CN110686274A - Air atomization device for main combustion stage of layered premixed combustion chamber - Google Patents
Air atomization device for main combustion stage of layered premixed combustion chamber Download PDFInfo
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- CN110686274A CN110686274A CN201910909921.2A CN201910909921A CN110686274A CN 110686274 A CN110686274 A CN 110686274A CN 201910909921 A CN201910909921 A CN 201910909921A CN 110686274 A CN110686274 A CN 110686274A
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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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Abstract
The invention discloses a main combustion stage air atomization device of a stratified partial premix combustion chamber, which comprises a fuel oil injection system, a first-stage swirler and a second-stage swirler, wherein first-stage swirl air enters a radial air flow passage of the second-stage swirler through the first-stage swirler, fuel oil sprayed out of a fuel oil injection short pipe is subjected to primary air atomization under the action of the first-stage swirl air to form an initial air atomization fog cone, second-stage swirl air enters a radial air flow passage of the second-stage swirler through blades of the second-stage swirler to perform transverse jet air atomization on the initial atomization fog cone to form fog drops with small and uniform droplet sizes, the fog drops are uniformly and rapidly mixed with air in high-speed and strong swirl air, and a uniform oil-gas mixture is formed at an axial outlet of the second-stage swirler to enter a downstream combustion chamber, the invention enhances the oil-gas mixing quality through step-by step-, can be used as a main combustion stage of staged combustion for low-emission combustion chambers of ground industrial gas turbines and aeroengines.
Description
Technical Field
The invention relates to the field of gas turbines, in particular to a main combustion stage air atomization device of a premixed combustion chamber, and particularly relates to a main combustion stage air atomization device of a layered partial premixed combustion chamber, which utilizes two-stage rotational flow to carry out step-by-step air atomization and strengthen oil-gas mixing.
Background
For gas turbine engines using liquid fuels, fuel atomization and mixing have a decisive influence on engine combustion performance, combustion efficiency and pollutant emissions, and therefore fuel atomization research has been focused on, which has also prompted the development of fuel atomization nozzles.
The international civil aviation organization has stricter and stricter pollutant emission standards for the aviation gas turbine, particularly the requirement on NOx pollutant emission, and low-pollution combustion becomes the development trend of the modern aeroengine combustion chamber. The requirements of the currently implemented CAEP6 standard are already very stringent, especially the NOx polluting emission requirements. The control of pollutant emissions is an important issue for research by all major airlines and research institutes, and low-pollution combustion technologies proposed so far include rich burn-quench-lean burn (RQL), lean premixed combustion (LPP), and lean direct injection combustion (LDI).
The international major airline companies GE, PW, R-R, Snecma have begun to study low pollution combustion technology. Recently, GE corporation developed a taps (twin Premixing combustor) low pollution combustor for the new generation of commercial aviation turbofan engine gen based on lean premixed combustion (LPP) technology, with 50% lower NOx emissions than the CAEP2(Committee on aviation Environmental Protection) emissions standard. In order to achieve good premixing of air and fuel prior to the combustion chamber, GE designs and develops various pre-swirl fuel nozzles, and various U.S. patents have been applied for different designs of the fuel nozzles of the TAPS combustion chamber, wherein the main combustion stage of the patents is that fuel is injected to the rear part of a main swirler to form a premixed and pre-evaporated fuel-air mixture, and the mixing and evaporation distances required by the mixing mode are long so as to ensure that the premixed and pre-evaporated fuel-air mixture is uniformly mixed, thereby increasing the length and weight of the combustion chamber. R-R company develops various fuel nozzles for staged combustion for an Engine3E core Engine based on an LDI combustion concept, an air atomizing nozzle or a centrifugal atomizing nozzle is adopted in a duty stage, a pre-film type air atomizing nozzle is adopted in a main combustion stage, and the NOx emission on an Engine full-ring test piece is reduced by 70% compared with the CAEP2 standard. The PW company developed TALON X combustors using RQL technology and was applied to PW1000G engine, and predicted NOx emissions to be 40% lower than CAEP 6. The low-pollution combustion chamber which is developed at present and adopts the lean premixed combustion technology effectively controls the flame temperature in the combustion chamber by controlling the equivalence ratio of a main combustion zone within the range of 0.5-0.7, so that the generation of thermal pollutants NOx is reduced. The key of the lean premixed combustion low-emission combustion chamber for reducing pollutant emission is effective and rapid mixing of the main combustion grade fuel oil, so that a local high-temperature area in the combustion chamber is avoided.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: in order to overcome the defects and shortcomings of the prior art, the invention provides the main combustion stage air atomization device of the layered premixed combustion chamber, which adopts a two-stage rotational flow step-by-step air atomization mode to enhance the rapid and uniform mixing of oil and gas, realizes the lean premixed combustion in the combustion chamber, avoids a local high-temperature region, improves the temperature distribution quality of the outlet of the combustion chamber and reduces the pollutant emission index.
The invention adopts the technical scheme for solving the technical problems that:
a main combustion stage air atomization device of a layered premixed combustion chamber comprises a fuel injection system, a primary swirler and a secondary swirler, and is characterized in that,
the secondary cyclone is integrally an annular cylindrical component and comprises a secondary cyclone outer ring, a secondary cyclone inner ring and secondary cyclone blades arranged between the secondary cyclone outer ring and the secondary cyclone inner ring, the secondary cyclone outer ring and the secondary cyclone inner ring both comprise a radial section and an axial section, the radial sections of the secondary cyclone outer ring and the secondary cyclone inner ring are mutually parallel to form a radial runner of the secondary cyclone, the axial sections of the secondary cyclone outer ring and the secondary cyclone inner ring are mutually parallel to form an axial runner of the secondary cyclone, the secondary cyclone blades are circumferentially arranged at the inlet of the radial runner of the secondary cyclone, a plurality of oil-gas mixture injection holes are circumferentially and uniformly distributed on the radial section of the secondary cyclone inner ring, and the radial positions of the oil-gas mixture injection holes are positioned at the downstream of the secondary cyclone blades,
the fuel injection system comprises an overall annular fuel main pipe, the fuel main pipe comprises an outer side wall and an inner side wall, a plurality of fuel injection short pipes are uniformly distributed on the inner side wall along the circumferential direction, the pipe diameters of the fuel injection short pipes are smaller than the aperture of the oil-gas mixture injection hole, each fuel injection short pipe correspondingly extends into each oil-gas mixture injection hole,
a plurality of primary cyclones which are uniformly arranged in the circumferential direction are arranged in a space between the inner side wall of the fuel oil main pipe and the radial section of the inner ring of the secondary cyclone, and each primary cyclone is arranged around the periphery of each fuel oil injection short pipe in a one-to-one correspondence mode.
In the main combustion stage air atomization device of the layered partially premixed combustion chamber, each fuel oil injection short pipe and each primary swirler are mutually matched to form a primary air atomization nozzle, the primary air atomization nozzle adopts a multipoint centrifugal nozzle or a direct injection nozzle to be combined with the primary swirler to carry out air atomization, high-pressure fuel oil in a fuel oil main pipe is sprayed out through the fuel oil injection short pipe, primary swirl air enters a radial flow channel of the secondary swirler through the primary swirler, the fuel oil sprayed out from the fuel oil injection short pipes is subjected to initial air atomization under the action of the primary swirl air to form an initial air atomization fog cone, and the primary swirler is used for improving the initial atomization quality. The high-speed whirl air of second grade and the initial atomizing fog awl of primary air atomizing nozzle formation mutually support and form into second grade air atomizing nozzle, second grade air atomizing nozzle adopts the high-speed whirl air of second grade and the initial atomizing fog awl of primary air atomizing nozzle formation to carry out fuel secondary atomization and mixing, and second grade whirl air carries out the secondary air atomizing through the radial runner of second grade swirler blade entering second grade swirler to with initial air atomizing fog awl effect, form the little and even fog droplet of liquid droplet size, the fog droplet is even in the air of high-speed and strong whirl, the quick mixing carries out with the air, forms even oil gas mixture at second grade swirler's axial outlet and gets into the combustion chamber in low reaches.
Preferably, the central line of each fuel injection short pipe coincides with the central line of the corresponding primary swirler, the central line of each fuel injection short pipe coincides with the central line of the corresponding oil-gas mixture injection hole, and the axial central line of the secondary swirler coincides with the axial central line of the fuel main pipe.
Preferably, in the axial position, the primary swirler is located between the fuel main pipe and the secondary swirler, the primary swirler concentric with each fuel injection short pipe is arranged by using an air flow passage formed by the fuel main pipe and the secondary swirler, primary swirling air around the fuel injection short pipes is formed by the air through the primary swirler, and the primary swirling air is atomized and mixed with the fuel at the outlets of the fuel injection short pipes to form an initial air atomization fog cone for primary air atomization.
Preferably, the primary air atomization fog cone enters a radial air flow channel of the secondary cyclone, and secondary air atomization and oil-gas mixing are carried out under the action of secondary high-speed cyclone air.
Preferably, the fuel injection short pipes are centrifugal nozzles or direct injection nozzles, and the number of the fuel injection short pipes arranged along the circumferential direction is 4-12.
Preferably, the fuel injection short pipe penetrates into the oil-gas mixture injection hole, and the tail end of the fuel injection short pipe is flush with the inner wall surface of the inner ring of the secondary cyclone.
Preferably, the first-stage swirler adopts a radial swirler, the swirler air channel adopts an equal cross section or a contracted cross section, the swirler swirl strength is greater than 0.6, and the number of the first-stage swirler channels is 6-18.
Preferably, the inclination angle of the first-stage swirler vanes is 15-75 degrees.
Preferably, the secondary swirler adopts a radial swirler or an axial swirler, and the number of the secondary swirler passages is 8-32.
Preferably, the inclination angle of the secondary cyclone blades is 15-75 degrees.
The invention relates to a main combustion stage air atomization device of a layered partially premixed combustion chamber, which has the working principle that: the fuel oil atomizing device is characterized in that the fuel oil is rapidly and uniformly mixed on the basis of a step-by-step air atomization principle, the primary air atomizing nozzle is used for improving the primary atomizing quality of fuel oil by combining a small amount of swirling air with a direct injection type or centrifugal nozzle, and on the basis, the secondary air atomizing nozzle is used for carrying out secondary air atomization on a primary fog cone by swirling air with a certain angle with the jet direction of the primary fog cone, so that the fuel oil and air are uniformly mixed.
Compared with the prior art, the air atomization device for the main combustion stage of the layered partially premixed combustion chamber has the advantages that:
(1) the invention adopts the principle of step-by-step swirl air atomization to realize the rapid and uniform mixing of oil and gas.
(2) The primary air atomizing nozzle utilizes a small amount of swirling air in combination with a direct injection or centrifugal nozzle for improving the primary atomization quality of the fuel.
(3) The secondary air atomizing nozzle carries out secondary atomization and mixing to the elementary fog awl of preliminary atomizing and mixing, has effectively strengthened the quick even mixing of fuel air.
(4) The oil gas is quickly and uniformly mixed, so that the generation of a local high-temperature area of a main combustion area can be avoided, the pollutant emission is favorably reduced, and the temperature and quality of the outlet of the combustion chamber are favorably regulated and controlled.
Drawings
FIG. 1 is a sectional view of the primary stage air atomizer for a stratified partially premixed combustor in accordance with the present invention;
fig. 2 is a partially enlarged view of fig. 1.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings and examples.
As shown in figures 1 and 2, the main combustion stage air atomization device of the layered partially premixed combustion chamber for enhancing oil-gas mixing disclosed by the invention enhances the rapid and uniform mixing of oil-gas by adopting a two-stage rotational flow step-by-step air atomization mode, and comprises a fuel oil injection system, a first-stage swirler and a second-stage swirler. The secondary cyclone is an annular cylindrical component integrally, and comprises a secondary cyclone outer ring 30, a secondary cyclone inner ring 31 and secondary cyclone blades 32 arranged between the secondary cyclone outer ring 30 and the secondary cyclone inner ring 31, wherein the secondary cyclone outer ring 30 and the secondary cyclone inner ring 31 both comprise a radial section and an axial section, the radial sections of the secondary cyclone outer ring 30 and the secondary cyclone inner ring 31 are mutually parallel to form a radial runner of the secondary cyclone, the axial sections of the secondary cyclone outer ring 30 and the secondary cyclone inner ring 31 are mutually parallel to form an axial runner of the secondary cyclone, the secondary cyclone blades 32 are circumferentially arranged at an inlet of the radial runner of the secondary cyclone, a plurality of oil-gas mixture injection holes 33 are circumferentially and uniformly distributed on the radial section of the secondary cyclone inner ring 31, and each oil-gas mixture injection hole 33 is located downstream of the secondary swirler vanes 32 in the radial direction; the fuel injection system comprises an overall annular fuel main pipe, the fuel main pipe comprises an outer side wall 10 and an inner side wall 11, a plurality of fuel injection short pipes 12 are uniformly distributed on the inner side wall 11 along the circumferential direction, the pipe diameters of the fuel injection short pipes 12 are smaller than the hole diameters of the oil-gas mixture injection holes 33, and the fuel injection short pipes 12 correspondingly extend into the oil-gas mixture injection holes 33 one by one; a plurality of primary cyclones 20 which are uniformly arranged in the circumferential direction are arranged in the space between the inner side wall 11 of the fuel oil main pipe and the radial section of the inner ring 31 of the secondary cyclones, and the primary cyclones 20 are arranged around the peripheries of the fuel oil injection short pipes 12 in a one-to-one correspondence mode.
Further, the center line of each fuel injection short pipe 12 coincides with the center line of the corresponding primary swirler 20, the center line of each fuel injection short pipe 12 coincides with the center line of the corresponding oil-gas mixture injection hole 33, and the axial center line of the secondary swirler coincides with the axial center line of the fuel main pipe. In the axial position, the primary swirler is positioned between the fuel main pipe and the secondary swirler, the primary swirler concentric with each fuel injection short pipe 12 is arranged by utilizing an air flow passage formed by the fuel main pipe and the secondary swirler, primary swirl air around the fuel injection short pipe 12 is formed by the air through the primary swirler, and the primary swirl air is atomized and mixed with the fuel at the outlet of the fuel injection short pipe 12 to form an initial air atomization fog cone 22 for primary air atomization. The primary air atomization spray cone 22 enters a radial air flow channel of the secondary cyclone, and secondary air atomization and oil-gas mixing are carried out under the action of secondary high-speed cyclone air 34. The fuel injection short pipes 12 are preferably centrifugal nozzles or direct injection nozzles, and the number of the fuel injection short pipes 12 arranged along the circumferential direction is 4-12. The first-stage swirler adopts a radial swirler, and the number of the first-stage swirler passages is 6-18. The inclination angle of the blades of the primary cyclone is 15-75 degrees. The secondary swirler adopts a radial swirler or an axial swirler, and the number of passages of the secondary swirler is 8-32. The inclination angle of the secondary cyclone blade is 15-75 degrees.
In the main combustion stage air atomization device of the layered partially premixed combustion chamber, each fuel oil injection short pipe 12 and each primary swirler 20 are matched with each other to form a primary air atomization nozzle, the primary air atomization nozzle adopts a multipoint centrifugal nozzle or a direct injection nozzle to be combined with the primary swirler to carry out air atomization, high-pressure fuel oil in a fuel oil main pipe is sprayed out through the fuel oil injection short pipe 12, primary swirl air 21 enters a radial flow channel of the secondary swirler through the primary swirler 20, the fuel oil sprayed out through the fuel oil injection short pipe 12 carries out initial air atomization under the action of the primary swirl air 21 to form an initial air atomization fog cone 22, and the primary swirler is used for improving initial atomization quality. The secondary air atomizing nozzle adopts the primary atomizing spray cone 22 formed by the secondary high-speed swirling air 34 and the primary air atomizing nozzle to carry out secondary fuel oil atomization and mixing, the secondary swirling air 34 enters a radial flow channel of the secondary swirler through secondary swirler vanes 32 and carries out secondary air atomization under the action of the primary air atomizing spray cone 22 to form mist drops 35 with small and uniform droplet size, the mist drops 35 are uniformly and rapidly mixed with air in the high-speed and strong swirling air, and uniform oil-gas mixture is formed at an axial outlet of the secondary swirler and enters a downstream combustion chamber.
When the main combustion stage air atomization device of the layered partially premixed combustion chamber works, high-pressure fuel oil in a fuel oil main pipe is sprayed out through the fuel oil spraying short pipe 12, primary rotational flow air 21 enters a radial air flow channel of a secondary cyclone through primary cyclone blades 20, and the fuel oil sprayed out through the fuel oil spraying short pipe 12 is subjected to initial air atomization under the action of the primary rotational flow air to form an initial air atomization fog cone 22; the secondary cyclone air 34 enters the radial air flow channel of the secondary cyclone through the secondary cyclone blades 32 and is atomized with the primary air atomization fog cone 22 to form fog drops 35 with small and uniform droplet size, and the fog drops 35 are uniformly and rapidly mixed with the air in the high-speed and strong-cyclone air.
The present invention is not limited to the above preferred embodiments, but rather, any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (10)
1. A main combustion stage air atomization device of a layered premixed combustion chamber comprises a fuel injection system, a primary swirler and a secondary swirler, and is characterized in that,
the secondary cyclone is integrally an annular cylindrical component and comprises a secondary cyclone outer ring, a secondary cyclone inner ring and secondary cyclone blades arranged between the secondary cyclone outer ring and the secondary cyclone inner ring, the secondary cyclone outer ring and the secondary cyclone inner ring both comprise a radial section and an axial section, the radial sections of the secondary cyclone outer ring and the secondary cyclone inner ring are mutually parallel to form a radial runner of the secondary cyclone, the axial sections of the secondary cyclone outer ring and the secondary cyclone inner ring are mutually parallel to form an axial runner of the secondary cyclone, the secondary cyclone blades are circumferentially arranged at the inlet of the radial runner of the secondary cyclone, a plurality of oil-gas mixture injection holes are circumferentially and uniformly distributed on the radial section of the secondary cyclone inner ring, and the radial positions of the oil-gas mixture injection holes are positioned at the downstream of the secondary cyclone blades,
the fuel injection system comprises an overall annular fuel main pipe, the fuel main pipe comprises an outer side wall and an inner side wall, a plurality of fuel injection short pipes are uniformly distributed on the inner side wall along the circumferential direction, the pipe diameters of the fuel injection short pipes are smaller than the aperture of the oil-gas mixture injection hole, each fuel injection short pipe correspondingly extends into each oil-gas mixture injection hole,
a plurality of primary cyclones which are uniformly arranged in the circumferential direction are arranged in a space between the inner side wall of the fuel oil main pipe and the radial section of the inner ring of the secondary cyclone, and each primary cyclone is arranged around the periphery of each fuel oil injection short pipe in a one-to-one correspondence mode.
2. The layered partially premixed combustor main combustion stage air atomizing device of the above claim, wherein the centerline of each fuel injection stub pipe coincides with the centerline of the corresponding primary swirler, and the centerline of each fuel injection stub pipe coincides with the centerline of the corresponding oil-gas mixture injection hole, and the axial centerline of the secondary swirler coincides with the axial centerline of the fuel manifold.
3. The primary air atomizing device for the stratified partially premixed combustor of the present invention as claimed in the above claim, wherein the primary swirler is disposed between the fuel manifold and the secondary swirler at an axial position, the primary swirler concentric with each fuel injection nozzle stub is disposed by an air flow path formed by the fuel manifold and the secondary swirler, the air passes through the primary swirler to form primary swirling air around the fuel injection nozzle stub, and the primary swirling air is atomized and mixed with the fuel at the outlet of the fuel injection nozzle stub to form an initial air atomization spray cone for primary air atomization.
4. The primary combustion stage air atomization device of the stratified partially premixed combustor as claimed in the preceding claim, wherein the primary air atomization spray cone enters the radial air flow channel of the secondary swirler for secondary air atomization and oil-gas mixing under the action of the secondary high-speed swirling air.
5. The air atomizing device for the main combustion stage of the stratified partially premixed combustion chamber as claimed in the preceding claim, wherein the fuel injection stubs adopt centrifugal nozzles or direct injection nozzles, and the number of the fuel injection stubs arranged along the circumferential direction is 4-12.
6. The primary fuel stage air atomizing device for a stratified partially premixed combustor as claimed in the preceding claim, wherein said fuel injection stub extends into said air-fuel mixture injection hole with its tip end flush with the inner wall surface of the inner ring of said secondary swirler.
7. The primary combustion stage air atomizing device of the stratified partially premixed combustor as claimed in the above claims, wherein the primary swirler is a radial swirler, the swirler air channel is designed to have a uniform cross section or a constricted cross section, the swirler swirl strength is greater than 0.6, and the number of the primary swirler channels is 6-18.
8. The air atomizing device for the main combustion stage of the stratified partially premixed combustor as claimed in the preceding claim, wherein the angle of inclination of the primary swirler vanes is 15-75 °.
9. The primary fuel stage air atomizing device of the stratified partially premixed combustor as claimed in the preceding claim, wherein the secondary swirler employs a radial swirler or an axial swirler, and the number of passages of the secondary swirler is 8-32.
10. The primary combustion stage air atomization device of the stratified partially premixed combustor as claimed in the preceding claim, wherein the secondary swirler vanes are inclined at an angle of 15-75 °.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112815355A (en) * | 2021-01-19 | 2021-05-18 | 重庆交通大学绿色航空技术研究院 | Flame stabilizing device of small turbine engine and turbine engine |
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