CN115218222B - A rotating sliding arc plasma enhanced combustion swirl device - Google Patents

Abstract

The invention discloses a rotating sliding arc plasma enhanced combustion swirl device, which includes a fuel nozzle, an insulating sleeve and a swirler; the swirler is an integrated structure and includes a primary swirler and a secondary swirler. , the first-level cyclone includes the inner sleeve of the first-level cyclone, the first-level cyclone guide blade, the outer sleeve of the first-level cyclone and the venturi tube. One end of the first-level cyclone guide blade is connected with the first-level cyclone guide blade. The outer wall surface of the inner sleeve of the cyclone is fixedly connected, the other end of the first-level cyclone guide vane is fixedly connected to the inner wall surface of the outer sleeve of the first-level cyclone, and the nozzle at the airflow inlet end of the venturi tube is connected to the inner wall surface of the first-level cyclone outer sleeve. The nozzle at the airflow outlet end of the outer casing of the flow device is butted; wherein, the inner sleeve of the primary cyclone is sleeved on the outside of the insulating casing and is fixedly connected to the insulating casing. The invention promotes the atomization and cracking of fuel, the full mixing of active components and atomized fuel, simplifies the structure of the combustion chamber swirler based on plasma excitation, and enhances the strength of the swirler.

Description

A rotating sliding arc plasma enhanced combustion swirl device

Technical field

The invention belongs to the technical field of gas turbine engines, and specifically relates to a rotating sliding arc plasma enhanced combustion swirl device.

Background technique

Currently, aeroengine combustion chambers have major practical problems such as poor fuel atomization quality at high altitude, low combustion efficiency, and insufficient ignition/extinguishing envelope. However, sliding arc plasma has obvious problems in improving the ignition capability of aeroengines and broadening the stable combustion range of aeroengines. The advantages. As shown in Figure 1, in 2018, the Air Force Engineering University of the Chinese People's Liberation Army disclosed a rotating sliding arc plasma fuel cracking head in the aeroengine combustion chamber in the invention number CN108180075A. This device does not change the structure of the original combustion chamber. Features, it can improve the uniformity of mixing of fuel and air, and produce active particles that can accelerate the chemical reaction of combustion; however, the discharge area of this device is greatly affected by the flow field, and its ability to adapt to different incoming flows is weak, and it can only be used when the fuel atomization cone angle is relatively large. Only under large conditions can a certain amount of fuel pass through, resulting in unsatisfactory fuel cracking effect. At the same time, the main body of the cyclone is made of Al2O3 ceramic material. Ceramic material has good high temperature resistance and insulation, but its high brittleness, low impact resistance, and brittleness make it difficult to meet the requirements of aeroengines in actual use. High strength requirements, easy to be damaged by vibration during flight, and poor working reliability.

Contents of the invention

The object of the present invention is to overcome the above-mentioned deficiencies in the prior art and provide a rotating sliding arc plasma enhanced combustion swirl device, which on the one hand promotes the atomization and cracking of fuel, and the active ingredients are combined with the atomization under the action of the swirler. The fuel is fully mixed. On the other hand, the cyclone adopts an integrated structure, which avoids the installation of electrodes on the cyclone, simplifies the structure of the cyclone, enhances the strength of the cyclone, and solves the existing problems based on plasma. The excited ceramic swirler in the combustion chamber is difficult to meet the strength requirements of the aeroengine in actual use. It is easily damaged by vibration during flight and has poor working reliability.

In order to achieve the above object, the technical solution adopted by the present invention is: a rotating sliding arc plasma enhanced combustion swirl device, which is characterized in that it includes a fuel nozzle, an insulating sleeve and a swirler, and the insulating sleeve is sleeved on the fuel The outer side of the nozzle, and is in clearance fit with the fuel nozzle; the swirler is an integrated structure and includes a primary swirler and a secondary swirler, and the secondary swirler is arranged outside the primary swirler , the first-level cyclone includes a first-level cyclone inner sleeve, a first-level cyclone guide blade, a first-level cyclone outer sleeve and a venturi tube, and the first-level cyclone guide blade One end is fixedly connected to the outer wall surface of the inner sleeve of the first-level cyclone, and the other end of the first-level cyclone guide vane is fixedly connected to the inner wall surface of the outer sleeve of the first-level cyclone. The venturi airflow The nozzle at the inlet end is connected with the nozzle at the airflow outlet end of the outer sleeve of the first-level cyclone; wherein, the inner sleeve of the first-level cyclone is sleeved on the outside of the insulating sleeve and is fixedly connected to the insulating sleeve.

The above-mentioned rotating sliding arc plasma enhanced combustion swirl device is characterized in that the swirler is made of conductive metal material and is connected to the anode high-voltage cable.

The above-mentioned rotating sliding arc plasma enhanced combustion swirl device is characterized in that the insulating sleeve is a high-temperature resistant ceramic insulating sleeve and is arranged between the swirler and the fuel nozzle to make the fuel nozzle and the swirl flow The devices are insulated, and when high voltage is applied, the discharge generates sliding arc plasma.

The above-mentioned rotating sliding arc plasma enhanced combustion swirl device is characterized in that the insulating sleeve and the inner sleeve of the primary swirler are fixedly connected by glue.

The above-mentioned rotating sliding arc plasma enhanced combustion swirl device is characterized in that the secondary swirler includes a secondary swirler guide vane, a secondary swirler outer sleeve and a bell mouth. One end of the secondary cyclone guide vane is connected to the outer wall surface of the primary cyclone outer sleeve, and the other end of the secondary cyclone guide vane is connected to the inner wall surface of the secondary cyclone outer sleeve. , the nozzle at the inlet end of the bell mouth airflow is connected with the nozzle at the airflow outlet end of the outer sleeve of the secondary cyclone, and the direction of the air outlet end of the guide vane of the secondary cyclone is in line with the air outlet end of the guide vane of the primary cyclone In the opposite direction.

The above-mentioned rotating sliding arc plasma enhanced combustion swirl device is characterized in that the outlet of the fuel nozzle is located at the inlet end of the venturi tube, and the inlet of the fuel nozzle connected to the oil pipe is installed in the aeroengine combustion chamber. On the box.

The above-mentioned rotating sliding arc plasma enhanced combustion swirl device is characterized in that the fuel nozzle, the insulating sleeve primary swirler and the secondary swirler are coaxially arranged.

The above-mentioned rotating sliding arc plasma enhanced combustion swirl device is characterized in that the inner surface of the venturi tube is an arc surface, and the arc surface forms a convergence at the air inlet end of the venturi tube. section, and an expansion section is formed at the outlet end of the venturi tube.

Compared with the prior art, the present invention has the following advantages:

1. On the one hand, the present invention promotes the atomization and cracking of fuel and the full mixing of active ingredients with the atomized fuel under the action of the cyclone. On the other hand, the cyclone adopts an integrated structure, which avoids the installation of electrodes on the cyclone. The structure simplifies the swirler structure and enhances the strength of the swirler. It solves the problem that the existing plasma-excited combustion chamber ceramic swirler cannot meet the strength requirements of aeroengines in actual use and is susceptible to damage during flight. Damage due to vibration and poor working reliability.

2. The plasma discharge part of the present invention is close to the fuel nozzle, and the arc is rotated and elongated by the first-level swirling flow, thereby improving the discharge efficiency. Moreover, the discharge part is on the only way for the fuel to be injected into the combustion chamber, which is conducive to enhancing combustion. stability, widen the stable working range of the combustion chamber, and improve the combustion efficiency of the aero-engine combustion chamber.

3. The present invention can be based on the metal swirler currently used in the swirl combustion chamber of the engine without changing the original structure and parameters, so it is easier to implement, reliable in operation and has a long service life.

4. Based on the problems existing in the prior art, the present invention adopts the integrated design of the cyclone and the combustion chamber head and adds a ceramic insulating sleeve. After many designs and modifications, and many tests, it has been proved that it is feasible and effective. Practical value.

The present invention will be described in further detail below through the drawings and examples.

Description of drawings

Figure 1 is a schematic three-dimensional structural diagram of the present invention.

Figure 2 is a cross-sectional view of the present invention.

Figure 3 is a front schematic view of the present invention.

Explanation of reference symbols:

10—Fuel nozzle; 20—Insulating sleeve; 30—Cyclone; 31—Inner sleeve of first-level cyclone; 32—First-level cyclone guide vane; 33—Outer sleeve of first-level cyclone; 34—venturi tube; 35—secondary cyclone guide vane; 36—secondary cyclone outer sleeve; 37—bell mouth.

Detailed ways

Embodiments of the invention will be described in more detail below with reference to the accompanying drawings. Although certain embodiments of the invention are shown in the drawings, it should be understood that the invention may be embodied in various forms and should not be construed as limited to the embodiments set forth herein, which rather are provided for A more thorough and complete understanding of the present invention. It should be understood that the drawings and embodiments of the present invention are for illustrative purposes only and are not intended to limit the scope of the present invention.

As shown in Figures 1 to 3, the present invention discloses a rotating sliding arc plasma enhanced combustion swirl device, which includes a fuel nozzle 10, an insulating sleeve 20 and a swirler 30. The insulating sleeve 20 is sleeved on The outer side of the fuel nozzle 10 and is in clearance fit with the fuel nozzle 10; the swirler 30 is an integrated structure and includes a primary swirler and a secondary swirler, and the secondary swirler is arranged on the primary swirler. Outside the flow device, the first-level cyclone includes a first-level cyclone inner sleeve 31, a first-level cyclone guide vane 32, a first-level cyclone outer sleeve 33 and a venturi tube 34. One end of the first-stage cyclone guide vane 32 is fixedly connected to the outer wall surface of the first-stage cyclone inner sleeve 31 , and the other end of the first-stage cyclone guide vane 32 is connected to the first-stage cyclone outer sleeve 33 The inner wall surface of the venturi tube 34 is fixedly connected, and the nozzle at the air flow inlet end of the venturi tube 34 is docked with the nozzle at the air flow outlet end of the first-level cyclone outer sleeve 33; wherein, the first-level cyclone inner sleeve 31 is sleeved on an insulating The outside of the sleeve 20 is fixedly connected to the insulating sleeve 20 .

In this embodiment, the fuel nozzle 10 is connected to the engine fuel pipeline and is commonly grounded. It serves as the cathode of the exciter, and the cyclone 30 serves as the anode. The cathode and the anode are separated by an insulating sleeve 20. Under the excitation of a strong electric field A plasma arc is generated between the cathode and anode, and a rotating sliding arc discharge is formed driven by the rotating airflow of the cyclone. On the one hand, the sliding arc plasma promotes the atomization and cracking of fuel. On the other hand, the active components generated by the sliding arc discharge are fully mixed with the atomized fuel under the action of the cyclone. At the same time, during the sliding arc plasma discharge, Under the action of temperature rise, the ignition and combustion support of the aeroengine combustion chamber are completed. The swirler 30 adopts an integrated structure, which reduces the installation of the swirler 30 and the electrodes, enhances the strength of the swirler, and solves the problem that the existing ceramic swirler in the combustion chamber based on plasma excitation is difficult to meet the actual use of aeroengines. Due to the strength requirements, it is easily damaged by vibration during flight and has poor working reliability.

In this embodiment, the cyclone 30 is made of conductive metal material and is connected to the anode high-voltage cable.

In this embodiment, the insulating sleeve 20 is a high-temperature resistant ceramic insulating sleeve, and is arranged between the swirler 30 and the fuel nozzle 10 to insulate the fuel nozzle and the swirler 30 and discharge when voltage is applied. A sliding arc is produced.

In this embodiment, the insulating sleeve 20 and the inner sleeve 31 of the primary cyclone are fixedly connected by glue.

As shown in Figures 1 to 3, the secondary cyclone includes a secondary cyclone guide blade 35, a secondary cyclone outer sleeve 36 and a bell mouth 37. The secondary cyclone guides the flow. One end of the blade 35 is connected to the outer wall surface of the primary cyclone outer sleeve 33, and the other end of the secondary cyclone guide blade 35 is connected to the inner wall surface of the secondary cyclone outer sleeve 36. The nozzle at the airflow inlet end of the bell mouth 37 is connected with the nozzle at the airflow outlet end of the secondary cyclone outer sleeve 36, and the air outlet direction of the secondary cyclone guide vane 35 is in the same direction as the primary cyclone guide vane 32. The end direction is opposite.

In this embodiment, the outlet of the fuel nozzle 10 is located at the inlet end of the venturi tube 34 , and the inlet of the fuel nozzle 10 connected to the oil pipe is installed on the casing outside the combustion chamber of the aircraft engine.

As shown in Figure 2, the fuel nozzle 10, the insulating sleeve 20, the primary swirler and the secondary swirler are coaxially arranged.

As shown in FIG. 2 , the inner surface of the venturi tube 34 is an arc-shaped surface, and the arc-shaped surfaces respectively form a convergence section at the air inlet end of the venturi tube 34 and a converging section at the air outlet end of the venturi tube 34 . The end forms an expansion segment.

In this embodiment, the inner surface shape of the venturi tube 344 adopts existing technology and is a convex arc surface structure. The two ends of the arc surface form a convergence section at the air inlet end of the venturi tube 34. The outlet end of the Venturi tube 34 forms an expansion section. The outer circumferential surface of the venturi tube 34 is a stepped surface, and the outer diameter at the rear end of the venturi tube 34 is smaller than the outer diameter at the front end. The venturi tube 34 is located in the combustion chamber flame tube. The cable passes through the cable installation hole of the flame tube of the aeroengine combustion chamber and is connected to the wall of the cyclone. The other end is connected to high-voltage alternating current. The venturi tube 34 on the swirler and the fuel nozzle 10 generate a plasma discharge arc under the stimulation of a strong electric field, and a rotating sliding arc discharge is formed driven by the rotating airflow of the swirler. On the one hand, the sliding arc plasma promotes the atomization and cracking of fuel. On the other hand, the active components generated by the sliding arc discharge are fully mixed with the atomized fuel under the action of the cyclone. At the same time, under the action of the sliding arc discharge plasma, Under the action of high temperature, the ignition and combustion control of the combustion chamber are completed.

The above are only preferred embodiments of the present invention and do not limit the present invention in any way. Any simple modifications, changes and equivalent structural transformations made to the above embodiments based on the technical essence of the present invention still belong to the technology of the present invention. within the protection scope of the scheme.

Claims (7)

1. A rotary sliding arc plasma enhanced combustion swirling device, comprising:

a fuel nozzle (10);

the insulation sleeve (20) is sleeved on the outer side of the fuel nozzle (10) and is in clearance fit with the fuel nozzle (10);

the cyclone (30), cyclone (30) is an integral structure and comprises a first-stage cyclone and a second-stage cyclone, the second-stage cyclone is arranged on the outer side of the first-stage cyclone, the first-stage cyclone comprises a first-stage cyclone inner sleeve (31), a first-stage cyclone guide vane (32), a first-stage cyclone outer sleeve (33) and a venturi (34), one end of the first-stage cyclone guide vane (32) is fixedly connected with the outer side wall surface of the first-stage cyclone inner sleeve (31), the other end of the first-stage cyclone guide vane (32) is fixedly connected with the inner side wall surface of the first-stage cyclone outer sleeve (33), and a nozzle at the air flow inlet end of the venturi (34) is in butt joint with a nozzle at the air flow outlet end of the first-stage cyclone outer sleeve (33);

wherein, the first-stage cyclone inner sleeve (31) is sleeved outside the insulating sleeve (20) and is fixedly connected with the insulating sleeve (20);

the cyclone (30) is made of conductive metal material and is connected with the anode high-voltage cable.

2. A rotary sliding arc plasma enhanced combustion cyclone apparatus as claimed in claim 1, wherein the insulating sleeve (20) is a high temperature resistant ceramic insulating sleeve and is arranged between the cyclone (30) and the fuel nozzle (10) to insulate the fuel nozzle from the cyclone (30), and the sliding arc plasma is generated by discharging when a high voltage is applied.

3. A rotary sliding arc plasma enhanced combustion cyclone apparatus as in claim 1, wherein the insulating sleeve (20) is fixedly connected with the primary cyclone inner sleeve (31) by means of cementing.

4. A rotary sliding arc plasma enhanced combustion cyclone device as claimed in claim 1, wherein the secondary cyclone comprises a secondary cyclone guide vane (35), a secondary cyclone outer sleeve (36) and a flare (37), one end of the secondary cyclone guide vane (35) is connected with the outer side wall surface of the primary cyclone outer sleeve (33), the other end of the secondary cyclone guide vane (35) is connected with the inner side wall surface of the secondary cyclone outer sleeve (36), the nozzle at the air flow inlet end of the flare (37) is in butt joint with the nozzle at the air flow outlet end of the secondary cyclone outer sleeve (36), and the air outlet end direction of the secondary cyclone guide vane (35) is opposite to the air outlet end direction of the primary cyclone guide vane (32).

5. A rotary sliding arc plasma enhanced combustion cyclone apparatus as claimed in claim 4, wherein the outlet of the fuel nozzle (10) is located at the inlet end of the venturi tube (34), and the inlet of the fuel nozzle (10) connecting oil pipe is installed on the combustion chamber casing of the aeroengine.

6. A rotary sliding arc plasma enhanced combustion cyclone apparatus as claimed in claim 4, wherein the fuel nozzle (10), the insulating sleeve (20) primary cyclone and the secondary cyclone are coaxially arranged.

7. A rotary sliding arc plasma enhanced combustion cyclone apparatus as claimed in claim 4, wherein the inner surface of the venturi tube (34) is an arc surface, and the arc surface forms a converging section at the air inlet end of the venturi tube (34) and an expanding section at the air outlet end of the venturi tube (34), respectively.