stage fuel spray bars 350 have 5 different axial length specifications, so that the total number of the main stage fuel spray bars 350 is an integral multiple of 5, and the main stage fuel spray bars 350 with different axial length specifications can be arranged in the circumferential direction in equal number, so that the stability of fuel injection is improved.
The total number of the main fuel stage fuel spray bars 350 ranges from 4 to 30. In other engine models, the number of main stage fuel spray bars 350 is selected by the operator to be the appropriate arrangement based on the specific injection requirements of the main stage 316.
Another arrangement of the main stage fuel spray bars 350 is that the main stage fuel spray bars 350 with the same axial length specification are circumferentially adjacently distributed to form groups 360, and a plurality of the groups 360 are circumferentially distributed. Referring specifically to fig. 6 and 7, main stage fuel spray bar 350 has 2 different axial length specifications 350A, 350B. The main combustion stage fuel spray bars 350 with the same axial length specification 350A are circumferentially and adjacently distributed to form a group 360; the primary stage fuel spray bars 350 of the same axial length specification 350B are circumferentially adjacent to one another to form groups 360 ', and groups 360 and 360' are circumferentially spaced to result in different distances from each primary stage fuel spray point 351 to the primary stage passage outlets. Those skilled in the art will appreciate that the arrangement of main stage fuel spray bars 350 in a set 360, 360' includes, but is not limited to, the embodiments shown in fig. 6 and 7.
The main stage fuel spray bars 350 of different axial length specifications may also be non-uniformly distributed circumferentially, i.e., the circumferential distance between adjacent pairs of main stage fuel spray bars 350 is not uniform. By arranging the main fuel level fuel spray rods 350 which are not uniformly distributed in the circumferential direction, the distances from the oil mist sprayed from the same main fuel level oil collecting annular cavity 320 to the flame front are inconsistent, coupling between the heat release pulsation and the inlet pressure pulsation of the combustion chamber is effectively avoided, and the phenomenon of combustion oscillation is restrained.
In combination with the above description of the staged fuel nozzle 310 for the annular combustion chamber, it can be understood that an annular combustion chamber 3 can be obtained, and the staged fuel nozzle 310 for the annular combustion chamber 3 can achieve the effects of eliminating and suppressing the oscillatory combustion under any operation condition of the engine, and meanwhile, the staged fuel nozzle for the annular combustion chamber has a simple structure and is easy to manufacture.
In addition, a method of suppressing combustion oscillations in an annular combustor can be understood that uses main stage fuel spray bars 350 of different axial lengths to provide non-uniform distribution of time of flight to the flame front at different fuel injection locations to avoid combustion oscillations. According to the method, the coupling phenomenon generated between the heat release pulsation and the inlet pressure pulsation of the combustion chamber is weakened by arranging the main combustion stage fuel spray rods 350 in uneven arrangement, so that the annular combustion chambers 3 of the main combustion stage fuel spray rods 350 with different specifications and axial lengths do not generate combustion oscillation under any working condition, potential safety hazards are eliminated, and the stability and the safety of the operation of an engine are ensured.
Although the present invention has been disclosed in terms of preferred embodiments, it is not intended to be limited thereto, and variations and modifications may be made by those skilled in the art without departing from the spirit and scope of the invention. For example, the number of axial length specifications for the main stage fuel spray bars may be selected by the operator for a particular combustion environment; for another example, the number of main stage fuel spray bars within a group having the same axial length specification may also be varied. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (9)
1. The annular combustion chamber staged fuel nozzle comprises a pre-combustion stage; and
a main combustion stage comprising a plurality of main combustion stage fuel spray bars,
the axial length of the plurality of main stage fuel spray bars has a plurality of specifications.
2. The annular combustor stage fuel nozzle as set forth in claim 1, wherein said primary fuel stage fuel lances having different axial length specifications are circumferentially adjacent.
3. The annular combustor stage fuel nozzle as claimed in claim 2, wherein the primary stage fuel spray bars are circumferentially adjacent in sequence as axial length increases or decreases.
4. The annular combustor stage fuel nozzle as set forth in claim 2, wherein said primary stage fuel spray bars of different axial length specifications are randomly circumferentially arranged.
5. The annular combustor stage fuel nozzle as set forth in claim 1, wherein said primary stage fuel spray bars having the same axial length specifications are circumferentially adjacently distributed to form groups, a plurality of said groups being circumferentially distributed.
6. The annular combustor stage fuel nozzle as set forth in claim 1, wherein the number of the main stage fuel spray bars is an integer multiple of the number of axial length specification types.
7. The annular combustor stage fuel nozzle as set forth in claim 1, wherein said primary stage fuel spray bars of different axial length specifications are circumferentially unevenly distributed.
8. Annular combustion chamber, characterized in that a staged fuel nozzle of the annular combustion chamber according to any of claims 1 to 7 is used.
9. A method for inhibiting oscillation combustion of an annular combustion chamber is characterized in that main combustion grade fuel spray rods with different specifications and axial lengths are adopted, so that the flight time of different fuel spray positions reaching a flame frontal surface is unevenly distributed, and combustion oscillation is avoided.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110332566.4A CN115127126A (en) | 2021-03-26 | 2021-03-26 | Annular combustion chamber and staged fuel nozzle and method for suppressing oscillatory combustion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110332566.4A CN115127126A (en) | 2021-03-26 | 2021-03-26 | Annular combustion chamber and staged fuel nozzle and method for suppressing oscillatory combustion |
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| CN115127126A true CN115127126A (en) | 2022-09-30 |
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| CN202110332566.4A Pending CN115127126A (en) | 2021-03-26 | 2021-03-26 | Annular combustion chamber and staged fuel nozzle and method for suppressing oscillatory combustion |
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4438626A (en) * | 1981-09-11 | 1984-03-27 | General Electric Company | Apparatus for attaching a ceramic member to a metal structure |
| US6540162B1 (en) * | 2000-06-28 | 2003-04-01 | General Electric Company | Methods and apparatus for decreasing combustor emissions with spray bar assembly |
| EP1828683A1 (en) * | 2004-12-01 | 2007-09-05 | United Technologies Corporation | Combustor for turbine engine |
| CN101907304A (en) * | 2009-06-08 | 2010-12-08 | 北京航空航天大学 | Concave surface type splash plate fuel-injection atomization device |
| CN102242939A (en) * | 2011-07-29 | 2011-11-16 | 北京航空航天大学 | Prefilming three-stage pre-mixing and pre-evaporating low-pollution combustor |
| CN102889618A (en) * | 2012-09-29 | 2013-01-23 | 中国科学院工程热物理研究所 | Annular combustion chamber based on Venturi pre-mixing bispin nozzle |
| CN104019465A (en) * | 2014-05-29 | 2014-09-03 | 南京航空航天大学 | Turbine-based combined cycle engine super-combustion chamber |
| CN105823087A (en) * | 2016-03-22 | 2016-08-03 | 北京航空航天大学 | Low-pollution combustor with main combustion grade adopting effervescent atomizer |
| CN110779040A (en) * | 2019-11-06 | 2020-02-11 | 四川航天中天动力装备有限责任公司 | Oil supply device applied to afterburner of small turbojet engine |
-
2021
- 2021-03-26 CN CN202110332566.4A patent/CN115127126A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4438626A (en) * | 1981-09-11 | 1984-03-27 | General Electric Company | Apparatus for attaching a ceramic member to a metal structure |
| US6540162B1 (en) * | 2000-06-28 | 2003-04-01 | General Electric Company | Methods and apparatus for decreasing combustor emissions with spray bar assembly |
| EP1828683A1 (en) * | 2004-12-01 | 2007-09-05 | United Technologies Corporation | Combustor for turbine engine |
| CN101907304A (en) * | 2009-06-08 | 2010-12-08 | 北京航空航天大学 | Concave surface type splash plate fuel-injection atomization device |
| CN102242939A (en) * | 2011-07-29 | 2011-11-16 | 北京航空航天大学 | Prefilming three-stage pre-mixing and pre-evaporating low-pollution combustor |
| CN102889618A (en) * | 2012-09-29 | 2013-01-23 | 中国科学院工程热物理研究所 | Annular combustion chamber based on Venturi pre-mixing bispin nozzle |
| CN104019465A (en) * | 2014-05-29 | 2014-09-03 | 南京航空航天大学 | Turbine-based combined cycle engine super-combustion chamber |
| CN105823087A (en) * | 2016-03-22 | 2016-08-03 | 北京航空航天大学 | Low-pollution combustor with main combustion grade adopting effervescent atomizer |
| CN110779040A (en) * | 2019-11-06 | 2020-02-11 | 四川航天中天动力装备有限责任公司 | Oil supply device applied to afterburner of small turbojet engine |
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