A high-temperature resistant fuel nozzle for aircraft engines

Abstract

This utility model discloses a high-temperature resistant fuel nozzle for aero-engines, relating to the field of fuel nozzle technology. It includes a mounting ring and an air guide assembly. The top of the air guide assembly is fixedly connected to the bottom of the mounting ring, and a cooling assembly is fixedly connected to the inner wall of the air guide assembly. The cooling assembly includes an inner air tube, and a honeycomb plate is fixedly connected to the inner wall of the inner air tube. The fuel nozzle is fixed to the outer wall of the inner air tube by a spiral ring, guiding the cooling airflow to form a spiral flow, increasing the contact area and turbulence intensity between the airflow and the inner air tube, improving heat exchange efficiency, reducing the fuel passage temperature, and preventing fuel vaporization at high temperatures from affecting injection performance. The honeycomb plate is arranged in a ring array on the inner wall of the inner air tube, dividing the cooling airflow into multiple fine streams that evenly cover the inner wall of the inner air tube, avoiding localized overheating. This fuel nozzle achieves the purpose of a high-temperature resistant fuel nozzle for aero-engines.

Description

Technical Field

[0001] This utility model relates to the field of fuel nozzle technology, specifically a high-temperature resistant fuel nozzle for aircraft engines. Background Technology

[0002] During service, aircraft engine fuel nozzles must withstand the scouring of high-temperature combustion gases (temperatures can reach over 1200℃) in the combustion chamber for extended periods. Their high-temperature resistance directly affects engine combustion efficiency and operational safety. Existing fuel nozzles face the following main technical challenges under high-temperature conditions:

[0003] Traditional nozzle cooling structures often employ a single-channel airflow design, with the cooling airflow flowing in a straight line. This results in a limited heat exchange area with the nozzle wall and the formation of dead airflow zones in certain areas, leading to uneven temperature distribution on the outer wall (temperature differences can reach 80-120℃). High-temperature areas are prone to material oxidation and ablation. Utility Model Content

[0004] (a) Technical problems to be solved

[0005] To address the shortcomings of existing technologies, this utility model provides a high-temperature resistant fuel nozzle for aero engines, which solves the problem that traditional nozzle cooling structures, which often employ a single-channel airflow design, are prone to creating localized airflow dead zones.

[0006] (II) Technical Solution

[0007] To achieve the above objectives, this utility model provides the following technical solution: a high-temperature resistant fuel nozzle for an aero-engine, comprising: an mounting ring, and further comprising: an air guiding assembly, the top of which is fixedly connected to the bottom of the mounting ring, and a cooling assembly fixedly connected to the inner wall of the air guiding assembly; the cooling assembly comprises an inner air pipe, the inner wall of which is fixedly connected to a honeycomb plate, the honeycomb plate being arranged in a circular array along the central axis of the inner air pipe, the outer wall of which is fixedly connected to a spiral ring, the top of which is fixedly connected to an air inlet pipe, and the inner wall of which is fixedly connected to an air-stopping shell via an air-stopping blowpipe, the top of which is fixedly connected to the inner wall of the air-stopping shell, the air-stopping blowpipe being arranged in a circular array along the central axis of the air-stopping shell, and the outer wall of which is fixedly connected to the inner wall of the inner air pipe.

[0008] Preferably, the air guiding assembly includes an inner tube, an outer tube is fixedly connected to the outer wall of the inner tube, and the top of the inner tube is fixedly connected to the bottom of the mounting ring.

[0009] Preferably, the outer tube has an air outlet groove in its wall, and the air outlet groove is arranged in a circular array along the central axis of the outer tube. The inner tube has an air guide groove in its wall, which is used to guide the fuel, and the air guide groove is arranged in a circular array along the central axis of the inner tube.

[0010] Preferably, the inner wall of the inner tube is fixedly connected to the outer wall of the spiral ring, the inner wall of the inner tube is fixedly connected to the outer wall of the cut-off blowpipe, and the inner wall of the inner tube is fixedly connected to the outer wall of the air inlet pipe.

[0011] (III) Beneficial Effects

[0012] This invention provides a high-temperature resistant fuel nozzle for aircraft engines. It has the following advantages:

[0013] (I) This high-temperature resistant fuel nozzle for aero-engines is fixed to the outer wall of the inner air tube by a spiral ring, which guides the cooling airflow to form a spiral flow, increases the contact area and turbulence intensity between the airflow and the inner air tube, improves heat exchange efficiency, reduces the temperature of the fuel passage, and prevents the fuel from affecting the injection performance due to high-temperature vaporization. The honeycomb plate annular array is arranged on the inner wall of the inner air tube, which divides the cooling airflow into multiple fine streams, evenly covering the inner wall of the inner air tube, avoiding local overheating, ensuring the temperature consistency inside the inner air tube, and extending the service life of the nozzle's internal components. The gas interception structure composed of the gas interception shell and the gas interception blowpipe directionally delivers the cooling airflow to the interlayer between the inner and outer tubes, providing secondary cooling to the high-temperature sensitive area, alleviating the deformation caused by thermal shock, and improving the nozzle's resistance to thermal fatigue.

[0014] (II) The high-temperature fuel nozzle for aero-engines, by setting up an interlayer channel formed by an inner tube and an outer tube, combined with an annular array of air guide grooves and air outlet grooves, allows the cooling airflow to uniformly cover the outer wall of the nozzle in a spiral shape, blocking the high-temperature gas from burning the nozzle body and improving the thermal protection capability. The air guide grooves guide the cooling airflow into the interlayer, and the air outlet grooves uniformly release the airflow to form a cooling layer. The combination of the two makes the temperature distribution of the outer wall more uniform, avoids material fatigue caused by local overheating, and enhances the structural stability of the nozzle under high-temperature conditions. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0016] Figure 2 This is a cross-sectional view of the present invention;

[0017] Figure 3 This is a schematic diagram of the air guiding component of this utility model;

[0018] Figure 4 This is a schematic diagram of the cooling component of this utility model.

[0019] In the diagram: 1. Mounting ring; 2. Air guide assembly; 3. Cooling assembly; 21. Inner tube; 22. Air guide groove; 23. Outer tube; 24. Air outlet groove; 31. Air inlet pipe; 32. Air cut-off shell; 34. Air cut-off blowpipe; 35. Spiral ring; 36. Inner air pipe; 37. Honeycomb panel. Detailed Implementation

[0020] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0021] Please see Figure 1-4 This utility model provides a technical solution: a high-temperature resistant fuel nozzle for an aero-engine, comprising: a mounting ring 1, and an air guide assembly 2, the top of which is fixedly connected to the bottom of the mounting ring 1, and a cooling assembly 3 fixedly connected to the inner wall of the air guide assembly 2; the cooling assembly 3 includes an inner air pipe 36, the inner wall of which is fixedly connected to a honeycomb plate 37, and the honeycomb plate 37 is arranged in a ring array along the central axis of the inner air pipe 36; a spiral ring 35 is fixedly connected to the outer wall of the inner air pipe 36. An intake pipe 31 is fixedly connected to the top of the pipe 36. An air-stopping shell 32 is fixedly connected to the inner wall of the inner pipe 36 through an air-stopping blow pipe 34. The top of the air-stopping blow pipe 34 is fixedly connected to the inner wall of the air-stopping shell 32, and the outer wall of the air-stopping blow pipe 34 is fixedly connected to the inner wall of the inner pipe 36. When fuel flows through the spiral ring 35, it is guided to form a spiral fuel. This spiral airflow has a larger contact area and a longer flow path, which can more effectively exchange heat with the outer wall of the inner pipe 36 and improve cooling efficiency.

[0022] The air guiding assembly 2 includes an inner tube 21, an outer tube 23 is fixedly connected to the outer wall of the inner tube 21, the top of the inner tube 21 is fixedly connected to the bottom of the mounting ring 1, and an air outlet groove 24 is opened in the wall of the outer tube 23, and the air outlet groove 24 is arranged in a ring array along the central axis of the outer tube 23.

[0023] The inner tube 21 has air guide grooves 22 in its wall, and the air guide grooves 22 are arranged in a ring array along the central axis of the inner tube 21. The inner wall of the inner tube 21 is fixedly connected to the outer wall of the spiral ring 35, the inner wall of the inner tube 21 is fixedly connected to the outer wall of the cut-off blowpipe 34, and the inner wall of the inner tube 21 is fixedly connected to the outer wall of the intake pipe 31. When fuel enters the air guide assembly 2 from the direction of the mounting ring 1, it will pass through these air guide grooves 22 and use the air guide grooves 22 to guide the injected fuel, thereby forcing the fuel to be injected in a spiral shape.

[0024] During the operation of aero engines, fuel nozzles need to face extremely harsh high-temperature environments. Their high-temperature resistance is directly related to the stability and safety of aero engines. In order to meet the reliable operation requirements of aero engines under high-temperature conditions, the high-temperature resistant fuel nozzle for aero engines introduced in this article achieves efficient cooling and heat dissipation and stable fuel injection through the coordinated work of various components, thereby improving the high-temperature resistance of the nozzle.

[0025] The overall structure of the fuel nozzle is based on the mounting ring 1, with the air guide assembly 2 and cooling assembly 3 arranged in an orderly manner, forming a system that integrates fuel injection and cooling. The mounting ring 1 is used to fix the nozzle in the corresponding position of the aero-engine, while the air guide assembly 2 and cooling assembly 3 are the core parts for achieving high temperature resistance. The two work together to complete key functions such as airflow guidance, cooling, and fuel injection.

[0026] The air guiding assembly 2 is mainly composed of an inner tube 21, an outer tube 23, an air guiding groove 22, and an air outlet groove 24. Its function is to guide the cooling airflow and provide cooling protection for the nozzle. The inner tube 21 and the outer tube 23 form a double-layer pipe structure, which provides a channel for the flow of cooling airflow.

[0027] The inner tube 21 has air guide grooves 22 arranged in a ring along its central axis. When fuel enters the air guide assembly 2 from the direction of the mounting ring 1, it will pass through these air guide grooves 22 and the air guide grooves 22 will guide the injected fuel, thereby forcing the fuel to be injected in a spiral shape.

[0028] The outer tube 23 has air outlet grooves 24 arranged in a ring along its central axis in the wall. The cooling airflow in the interlayer flows out through these air outlet grooves 24. The ring array design of the air outlet grooves 24 allows the cooling airflow to wrap around the outer wall of the nozzle in all directions, carrying away the heat generated by the nozzle during operation, reducing the temperature of the outer wall of the nozzle, and thus protecting the nozzle from high temperature damage.

[0029] The inner tube 21 is fixedly connected to the mounting ring 1, ensuring a stable connection between the air guide assembly 2 and the entire engine system. It also ensures the stability of the cooling airflow input path. The cooperation between the outer tube 23 and the inner tube 21 forms a complete air guide channel, allowing the cooling airflow to flow smoothly and achieve efficient cooling.

[0030] The cooling assembly 3 is a key component for achieving the high-temperature resistance of the nozzle. It consists of an inner air pipe 36, a honeycomb plate 37, a spiral ring 35, an air inlet pipe 31, a cut-off blowpipe 34, and a cut-off shell 32, and is mainly used to cool the inside of the nozzle.

[0031] The intake pipe 31 is connected to an external cooling air source. The cooling airflow enters the inner air pipe 36 through the intake pipe 31. The inner air pipe 36 is the main channel for the cooling airflow to flow inside the cooling assembly 3. The spiral ring 35 is fixed on the outer wall of the inner air pipe 36. When fuel flows through the spiral ring 35, it is guided to form a spiral fuel flow. This spiral airflow has a larger contact area and a longer flow path, which can more effectively exchange heat with the outer wall of the inner air pipe 36 and improve the cooling efficiency.

[0032] The honeycomb panels 37 are arranged in a ring array on the inner wall of the inner air pipe 36 along the central axis of the inner air pipe 36. The design of the honeycomb panels 37 increases the contact area between the cooling airflow and the inner wall of the inner air pipe 36, and also plays a role in the uniform distribution of the airflow, so that the cooling airflow can cool the inside of the inner air pipe 36 more evenly, ensuring the uniformity of the internal temperature of the inner air pipe 36 and avoiding the occurrence of local overheating.

[0033] The gas-blocking shell 32 is fixedly connected to the inner wall of the inner air pipe 36 through the gas-blocking blowpipe 34. The combination of the gas-blocking shell 32 and the gas-blocking blowpipe 34 forms a gas-blocking structure. When the cooling airflow flows through the gas-blocking shell 32, part of the airflow will be guided to the space between the inner pipe 21 and the outer pipe 23 through the gas-blocking blowpipe 34 to perform targeted cooling on the inner pipe 21 and the outer pipe 23, thereby further improving the cooling effect.

[0034] The cooling assembly 3 achieves efficient cooling of the nozzle interior through the synergistic effect of components such as the spiral ring 35, honeycomb plate 37, air cut-off blowpipe 34, and air cut-off shell 32. This reduces the temperature inside the nozzle, ensures stable fuel flow and injection inside the nozzle, and protects the internal components of the nozzle from high temperatures.

[0035] During the operation of the fuel nozzle, fuel enters the air guide assembly 2 and the cooling assembly 3 through the mounting ring 1. At the same time, the cooling airflow also enters the corresponding channels through the air guide assembly 2 and the cooling assembly 3. The two work together to achieve stable fuel injection and effective cooling of the nozzle.

[0036] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0037] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A high-temperature resistant fuel nozzle for an aircraft engine, comprising: The mounting ring (1) is characterized in that it further includes: an air guiding component (2), the top of which is fixedly connected to the bottom of the mounting ring (1), and a cooling component (3) is fixedly connected to the inner wall of the air guiding component (2). The cooling assembly (3) includes an inner air pipe (36), the inner wall of which is fixedly connected to a honeycomb plate (37), and the honeycomb plate (37) is arranged in a ring array along the central axis of the inner air pipe (36). The outer wall of the inner air pipe (36) is fixedly connected to a spiral ring (35), the top of which is fixedly connected to an air inlet pipe (31), and the inner wall of the inner air pipe (36) is fixedly connected to an air-blocking shell (32) through an air-blocking blowpipe (34), and the top of the air-blocking blowpipe (34) is fixedly connected to the inner wall of the air-blocking shell (32).

2. The high-temperature resistant fuel nozzle for an aircraft engine according to claim 1, characterized in that: The outer wall of the cut-off blowpipe (34) is fixedly connected to the inner wall of the inner air pipe (36).

3. The high-temperature resistant fuel nozzle for an aircraft engine according to claim 1, characterized in that: The air guiding assembly (2) includes an inner tube (21), an outer tube (23) is fixedly connected to the outer wall of the inner tube (21), and the top of the inner tube (21) is fixedly connected to the bottom of the mounting ring (1).

4. The high-temperature resistant fuel nozzle for an aircraft engine according to claim 3, characterized in that: The outer tube (23) has an air outlet groove (24) in its wall, and the air outlet groove (24) is arranged in a ring array along the central axis of the outer tube (23).

5. A high-temperature resistant fuel nozzle for an aircraft engine according to claim 3, characterized in that: The inner tube (21) has an air guide groove (22) in its wall, and the air guide groove (22) is arranged in a ring array along the central axis of the inner tube (21).

6. A high-temperature resistant fuel nozzle for an aircraft engine according to claim 3, characterized in that: The inner wall of the inner tube (21) is fixedly connected to the outer wall of the spiral ring (35), the inner wall of the inner tube (21) is fixedly connected to the outer wall of the cut-off blowpipe (34), and the inner wall of the inner tube (21) is fixedly connected to the outer wall of the air inlet pipe (31).

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