CN115127122A - Nozzle with premixing cavity and application thereof - Google Patents
Nozzle with premixing cavity and application thereof Download PDFInfo
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- CN115127122A CN115127122A CN202210757869.5A CN202210757869A CN115127122A CN 115127122 A CN115127122 A CN 115127122A CN 202210757869 A CN202210757869 A CN 202210757869A CN 115127122 A CN115127122 A CN 115127122A
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- nozzle
- cavity
- air inlet
- air
- oil
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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
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/38—Nozzles; Cleaning devices therefor
- F23D11/383—Nozzles; Cleaning devices therefor with swirl means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/40—Mixing tubes or chambers; Burner heads
- F23D11/402—Mixing chambers downstream of the nozzle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/48—Nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/60—Devices for simultaneous control of gas and combustion air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/62—Mixing devices; Mixing tubes
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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
- F23R3/36—Supply of different fuels
Abstract
A nozzle with a premixing cavity comprises a nozzle body, a vortex cover and a swirler, wherein the nozzle body comprises a main oil way for supplying oil in a combustion process and an auxiliary oil way for supplying oil in an ignition process, the vortex cover is assembled outside a nozzle end of the nozzle body and forms a cavity structure with the nozzle body, the swirler is assembled in an inner cavity of a nozzle component of the nozzle body, an air inlet mechanism and a premixing cavity for premixing fuel and air are respectively arranged in the nozzle body, the input end of the air inlet mechanism is communicated to high-pressure air, the output end of the air inlet mechanism is communicated to the input end of the premixing cavity, the output end of the premixing cavity is communicated with the nozzle component of the nozzle body, and the input end of the premixing cavity is also communicated with the auxiliary oil way; the invention also discloses the application of the nozzle with the premixing cavity. The invention can greatly improve the fuel atomization performance of low oil pressure, meet the requirement of reliable starting, greatly improve the ignition performance and reduce the pollutant emission.
Description
Technical Field
The invention relates to the technical field of low-emission and energy-saving combustion, in particular to a nozzle with a premixing cavity. The invention further relates to a use comprising a nozzle with a premix chamber as described above.
Background
The fuel nozzle is one of important parts on an aircraft engine, and is related to reliable ignition and stable combustion of a combustion chamber, and directly influences performance parameters such as combustion efficiency, outlet temperature distribution and flameout boundary of the combustion chamber.
The fuel nozzle commonly used for the aircraft engine mainly comprises a pressure atomizing nozzle (also called a centrifugal nozzle), a pneumatic atomizing nozzle, an evaporating pipe, an oil thrower and the like. The type of fuel nozzle adopted by an aircraft engine to supply fuel to a combustion chamber is uncertain, has no difference between the quality and the quality, and is mainly related to factors such as the design tradition of an engine design company, the application of the engine, the type of the combustion chamber and the like. Particularly on small aircraft engines, the types of fuel nozzles are more diverse, for example, one of the classic successes in the engine seriation, the PT6 series of engines from P & WC company, which use pressure atomizing nozzles; the T700 series engine of GE company of America adopts the pneumatic atomizing nozzle in order to meet the design requirements of high temperature rise and high heat capacity intensity; RTM322 engine developed by cooperation of Rolls-Royce and French TM in England uses evaporator tube; the Arriel series of the french TM company uses a fuel nozzle of a slinger to accommodate the structural requirements of a baffled combustion chamber.
In view of the fuel nozzles adopted by most of the current aircraft engines, the pressure atomizing nozzle is still the mainstream of the fuel nozzle selection of the engine combustion chamber due to the mature development and has wide application. The pressure atomizing nozzle can be divided into a single-oil-way pressure atomizing nozzle and a double-oil-way pressure atomizing nozzle, the single-oil-way pressure atomizing nozzle is simple in structure and low in cost, and the defects that the oil supply range is narrow and the required oil supply pressure is high exist. Particularly, with the requirements of modern aircraft engines on wider and wider oil supply range and increasingly higher requirements on high temperature rise, high altitude ignition (high altitude performance) and the like, the single-oil-way nozzle cannot meet the oil supply requirements of the engines, so that the double-oil-way nozzle with wide oil supply range, good atomization quality and wide lean blowout limit is more and more applied.
Two oil paths (main and auxiliary oil paths) are arranged in the double-oil-path pressure atomizing nozzle, and the working principle is as follows: when the engine is in low state (ignition and slow running), only the auxiliary oil passage is used for supplying oil. Along with the increase of the power of the engine, when the oil supply pressure is increased to a certain value, the oil distribution valve in the fuel oil distributor or the nozzle is opened, and the main oil passage and the auxiliary oil passage simultaneously supply oil so as to meet the oil supply requirement of the engine in a high-power state. According to the structural form, as shown in fig. 1, the double-oil-path pressure atomizing nozzle has three types: 1) two-way single-chamber single-nozzle. The fuel oil of the main oil circuit and the auxiliary oil circuit shares one swirl chamber and is sprayed out from the same nozzle. The fuel regulation ratio can reach 1: 20-30. Its disadvantages are: the back pressure of the secondary circuit affects the primary circuit and causes an increase in the flow non-uniformity of the fuel rail when the back pressures of the individual nozzles are different. In addition, pressure loss is caused by the fact that fuel oil of the main oil path and the auxiliary oil path is mixed in the same swirl chamber, and the total fuel supply quantity is not equal to the sum of the flow quantities of the main oil path and the auxiliary oil path when the main oil path and the auxiliary oil path work independently. This type of nozzle was used primarily on early aircraft engines. 2) The double-path double-chamber single-nozzle is also called a series double-oil-way nozzle. The fuel oil in the main and auxiliary oil channels has independent swirl chambers and is sprayed out from the same nozzle. The back pressure of the auxiliary oil way of the nozzle has little influence on the main oil way, but the pressure of fuel supplied when the main oil way is just opened is very low, so that the fuel cannot be driven to rotate by the auxiliary oil way, and the atomization quality of the nozzle is inferior to that of a single-chamber single-nozzle. 3) The double-path double-chamber double-nozzle is also called a parallel double-oil-way nozzle. The main and auxiliary oil paths have independent swirl chambers and nozzles. The main and auxiliary fuel flows in the nozzle are not interfered with each other, and are respectively sprayed out from the main and auxiliary nozzles after the respective swirl chambers rotate. This type of nozzle finds mature application in contemporary aircraft engines. The core structures of the main oil circuit and the auxiliary oil circuit of the three types of double-oil circuit fuel oil nozzles are the same as that of a common single-oil circuit pressure atomizing nozzle, and the double-oil circuit double-nozzle double-oil circuit fuel oil nozzle is composed of a tangential oil inlet groove, a cyclone chamber, a nozzle and the like, and has the advantage that the main oil circuit and the auxiliary oil circuit are not interfered with each other, so that the double-oil circuit double-nozzle double-oil circuit fuel oil nozzle is widely applied.
However, the existing dual-oil-way fuel nozzle technology mainly has the following defects: 1) the atomization ability is poor at low oil pressure; 2) fuel atomization becomes worse when the fuel supply pressure is lowered under high altitude conditions, and further improvement is required.
Disclosure of Invention
The invention provides a nozzle with a premixing cavity and application thereof, and aims to solve the technical problem of poor atomization when the oil supply pressure is reduced under low oil pressure and high altitude conditions in the conventional double-oil-way nozzle.
According to an aspect of the present invention, there is provided a nozzle having a premixing chamber, comprising a nozzle body having a dual oil passage structure including a main oil passage for oil supply for a combustion process and a sub oil passage for oil supply for an ignition process, a swirl cover detachably fitted to an outside of a nozzle end of the nozzle body to form a chamber structure with the nozzle body, and a swirler fitted in an inner chamber of a spout assembly of the nozzle body,
the nozzle body is internally provided with an air inlet mechanism and a premixing cavity for premixing fuel and air, the input end of the air inlet mechanism is communicated to high-pressure air, the output end of the air inlet mechanism is communicated to the input end of the premixing cavity, the output end of the premixing cavity is communicated with a nozzle component of the nozzle body, the input end of the premixing cavity is also communicated with an auxiliary oil way, and the high-pressure air and the fuel are respectively introduced into the premixing cavity through the air inlet mechanism and the auxiliary oil way;
the air inlet mechanism is positioned in a cavity structure formed between the vortex cover and the nozzle body.
As a further improvement of the above technical solution: the fuel is one of fuel oil or fuel gas.
Further, an air stabilizing mechanism is arranged in the nozzle body and arranged between the air inlet mechanism and the premixing cavity;
the gas stabilizing mechanism comprises a gas inlet cavity; the air inlet cavity is positioned in a cavity formed by the vortex cover and the nozzle body, one end of the air inlet cavity is connected with the input end of the air inlet mechanism, and the other end of the air inlet cavity is connected with the input end of the premixing cavity.
A movable air blocking mechanism and an elastic body fixedly connected with the air blocking mechanism are arranged in the air inlet cavity,
high-pressure air is introduced through the air inlet mechanism and acts on the choke mechanism to move the choke mechanism and compress the elastic body, and the elastic body automatically rebounds to the initial position after the high-pressure air stops introducing.
Further, when the nozzle application environment is free of a high-altitude environment, the premixing cavity is provided with an air leakage hole communicated with the air inlet cavity; when the nozzle application environment has a high-altitude environment, the premixing cavity is not provided with air leakage holes or is provided with air leakage holes.
Furthermore, the elastic body is one of a spring, a rubber body with a fuel circulation hole and an elastic frame consisting of a plurality of elastic cylinders.
Furthermore, the air blocking mechanism is of a plate-shaped structure and is used for being attached to a communication position of the air inlet cavity and the air inlet mechanism when no high-pressure air acts or after the high-pressure air stops acting, so that the communication position is sealed, and air inlet of the input end of the premixing cavity is blocked.
Furthermore, the air inlet mechanism comprises a diffusion hole positioned on the nozzle body and a first air inlet hole positioned on the premixing cavity, the diffusion hole is positioned on the nozzle body at the input end of the air inlet mechanism, and the diffusion hole and the vortex cover are connected with a cavity formed by the nozzle body; the first air inlet hole is also connected with a cavity formed by the vortex cover and the nozzle body. The pressure of the inlet gas is increased after the nozzle passes through the diffusion hole, the average diameter of the premixed oil drops can be reduced due to the pressure rise, the atomization effect is enhanced, the combustion is more sufficient, and the pollutant emission is reduced; meanwhile, the gas inlet speed can be reduced, the retention time of high-pressure gas in the premixing cavity is prolonged, the premixing working time is prolonged, premixing is more sufficient, combustion is more sufficient, and pollutant emission is reduced.
Under high altitude environment, can set up the hole of losing heart, also can not set up the hole of losing heart, the principle is as follows:
when the nozzle with the premixing cavity works, oil is supplied and ignited through the auxiliary oil way, the oil supply pressure is far lower than the gas pressure of the gas inlet cavity, so that the gas acts on the gas stabilizing mechanism and the elastic body, and the gas can enter the premixing cavity to be premixed with the fuel after swirling through the gas inlet hole I (the gas inlet hole I has the swirling function);
when the air release hole is formed, after the high-pressure air is premixed with a large amount of fuel oil, the pressure of the premix is reduced, part of the fuel oil and oil-gas premix enters the air inlet cavity at the moment, the internal pressure and the external pressure of the air stabilizing mechanism are balanced after the acting force of the elastic body is added, after ignition is finished, the auxiliary oil path stops oil supply, the pressure of the air inlet cavity and the pressure of the premixing cavity are consistent with the internal pressure of the flame tube, the air stabilizing mechanism can rebound to the communication position of the air inlet cavity and the air inlet mechanism after the acting force of the elastic body is added, the communication position is sealed, and the main oil path can normally supply oil.
If the air release hole is not formed, after ignition is completed, the auxiliary oil way stops supplying oil, the main oil way normally supplies oil to work, but the air stabilizing mechanism and the elastic body cannot reset, high-pressure air still flows into the air inlet hole, the auxiliary oil way can be used as a rotational flow air way to enhance atomization after fuel oil of the main oil way is sprayed out, after the whole engine stops working, the air inlet pressure is reduced, the elastic body enables the air stabilizing mechanism to be attached to the communication position of the air inlet mechanism, then the air inlet mechanism is reset and sealed, in a high-altitude environment, atomization ignition and combustion can be realized without forming the air release hole, and the atomization function is not influenced.
In the high altitude state, the air input of the engine is reduced, the fuel oil quantity required is reduced, when the working height of the engine is very high, the difference between the required fuel oil quantity and the ground state is obvious, the fuel supply pressure is obviously reduced, at the moment, the oil pressure reduction is small, the atomization effect which can be achieved by the centrifugal atomization nozzle suitable for high oil pressure is obviously reduced, the use height of the engine is limited, but the auxiliary oil way in the embodiment is used as a rotational flow air way to strengthen the atomization of the fuel oil sprayed out from the main oil way, the problem is solved, the oil pressure span suitable for the fuel nozzle is increased, the usable height of the engine is increased, and the height range of the nozzle is favorably expanded.
Further, the spout subassembly includes main spout and vice spout, main spout is installed in vice spout, forms cavity structures between main spout and the vice spout, this cavity structures and premixing chamber intercommunication, the swirler is installed in main spout, main oil circuit and main spout intercommunication are equipped with whirl groove one and whirl hole in the cavity that forms between main spout and the vice spout, whirl hole is close to premixing chamber lays, whirl groove one keeps away from premixing chamber lays, whirl hole and whirl groove one set up respectively on main spout and/or vice spout.
Furthermore, the swirler is provided with a throttle hole and a swirl groove II, the fuel sprayed out of the main oil path is communicated with the swirl groove II through the throttle hole, and the swirl groove II is communicated with the swirl chamber of the main nozzle (namely the inner cavity of the main nozzle).
Furthermore, a heat insulation sleeve is arranged outside the nozzle body, and a second air inlet hole for introducing external high-pressure air into the air inlet mechanism is formed in the heat insulation sleeve.
According to another aspect of the invention, a combustion chamber is also provided, which comprises the nozzle, the flame tube and the combustion chamber casing, wherein the nozzle is fixed on the combustion chamber casing, and the nozzle penetrates through the wall of the flame tube and is positioned inside the flame tube.
According to another aspect of the invention, there is also provided an aircraft engine comprising a combustion chamber as described above.
According to another aspect of the invention, there is also provided a gas turbine comprising a combustor as described above.
The invention has the following beneficial effects:
1. the nozzle with the premixing cavity provided by the invention has the advantages that the fuel provided by the auxiliary oil path for ignition starting and the high-pressure air are quickly premixed in the premixing cavity and then are sprayed out through the nozzle component with the swirler, oil mist formed by swirling after oil gas is fully premixed can be fully combusted, the ignition performance can be greatly improved, the pollutant emission can be reduced, the low-pollution emission requirement can be met, the fuel can be fuel oil or fuel gas, and the application range is wider;
2. the nozzle with the premixing cavity adopts the auxiliary oil way to provide fuel for ignition starting and high-pressure air to be quickly premixed in the premixing cavity, and the air stabilizing mechanism is arranged to be used with the premixing cavity, so that the fluctuation problem during ignition starting in a low oil pressure state can be effectively relieved, and the reliable starting process is ensured;
3. when the low-oil-pressure premixing nozzle is started, because the oil pressure is too small, the atomization effect which can be achieved by using centrifugal atomization alone is poor, the diameter requirement precision of a nozzle assembly of the nozzle is high, the smaller the oil pressure is, the smaller the diameter of the nozzle assembly of the nozzle is required to be, the processing error and the slight fluctuation of oil pressure of oil supply can cause obvious influence on the atomization effect, and the requirements on the processing precision and the stability of the oil pressure of the oil supply are reduced, the process difficulty is reduced, and the production economy is improved;
4. the nozzle with the premixing cavity can fully ensure the fuel oil atomization performance of low oil pressure, meets the requirement of reliable ignition starting, is friendly to small and medium-sized aircraft engines with very low fuel oil pressure during ignition starting, and is particularly superior to other double-oil-way nozzles in the types with too low oil pressure and too high working oil pressure during ignition starting;
5. according to the invention, high-pressure air enters the flame tube after being swirled through the swirl cover blades and the flow channel with the performance of the heat insulation sleeve, so that the combustion efficiency can be improved, and the pollutant emission can be reduced; and the vortex cover is directly detachably arranged outside the nozzle body, so that the functions of dismounting, maintaining, replacing and the like of the nozzle body are facilitated, the volume of the whole fuel nozzle can be reduced, and the fuel nozzle is more suitable for the characteristics of simple structure and small volume of a small and medium-sized aero-engine.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic view of a nozzle with a premix chamber according to a preferred embodiment of the present invention;
FIG. 2 is a schematic representation of the operation of a preferred embodiment of the nozzle of the present invention with a premix chamber;
FIG. 3 is a schematic view of the construction of a nozzle body according to a preferred embodiment of the present invention;
FIG. 4 is a top view of FIG. 3;
FIG. 5 is a sectional view A-A of FIG. 3;
FIG. 6 is a schematic view of the structure of the vortex cover of the preferred embodiment of the present invention.
Illustration of the drawings:
1. a nozzle body; 11. a main oil path; 12. an auxiliary oil path; 13. a main nozzle; 14. a secondary spout; 15. a first swirling groove; 16. a swirl hole; 17. a diffusion hole; 2. a vortex cover; 21. a vortex sheet; 3. a swirler; 31. an orifice; 32. a second rotary chute; 4. an air intake mechanism; 5. a premix chamber; 51. an air release hole; 52. a first air inlet; 6. a gas stabilizing mechanism; 61. an air inlet cavity; 62. a choke mechanism; 63. an elastomer; 7. a heat insulating sleeve; 71. a second air inlet; 8. a flame tube; 9. a combustor casing.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
As shown in fig. 1 to 6, a nozzle with a premixing chamber includes a nozzle body 1, a swirl cover 2 and a swirler 3, the nozzle body 1 has a double oil path structure including a main oil path 11 for supplying oil for a combustion process and a sub oil path 12 for supplying oil for an ignition process, the swirl cover 2 is detachably mounted to the outside of a nozzle end of the nozzle body 1 and forms a cavity structure with the nozzle body 1, the swirler 3 is mounted in an inner cavity of a nozzle assembly of the nozzle body 1, the nozzle body 1 is internally provided with an air inlet mechanism 4 and a premixing cavity 5 for premixing fuel and air, the input end of the air inlet mechanism 4 is communicated with high-pressure air, the output end of the air inlet mechanism 4 is communicated with the input end of the premixing cavity 5, the output end of the premixing cavity 5 is communicated with the nozzle component of the nozzle body 1, the input end of the premixing cavity 5 is also communicated with the auxiliary oil way 12, and high-pressure air and fuel are respectively introduced into the premixing cavity 5 through the air inlet mechanism 4 and the auxiliary oil way 12; the air inlet mechanism 4 is positioned in a cavity structure formed between the vortex cover 2 and the nozzle body 1.
The nozzle with the premixing cavity mainly solves the problem of how to improve the ignition performance in a low oil pressure state, fuel and high-pressure air provided by an auxiliary oil way are firstly quickly premixed in the premixing cavity 5 and then are sprayed out in a swirling flow mode through the swirling flow chamber of the swirler 3, oil mist formed by swirling flow after oil and gas are fully premixed can be fully combusted, the ignition performance can be greatly improved, pollutant emission can be reduced, and the low-pollution emission requirement can be met; in addition, the nozzle with the premixing cavity can fully ensure the fuel atomization performance in a low oil pressure state, meets the requirement of reliable starting, is friendly to small and medium-sized aircraft engines with low fuel oil pressure in ignition starting, and is particularly suitable for models with low oil pressure and high working oil pressure in ignition starting.
When the nozzle is started at low oil pressure, the oil pressure is too small, the atomization effect which can be achieved by using centrifugal atomization alone is poor, the diameter requirement precision of the nozzle assembly of the nozzle is high, the smaller the oil pressure is, the smaller the diameter of the nozzle assembly is required to be, the machining error and the slight fluctuation of oil supply pressure can cause obvious influence on the atomization effect, the requirements on the machining precision and the stability of the oil supply pressure are reduced through the nozzle with the premixing cavity, the process difficulty is reduced, and the production economy is improved.
In this embodiment, the fuel is fuel oil, and in other embodiments, the fuel may be gas.
In the embodiment, an air stabilizing mechanism 6 is further arranged in the nozzle body 1, and the air stabilizing mechanism 6 is arranged between the air inlet mechanism 4 and the premixing cavity 5; the gas stabilizing mechanism 6 comprises a gas inlet cavity 61; the air inlet cavity 61 is positioned in a cavity formed by the vortex cover 2 and the nozzle body 1, one end of the air inlet cavity 61 is connected with the input end of the air inlet mechanism 4, and the other end of the air inlet cavity is connected with the input end of the premixing cavity.
In this embodiment, a movable choke mechanism 62 and an elastic body 63 fixedly connected with the choke mechanism 62 are arranged in the air inlet cavity 61, high-pressure air is introduced through the air inlet mechanism 4 and acts on the choke mechanism 62 to move the choke mechanism 62 and compress the elastic body 63, and the elastic body 63 automatically rebounds to the initial position after the high-pressure air stops introducing.
In this embodiment, when the nozzle application environment has no high-altitude environment, the premixing cavity 5 is provided with an air release hole 51 communicated with the air inlet cavity 61; when the nozzle application environment has a high altitude environment, the pre-mixing chamber 5 is not provided with the air release hole 51.
In this embodiment, the air blocking mechanism 62 and the elastic body 63 must be added when the air release hole 51 is opened, otherwise the premix in the premix chamber 5 will be ejected from the air release hole 51, and the nozzle will not work normally. When the air release hole 51 is not formed, the air blocking mechanism 62 and the elastic body 63 are additionally arranged, so that the condition that foreign matters in air enter the nozzle premixing cavity 5, the main oil way 11 and the auxiliary oil way 12 in a non-working state is mainly avoided, the internal blockage of the nozzle caused by non-working requirements is avoided, and the working safety coefficient of the nozzle is improved.
In this embodiment, the elastic body 63 is one of a spring, a rubber body with a fuel circulation hole, and an elastic frame composed of a plurality of elastic cylinders, and in any structure, the elastic body can be compressed under the action of gas and can automatically return when the gas is lost.
In this embodiment, the choke mechanism 62 is a plate-shaped structure, and the choke mechanism 62 is used to attach to the communication between the air intake chamber 61 and the air intake mechanism 4 when no high-pressure air acts or after the high-pressure air stops acting, so as to seal the communication and block the air intake at the input end of the premixing chamber 5.
In this embodiment, the air inlet mechanism 4 includes a diffusion hole 17 located on the nozzle body 1 and an air inlet hole 52 located on the premixing chamber 5, the diffusion hole 17 is located on the nozzle body 1 at the input end of the air inlet mechanism 4, the diffusion hole 17 and the vortex cover 2 are connected with the cavity formed by the nozzle body 1, the air inlet hole 52 is also connected with the cavity formed by the vortex cover 2 and the nozzle body 1, the high-pressure air flow rate at the air input end of the diffusion hole 17 is relatively high, after the air flow passes through the diffusion hole 17, the pressure rises, the speed is reduced, the average diameter of premixed oil drops can be reduced due to the rise of the pressure, the combustion is more sufficient, the pollutant emission is reduced, and meanwhile, the air inlet speed can be reduced, the residence time of the high-pressure air in the premixing chamber is prolonged, the premixing operation time period is prolonged, the premixing is more sufficient, the combustion is more sufficient, and the pollutant emission is reduced.
In this embodiment, the intake chamber 61 functions to: high-pressure air enters the premixing cavity 5 from the cavity formed by the vortex cover 2 and the nozzle body 1 after being diffused through the diffusion hole 17.
The basic working principle of the two cases of arranging the air release holes 51 and not arranging the air release holes 51 is as follows:
under the condition that the air release hole is not formed, after ignition is finished, the auxiliary oil way stops supplying oil, the main oil way normally supplies oil to work, but the air stabilizing mechanism and the elastic body cannot reset, high-pressure air still flows into the premixing cavity (in the air inlet hole I52) from the air inlet mechanism, and at the moment, the auxiliary oil way can be used as a rotational flow air way to enhance atomization of fuel oil sprayed out of the main oil way.
The air intake amount of the engine is reduced in a high altitude state, the required fuel oil amount is reduced, when the working height of the engine is very high, the difference between the required fuel oil amount and the ground state is obvious, the fuel supply pressure is obviously reduced, at the moment, the oil pressure reduction is small, the available atomization effect of a centrifugal atomization nozzle suitable for high oil pressure is obviously reduced, the use height of the engine is limited, but the auxiliary oil path in the embodiment is used as a rotational flow air path to strengthen the atomization of fuel oil sprayed out of a main oil path, the problem is solved, the oil pressure span suitable for a fuel oil nozzle is increased, the usable height of the engine is increased, and the height range of the fuel oil nozzle is favorably expanded.
In this embodiment, the nozzle body component includes main nozzle 13 and auxiliary nozzle 14, main nozzle 13 is installed in auxiliary nozzle 14, form cavity structure between main nozzle 13 and the auxiliary nozzle 14, this cavity structure and premix chamber 5 intercommunication, swirler 3 is installed in main nozzle 13, main oil circuit 11 and main nozzle 13 intercommunication, be equipped with whirl groove one 15 and whirl hole 16 in the cavity that forms between main nozzle 13 and the auxiliary nozzle 14, whirl hole 16 is close to premix chamber 5 and lays, whirl groove one 15 is far away from premix chamber 5 and lays, whirl hole 16 and whirl groove one 15 set up respectively on main nozzle 13 and/or auxiliary nozzle 14.
In this embodiment, the swirler 3 is provided with the orifice 31 and the swirl groove two 32, the fuel ejected from the main oil path 11 is communicated with the swirl groove two 32 through the orifice 31, and the swirl groove two 32 is communicated with the swirl chamber of the main nozzle 13.
In this embodiment, a heat insulating sleeve 7 is provided outside the nozzle body 1, and a second air intake hole 71 for introducing high-pressure outside air into the air intake mechanism 4 is provided in the heat insulating sleeve 7.
The embodiment also provides a combustion chamber, which comprises the nozzle, the flame tube 8 and the combustion chamber casing 9, wherein the nozzle is fixed on the combustion chamber casing 9, the nozzle assembly of the nozzle penetrates through the wall of the flame tube 8 and is positioned inside the flame tube 8, and the combustion chamber is mainly applied to low-emission energy-saving combustion machines in which fuel oil or fuel gas and air are premixed in advance.
The embodiment also provides an aircraft engine comprising the combustion chamber.
The embodiment also provides a gas turbine which comprises the combustion chamber.
The working principle of the nozzle with the premixing cavity of the embodiment is as follows:
when the nozzle with the premix chamber of the present embodiment is not in operation, as in the case of the fuel nozzle shown in fig. 2, the elastic body 63 attaches the choke mechanism 62 to the diffuser hole 17 of the nozzle body 1.
When high-pressure air enters two channels between the wall of a combustion chamber casing and the wall of a flame tube of a combustion chamber, the auxiliary oil way 12 on the nozzle body 1 starts to supply low-pressure oil, the high-pressure air enters the inner cavity of the heat insulating sleeve 7 through the second air inlet hole 71 on the heat insulating sleeve 7, and a part of the high-pressure air enters the flame tube 8 from the output port between the heat insulating sleeve 7 and the vortex cover 2 after being swirled by the vortex sheet 21 on the outer surface of the vortex cover 2; because the pressure of the fuel in the auxiliary oil path 12 is less than the pressure of the high-pressure air, the other part of the high-pressure air acts on the choke mechanism 62 through the diffusion hole 17 on the nozzle body 1 and compresses the elastic body 63, at this time, the residual fuel in the cavity where the elastic body 63 is located enters the fuel-air premixing cavity 5 through the air release hole 51 on the nozzle body 1, meanwhile, the high-pressure air enters the fuel-air premixing cavity 5 through the air inlet hole one 17 on the nozzle body 1, the fuel enters the fuel-air premixing cavity 5 through the auxiliary oil path 12 on the nozzle body 1, and the high-pressure air and the fuel perform primary rotational flow premixing in the fuel-air premixing cavity 5; after that, the oil-gas mixture enters the cavity formed by the main nozzle 13 and the auxiliary nozzle 14 through the swirl hole 16 on the main nozzle 13, and then enters the swirl chamber of the auxiliary nozzle 14 through the swirl groove 15 on the main nozzle 13 and then is sprayed into the flame tube 8 for providing fuel for ignition.
After the ignition and the low-oil-pressure working state are finished, the oil pressure of the auxiliary oil path 12 on the nozzle body 1 is kept unchanged, and when the high-oil-pressure working state (at the moment, a combustion process needs to be carried out in the flame tube 8) needs to be entered, a main oil path 11 on the nozzle body 1 is opened for supplying oil, the fuel oil enters a main nozzle 13 cavity through a throttling hole 31 on the swirler 3, enters a main nozzle 13 swirl chamber through a swirl groove II 32 on the swirler 3 and is then injected into the flame tube 8; after the work is finished, the main oil path 11 on the nozzle body 1 and the auxiliary oil path 12 on the nozzle body 1 stop supplying oil, the gas pressure in the flame tube 8 is always less than or equal to the air pressure of the two-channel hole, along with the end of the work, the air pressure in the two-channel hole is reduced, the elastic body 63 rebounds, the air blocking mechanism 62 is attached to the diffusion hole 17 on the nozzle body 1 again, and part of the oil-gas mixture enters the cavity of the elastic body 63 through the air release hole 51 on the nozzle body 1.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (14)
1. A nozzle with a premixing cavity, comprising a nozzle body (1), a vortex cover (2) and a swirler (3), wherein the nozzle body (1) is of a double-oil-way structure and comprises a main oil way (11) for supplying oil in a combustion process and an auxiliary oil way (12) for supplying oil in an ignition process, the vortex cover (2) is detachably assembled outside a nozzle end of the nozzle body (1) and forms a cavity structure with the nozzle body (1), and the swirler (3) is assembled in an inner cavity of a nozzle assembly of the nozzle body (1),
an air inlet mechanism (4) and a premixing cavity (5) for premixing fuel and air are respectively arranged in the nozzle body (1), the input end of the air inlet mechanism (4) is communicated to high-pressure air, the output end of the air inlet mechanism (4) is communicated to the input end of the premixing cavity (5), the output end of the premixing cavity (5) is communicated with a nozzle component of the nozzle body (1), the input end of the premixing cavity (5) is also communicated with an auxiliary oil way (12), and the high-pressure air and the fuel are respectively introduced into the premixing cavity (5) through the air inlet mechanism (4) and the auxiliary oil way (12);
the air inlet mechanism (4) is positioned in a cavity structure formed between the vortex cover (2) and the nozzle body (1).
2. The nozzle with premix chamber of claim 1,
the fuel is one of fuel oil or fuel gas.
3. The nozzle with premix chamber of claim 1,
the nozzle body (1) is also internally provided with an air stabilizing mechanism (6), and the air stabilizing mechanism (6) is arranged between the air inlet mechanism (4) and the premixing cavity (5);
the air stabilizing mechanism (6) comprises an air inlet cavity (61); the air inlet cavity (61) is located in a cavity formed by the vortex cover (2) and the nozzle body (1), one end of the air inlet cavity (61) is connected with the input end of the air inlet mechanism (4), and the other end of the air inlet cavity is connected with the input end of the premixing cavity.
4. The nozzle with premix chamber of claim 3,
a movable air blocking mechanism (62) and an elastic body (63) fixedly connected with the air blocking mechanism (62) are arranged in the air inlet cavity (61),
high-pressure air is introduced through the air inlet mechanism (4) and acts on the choke mechanism (62) to move the choke mechanism (62) and compress the elastic body (63), and the elastic body (63) automatically rebounds to the initial position after the high-pressure air stops introducing.
5. The nozzle with the premixing chamber as claimed in claim 3 or 4, wherein when the nozzle is used in an environment without high altitude, the premixing chamber (5) is provided with a gas discharge hole (51) communicated with the gas inlet chamber (61); when the nozzle application environment has a high-altitude environment, the premixing cavity (5) is not provided with the air leakage hole (51) or is provided with the air leakage hole (51).
6. The nozzle with premix chamber of claim 4,
the elastic body (63) is one of an elastic frame consisting of a spring, a rubber body with a fuel circulation hole and a plurality of elastic cylinders.
7. The nozzle with premix chamber of claim 4,
the air blocking mechanism (62) is of a plate-shaped structure, and the air blocking mechanism (62) is attached to the communication position of the air inlet cavity (61) and the air inlet mechanism (4) when no high-pressure air acts or after the high-pressure air stops acting, so that the communication position is sealed, and air inlet of the input end of the premixing cavity (5) is blocked.
8. Nozzle with premix chamber according to any of claims 1 to 4,
the air inlet mechanism (4) comprises a diffusion hole (17) positioned on the nozzle body (1) and a first air inlet (52) positioned on the premixing cavity (5), the diffusion hole (17) is positioned on the nozzle body (1) at the input end of the air inlet mechanism (4), and the diffusion hole (17) and the vortex cover (2) are connected with a cavity formed by the nozzle body (1); the first air inlet hole (52) is also connected with a cavity formed by the vortex cover (2) and the nozzle body (1).
9. Nozzle with premix chamber according to any of claims 1 to 4,
the spout subassembly includes main spout (13) and vice spout (14), main spout (13) are installed in vice spout (14), form cavity structures between main spout (13) and vice spout (14), this cavity structures and premix chamber (5) intercommunication, swirler (3) are installed in main spout (13), main oil circuit (11) and main spout (13) intercommunication, are equipped with whirl groove (15) and whirl hole (16) in the cavity that forms between main spout (13) and vice spout (14), whirl hole (16) are close to premix chamber (5) are laid, whirl groove (15) are kept away from premix chamber (5) are laid, whirl hole (16) and whirl groove (15) set up respectively on main spout (13) and/or vice spout (14).
10. The nozzle with premix chamber of claim 9,
be equipped with orifice (31) and swirl groove two (32) on swirler (3), the fuel of blowout passes through orifice (31) and communicates with swirl groove two (32) in main oil circuit (11), swirl groove two (32) communicate with the swirl chamber of main jet (13).
11. Nozzle with premix chamber according to any of claims 1 to 4,
and a heat insulation sleeve (7) is arranged outside the nozzle body (1), and a second air inlet hole (71) for introducing external high-pressure air into the air inlet mechanism (4) is formed in the heat insulation sleeve (7).
12. A combustion chamber, characterized in that it comprises a nozzle according to any one of claims 1 to 11, a flame tube (8) and a combustion chamber casing (9), said nozzle being fixed to the combustion chamber casing (9), the nozzle assembly of the nozzle passing through the wall of the flame tube (8) and being inside the flame tube (8).
13. An aircraft engine comprising the combustion chamber of claim 12.
14. A gas turbine comprising the combustor of claim 12.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210757869.5A CN115127122B (en) | 2022-06-29 | 2022-06-29 | Nozzle with premixing cavity and application thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210757869.5A CN115127122B (en) | 2022-06-29 | 2022-06-29 | Nozzle with premixing cavity and application thereof |
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| CN115127122A true CN115127122A (en) | 2022-09-30 |
| CN115127122B CN115127122B (en) | 2023-09-12 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116066270A (en) * | 2023-03-08 | 2023-05-05 | 山东赛马力发电设备有限公司 | Mixing device for combustible mixture of combustion engine |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB9814060D0 (en) * | 1997-07-09 | 1998-08-26 | Deutsch Zentr Luft & Raumfahrt | Atomiizing nozzle for atomizing fuel in burners |
| US20020125336A1 (en) * | 2001-03-07 | 2002-09-12 | Bretz David H. | Air assist fuel nozzle |
| CN101169252A (en) * | 2007-11-29 | 2008-04-30 | 北京航空航天大学 | Aerial engine lean premixed preevaporated low contamination combustion chamber |
| CN202852884U (en) * | 2012-09-03 | 2013-04-03 | 中国航空动力机械研究所 | Double-oil-line centrifugal atomization jet device |
| CN106996561A (en) * | 2017-06-05 | 2017-08-01 | 中国航发湖南动力机械研究所 | Fuel atomizer |
| CN110513679A (en) * | 2019-08-21 | 2019-11-29 | 三一汽车制造有限公司 | Spray gun, burner and control method |
| CN112797423A (en) * | 2020-12-31 | 2021-05-14 | 南京博纳能源环保科技有限公司 | Atomizing nozzle and waste liquid incineration device |
| CN113188152A (en) * | 2021-05-10 | 2021-07-30 | 中国航发湖南动力机械研究所 | Fuel nozzle with multi-stage rotational flow |
| CN114046537A (en) * | 2021-12-10 | 2022-02-15 | 浙江意动科技股份有限公司 | Combined premixing nozzle of microminiature gas turbine |
-
2022
- 2022-06-29 CN CN202210757869.5A patent/CN115127122B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB9814060D0 (en) * | 1997-07-09 | 1998-08-26 | Deutsch Zentr Luft & Raumfahrt | Atomiizing nozzle for atomizing fuel in burners |
| US20020125336A1 (en) * | 2001-03-07 | 2002-09-12 | Bretz David H. | Air assist fuel nozzle |
| CN101169252A (en) * | 2007-11-29 | 2008-04-30 | 北京航空航天大学 | Aerial engine lean premixed preevaporated low contamination combustion chamber |
| CN202852884U (en) * | 2012-09-03 | 2013-04-03 | 中国航空动力机械研究所 | Double-oil-line centrifugal atomization jet device |
| CN106996561A (en) * | 2017-06-05 | 2017-08-01 | 中国航发湖南动力机械研究所 | Fuel atomizer |
| CN110513679A (en) * | 2019-08-21 | 2019-11-29 | 三一汽车制造有限公司 | Spray gun, burner and control method |
| CN112797423A (en) * | 2020-12-31 | 2021-05-14 | 南京博纳能源环保科技有限公司 | Atomizing nozzle and waste liquid incineration device |
| CN113188152A (en) * | 2021-05-10 | 2021-07-30 | 中国航发湖南动力机械研究所 | Fuel nozzle with multi-stage rotational flow |
| CN114046537A (en) * | 2021-12-10 | 2022-02-15 | 浙江意动科技股份有限公司 | Combined premixing nozzle of microminiature gas turbine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116066270A (en) * | 2023-03-08 | 2023-05-05 | 山东赛马力发电设备有限公司 | Mixing device for combustible mixture of combustion engine |
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| CN115127122B (en) | 2023-09-12 |
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