CN111520757A - Direct injection type concave cavity swirl nozzle - Google Patents
Direct injection type concave cavity swirl nozzle Download PDFInfo
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- CN111520757A CN111520757A CN202010240303.6A CN202010240303A CN111520757A CN 111520757 A CN111520757 A CN 111520757A CN 202010240303 A CN202010240303 A CN 202010240303A CN 111520757 A CN111520757 A CN 111520757A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The invention provides a direct injection type concave cavity swirl nozzle, which comprises structures such as an oil inlet, an oil delivery pipe, an annular cavity, a concave cavity, an oil injection hole and the like, and has the advantages that: compare the head with conventional direct injection formula nozzle and have the cavity structure, the defeated oil pipe fuel of inside center is direct by the blowout of central nozzle opening, and the defeated oil pipe of two sides carries the fuel to get into the ring chamber, spout by four rows of crisscross nozzle openings of arranging (direct injection nozzle opening and radial nozzle opening) again, can form the weak whirl of minizone in the cavity, the fuel is broken with higher speed, shortens the fuel atomization distance, improves the fuel atomization quality, even fuel distributes also can effectual reduction pollutant and discharges.
Description
Technical Field
The invention relates to the field of aeroengine combustion chambers, in particular to a direct-injection type concave cavity swirl nozzle.
Background
With the continuous development of the aviation industry, higher requirements are put on the performances of the aero-engine, the modern aero-engine develops towards the directions of high performance, high thrust-weight ratio, low emission and economy, and in order to meet the current requirements on the engine, each link of the engine design faces huge challenges. The combustion chamber is used as a main power supply structure of an aircraft engine, and has the main functions of diffusion, speed reduction and fuel preparation, a low-speed area or a backflow area is formed to stabilize flame, and the performance of the combustion chamber directly influences various indexes such as engine thrust, emission and the like, so the design of the combustion chamber is particularly important. The modern aeroengine combustion chamber mainly adopts the principle of air splitting, and the main components of the combustion chamber structure comprise an outer casing, a diffuser, a flame tube, a fuel nozzle and a flame stabilizing device, so that the requirements of the combustion chamber on stable combustion, low pollutant emission, high durability and uniform outlet temperature distribution coefficient are met.
One of the key technologies of the combustion chamber for influencing the emission lies in the oil injection mode of the head part of the combustion chamber, the advanced fuel oil atomization mode can well meet the performance requirements of combustion stability and low emission of the combustion chamber, and the common structure of the head part of the combustion chamber adopts a combination form of a two-stage swirler, a direct injection type fuel nozzle and a venturi tube at present. Mixing high-speed airflow from the compressor with fuel oil through a swirler to provide a proper fuel-air ratio for combustion in the combustion chamber, and generating a backflow zone stable flame near the head outlet; however, the currently commonly used direct injection type fuel nozzle has a small equivalent diameter, which easily causes the problem of nozzle blockage, and causes obvious total pressure loss, and affects the stability and reliability of the engine combustion chamber, so the research on the fuel injection mode and the fuel atomization effect is always an important aspect of the head research of the combustion chamber.
Jet atomization of fuel is one of important research points of the combustion process of an aircraft engine, the atomization level and the mixing level of the fuel are closely related to the combustion performance and emission indexes of a combustion chamber, and the design of the head of the combustion chamber is particularly critical as an upstream boundary for jet crushing and atomization of the fuel, so that the flow characteristic and the atomization mode of the fuel are directly influenced. Therefore, the reasonable optimization of the nozzle which is the main part for supplying fuel to the combustion chamber is the most direct means capable of improving the fuel atomization, so that the fuel supply can be stabilized even if the combustion chamber is under different working conditions, the fuel injection distance is shortened, the fuel atomization effect is improved, and the oil-gas mixing level in the combustion chamber is improved, thereby not only having positive influence on the combustion process in the combustion chamber, but also having important influence on realizing the high-efficiency clean utilization of energy.
Disclosure of Invention
The invention aims to solve the technical problem of providing a direct-injection type concave cavity swirl nozzle, which achieves the effects of improving the fuel atomization level, stabilizing combustion and reducing pollutant emission by improving a direct-injection type nozzle at the head part of a combustion chamber.
Technical scheme
The invention aims to provide a direct-injection type concave cavity swirl nozzle which can improve the fuel atomization level, stabilize combustion and reduce pollutant discharge.
The technical scheme of the invention is as follows:
direct-injection type concave cavity swirl nozzle, its characterized in that: the direct injection type cavity swirl nozzle comprises an oil inlet hole, a side oil delivery pipe, a central oil delivery pipe, an annular cavity, a radial oil injection hole, a direct injection oil injection hole, a cavity, a first-stage radial oil injection hole, a second-stage radial oil injection hole and a central oil injection hole.
The direct injection type concave cavity swirl nozzle is characterized in that: the outer diameter of the direct-injection type concave cavity swirl nozzle is 20-25mm, the outer wall of the head part is streamline, and the outlet is 1/6 with the depth of a concave cavity structure equal to the full length; the fuel oil sprayed from the radial fuel spray holes drives the fuel oil sprayed from the direct fuel spray holes to form weak rotational flow in the concave cavity, so that the crushing and atomization of the fuel oil are accelerated, and the fuel oil spraying distance is shortened.
The direct injection type concave cavity swirl nozzle is characterized in that: the oil delivery pipe is divided into two side oil delivery pipes and a central oil delivery pipe, the side oil delivery pipes enter from the oil inlet hole, the central oil delivery pipe is divided into three parts at the full length 1/3, the diameter of the central oil delivery pipe is 2-3mm, fuel oil is directly sprayed out from the central oil injection hole, the diameter of the side oil delivery pipe is 5-7mm, and the fuel oil enters the annular cavity to provide fuel oil for the multi-stage oil injection hole at the head.
The direct injection type concave cavity swirl nozzle is characterized in that: two rows of direct injection oil injection holes with the aperture of 1-2mm are annularly arranged; the radial oil spray holes are divided into a first-stage radial oil spray hole and a second-stage radial oil spray hole, the included angle between the diameter of the first-stage radial oil spray hole and the circumferential tangent is 50-60 degrees, and the included angle between the diameter of the second-stage radial oil spray hole and the circumferential tangent is 75-90 degrees.
The direct injection type concave cavity swirl nozzle is characterized in that: enters the annular cavity at about 3/4 full length from the inlet, and the wall thickness of the annular cavity is 2-3 mm.
The invention has the following beneficial effects:
compared with the conventional direct injection type nozzle, the direct injection type concave cavity swirl nozzle has the advantages that the head concave cavity structure is adopted, the two side oil delivery pipes convey fuel oil to enter the annular cavity, and then the fuel oil is sprayed out from the four rows of staggered fuel spray holes (direct fuel spray holes and radial fuel spray holes), so that a small-range weak swirl can be formed in the concave cavity, the fuel oil crushing is accelerated, the fuel oil atomization distance is shortened, the fuel oil atomization quality is improved, and the pollutant emission can be effectively reduced due to uniform fuel oil distribution.
Drawings
FIG. 1: schematic diagram of overall structure of direct-injection type concave cavity swirl nozzle
FIG. 2: axial section view of direct-injection type concave cavity swirl nozzle
FIG. 3: sectional view of radial oil spray hole at head of direct-injection type concave cavity swirl nozzle
In the figure: 1. the oil inlet, 2, defeated oil pipe of side, 3, central defeated oil pipe, 4, ring chamber, 5, radial nozzle, 6, direct nozzle, 7, cavity, 8, the radial nozzle of one-level, 9, the radial nozzle of second grade, 10, central nozzle.
Detailed Description
The invention will now be further described with reference to the accompanying drawings in which:
with reference to fig. 1, 2, and 3, the present invention provides a solution for a direct-injection, re-entrant swozzle. Fig. 1 is a schematic view of the overall structure of a direct-injection type concave cavity swirl nozzle, fig. 2 is a sectional view of a center axis of the direct-injection type concave cavity swirl nozzle, and fig. 3 is a sectional view of a radial oil spray hole at the head of the direct-injection type concave cavity swirl nozzle.
The specific process comprises the following steps: the fuel enters the nozzle through the fuel inlet (1), the fuel is divided into a side fuel delivery pipe (2) and a central fuel delivery pipe (3) at the full length of 1/3, the fuel of the central fuel delivery pipe (3) is directly sprayed out through the central fuel spray hole (10), the side fuel delivery pipe (2) delivers the fuel into the annular cavity (4) to supply fuel for the multi-stage fuel spray hole, the fuel sprayed out from the radial fuel spray hole (5) can form a rotational flow structure in the cavity (7), and the rotational flow structure and the direct fuel spray hole (6) are distributed in a staggered manner to drive the direct fuel spray to form rotational flow together, and the rotational flow effect is weakened, so that the fuel can be sprayed out through a more concentrated spray cone angle when being sprayed out of the nozzle, and meanwhile, the fuel can be; the fuel sprayed from the radial fuel spray holes (5) and the direct fuel spray holes (6) in the concave cavity (7) collides to break the fuel in a large area, and meanwhile, the weak rotational flow generated in the concave cavity (7) further breaks and atomizes the fuel by the shearing action of the airflow. The fuel then enters the combustion chamber through the head outlet and mixes with the high velocity swirling air flow from the swirler and enters the combustion chamber for combustion.
Claims (5)
1. Direct-injection type concave cavity swirl nozzle, its characterized in that: the direct injection type cavity swirl nozzle comprises an oil inlet hole, a side oil delivery pipe, a central oil delivery pipe, an annular cavity, a radial oil injection hole, a direct injection oil injection hole, a cavity and a central oil injection hole; the fuel is sprayed out through a plurality of oil spray holes to form a weak rotational flow structure in the cavity structure, so that the fuel atomization level is improved, the combustion is stable, and the pollutant emission is reduced.
2. The direct cavity swirl nozzle of claim 1, wherein: the outer diameter of the direct-injection type concave cavity swirl nozzle is 20-25mm, the outer wall of the head part is streamline, and the outlet is 1/6 with the depth of a concave cavity structure equal to the full length; the fuel oil sprayed from the radial fuel spray holes drives the fuel oil sprayed from the direct fuel spray holes to form weak rotational flow in the concave cavity, so that the crushing and atomization of the fuel oil are accelerated, and the fuel oil spraying distance is shortened.
3. The direct cavity swirl nozzle of claim 1, wherein: the oil delivery pipe is divided into two side oil delivery pipes and a central oil delivery pipe, the side oil delivery pipes enter from the oil inlet hole, the central oil delivery pipe is divided into three parts at the full length 1/3, the diameter of the central oil delivery pipe is 2-3mm, fuel oil is sprayed out from the central oil injection hole, the diameter of the side oil delivery pipe is 5-7mm, and the fuel oil enters the annular cavity to provide fuel oil for the multi-stage oil injection hole at the head.
4. The direct cavity swirl nozzle of claim 1, wherein: two rows of direct injection oil injection holes with the aperture of 1-2mm are annularly arranged; the radial oil spray holes are divided into a first-stage radial oil spray hole and a second-stage radial oil spray hole, the included angle between the diameter of the first-stage radial oil spray hole and the circumferential tangent is 50-60 degrees, and the included angle between the diameter of the second-stage radial oil spray hole is 3-4mm and the circumferential tangent is 75-90 degrees.
5. The direct cavity swirl nozzle of claim 1, wherein: enters the annular cavity at about 3/4 full length from the inlet, and the wall thickness of the annular cavity is 2-3 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010240303.6A CN111520757B (en) | 2020-03-31 | 2020-03-31 | Direct injection type concave cavity swirl nozzle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010240303.6A CN111520757B (en) | 2020-03-31 | 2020-03-31 | Direct injection type concave cavity swirl nozzle |
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| CN111520757A true CN111520757A (en) | 2020-08-11 |
| CN111520757B CN111520757B (en) | 2022-06-10 |
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2020
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Inventor after: Zhang Qun Inventor after: Wang Zixin Inventor after: Cao Tingting Inventor after: Hu Fan Inventor after: Li Xiaolong Inventor after: Cheng Xiangwang Inventor before: Zhang Qun Inventor before: Cao Tingting Inventor before: Hu Fan Inventor before: Li Xiaolong Inventor before: Cheng Xiangwang |
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