CN115899766A - Combustion chamber - Google Patents

Abstract

The invention discloses a combustion chamber which comprises a casing assembly, a flame tube, an oil supply assembly and a premixing pre-evaporation tube. The casing assembly is formed with an inner cavity, an air inlet and a fuel gas outlet. The flame tube is arranged in the inner cavity, and the inner part of the flame tube is divided into a main combustion area, an annular vortex area and a mixing area. The oil supply assembly comprises a main combustion stage nozzle and an on-duty stage nozzle, the main combustion stage nozzle is mounted on the flame tube and communicated with the main combustion area, and the on-duty stage nozzle is mounted at the head of the flame tube and communicated with the annular vortex area. The premixing pre-evaporation pipe is arranged between the main combustion stage nozzle and the flame tube and is used for premixing and pre-evaporating the mixture of air and oil mist. The invention provides a wide-range oil-gas adaptive premixing pre-evaporation low-pollution combustion chamber, which effectively reduces NO _X The discharge and the flow loss are small, and a more ideal outlet temperature field can be obtained; realizes the ignition flame linkage of the full-ring combustion chamber, has high altitude ignition height,the combustion chamber can be ignited and flame-linked in a wide oil-gas ratio range; the flame stability of the whole combustion chamber is better.

Description

combustion chamber

technical field

The invention relates to the technical field of aero-engines, in particular to a combustion chamber.

Background technique

With the rapid development of the aviation industry, the operating environment faced by aero-engines is becoming more and more complex. The problems of reliable ignition under multiple working conditions in the combustion chamber and stable and efficient combustion in a wide range of oil and gas are more prominent. It is urgent to carry out research on new combustion schemes and technologies.

At present, according to the different characteristics of the head, the combustion chamber can be divided into two types: one is the annular vortex combustion chamber whose flow field is organized by the swirl plate and the impact hole, which is very good at high-altitude ignition, but there is a head The problems of weak flow, weak oil-gas mixing, and poor quality of the outlet temperature field; the second is the swirl-type combustion chamber that organizes the flow field through a vortex, which stabilizes the flame through the swirling airflow at the head, and can strengthen the oil-gas mixing. The oil and gas are mixed evenly in space, which can significantly improve the quality of the outlet temperature field. Based on the concept of partitioned combustion, in recent years, a combustor with a combination of annular vortex and swirl has also appeared. Due to the characteristics of stable and efficient combustion in a wide range of oil and gas, it is called WFA (Wide-range Fuel-air Adapted) combustor. , this wide-area oil-gas adaptable combustor combines the advantages of the annular vortex and swirl-type combustors. On the one hand, it can ensure the ignition performance and combustion efficiency of the combustor under multiple working conditions. On the other hand, it can effectively improve the combustion efficiency in the flame tube. The distribution of oil and gas finally obtains a relatively uniform outlet temperature field.

Existing WFA combustion chambers include inner casing, outer casing, flame tube inner ring, flame tube outer ring, diffuser, nozzle and other components. Without uniform pre-mixing with air, the lean combustion performance in the main combustion zone is relatively low, and the combustion temperature is relatively high, resulting in high NO _X emissions.

Contents of the invention

The main purpose of the present invention is to provide a combustion chamber, aiming at realizing the premixed pre-evaporative combustion of the main combustion grade fuel oil in a lean atmosphere, so as to reduce the temperature of the main combustion zone, suppress the generation of _NOx , and thereby reduce pollution.

In order to achieve the above object, the present invention proposes a combustion chamber, which is applied to an aero-engine, including:

The casing assembly is formed with an inner cavity and an air inlet and a gas outlet communicating with the inner cavity;

The flame tube is arranged in the inner cavity, and the inner part of the flame tube is the main combustion area, the ring vortex area and the mixing area. Outlet connectivity; and

The oil supply assembly includes a main fuel level nozzle and a duty level nozzle, the main fuel level nozzle is installed on the flame tube and communicates with the main combustion zone, the duty level nozzle is installed on the head of the flame tube and communicating with said annular vortex; and

The pre-mixing and pre-evaporating pipe is arranged between the main combustion stage nozzle and the flame tube, and the pre-mixing and pre-evaporating pipe is provided with a mixing and evaporating channel for pre-mixing and pre-evaporating the mixture of air and oil mist .

Optionally, the outlet end of the pre-mixing and pre-evaporating tube is provided with a contraction nozzle for anti-backfire.

Optionally, the outlet end of the pre-mixing pre-evaporation tube is installed on the flame tube through a swirl assembly, and the swirl assembly includes a head inner swirler and a head inner swirler surrounding the The head external cyclone, the head internal cyclone communicates with the outlet end of the pre-mixing pre-evaporation tube.

Optionally, the swirl assembly further includes an inlet swirl, and the inlet swirl is arranged at the inlet end of the main combustion stage nozzle and the pre-mixing and pre-evaporating pipe.

Optionally, the fuel distribution ratio of the main fuel-level nozzles and the duty-level nozzles is 4:1.

Optionally, the head of the flame tube is radially divided into an annular vortex flow head and a swirl flow head, the annular vortex flow head forms the annular vortex region, and the swirl flow head forms In the main combustion zone, the annular vortex flow head and the swirl flow head are connected through a support plate, and the support plate is provided with a support plate air intake hole.

Optionally, an annular vortex flow sheet is installed in the top end of the annular vortex flow head, and an annular vortex air inlet is opened on the top end of the annular vortex flow head, and the front wall of the annular vortex flow head is opened There are jet holes on the front wall of the annular vortex, and jet holes on the rear wall of the annular vortex are opened on the rear wall of the flow head of the annular vortex.

Optionally, the on-duty nozzle is a single oil circuit centrifugal nozzle or a double oil circuit centrifugal nozzle, and the on-duty nozzle is installed on the front wall of the concave cavity of the annular vortex flow head, and its injection direction is toward the Spray near the ring vortex flow sheet;

The main combustion stage nozzle is a single oil circuit centrifugal nozzle or a double oil circuit centrifugal nozzle, and the main combustion stage nozzle is inserted into the mixing evaporation channel along the center line of the inlet swirler.

Optionally, the combustion chamber further includes an igniter, the casing assembly is provided with an electric nozzle hole, the igniter is installed in the electric nozzle hole and extends into the annular vortex region, and the igniter The ignition nozzle is flush with the inner wall of the annular vortex flow head.

Optionally, the inner ring wall of the flame tube is provided with inner ring main combustion holes, inner ring mixing holes and cooling holes, and the outer ring wall of the flame tube is provided with outer ring mixing holes; wherein, the inner The ring main combustion hole is used to cut off the main flow backflow area, supplementary combustion and strengthen the mainstream oil-gas mixing, the inner ring mixing hole and the outer ring mixing hole are used to adjust the outlet temperature field; the cooling holes are fully divergent multiple oblique hole;

The airflow inlet includes the air inlet of the support plate, the air inlet of the annular vortex, the main combustion hole of the inner ring, the mixing hole of the inner ring, the mixing hole of the outer ring and the cooling hole.

In the technical solution of the present invention, the combustion chamber includes a casing assembly, a flame tube, an oil supply assembly, and a pre-mixing pre-evaporation tube; the casing assembly is formed with an inner cavity and an air inlet and a gas outlet communicating with the inner cavity; The flame tube is located in the inner cavity, and the inner part of the flame tube is the main combustion area, the ring vortex area and the mixing area. The flame tube is provided with an airflow inlet, and the mixing area of the flame tube is connected with the gas outlet; Nozzles and duty-level nozzles, the main fuel-level nozzles are installed on the flame tube and connected to the main combustion zone, and the duty-level nozzles are installed on the head of the flame tube and connected to the annular vortex area; pre-mixing and pre-evaporation pipes are installed on the main fuel-level nozzles and Between the flame tubes, the pre-mixing and pre-evaporating tube is provided with a mixing and evaporating channel for pre-mixing and pre-evaporating the mixture of air and oil mist.

The present invention adds a premixing and pre-evaporation tube between the nozzle of the main combustion stage and the main combustion zone, which realizes the premixing and pre-evaporation combustion of the main combustion fuel in a lean atmosphere, and the fuel in the main combustion zone deviates from the equivalent ratio combustion as far as possible, and can Effectively reduce the flame temperature, thereby inhibiting the formation of NO _X , and finally reducing the NO _X emission of the entire combustion chamber.

Description of drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are only These are some embodiments of the present invention. For those skilled in the art, other drawings can also be obtained according to the structures shown in these drawings without creative effort.

Fig. 1 is the structural representation of an embodiment of the combustion chamber of the present invention;

Fig. 2 is a schematic structural view of the premixed preevaporator tube, the main combustion stage nozzle and the swirl assembly in an embodiment of the combustion chamber of the present invention;

Fig. 3 is a schematic structural view of the head of the flame tube in an embodiment of the combustion chamber of the present invention.

Explanation of reference numbers:

10. Case assembly; 20. Flame cylinder; 40. Premixing and pre-evaporating tube; 60. Diffuser; 201. Main combustion zone; 202. Ring vortex zone; 203. Blending zone; 31. Main combustion nozzle; 32. On-duty nozzle; 401. Mixed evaporation channel; 402. Shrink nozzle; 51. Head inner swirler; 52. Head outer swirler; 53. Inlet swirler; 23. Support plate; 23a. Branch plate air intake hole; 24, annular vortex flow sheet; 24a, annular vortex air intake hole; 24b, annular vortex front wall jet hole; 24c, annular vortex rear wall jet hole; 10d, electric nozzle hole; 25a, inner ring main Burning holes; 25b, mixing holes in the inner ring; 25c, mixing holes in the outer ring; 25d, cooling holes.

The realization of the purpose of the present invention, functional characteristics and advantages will be further described in conjunction with the embodiments and with reference to the accompanying drawings.

Detailed ways

The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

It should be noted that if there is a directional indication (such as up, down, left, right, front, back...) in the embodiment of the present invention, the directional indication is only used to explain the position in a certain posture (as shown in the accompanying drawing). If the specific posture changes, the directional indication will also change accordingly.

In addition, if there are descriptions involving "first", "second" and so on in the embodiments of the present invention, the descriptions of "first", "second" and so on are only for descriptive purposes, and should not be interpreted as indicating or implying Its relative importance or implicitly indicates the number of technical features indicated. Thus, the features defined as "first" and "second" may explicitly or implicitly include at least one of these features. In addition, if the meaning of "and/or" appearing in the whole text includes three parallel schemes, taking "A and/or B" as an example, it includes scheme A, scheme B, or schemes in which both A and B are satisfied . In addition, the technical solutions of the various embodiments can be combined with each other, but it must be based on the realization of those skilled in the art. When the combination of technical solutions is contradictory or cannot be realized, it should be considered that the combination of technical solutions does not exist , nor within the scope of protection required by the present invention.

In recent years, the Aviation Protection Committee (CAEP) under the International Civil Aviation Organization (ICAO) has formulated a series of pollution emission standards for aviation power plants, among which the emission limits for NO _X have become increasingly stringent, and the Advisory Council for Aviation Research in Europe (ACARE) has also It is proposed that by 2050, _NOx emissions should be reduced by 90% compared with 2000. Therefore, low _NOx emission is an important evaluation index for low-pollution combustors. A number of studies on low-pollution combustion technologies have shown that improving lean combustion performance and reducing combustion temperature in the main combustion zone can effectively suppress the formation of NO _X , while lean premixed pre-evaporation (LPP, Lean Premixed Pre-evaporation) combustion It is one of the most potential combustion methods. The basic mode of realizing lean-fuel premixing pre-evaporation is to pre-evaporate fuel, mix it with air evenly, enter the main combustion zone, and burn in a lean atmosphere.

In view of this, the present invention proposes a combustor, which is applied to an aero-engine, especially a gas turbine. The invention is based on the concept of zoned combustion, and relates to a combustor combined with a swirl type and a swirl type, which belongs to a WFA combustor due to its characteristics of stable and high-efficiency combustion in a wide range of oil and gas. On the one hand, it can ensure the ignition performance and combustion efficiency of the combustion chamber under multiple working conditions, on the other hand, it can effectively improve the oil and gas distribution in the flame tube, and finally obtain a more uniform outlet temperature field.

Referring to FIG. 1 and FIG. 2 , in an embodiment of the present invention, the combustion chamber includes a casing assembly 10 , a flame tube 20 , an oil supply assembly and a pre-mixing and pre-evaporating tube 40 . The casing assembly 10 is formed with an inner cavity and an air inlet and a gas outlet communicating with the inner cavity. The flame tube 20 is located in the inner cavity, and the inside of the flame tube 20 is a main combustion zone 201, a vortex zone 202 and a mixing zone 203. The flame tube 20 is provided with an airflow inlet, and the mixing zone 203 of the flame tube 20 communicates with the gas outlet. The fuel supply assembly includes a main combustion nozzle 31 and a duty nozzle 32. The main combustion nozzle 31 is installed on the flame tube 20 and communicates with the main combustion area 201. The duty nozzle 32 is installed on the head of the flame tube 20 and communicates with the annular vortex area. 202. The pre-mixing and pre-evaporating pipe 40 is arranged between the main combustion stage nozzle 31 and the flame cylinder 20, and the pre-mixing and pre-evaporating pipe 40 is provided with a mixing and evaporating channel 401 for pre-mixing and pre-evaporating the mixture of air and oil mist.

In this embodiment, the casing assembly 10 may include an inner casing and an outer casing, and an air inlet is provided at one end of the casing assembly 10, and a diffuser 60 is installed at the air inlet to perform pressurization and deceleration processing on the incoming air. The other end of the casing assembly 10 is provided with a gas outlet, and the gas outlet of the flame tube 20 is installed at the gas outlet.

The flame tube 20 may include an inner ring, an outer ring and a head. The inner ring and the outer ring of the flame tube 20 are surrounded by a mixing zone 203. The head of the flame tube 20 is divided into a ring vortex flow head and a swirl flow head radially. The flow head, the ring vortex flow head forms the ring vortex area 202 , and the swirl flow head forms the main combustion area 201 .

The fuel supply assembly also includes a main fuel oil main pipe and a duty fuel main pipe for delivering fuel oil. Wherein, there are at least one nozzle 31 for the main combustion stage and one nozzle 32 for the duty stage, which is not limited here.

The shape of the mixing and evaporating channel 401 of the pre-mixing and pre-evaporating pipe 40 is not limited, and it is preferably a circular channel. The outlet end of the pre-mixing and pre-evaporating pipe 40 is provided with a contraction nozzle 402, which can play a certain role in preventing backfire. By setting a pre-mixing pre-evaporator tube 40 with a shrinking nozzle 402 in the main combustion stage, on the one hand, the complete atomization of the main combustion stage fuel can be achieved, and on the other hand, the fuel can be fully mixed with air, and the tempering is taken into account in the design The problem of spontaneous combustion ensures the normal operation of the LPP working mode.

The present invention combines the main combustion stage and LPP combustion technology of the WFA combustion chamber to realize the premixing and pre-evaporation combustion of the main combustion stage fuel oil in a lean atmosphere, so as to reduce the temperature of the main combustion area 201 and suppress the formation of _NOx , thereby reducing the pollute.

Mainly referring to Fig. 2, in one embodiment, the outlet end of the pre-mixing pre-evaporation tube 40 can be installed on the flame tube 20 through the swirl assembly, the swirl assembly includes a head inner swirler 51 and an inner swirl around the head The head external swirler 52 on the outside of the swirler 51, the head inner swirler 51 communicates with the outlet end of the pre-mixing pre-evaporation pipe 40.

In this embodiment, the swirl assembly may further include an inlet swirler 53 , and the inlet swirl 53 is arranged at the inlet end of the main combustion stage nozzle 31 and the pre-mixing and pre-evaporating pipe 40 .

The present invention adopts the design of the inner swirler 51 at the head and the outer swirler 52 at the head, which can strengthen the mixing of oil and gas in the main combustion zone 201 without causing a large flow loss, and can also obtain a more ideal outlet temperature field .

The duty-level nozzle 32 can be installed on the front wall of the concave cavity, and can adopt a single oil circuit centrifugal nozzle or a double oil circuit centrifugal nozzle, and the injection direction is to spray near the top swirl sheet at a three-dimensional angle including a certain tangential angle. The main combustion stage nozzle 31 can also adopt a single oil circuit centrifugal nozzle or a double oil circuit centrifugal nozzle, which is inserted into the mixing evaporation channel 401 along the centerline of the inlet swirler 53, and most of the fuel is completely evaporated after passing through the premixing and pre-evaporating section A small amount of liquid droplets hit the wall of the pre-mixing pre-evaporation tube 40, and secondary atomization is performed at the outlet.

Since the main combustion stage nozzle 31 uses a centrifugal nozzle to atomize the fuel, in the LPP working mode, the main combustion zone 201 can be operated in a fuel-lean state by adjusting the fuel-air ratio, and the oil mist sprayed by the centrifugal nozzle is misted under the action of the swirling air The mixture of air and oil mist enters the mixed evaporation channel 401 to fully mix and evaporate. The fuel distribution ratio of the main combustion stage nozzle 31 and the duty stage nozzle 32 is approximately 4:1, and the equivalence ratio of the premixing and pre-evaporation section is designed outside the flammability limit, which can prevent this section from flashing back, and at the same time design the oil vapor to stay in this section The time is outside the spontaneous combustion time to prevent spontaneous combustion. The outlet end of the pre-mixing pre-evaporator tube 40 is designed with a shrinking nozzle 402, which can also play a certain role in preventing backfire.

In addition, a head inner swirler 51 is designed on the outside of the shrinking nozzle 402, and a strong swirling flow opaque design is adopted. After a small part of the main combustion air passes through the inner swirler, a recirculation zone with a certain scale can be formed downstream. On the one hand, the existence of the recirculation zone can strengthen the flame stability, and at the same time, it can be used as an ignition source to stabilize the oil and gas of the main fuel level alone, which is beneficial to the mutual support between the main fuel level and the duty level. On the other hand, the spatial distribution of the flow field structure is relatively regular , so that the flow field structure is easy to control and facilitates tissue combustion. The external swirl 52 of the head can be designed with weak swirl flow and light transmission. This light-transmittance swirl combines the advantages of swirl flow and direct flow, and can strengthen the mixing of oil and gas without causing a large total pressure. loss. The LPP design of the main combustion stage adds a pre-mixing pre-evaporator tube 40, which is more convenient to replace and install structurally. At the same time, the fuel in the main combustion zone 201 deviates from the equivalence ratio as far as possible, which can effectively reduce the flame temperature, thereby suppressing the formation of NO _X , and finally reducing the overall _NOx emissions from the combustion chamber.

Referring to FIG. 3 , in one embodiment, the annular vortex flow head and the swirl flow head can be connected through a support plate 23 , and the support plate 23 is provided with a support plate air inlet 23a.

A support plate 23 is used between the duty stage and the main combustion stage to connect, and a small amount of straight-through airflow can enter the flame cylinder 20 through the support plate air intake holes 23a on the front and rear walls of the support plate 23 . On the one hand, the design of the support plate 23 can protect the flow in the duty class from being affected by the mainstream flow, thereby helping the duty class to maintain better ignition performance and wide-range flame stability. On the other hand, the existence of the support plate 23 can strengthen the duty class. The radial flow between the adjacent areas between the stage and the main combustion stage makes the flame in the concave cavity spread to the main combustion stage smoothly, which is beneficial to the flame transfer between the duty stage and the main combustion stage. In addition, the downstream of the support plate 23 can be An axial recirculation zone is formed, so the support plate 23 also has a certain flame stabilizing ability. Because the duty stage, the main combustion stage, and the support plate 23 all have certain flame stabilization capabilities, and are independent of each other in space and have radial flow, so the three can support each other, which can greatly enhance flame stability.

That is to say, the structure of the support plate 23 on the one hand protects the independence of the duty stage and the LPP main combustion stage, on the other hand, it can also make the flame stability of the combustion chamber have "triple insurance", and at the same time, the "triple insurance" can support each other , so the flame stability of the entire combustion chamber is better.

In addition, the present invention adopts radial classification, compact structure, and small cooling area. The LPP main combustion stage adopts the design scheme of internal strong and external weak swirler, and at the same time matches the pre-mixing and pre-evaporation pipe 40, and utilizes a small total pressure loss to strengthen The mixing of oil and gas in the main combustion zone 201 is ensured, the outlet temperature distribution of the flame tube 20 is more ideal, and the wall surface temperature of the flame tube 20 is effectively reduced.

Referring to Fig. 1 to Fig. 3, in one embodiment, the top end of the annular vortex flow head of the combustion chamber is equipped with an annular vortex flow piece 24, and the top end of the annular vortex flow head is provided with an annular vortex inlet hole 24a, The front wall of the orbital vortex flow head is provided with an annular vortex front wall injection hole 24b, and the rear wall of the annular vortex flow head is provided with an annular vortex rear wall jet hole 24c.

The on-duty nozzle 32 of the combustion chamber can use centrifugal nozzles to supply oil tangentially, and the annular vortex area 202 forms a large-scale tangential flow in space through the combination mode of the static pressure air intake of the annular vortex inlet 24a and the circumferential swirl vane, and Under the truncation effect of the jet hole 24b on the front wall of the annular vortex and the jet hole 24c on the rear wall of the annular vortex, a plurality of recirculation areas of different scales are formed in the annular vortex area 202 . The duty-level annular vortex head can not only realize reliable ignition and joint flame at high altitude ignition height above 8km with a small number of fuel nozzles, but also realize efficient and stable combustion under low working conditions, and can better undertake the function of flame stability to adapt to Changeable and complex working environment.

Referring to Fig. 1 and Fig. 3, in one embodiment, casing assembly 10 can be provided with electric nozzle hole 10d, and igniter is installed in electric nozzle hole 10d and extends into annular vortex region 202, and the ignition electric nozzle of igniter and The inner wall surface of the annular vortex flow head is even.

In this embodiment, the ignition of the combustion chamber is directly ignited by a high-energy ignition nozzle, and the nozzle hole 10d can be opened on the outer casing.

Mainly referring to Fig. 1, in one embodiment, according to the needs of flow, mixing and cooling, the inner ring wall of the flame tube 20 is provided with an inner ring main combustion hole 25a, an inner ring mixing hole 25b and a cooling hole 25d, and the flame tube 20 The outer ring wall surface of the outer ring is provided with an outer ring mixing hole 25c; wherein, the inner ring main combustion hole 25a is used to cut off the main flow backflow area, supplementary combustion and strengthen the mainstream oil-gas mixing, and the inner ring mixing hole 25b and the outer ring mixing hole 25c are used for To adjust the outlet temperature field; the cooling hole 25d is a fully divergent multi-slope hole, and the angle of the multi-slope hole is a compound angle with a three-dimensional angle in space.

With reference to Fig. 1 and Fig. 3, in the present embodiment, the airflow inlet of flame cylinder 20 comprises support plate inlet hole 23a, ring vortex inlet hole 24a, inner ring main combustion hole 25a, inner ring mixing hole 25b, outer ring mixing hole Mixing hole 25c and cooling hole 25d.

In this embodiment, six airflow inlets are designed in the combustion chamber, so the flame cylinder 20 can be divided into a main combustion zone 201 , a vortex zone 202 and a mixing zone 203 . The ring vortex area 202 is mainly responsible for the ignition and co-flame function, the main combustion area 201 can achieve low _NOx generation through LPP technology, so it mainly undertakes the role of reducing _NOx emissions, and the mixing area 203 helps to obtain a more uniform flame tube 20 outlet temperature field.

The present invention provides an LPP low-pollution combustion chamber suitable for wide-area oil and gas, which combines the characteristics of the two types of combustion chambers, the annular vortex type and the swirling flow type, and has the same characteristics as the conventional combustion chamber in terms of aerodynamics. Enter the combustion chamber after the pressure drop speed, is also divided into three ways and enters the inside of the flame tube 20 from the inner ring, the outer ring and the head of the flame tube 20 respectively. Fuel enters the inside of the flame tube 20 radially through the duty stage nozzle 32 and the main combustion stage nozzle 31 , the duty stage is located outside the inner cavity of the casing assembly 10 , and the main combustion stage is located inside the interior cavity of the casing assembly 10 .

The above descriptions are only optional embodiments of the present invention, and do not limit the patent scope of the present invention. Under the inventive concept of the present invention, the equivalent structural transformation made by using the description of the present invention and the contents of the accompanying drawings, or direct/indirect Application in other related technical fields is included in the patent protection scope of the present invention.

Claims (10)

1. A combustion chamber for an aircraft engine, comprising:

the casing assembly is provided with an inner cavity, an air inlet and a fuel gas outlet which are communicated with the inner cavity;

the flame tube is arranged in the inner cavity, the inner part of the flame tube is divided into a main combustion area, an annular vortex area and a mixing area, the flame tube is provided with an airflow inlet, and the mixing area of the flame tube is communicated with the fuel gas outlet; and

the oil supply assembly comprises a main combustion stage nozzle and an on-duty stage nozzle, the main combustion stage nozzle is mounted on the flame tube and communicated with the main combustion zone, and the on-duty stage nozzle is mounted at the head of the flame tube and communicated with the annular vortex zone; and

the premixing pre-evaporation pipe is arranged between the main combustion stage nozzle and the flame tube, and is provided with a mixing evaporation channel for premixing and pre-evaporating the mixture of air and oil mist.

2. The combustor of claim 1, wherein the outlet end of said pre-mix pre-evaporator tube is provided with a converging nozzle for flashback prevention.

3. The combustor of claim 2, wherein the outlet ends of the pre-mix pre-evaporator tubes are mounted to the liner by a swirler assembly, the swirler assembly including an inner-header swirler in communication with the outlet ends of the pre-mix pre-evaporator tubes and an outer-header swirler surrounding the outer side of the inner-header swirler.

4. The combustor of claim 3, wherein the swirl assembly further comprises an inlet swirler disposed at an inlet end of the main combustion stage nozzle and the pre-mix pre-evaporator tube.

5. The combustor of claim 1, wherein the fuel distribution ratio of the main burner stage nozzles to the class stage nozzles is 4:1.

6. The combustor of claim 4, wherein the head of the liner is radially divided into a vortex-surrounding flow head and a swirl flow head, the vortex-surrounding flow head forms the vortex-surrounding region, the swirl flow head forms the main combustion region, the vortex-surrounding flow head and the swirl flow head are connected by a support plate, and the support plate is provided with a support plate air inlet hole.

7. The combustor according to claim 6, wherein a vortex sheet is installed in a top end of the vortex-surrounding flow head, a vortex inlet hole is formed in the top end of the vortex-surrounding flow head, a vortex front wall jet hole is formed in a front wall of the vortex-surrounding flow head, and a vortex rear wall jet hole is formed in a rear wall of the vortex-surrounding flow head.

8. The combustor of claim 7, wherein the class spray nozzle is a single oil path centrifugal spray nozzle or a double oil path centrifugal spray nozzle, and is mounted on a front wall of a cavity of the ring vortex flow head and has a spray direction of spraying near the ring vortex flow sheet;

the main combustion stage nozzle is a single-oil-way centrifugal nozzle or a double-oil-way centrifugal nozzle, and is inserted into the mixed evaporation channel along the center line of the inlet swirler.

9. The combustor of claim 7, further comprising an igniter, wherein the casing assembly is provided with a nozzle hole, wherein the igniter is mounted in the nozzle hole and extends into the ring vortex zone, and wherein an ignition nozzle of the igniter is flush with an inner wall surface of the ring vortex flow head.

10. The combustion chamber as claimed in claim 7, wherein the inner ring wall of the flame tube is provided with an inner ring main combustion hole, an inner ring mixing hole and a cooling hole, and the outer ring wall of the flame tube is provided with an outer ring mixing hole; the inner ring main combustion hole is used for cutting off a main flow backflow area, afterburning and strengthening main flow oil-gas mixing, and the inner ring mixing hole and the outer ring mixing hole are used for adjusting an outlet temperature field; the cooling holes are full-divergence multi-inclined holes;

the airflow inlet comprises the support plate air inlet, the ring vortex air inlet, the inner ring main combustion hole, the inner ring mixing hole, the outer ring mixing hole and the cooling hole.

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