A three-stage cyclone structure and an aeroengine

Abstract

The application provides a three-stage cyclone structure and an aero-engine, wherein a pressure atomizer (11) is arranged at the center of a first-stage cyclone (1); a Venturi tube (21) is arranged at the center of a second-stage cyclone (2), the Venturi tube (21) is sleeved on the outer ring of the pressure atomizer (11); a sleeve (31) is arranged at the center of a third-stage cyclone (3), the sleeve (31) is sleeved on the outer ring of the Venturi tube (21); a plurality of axial direct injection nozzles (32) are arranged on the third-stage cyclone (3) and surround the sleeve (31); a radial air inlet (33) is arranged on the outer ring of the third-stage cyclone (3) and is located at the outlet of the direct injection nozzle (32), so that the radial air inlet directly mixes with the axial fuel sprayed by the direct injection nozzle (32). Through the three-stage pre-combustion structure and the radial atomization technology, multi-stage atomization and cyclone can be realized, and the mixing uniformity of the fuel and the air is improved.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine combustion technology, and relates to a three-stage cyclone structure and an aero-engine. Background Technology

[0002] In the combustion process of aero-engines, fuel atomization and thorough air-fuel mixing are key factors in improving combustion efficiency and stability. Currently, in commonly used combustor structures, the swirler design primarily aims to enhance mixing by adjusting the airflow and fuel spray patterns. Traditional combustor swirler structures typically feature only single-stage or two-stage swirl, but with increasing demands for fuel injection, this structure can no longer meet the requirements for high-efficiency combustion.

[0003] Traditional cyclones have limited fuel atomization capabilities, often failing to achieve complete fuel particle atomization, leading to incomplete combustion and the generation of large amounts of unburned hydrocarbons and nitrogen oxides. This not only affects engine combustion efficiency but also increases emissions pollution. Summary of the Invention

[0004] The purpose of this invention is to provide a three-stage cyclone structure and an aero-engine for controlling and optimizing the fuel atomization effect in the combustion chamber, thereby improving combustion efficiency, reducing pollution emissions, and improving the overall performance of the combustion chamber.

[0005] The first aspect of the present invention provides a three-stage hydrocyclone structure, comprising: a first-stage hydrocyclone 1, a second-stage hydrocyclone 2, and a third-stage hydrocyclone 3; The first-stage cyclone separator 1 is equipped with a pressure atomizer 11 at its center, which is used to atomize fuel and spray it out axially. The second-stage cyclone separator 2 has a Venturi tube 21 at its center. The Venturi tube 21 is fitted around the outer ring of the pressure atomizer 11. The gas supplied by the airflow outlet of the first-stage cyclone separator 1 mixes with the fuel sprayed from the pressure atomizer 11 inside the Venturi tube 21. The third-stage cyclone separator 3 has a centrally located sleeve 31, which is fitted around the outer ring of the Venturi tube 21. The gas supplied by the airflow outlet of the second-stage cyclone separator 2 is further mixed with the oil-gas mixture inside the sleeve 31 to form a pre-combustion stage cyclone spray 35. Multiple axially directed nozzles 32 are arranged around the sleeve 31 on the third-stage cyclone separator 3. A radial air inlet 33 is arranged on the outer ring of the third-stage cyclone separator 3 and is located at the outlet of the direct-inlet nozzles 32, so that the radial air intake is directly mixed with the axial fuel sprayed by the direct-inlet nozzles 32 to form a main combustion stage cyclone spray 34.

[0006] By employing a three-stage pre-combustion structure and radial atomization technology, multi-stage atomization and swirl are achieved, improving the uniformity of fuel-air mixing, thereby enhancing combustion efficiency and stability and meeting the requirements of modern aero-engines for high efficiency and low emissions. Optionally, the end face of the oil chamber of the third-stage hydrocyclone 3 is provided with multiple through holes as direct-injection nozzles.

[0007] Optionally, the inner diameter of the through hole is no more than 3mm.

[0008] Optionally, the cross-section of the radial air inlet 33 is rectangular and inclined at a preset angle to the radial direction to provide centrifugal force for radial air intake.

[0009] Optionally, the radial air inlet 33 has an axial length of not less than 2 cm.

[0010] Optionally, the outlet end face of the pressure atomizer 11 does not exceed the outlet end face of the venturi tube 21, and the outlet end face of the venturi tube 21 does not exceed the outlet end face of the sleeve 31.

[0011] A second aspect of the present invention provides an aero-engine employing a three-stage cyclone structure as described in any one of the first aspects.

[0012] Optionally, the inner diameter of sleeve 31 can be adjusted according to the thrust of the aircraft engine.

[0013] Optionally, the greater the thrust of the aircraft engine, the larger the inner diameter of the sleeve 31.

[0014] This invention provides a three-stage swirler structure and an aero-engine. Through a three-stage pre-combustion structure and radial atomization technology, fuel is progressively atomized and uniformly mixed in different swirler stages, thereby improving combustion efficiency and stability in the combustion chamber. The swirler of this invention includes a first and second pre-combustion stage and a main combustion stage swirler. By setting up a three-stage swirler structure and radial atomization design, the fuel can be atomized and finely mixed in multiple stages, achieving effects such as fine fuel atomized particles, complete combustion, and high combustion efficiency. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. The drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 A schematic diagram of the three-stage hydrocyclone structure provided by the present invention; Explanation of reference numerals in the attached figures: 1-First stage hydrocyclone; 2-Second stage hydrocyclone; 3-Third-stage hydrocyclone; 11-Pressure atomizer; 21-Venture tube; 31-Sleeve; 32 - Direct-fire nozzle; 33 - Radial air inlet; 34 - Main combustion stage cyclone spray; 35-Pre-combustion stage cyclone spray. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0018] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0019] In the description of this invention, it should be noted that the directions or positional relationships indicated by terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of describing and simplifying the invention, and should not be construed as limiting the invention. Furthermore, the use of ordinal numbers (e.g., "first and second," etc.) is for distinguishing objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0020] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly, encompassing both direct connection and indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0021] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0022] The present invention will be further described in detail below with reference to the embodiments and accompanying drawings, but the embodiments of the present invention are not limited thereto.

[0023] like Figure 1 As shown, the present invention provides a novel three-stage hydrocyclone structure, comprising: a first-stage hydrocyclone 1, a second-stage hydrocyclone 2, and a third-stage hydrocyclone 3; The first-stage cyclone separator 1 is equipped with a pressure atomizer 11 at its center, which is used to atomize fuel and spray it out axially. The second-stage cyclone separator 2 has a Venturi tube 21 at its center. The Venturi tube 21 is fitted around the outer ring of the pressure atomizer 11. The gas supplied by the airflow outlet of the first-stage cyclone separator 1 mixes with the fuel sprayed from the pressure atomizer 11 inside the Venturi tube 21. The third-stage cyclone separator 3 has a centrally located sleeve 31, which is fitted around the outer ring of the Venturi tube 21. The gas supplied by the airflow outlet of the second-stage cyclone separator 2 is further mixed with the oil-gas mixture inside the sleeve 31 to form a pre-combustion stage cyclone spray 35. Multiple axially directed nozzles 32 are arranged around the sleeve 31 on the third-stage cyclone separator 3. A radial air inlet 33 is arranged on the outer ring of the third-stage cyclone separator 3 and is located at the outlet of the direct-inlet nozzles 32, so that the radial air intake is directly mixed with the axial fuel sprayed by the direct-inlet nozzles 32 to form a main combustion stage cyclone spray 34.

[0024] Optionally, the oil chamber of the third-stage hydrocyclone 3 has multiple through holes on its end face, serving as direct-fire nozzles. For example, the inner diameter of the through holes is no greater than 3 mm.

[0025] In one embodiment, the radial air inlet 33 has a rectangular cross-section and is inclined at a predetermined angle to the radial direction to provide centrifugal force for radial air intake. For example, the axial length of the radial air inlet 33 is not less than 2 cm.

[0026] Based on the parameters of the blade cyclone separator, the inlet parameters of the pre-combustion stage cyclone separator and the main combustion stage cyclone separator are designed. The dimensionless inlet flow rate distribution of each stage cyclone separator is set as follows: the inlet flow rate of the first stage cyclone separator is not greater than 8%, the inlet flow rate of the second stage cyclone separator is not greater than 10%, and the inlet flow rate of the third stage cyclone separator is not less than 82%.

[0027] For the operating parameters of high-thrust aero-engines, fuel needs to be supplied jointly by the main combustion stage and the pre-combustion stage swirlers during climb and takeoff. In order to reduce NOx emissions during climb and takeoff, it is also necessary to ensure a reasonable distribution of wall cooling gas and mixed gas for regulating the combustion chamber outlet temperature field. The combustion gas distribution should not be less than 70%, of which the gas distribution of the pre-combustion stage should not exceed 22% and the gas distribution of the main combustion stage should not be less than 78%.

[0028] Different thrust aero engines have different structural parameters. For low-thrust recirculating combustion chambers or low-thrust direct-flow combustion chambers, swirler structures of different specifications and sizes can be used. At the same time, the venturi tube and sleeve also have the characteristics of proportional reduction.

[0029] like Figure 1 As shown, the outlet end face of the pressure atomizer 11 does not exceed the outlet end face of the Venturi tube 21, and the outlet end face of the Venturi tube 21 does not exceed the outlet end face of the sleeve 31.

[0030] The design principle of this invention is: This invention presents a novel three-stage cyclone separator design based on multi-stage cyclone and radial atomization injection technology. Through the structure of the pre-combustion stage's first and second stages and the main combustion stage's cyclone separators, fuel can be gradually atomized at different stages, thereby achieving more complete combustion. The two-stage cyclone separators in the pre-combustion stage are used for preliminary atomization and mixing of the fuel, ensuring that the fuel has a certain degree of mixing uniformity and atomization before entering the main combustion stage. With the help of the venturi tube, the airflow forms a high-speed rotating flow structure inside the cyclone separator, making the fuel more evenly and finely distributed within the combustion zone during atomization, thus improving combustion efficiency. Furthermore, the main combustion stage cyclone separator further enhances the efficiency of atomization, resulting in finer fuel particles and more complete combustion.

[0031] The working process of this invention is as follows: Fuel enters the first and second stage cyclones of the pre-combustion stage through a pressure atomizer. At this stage, the fuel is initially atomized and mixed with air to form fine fuel particles.

[0032] The fuel particles enter the main combustion stage cyclone separator via a direct injection nozzle and venturi tube, where they are further refined and fully atomized.

[0033] With the cooperation of the sleeve and the venturi tube, the airflow velocity increases, and the fuel particles are evenly distributed in the combustion chamber under the action of the airflow.

[0034] Under the action of various swirlers and spray devices, fuel and air are fully mixed in the combustion chamber to complete the combustion process.

[0035] This invention's novel three-stage cyclone separator achieves highly efficient fuel-air mixing through three-stage atomization and cyclone design, improving combustion efficiency and stability in the combustion chamber while reducing combustion temperature and pollution emissions. Its modular structure facilitates maintenance and replacement, enhancing the equipment's adaptability and reliability. This device is not only suitable for high-temperature, high-pressure combustion environments but can also be adjusted according to different combustion conditions, exhibiting high adaptability. Furthermore, through the application of cooling channels and heat-resistant materials, the cyclone separator structure of this invention possesses superior high-temperature resistance and a long service life, demonstrating promising prospects for industrial applications and meeting the high-efficiency and environmentally friendly requirements of modern aero-engine combustion chambers.

[0036] The difference between this novel three-stage hydrocyclone and a traditional hydrocyclone: 1. Multi-stage vortex design: Traditional cyclones are mostly single-stage or two-stage cyclones, while this invention adopts a three-stage cyclone structure, which greatly enhances the mixing effect of fuel and air.

[0037] 2. Radial atomization: Traditional cyclones mainly use axial injection, which results in poor atomization. This invention improves the uniformity and efficiency of fuel atomization through radial atomization.

[0038] 3. Venturi tube auxiliary: Traditional cyclones typically do not have a venturi tube, but this invention accelerates airflow through the venturi tube, thereby improving combustion efficiency.

[0039] 4. Cooling structure: Traditional cyclones are easily damaged in high-temperature environments. However, this invention redesigns the radial air inlet 33 with a large airflow, which enables the direct-injection fuel to be fully mixed with the radial air inlet 33 of the third-stage cyclone. This reduces the temperature rise near the cooling channel, improves combustion efficiency, and enhances the high-temperature resistance and service life of the cyclone.

[0040] 5. Adjustable sleeve design: Traditional cyclone separators have a relatively fixed structure, while this invention incorporates an adjustable sleeve in the main combustion stage to adapt to different combustion conditions.

[0041] The main innovative aspects of this invention are as follows: 1. Multi-stage atomization structure of the first and second stage cyclones in the pre-combustion stage: Two swirlers, designated as the first and second stage swirlers, are installed in the pre-combustion stage to initially atomize the fuel before it enters the main combustion stage. This structure helps to further refine fuel particles and initially mix them with air, thereby improving fuel atomization quality and combustion efficiency.

[0042] 2. High-efficiency spray device for the main combustion stage cyclone: The main combustion stage cyclone separator uses a specially designed spray device that can further atomize the fuel on the basis of the pre-combustion stage atomization, making the fuel particles more evenly and finely distributed, thereby promoting the full mixing of fuel and air and improving combustion efficiency.

[0043] 3. Direct injection nozzle: The direct injection nozzle design ensures that the fuel is evenly distributed in the main combustion zone, avoiding uneven fuel distribution and local overheating caused by unreasonable nozzle design, and improving the uniformity of temperature distribution in the combustion chamber.

[0044] 4. Pressure atomizer: By incorporating a pressure atomizer into the fuel injection system, high-pressure fuel atomization technology is used to atomize the fuel during injection, further improving fuel atomization and combustion efficiency. This design effectively reduces the diameter of fuel particles, promoting complete combustion.

[0045] 5. Venturi structure: A venturi structure is designed in the airflow channel of the cyclone separator. By reducing the cross-sectional area of ​​the airflow channel, the airflow velocity is increased, and a low-pressure zone is formed in the venturi region, which helps fuel atomization and further enhances the mixing effect of air and fuel.

[0046] 6. Multi-stage adjustment function of the sleeve: The sleeve design in the hydrocyclone has a multi-stage adjustment function, which can flexibly adjust the opening of the sleeve according to different working conditions, thereby controlling the airflow distribution and fuel atomization effect, and realizing the multi-condition adaptability of the hydrocyclone.

[0047] 7. Staged combustion control: The staged design, consisting of a pre-combustion stage and a main combustion stage, achieves different levels of combustion control. The pre-combustion stage provides initial fuel atomization and mixing, while the main combustion stage is responsible for efficient combustion. This design helps to lower combustion temperatures and reduce the formation of nitrogen oxides.

[0048] 8. Improved radial swirl channel design: By optimizing the radial design of the swirl channel, a stable rotating flow of air is formed in the radial direction, which increases the contact area between fuel and air, and makes the fuel more evenly distributed in the combustion chamber, thereby improving combustion efficiency.

[0049] 9. Multi-stage spray area distribution: Multi-stage spray zones are designed based on different levels of cyclones to control the atomization distribution of fuel. Each spray zone operates independently but works in coordination to ensure uniform fuel distribution throughout the combustion chamber and reduce incomplete combustion.

[0050] 10. Modular design facilitates maintenance: The overall hydrocyclone structure adopts a modular design, allowing each stage of the hydrocyclone and spray device to be disassembled independently for easy replacement and maintenance. This design not only extends the service life of the equipment but also reduces maintenance costs and enhances its reliability.

[0051] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. A three-stage hydrocyclone structure, characterized in that, include: First-stage hydrocyclone (1), second-stage hydrocyclone (2) and third-stage hydrocyclone (3); The first-stage cyclone separator (1) has a pressure atomizer (11) at its center, which is used to atomize the fuel and spray it out axially. The second-stage cyclone separator (2) has a Venturi tube (21) at its center. The Venturi tube (21) is fitted around the outer ring of the pressure atomizer (11). The gas supplied by the airflow outlet of the first-stage cyclone separator (1) mixes with the fuel sprayed from the pressure atomizer (11) inside the Venturi tube (21). The third-stage cyclone separator (3) has a sleeve (31) at its center, which is fitted around the outer ring of the Venturi tube (21). The gas supplied by the gas outlet of the second-stage cyclone separator (2) is further mixed with the oil-gas mixture inside the sleeve (31) to form a pre-combustion stage cyclone spray (35). The third-stage cyclone separator (3) has multiple axially oriented direct-injection nozzles (32) arranged around the sleeve (31). The outer ring of the third-stage cyclone separator (3) has a radial air inlet (33) located at the outlet of the direct-injection nozzles (32), so that the radial air intake is directly mixed with the axial fuel sprayed by the direct-injection nozzles (32) to form a main combustion stage cyclone spray (34).

2. The three-stage hydrocyclone structure according to claim 1, characterized in that, The oil chamber of the third-stage hydrocyclone (3) has multiple through holes on its end face, which serve as direct-shot nozzles.

3. The three-stage hydrocyclone structure according to claim 1, characterized in that, The inner diameter of the through hole should not exceed 3mm.

4. The three-stage hydrocyclone structure according to claim 1, characterized in that, The radial air inlet (33) has a rectangular cross-section and is inclined at a preset angle to the radial direction, providing centrifugal force for radial air intake.

5. The three-stage hydrocyclone structure according to claim 1, characterized in that, The radial air inlet (33) has an axial length of not less than 2 cm.

6. The three-stage hydrocyclone structure according to claim 1, characterized in that, The outlet end face of the pressure atomizer (11) does not exceed the outlet end face of the Venturi tube (21), and the outlet end face of the Venturi tube (21) does not exceed the outlet end face of the sleeve (31).

7. An aircraft engine, characterized in that, The three-stage cyclone structure is adopted as described in any one of claims 1-6.

8. The aero-engine according to claim 7, characterized in that, The inner diameter of the sleeve (31) is adjusted according to the thrust of the aircraft engine.

9. The aero-engine according to claim 8, characterized in that, The greater the thrust of the aero engine, the larger the inner diameter of the sleeve (31).

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