Combustion components and aircraft engines

Abstract

The present invention belongs to the technical field of aircraft engines, and provides a combustion assembly and an aircraft engine, wherein the combustion assembly includes: a flame tube, which is formed with a combustion chamber; a nozzle, which is arranged in the combustion chamber, and the nozzle has a first flow channel, a second flow channel and a third flow channel, wherein the first flow channel is arranged around the second flow channel, the first flow channel has a first outlet, the second flow channel has a second outlet, the second outlet is located in the first outlet, the third flow channel is arranged in the second flow channel and is close to the second outlet, and the third flow channel connects the second flow channel and the combustion chamber; wherein the first flow channel is suitable for passing air, and the second flow channel is suitable for passing liquid hydrogen. By setting two flow channels, hydrogen and air flow in different flow channels, so that air and hydrogen flow separately, it is possible to avoid problems such as self-ignition and backfire of hydrogen in the nozzle.

Description

Technical Field

[0001] The invention belongs to the technical field of aeroengines, and in particular relates to a combustion component and an aeroengine. Background Art

[0002] In the aviation field, an aircraft engine is an engine that provides power for the flight of an aircraft. Among them, the hydrogen-fueled turbojet engine is a relatively simple zero-carbon emission new energy engine. The hydrogen-fueled turbojet engine uses hydrogen as fuel. Due to the low density of hydrogen, aircraft cannot directly carry hydrogen for use, so liquid hydrogen is required as the storage fuel of the aircraft. The temperature of liquid hydrogen is very low, and it needs to be heated before use to convert the liquid hydrogen into hydrogen at a suitable temperature before it can be used as fuel in the combustion chamber.

[0003] In the related prior art, an evaporator tube structure is often used to heat the fuel. The fuel nozzle is inserted into the evaporator tube from the air inlet end of the evaporator tube. The fuel enters the evaporator tube after being sprayed out through the nozzle, and is heated by the evaporator tube wall and airflow, causing part of the fuel to evaporate to form fuel vapor. The fuel droplets and vapor are sprayed along the evaporator tube in the opposite direction of the gas flow to the head area of ​​the combustion chamber, and are further mixed with the air at the head of the combustion chamber, evaporated and burned.

[0004] However, since hydrogen has a very low ignition point, it is easy for hydrogen to spontaneously ignite and backfire in the evaporator tube, which can cause evaporator tube ablation and engine failure. Summary of the invention

[0005] In view of this, the present invention provides a combustion assembly and an aircraft engine to solve the problem in the prior art that liquid hydrogen evaporates and burns in an evaporator tube under heat, and is prone to spontaneous combustion due to its low ignition point.

[0006] On the one hand, the present invention provides a combustion assembly, which includes: a flame tube forming a combustion chamber; a nozzle arranged in the combustion chamber, the nozzle having a first flow channel, a second flow channel and a third flow channel, the first flow channel is arranged around the second flow channel, the first flow channel has a first outlet, the second flow channel has a second outlet, the second outlet is located in the first outlet, the third flow channel is arranged in the second flow channel and close to the second outlet, and the third flow channel connects the second flow channel and the combustion chamber; wherein, the first flow channel is suitable for passing air, and the second flow channel is suitable for passing liquid hydrogen.

[0007] The beneficial effect is that liquid hydrogen enters the second flow channel and air enters the first flow channel. As the air gradually flows in the first flow channel toward the first outlet, it is gradually heated by the combustion chamber, so that the heated air transfers heat to the second flow channel. The liquid hydrogen in the second flow channel gradually changes from liquid to gas after heating. Part of the gaseous hydrogen enters the combustion chamber from the second flow channel to participate in combustion, and another part of the gaseous hydrogen flows out from the second outlet and passes through the first outlet. Hydrogen and air flow in different flow channels, so that air and hydrogen flow separately, which can avoid problems such as self-ignition and flashback of hydrogen in the nozzle.

[0008] As an optional embodiment, the nozzle includes: an outer sleeve; an inner sleeve, which is sleeved inside the outer sleeve, and the inner sleeve forms the second flow channel; wherein the first flow channel is formed between the inner wall of the outer sleeve and the outer wall of the inner sleeve.

[0009] The beneficial effect is that the first flow channel and the second flow channel are formed by placing the inner sleeve in the outer sleeve, which has a simple structure and is easy to implement.

[0010] As an optional embodiment, a first connecting port is provided on the side wall of the outer sleeve at one end close to the first outlet, a second connecting port is provided on the side wall of the inner sleeve at one end close to the second outlet, and the nozzle also includes a connecting pipe, one end of the connecting pipe is connected to the first connecting port, and the other end of the connecting pipe is connected to the second connecting port.

[0011] The beneficial effect is that the connecting pipe is arranged in the first flow channel, and the two ends of the connecting pipe are respectively connected to the outer sleeve and the inner sleeve, so the structure is simple and reliable.

[0012] As an optional embodiment, the first connection port is set to be multiple along the circumferential direction of the outer sleeve, the second connection port is set to be multiple along the circumferential direction of the inner sleeve, and the multiple first connection ports are set to the multiple second connection ports in a one-to-one correspondence.

[0013] The beneficial effect is that, by providing a plurality of third flow channels, a plurality of hydrogen ejection points can be formed on the outer sleeve, so that the hydrogen is more evenly distributed in the flame tube and burns more fully.

[0014] As an optional implementation manner, the shape of the third flow channel enables the airflow entering the third flow channel to form a swirl.

[0015] The beneficial effect is that the shape of the third flow channel allows the airflow entering the third flow channel to form a swirl, which can enhance the mixing of air and hydrogen, making the gas mixing more uniform, which is conducive to more complete combustion and improved combustion efficiency.

[0016] As an optional implementation, the third flow channel is in a blade shape.

[0017] The beneficial effect is that the blade-shaped third flow channel generates a swirl when the gas enters and flows through the third flow channel.

[0018] As an optional embodiment, a side wall of the nozzle is provided with a cooling hole, and the cooling hole connects the combustion chamber and the first flow channel.

[0019] The beneficial effect is that the cooling hole is opened on the side wall of the outer sleeve, and the cooling hole connects the first flow channel and the combustion chamber, so that air can enter the cooling chamber through the cooling hole, and then approach or contact the outside of the outer sleeve located in the cooling chamber. The air in the outer sleeve is ejected from the cooling hole, which can protect the outer sleeve from ablation.

[0020] As an optional implementation, the cooling hole is an inclined hole, and an angle is formed between a center line of the inclined hole and an outer side wall of the nozzle, and the angle is an acute angle.

[0021] The beneficial effect is that the cooling hole is an inclined hole arranged along the air flow direction of the first flow channel, and the air flow of the first flow channel can be sprayed out obliquely along the inclined hole, so that it can better approach or fit the outer wall of the outer sleeve and cover the outer wall of the outer sleeve, so that the air entering the combustion chamber through the cooling hole can protect the outer sleeve.

[0022] As an optional embodiment, the nozzle has a bending portion, so that the airflow in the nozzle changes direction at the bending portion.

[0023] The beneficial effect is that the nozzle is bent so that the liquid hydrogen entering the second flow channel flows downward under the action of gravity, and then is gradually heated in the second flow channel and vaporized to become gas. The lower part of the nozzle is horizontally arranged to slow down the flow rate of the hydrogen, so that the hydrogen can participate in the combustion process after being fully vaporized.

[0024] On the other hand, the present invention further provides an aircraft engine, comprising any one of the combustion components described above.

[0025] The beneficial effect is that, since the above-mentioned aircraft engine includes the above-mentioned combustion assembly, the above-mentioned aircraft engine has all the beneficial effects of the combustion assembly, which will not be repeated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0027] Figure 1 It is a structural schematic diagram of a combustion assembly according to an embodiment of the present invention;

[0028] Figure 2 is a schematic diagram of the working state of the combustion assembly of an embodiment of the present invention;

[0029] Figure 3 A schematic diagram of the angle arrangement of the cooling holes of the combustion assembly according to an embodiment of the present invention;

[0030] Figure 4 This is a schematic diagram of the three-dimensional structure of the connecting pipe of the combustion assembly according to an embodiment of the present invention;

[0031] Figure 5 A schematic diagram of the installation structure of the connecting pipe of the combustion assembly according to an embodiment of the present invention.

[0032] Description of reference numerals:

[0033] 1. Outer sleeve;

[0034] 1001, first flow channel;

[0035] 1002, first exit;

[0036] 101. Cooling hole;

[0037] 102. A first connection port;

[0038] 2. Inner casing;

[0039] 2001, Second Flow Channel;

[0040] 2002, Second Exit;

[0041] 201, second connection port;

[0042] 3. Connecting pipe;

[0043] 3001. The third flow channel. DETAILED DESCRIPTION

[0044] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0045] At present, the main structure of steel structure combustion components at home and abroad adopts steel trusses, and the enclosure system adopts metal panels, including corrugated steel plates and aluminum alloy plates. The enclosure system has the following shortcomings:

[0046] Combine the following Figures 1 to 5 , describing an embodiment of the present invention.

[0047] like Figure 1 and Figure 2 As shown, according to an embodiment of the present invention, a combustion assembly is provided, the combustion assembly includes a flame tube and a nozzle, the flame tube forms a combustion chamber, the nozzle is arranged in the combustion chamber, the nozzle has a first flow channel 1001, a second flow channel 2001 and a third flow channel 3001, the first flow channel 1001 is arranged around the second flow channel 2001, the first flow channel 1001 has a first outlet 1002, the second flow channel 2001 has a second outlet 2002, the second outlet 2002 is located in the first outlet 1002, the third flow channel 3001 is arranged in the second flow channel 2001 and is close to the second outlet 2002, and the third flow channel 3001 connects the second flow channel 2001 and the combustion chamber; wherein, the first flow channel 1001 is suitable for passing air, and the second flow channel 2001 is suitable for passing liquid hydrogen.

[0048] The first flow channel 1001 mentioned above further has a first inlet, and the first inlet is used to introduce air into the first flow channel 1001 . The second flow channel 2001 further has a second inlet, and the second inlet is used to introduce liquid hydrogen into the second flow channel 2001 .

[0049] Liquid hydrogen enters the second flow channel 2001 from the second inlet, and air enters the first flow channel 1001 from the first inlet. As the air gradually flows in the first flow channel 1001 toward the first outlet 1002, it is gradually heated by the combustion chamber, so that the heated air transfers heat to the second flow channel 2001, and the liquid hydrogen in the second flow channel 2001 gradually changes from liquid to gas after being heated. A part of the gaseous hydrogen enters the combustion chamber from the second flow channel 2001 to participate in combustion, and another part of the gaseous hydrogen flows out from the second outlet 2002 and passes through the first outlet 1002.

[0050] Understandably, in the end, the hydrogen is divided into two parts, one part is sprayed from the outlet of the third flow channel 3001 to the main combustion area of ​​the flame tube to participate in combustion, and the other part is sprayed from the outlet of the second flow channel 2001 and mixed with the air in the first flow channel 1001 and then enters the head area of ​​the flame tube to participate in combustion.

[0051] Hydrogen and air flow in different flow channels, so that air and hydrogen flow separately, which can avoid problems such as self-ignition and backfire of hydrogen in the nozzle.

[0052] Furthermore, the nozzle has a bending portion, so that the airflow in the nozzle changes direction at the bending portion.

[0053] It can be understood that the nozzle can form an upper pipeline and a lower pipeline through a bending portion, the upper pipeline is vertically arranged or inclined, and the lower pipeline is horizontally arranged, so that the liquid hydrogen entering the second flow channel 2001 flows downward under the action of gravity, and then as the liquid hydrogen is gradually heated in the second flow channel 2001, it vaporizes and turns into gas. The lower part of the nozzle is horizontally arranged, which can slow down the flow speed of the hydrogen, so that the hydrogen can participate in the combustion process after being fully vaporized.

[0054] Furthermore, the nozzle includes an outer sleeve 1 and an inner sleeve 2, the inner sleeve 2 is sleeved inside the outer sleeve 1, and the inner sleeve 2 forms a second flow channel 2001; wherein a first flow channel 1001 is formed between the inner wall of the outer sleeve 1 and the outer wall of the inner sleeve 2.

[0055] It can be understood that the outer sleeve 1 and the inner sleeve 2 are hollow pipes respectively, the liquid hydrogen enters the second pipe from the air inlet end of the inner sleeve 2, and the air enters the annular space between the outer sleeve 1 and the inner sleeve 2 from the air inlet end of the outer sleeve 1, and the outside of the outer sleeve 1 is the high-temperature combustion gas in the flame tube. The high-temperature combustion gas heats the outer sleeve 1, and the temperature of the inner sleeve 2 increases under the action of radiation heat transfer of the outer sleeve 1 and air heating, so that the inner sleeve 2 heats the liquid hydrogen therein, and the liquid hydrogen vaporizes and becomes hydrogen.

[0056] Furthermore, a first connecting port 102 is provided on the side wall of the outer sleeve 1 at one end close to the first outlet 1002, a second connecting port 201 is provided on the side wall of the inner sleeve 2 at one end close to the second outlet 2002, and the nozzle also includes a connecting pipe 3, one end of the connecting pipe 3 is connected to the first connecting port 102, and the other end of the connecting pipe 3 is connected to the second connecting port 201.

[0057] It can be understood that the shape of the cross section of the connecting pipe 3 matches the shape of the first connecting port 102 and the second connecting port 201, so that the connecting pipe 3 can be connected between the first connecting port 102 and the second connecting port 201. The inner sleeve 2 heats the incoming liquid hydrogen so that the liquid hydrogen is vaporized into hydrogen, and a part of the hydrogen is sprayed into the combustion chamber through the connecting pipe 3 and the first connecting port 102 for combustion.

[0058] The shape of the third flow channel 3001 allows the airflow entering the third flow channel 3001 to form a swirl, which can enhance the mixing of air and hydrogen, making the gas mixing more uniform, which is conducive to more complete combustion and improved combustion efficiency.

[0059] More specifically, Figure 4 When the first connection port 102 and the second connection port 201 are in the shape of blades, the connection pipe 3 is also in the shape of blades, so that when the gas enters the connection pipe 3 and flows through the third flow channel 3001 of the connection pipe 3, a swirl will be generated.

[0060] In another embodiment, if Figure 5 As shown, a plurality of first connection ports 102 are arranged along the outer circumference of the outer sleeve 1 , a plurality of second connection ports 201 are arranged along the outer circumference of the inner sleeve 2 , and the plurality of first connection ports 102 and the plurality of second connection ports 201 are arranged in one-to-one correspondence.

[0061] It is understandable that the outer sleeve 1 is a cylindrical tube, and the outer sleeve 1 is provided with a plurality of first connection ports 102 along the circumferential direction. For example, four first connection ports 102 may be provided. Similarly, the inner sleeve 2 is also a cylindrical structure, and the inner sleeve 2 is also provided with a plurality of second connection ports 201 along the circumferential direction, and the second connection ports 201 are also provided in four. Of course, the connecting pipe 3 is also provided in four. In addition, the first flow channel 1001 and the second flow channel 2001 may be provided with a plurality of groups of connection ports in the flow direction of the gas. Each group of connection ports includes a plurality of first connection ports 102 and a second connection port 201 provided in the circumferential direction, so that a plurality of hydrogen ejection points may be formed on the outer sleeve 1, so that the hydrogen is more evenly distributed in the flame tube and burns more fully.

[0062] In another embodiment, the side wall of the nozzle is provided with a cooling hole 101, and the cooling hole 101 connects the combustion chamber and the first flow channel 1001. Since the cooling hole 101 is initially on the outer wall of the nozzle, that is, the cooling hole 101 is opened on the side wall of the outer sleeve 1, the cooling hole 101 connects the first flow channel 1001 and the combustion chamber, so that air can enter the cooling chamber through the cooling hole 101, and then approach or contact the outside of the outer sleeve 1 located in the cooling chamber, and the air in the outer sleeve 1 is ejected from the cooling hole 101, which can protect the outer sleeve 1 from ablation.

[0063] Among them, Figure 3 As shown, the cooling hole 101 is an inclined hole, and an angle is formed between the center line of the inclined hole and the outer wall of the nozzle, and the angle is an acute angle. For example, the angle can be 45°. It can be understood that the cooling hole 101 is an inclined hole arranged along the airflow direction of the first flow channel 1001, and the airflow of the first flow channel 1001 can be sprayed out along the inclined hole, so that it can better approach or fit with the outer wall of the outer sleeve 1, covering the outer wall of the outer sleeve 1, so that the air entering the combustion chamber through the cooling hole 101 can play a role in protecting the outer sleeve 1.

[0064] On the other hand, an embodiment of the present application further provides an aircraft engine, the aircraft engine comprising any one of the combustion components.

[0065] Understandably, the combustion assembly is arranged inside the flame tube, used for heating liquid hydrogen, mixing with air, and forming a head reflow zone, and is suitable for use in hydrogen fueled turbojet engines. Since hydrogen has a very low ignition point, hydrogen and air are separated, which avoids hydrogen self-ignition and flashback, avoids nozzle ablation, and reduces the engine failure rate.

[0066] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention.

Claims

1. A combustion assembly, characterized in that: include: A flame tube forming a combustion chamber; A nozzle, arranged in the combustion chamber, the nozzle comprising a first flow channel (1001), a second flow channel (2001) and a third flow channel (3001), the first flow channel (1001) being arranged around the second flow channel (2001), the first flow channel (1001) having a first outlet (1002), the second flow channel (2001) having a second outlet (2002), the second outlet (2002) being located in the first outlet (1002), the third flow channel (3001) being arranged in the second flow channel (2001) and close to the second outlet (2002), the third flow channel (3001) being connected with the second flow channel (2001) and the combustion chamber; Wherein, the first flow channel (1001) is suitable for passing air, and the second flow channel (2001) is suitable for passing liquid hydrogen; The nozzle has a bending portion so that the airflow in the nozzle changes its flow direction at the bending portion; the nozzle forms an upper pipeline and a lower pipeline through the bending portion, the upper pipeline is vertically arranged or inclined, and the lower pipeline is horizontally arranged.

2. The combustion assembly according to claim 1, characterized in that The nozzle comprises: An outer sleeve (1); An inner sleeve (2) is sleeved inside the outer sleeve (1), and the inner sleeve (2) forms the second flow channel (2001); Wherein, the first flow channel (1001) is formed between the inner wall of the outer sleeve (1) and the outer wall of the inner sleeve (2).

3. The combustion assembly according to claim 2, characterized in that: A first connection port (102) is provided on the side wall of one end of the outer sleeve (1) close to the first outlet (1002), and a second connection port (201) is provided on the side wall of one end of the inner sleeve (2) close to the second outlet (2002). The nozzle also includes a connection pipe (3), one end of the connection pipe (3) is connected to the first connection port (102), and the other end of the connection pipe (3) is connected to the second connection port (201).

4. The combustion assembly according to claim 3, characterized in that: The first connection ports (102) are arranged in plurality along the outer circumferential direction of the outer sleeve (1), and the second connection ports (201) are arranged in plurality along the outer circumferential direction of the inner sleeve (2), and the plurality of first connection ports (102) and the plurality of second connection ports (201) are arranged in one-to-one correspondence.

5. The combustion assembly according to claim 3, characterized in that: The shape of the third flow channel (3001) enables the airflow entering the third flow channel (3001) to form a swirl.

6. The combustion assembly according to any one of claims 1 to 5, characterized in that: The third flow channel (3001) is in the shape of a blade.

7. The combustion assembly according to any one of claims 1 to 4, characterized in that: A cooling hole (101) is provided on the side wall of the nozzle, and the cooling hole (101) is connected to the combustion chamber and the first flow channel (1001).

8. The combustion assembly according to claim 7, characterized in that The cooling hole (101) is an inclined hole, and an angle is formed between a center line of the inclined hole and an outer side wall of the nozzle, and the angle is an acute angle.

9. An aircraft engine, characterized in that: Comprising a combustion assembly as claimed in any one of claims 1 to 8.

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