Combustion chamber structure and turbojet engine

Abstract

The present application relates to turbojet engine technical field, disclose a kind of combustion chamber structure and turbojet engine, combustion chamber structure includes: casing, flame tube and hydrogen nozzle;Flame tube is arranged in the inside of casing, the airflow passage between its outer wall and the inner wall of casing is formed, for cooling the outer surface of flame tube and providing the required air for combustion process.Hydrogen nozzle is made of built-in main pipe and nozzle piece, built-in main pipe is located in airflow passage, by with external hydrogen supply pipeline connection, realize the efficient delivery of hydrogen.Nozzle piece one end is connected built-in main pipe, the other end is worn in the side wall of flame tube and extends to the inside of flame tube, ensure that hydrogen can be accurately sprayed into combustion zone.The design greatly optimizes combustion efficiency, while significantly simplifying combustion chamber structure.

Description

Technical Field

[0001] This invention relates to the field of turbojet engine technology, specifically to a combustion chamber structure and a turbojet engine. Background Technology

[0002] Nozzles and flame tubes are crucial components of the combustion chamber. In conventional engine combustion chambers, fuel nozzles atomize the fuel delivered to the combustion chamber and inject it into the flame tube for combustion. This new concept proposes a novel cycle engine that replaces existing fuels with complex components like fuel oil with high-specific-heat, low-molecular-weight hydrogen fuel. This new engine can serve as a propulsion system for supersonic cruise missiles, high-speed reconnaissance aircraft, long-range attack aircraft, and is also an ideal propulsion system for the first stage of orbital vehicles, possessing significant performance advantages and broad application prospects.

[0003] Hydrogen fuel cell engines use gaseous hydrogen as fuel. In the field of hydrogen fuel utilization, the combustion chamber is the core component for achieving combustion organization, directly affecting combustion efficiency and emission performance. However, in existing technologies, hydrogen fuel cell combustion chambers typically employ a hydrogen nozzle combined with a vortex generator, or achieve combustion organization through multiple premixing tubes. The designs of existing technologies are complex in terms of manufacturing processes, requiring a large variety and number of components. Furthermore, the combustion chamber structure design occupies a significant amount of space outside the casing and at the head of the flame tube, not only increasing manufacturing costs but also limiting the optimization of the equipment's size. Summary of the Invention

[0004] In view of this, the present invention provides a combustion chamber structure and a turbojet engine to solve the problems of complex combustion chamber structure design, large space occupation, and high manufacturing cost in the prior art.

[0005] To solve the above-mentioned technical problems, the technical solution of the present invention is as follows:

[0006] In a first aspect, the present invention provides a combustion chamber structure, comprising: a casing, a flame tube, and a hydrogen nozzle; the flame tube is disposed within the casing, and an airflow channel is formed between the outer wall of the flame tube and the inner wall of the casing; the hydrogen nozzle comprises an internal main pipe and a nozzle component disposed in connection with each other, the internal main pipe being located within the airflow channel, one end of the nozzle component being connected to the internal main pipe, and the other end being inserted through the side wall of the flame tube to extend into the interior of the flame tube.

[0007] It has the following advantages:

[0008] By placing the flame tube inside the casing and forming an airflow channel between the outer wall of the flame tube and the inner wall of the casing, and using a hydrogen nozzle built into the airflow channel—which includes a connected internal main pipe and nozzle components—the gas supply and injection devices are integrated, achieving efficient control of hydrogen injection and reducing system complexity. The nozzle components directly penetrate the side wall of the flame tube and extend into the interior of the flame tube, contributing to uniform combustion. This combustion chamber has a simple and compact structure with low manufacturing cost. Furthermore, its structure is easy to manufacture and assemble, effectively improving the industrial production efficiency and economic benefits of the product.

[0009] According to a first aspect of the present invention, the built-in manifold includes:

[0010] A hydrogen supply pipe, one end of which passes through the casing to extend to communicate with an external pipeline;

[0011] A ring pipe is located at the other end of the hydrogen supply pipe and is connected to the hydrogen supply pipe. The side wall of the ring pipe is provided with a plurality of first through holes.

[0012] A branch pipe, one end of which passes through the first through hole to extend into the annular pipe and communicate with the annular pipe, and the other end of which communicates with the nozzle component.

[0013] According to a first aspect of the present invention, the other end of the branch pipe is bent toward the inner diameter side to form a hook-shaped arrangement.

[0014] According to a first aspect of the present invention, along the axial direction of the flame tube, the nozzle is obliquely inserted through the side wall of the flame tube to extend obliquely into the interior of the flame tube.

[0015] According to a first aspect of the present invention, the nozzle assembly includes a sealing pipe, a transition pipe, a flow divider pipe, and a throttling pipe connected in sequence;

[0016] One end of the sealing pipe is connected to the other end of the branch pipe. The sealing pipe is bent into a bull horn-shaped structure, and part of the sealing pipe extends into the flame tube.

[0017] One end of the transition tube is connected to the other end of the sealing tube, the other end of the transition tube is connected to one end of the diverter tube, the other end of the diverter tube is connected to one end of the throttling tube, and the throttling tube is connected to the flame tube.

[0018] The transition tube, the diverter tube, and the throttling tube are all located inside the flame tube.

[0019] According to a first aspect of the present invention, the inlet ends of the sealing pipe, the transition pipe, the diverter pipe and the throttling pipe are all provided with a chamfer angle of 10° to 45° along the hydrogen flow direction.

[0020] According to a first aspect of the present invention, the transition tube, the diverter tube, and the throttling tube are all straight tubes, the outer diameter of the transition tube is equal to the inner diameter of the sealing tube, and the inner diameter of the diverter tube is equal to the inner diameter of the transition tube.

[0021] According to a first aspect of the present invention, along the hydrogen flow direction, the outlet end of the diverter has a stepped platform extending axially, the outer diameter of the throttling tube is equal to the inner diameter of the stepped platform, the inlet end of the throttling tube extends into the diverter, a plurality of purge holes are formed on the side wall of the throttling tube near the inlet end, an intake gap is formed between the outer wall of the throttling tube and the inner wall of the diverter, and the purge holes are located in the diverter and communicate with the intake gap.

[0022] According to a first aspect of the present invention, a plurality of purge holes are provided, the opening direction of the purge holes is tangent to the cross-sectional circle of the throttling tube, and the plurality of purge holes are evenly spaced along the circumference of the throttling tube.

[0023] Secondly, the present invention also provides a turbojet engine including the aforementioned combustion chamber structure. Attached Figure Description

[0024] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0025] Figure 1 This is a half-sectional schematic diagram of a combustion chamber structure provided in the first aspect embodiment of the present invention;

[0026] Figure 2 This is a cross-sectional schematic diagram of the built-in main pipe provided in the first aspect embodiment of the present invention;

[0027] Figure 3 This is a cross-sectional schematic diagram of the nozzle component provided in the first aspect embodiment of the present invention;

[0028] Figure 4 for Figure 3 A partial schematic diagram of point A in the diagram.

[0029] Explanation of reference numerals in the attached figures:

[0030] 1. Casing; 2. Flame tube; 3. Hydrogen nozzle; 31. Internal main pipe; 32. Nozzle fittings; 311. Hydrogen supply pipe; 312. Ring pipe; 313. Branch pipe; 321. Sealing pipe; 322. Transition pipe; 323. Diverter pipe; 324. Throttling pipe; 3231. Stage; 3232. Inlet slot; 3241. Purge port; 4. Airflow channel. Detailed Implementation

[0031] 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.

[0032] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0033] 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. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0034] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0035] Reference Figure 1 As shown, the present invention provides a combustion chamber structure, including: a casing 1, a flame tube 2, and a hydrogen nozzle 3; the flame tube 2 is disposed inside the casing 1, and an airflow channel 4 is formed between the outer wall of the flame tube 2 and the inner wall of the casing 1; the hydrogen nozzle 3 includes an internal main pipe 31 and a nozzle component 32 disposed in connection with each other, the internal main pipe 31 is located inside the airflow channel 4, one end of the nozzle component 32 is connected to the internal main pipe 31, and the other end passes through the side wall of the flame tube 2 to extend into the interior of the flame tube 2.

[0036] Specifically, the combustion chamber structure includes a casing 1, a flame tube 2, and a hydrogen nozzle 3. The flame tube 2 is located inside the casing 1, with its outer wall forming an airflow channel 4 between it and the inner wall of the casing 1. This channel cools the outer surface of the flame tube 2 and provides the necessary air for the combustion process. The hydrogen nozzle 3 consists of an internal main pipe 31 and a nozzle assembly 32. The internal main pipe 31 is located within the airflow channel 4 and is connected to an external hydrogen supply pipe 311 to achieve efficient hydrogen delivery. One end of the nozzle assembly 32 is connected to the internal main pipe 31, and the other end passes through the side wall of the flame tube 2 and extends into the interior of the flame tube 2, ensuring that hydrogen is accurately injected into the combustion zone. This design significantly optimizes combustion efficiency while greatly simplifying the combustion chamber structure.

[0037] By placing the flame tube 2 inside the casing 1 and forming an airflow channel 4 between the outer wall of the flame tube 2 and the inner wall of the casing 1, and using a hydrogen nozzle 3 built into the airflow channel 4 (the hydrogen nozzle 3 includes a connected internal main pipe 31 and nozzle component 32), the gas supply and injection devices are integrated, achieving efficient control of hydrogen injection and reducing system complexity. The nozzle component 32 directly penetrates the side wall of the flame tube 2 and extends into the interior of the flame tube 2, contributing to uniform combustion. This combustion chamber has a simple structure, compact size, and low manufacturing cost. Furthermore, this combustion chamber structure is easy to manufacture and assemble, effectively improving the industrial production efficiency and economic benefits of the product.

[0038] Reference Figure 2 As shown, in a first aspect embodiment of the present invention, the built-in main pipe 31 includes: a hydrogen supply pipe 311, a ring pipe 312, and a branch pipe 313; one end of the hydrogen supply pipe 311 passes through the casing 1 to extend to communicate with an external pipeline; the ring pipe 312 is disposed at the other end of the hydrogen supply pipe 311 and communicates with the hydrogen supply pipe 311, and a plurality of first through holes are provided on the side wall of the ring pipe 312; one end of the branch pipe 313 passes through the first through hole to extend into the ring pipe 312 and communicates with the ring pipe 312, and the other end of the branch pipe 313 communicates with the nozzle component 32.

[0039] Specifically, the built-in main pipe 31 includes a hydrogen supply pipe 311, a ring pipe 312, and several branch pipes 313. One end of the hydrogen supply pipe 311 is connected to an external pipeline, and the other end is connected to the ring pipe 312. The side wall of the ring pipe 312 has several evenly distributed first through holes. One end of each branch pipe 313 passes through a first through hole and is connected to the ring pipe 312, while the other end is connected to the nozzle component 32. This arrangement effectively improves the uniformity of hydrogen distribution and reduces the complexity of the hydrogen supply system.

[0040] In a first aspect of the invention, the other end of the branch pipe 313 is bent toward the inner diameter side to form a hook-shaped arrangement.

[0041] Specifically, branch pipe 313 is made of small-diameter hollow pipe bent into a hook shape, with one end welded to ring pipe 312.

[0042] In a first aspect of the present invention, along the axial direction of the flame tube 2, the nozzle 32 is obliquely inserted through the side wall of the flame tube 2 to extend obliquely into the interior of the flame tube 2.

[0043] Specifically, along the axial direction of the flame tube 2, the nozzle component 32 is inclinedly inserted through the side wall of the flame tube 2 and extends into its interior. This inclined arrangement enhances the mixing effect of hydrogen and air, thereby improving combustion efficiency. At the same time, this design helps reduce the heat loss of the nozzle component 32 and extends its service life.

[0044] Reference Figure 3 As shown, in a first aspect embodiment of the present invention, the nozzle component 32 includes a sealing pipe 321, a transition pipe 322, a diverter pipe 323, and a throttling pipe 324 connected in sequence; one end of the sealing pipe 321 is connected to the other end of the branch pipe 313, the sealing pipe 321 is bent into a bull's horn-shaped structure, and part of the sealing pipe 321 extends into the flame tube 2; one end of the transition pipe 322 is connected to the other end of the sealing pipe 321, the other end of the transition pipe 322 is connected to one end of the diverter pipe 323, the other end of the diverter pipe 323 is connected to one end of the throttling pipe 324, and the throttling pipe 324 is connected to the flame tube 2; the transition pipe 322, the diverter pipe 323, and the throttling pipe 324 are all located inside the flame tube 2.

[0045] Specifically, the nozzle assembly 32 is constructed from multiple welded pipe sections, reducing costs. The nozzle assembly 32 includes a sealing pipe 321, a transition pipe 322, a diverter pipe 323, and a throttling pipe 324, which are connected sequentially. The sealing pipe 321 is curved into a bull's horn shape and partially extends into the flame tube 2. The transition pipe 322, diverter pipe 323, and throttling pipe 324 are all straight pipes located inside the flame tube 2. The bull's horn-shaped structure of the sealing pipe 321 reduces turbulence in the hydrogen flow during injection, while simultaneously improving combustion stability.

[0046] In a first aspect embodiment of the present invention, the inlet ends of the sealing pipe 321, the transition pipe 322, the diverter pipe 323 and the throttling pipe 324 are all provided with a chamfer angle of 10° to 45° along the hydrogen flow direction.

[0047] Specifically, the chamfered angle design creates an airflow guide surface at the inlet ends of the sealing pipe 321, transition pipe 322, diverter pipe 323, and throttling pipe 324, facilitating airflow and preventing obstruction at the connection points.

[0048] In a first aspect embodiment of the present invention, the transition pipe 322, the diversion pipe 323 and the throttling pipe 324 are all straight pipes, the outer diameter of the transition pipe 322 is equal to the inner diameter of the sealing pipe 321, and the inner diameter of the diversion pipe 323 is equal to the inner diameter of the transition pipe 322.

[0049] In a first aspect embodiment of the present invention, along the hydrogen flow direction, the outlet end of the diverter 323 has a stepped stage 3231 extending axially, the outer diameter of the throttling tube 324 is equal to the inner diameter of the stepped stage 3231, the inlet end of the throttling tube 324 extends into the diverter 323, a plurality of purge holes 3241 are provided on the side wall of the throttling tube 324 near the inlet end, an intake gap 3232 is formed between the outer wall of the throttling tube 324 and the inner wall of the diverter 323, and the purge holes 3241 are located in the diverter 323 and communicate with the intake gap 3232.

[0050] In a first aspect embodiment of the present invention, a plurality of purge holes 3241 are provided, the opening direction of the purge holes 3241 is tangent to the cross-sectional circle of the throttling tube 324, and the plurality of purge holes 3241 are evenly spaced along the circumference of the throttling tube 324.

[0051] Reference Figure 4 As shown, specifically, along the hydrogen flow direction, the outlet end of the splitter pipe 323 has an axially extending stepped section 3231, and the inlet end of the throttling pipe 324 extends into the splitter pipe 323. Several purge holes 3241 are formed on the side wall of the throttling pipe 324 near the inlet end, and the direction of the purge holes 3241 is tangent to the axial section of the throttling pipe 324. The purge holes 3241 are evenly distributed around the circumference of the throttling pipe 324, forming an intake gap 3232 between the purge holes and the inner wall of the splitter pipe 323. This gap is used to introduce a small amount of cooling air to form a gas film protection, significantly reducing the heat loss of the nozzle component 32 and enhancing its durability.

[0052] In a first aspect embodiment of the present invention, the working principle is as follows:

[0053] Hydrogen gas enters the ring pipe 312 along the hydrogen supply pipe 311, and then flows to each branch pipe 313. It is then injected into the sealing pipe 321 from the outlet of the branch pipe 313. The depth to which the branch pipe 313 is inserted into the sealing pipe 321 is no less than 5 times its inner diameter, and the inner diameter of the sealing pipe 321 is 2 to 6 times the outer diameter of the branch pipe 313. The outer side of the sealing pipe 321 is the airflow channel 4 between the flame tube 2 and the casing 1. The pressure in the airflow channel 4 is greater than the pressure in the sealing pipe 321. By adjusting the area ratio of the inner diameter of the sealing pipe 321 to the outer diameter of the branch pipe 313, and the depth to which the branch pipe 313 is inserted into the sealing pipe 321, the hydrogen gas can be sealed inside the sealing pipe 321 by the air pressure in the airflow channel 4, preventing leakage into the two channels and thus simplifying the connection structure.

[0054] Air and hydrogen enter the transition pipe 322 along the sealing pipe 321, flowing towards the splitter pipe 323 and the throttling pipe 324. Inside the splitter pipe 323, the airflow adheres to the pipe wall, while the hydrogen flow is mainly concentrated at the center. A thin layer of air adhering to the pipe wall is the boundary layer flow, which has a low velocity and is prone to flashback. To reduce the risk of boundary layer flashback, a step and an air inlet are installed inside the splitter pipe 323. The low-velocity boundary layer flow enters the air inlet gap 3232, while the high-velocity center flow enters the throttling pipe 324. After entering the air inlet gap 3232, the low-velocity boundary layer flow enters the throttling pipe 324 along the purge hole 3241, tangentially penetrating the inner wall of the throttling pipe 324. This creates a circumferential swirling flow along the inner wall, breaking the boundary layer on the inner wall of the throttling pipe and preventing the flame in the flame tube 2 from flashing upstream along the boundary layer.

[0055] Secondly, the present invention also provides a turbojet engine, including a combustion chamber structure.

[0056] Specifically, a turbojet engine was constructed based on the combustion chamber structure. This turbojet engine significantly improves fuel combustion efficiency while reducing overall manufacturing and maintenance costs by optimizing the combustion chamber structure and hydrogen distribution method.

[0057] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A combustion chamber structure, characterized in that, include: Casing (1); A flame tube (2) is disposed inside the casing (1), and an airflow channel (4) is formed between the outer wall of the flame tube (2) and the inner wall of the casing (1). The hydrogen nozzle (3) includes an internal main pipe (31) and a nozzle component (32) connected to each other. The internal main pipe (31) is located in the airflow channel (4). One end of the nozzle component (32) is connected to the internal main pipe (31), and the other end passes through the side wall of the flame tube (2) to extend into the interior of the flame tube (2). The nozzle component (32) includes a sealing pipe (321), a transition pipe (322), a diverter pipe (323), and a throttling pipe (324) connected in sequence. One end of the sealing pipe (321) is connected to the other end of the built-in main pipe (31). The sealing pipe (321) is bent into a bull horn-shaped structure. The sealing pipe (321) extends into the flame tube (2). One end of the transition pipe (322) is connected to the other end of the sealing pipe (321), the other end of the transition pipe (322) is connected to one end of the diverter pipe (323), the other end of the diverter pipe (323) is connected to one end of the throttling pipe (324), and the throttling pipe (324) is connected to the flame tube (2). The transition tube (322), the diversion tube (323), and the throttling tube (324) are all located inside the flame tube (2).

2. The combustion chamber structure according to claim 1, characterized in that, The built-in manifold (31) includes: Hydrogen supply pipe (311), one end of which passes through the casing (1) to extend to communicate with an external pipeline; A ring pipe (312) is located at the other end of the hydrogen supply pipe (311) and is connected to the hydrogen supply pipe (311). The side wall of the ring pipe (312) is provided with a plurality of first through holes. Branch pipe (313), one end of which passes through the first through hole to extend into the ring pipe (312) and communicates with the ring pipe (312), and the other end of which communicates with the nozzle component (32).

3. The combustion chamber structure according to claim 2, characterized in that, The other end of the branch pipe (313) is bent toward the inner diameter side to form a hook-shaped arrangement.

4. The combustion chamber structure according to claim 2, characterized in that, Along the axial direction of the flame tube (2), the nozzle (32) is obliquely inserted through the side wall of the flame tube (2) to extend obliquely into the interior of the flame tube (2).

5. The combustion chamber structure according to claim 1, characterized in that, Along the hydrogen flow direction, the inlet ends of the sealing pipe (321), the transition pipe (322), the diverting pipe (323), and the throttling pipe (324) are all provided with a chamfer angle of 10°~45°.

6. The combustion chamber structure according to claim 1, characterized in that, The transition pipe (322), the diverter pipe (323), and the throttling pipe (324) are all straight pipes. The outer diameter of the transition pipe (322) is equal to the inner diameter of the sealing pipe (321), and the inner diameter of the diverter pipe (323) is equal to the inner diameter of the transition pipe (322).

7. The combustion chamber structure according to any one of claims 1-6, characterized in that, Along the hydrogen flow direction, the outlet end of the diverter (323) has a stepped platform (3231) extending axially. The outer diameter of the throttling pipe (324) is equal to the inner diameter of the stepped platform (3231). The inlet end of the throttling pipe (324) extends into the diverter (323). Several purge holes (3241) are provided on the side wall of the throttling pipe (324) near the inlet end. An air intake gap (3232) is formed between the outer wall of the throttling pipe (324) and the inner wall of the diverter (323). The purge holes (3241) are located in the diverter (323) and communicate with the air intake gap (3232).

8. The combustion chamber structure according to claim 7, characterized in that, The purge holes (3241) are provided in multiple ways. The opening direction of the purge holes (3241) is tangent to the cross-sectional circle of the throttling tube (324). The multiple purge holes (3241) are evenly spaced along the circumference of the throttling tube (324).

9. A turbojet engine, characterized in that, Includes the combustion chamber structure as described in any one of claims 1-8.

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