A main combustion chamber nozzle for an aeroengine

Abstract

The application relates to the technical field of aero-engines and discloses a main combustion chamber nozzle for an aero-engine, which can realize detachable installation and fixation of a fuel injection hole-equipped fuel injection shaft and a nozzle fixing base, avoids the problem that an extrusion deformation is easily caused in the assembly process of a sealing ball head of a conventional fuel nozzle fixing base, flow exceeds the standard, the risk of overall scrapping of a fuel manifold assembly is reduced, and the reliability of the fuel nozzle is improved; and the fuel injection hole on the detachable fuel injection shaft can control the flow characteristics of the nozzle, fuel flow uniformity efficient disassembly and assembly and debugging on the fuel manifold assembly can be realized, and the use and maintenance are facilitated.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology and discloses a main combustion chamber nozzle for aero-engines. Background Technology

[0002] Currently, the fuel manifold and fuel nozzles in the main combustion chamber of aero engines are generally separate structures, connected by ball-cone fitting or welding to form a fuel manifold with nozzles. This type of fuel manifold with nozzles has a complex structure, large size, heavy weight, complicated flow rate adjustment, and high operating and maintenance costs.

[0003] Furthermore, aero engines have high requirements for the flow uniformity of fuel nozzles in the main combustion chamber, and need to meet optimal combustion chamber outlet temperature distribution. Therefore, fuel nozzles need to be repeatedly disassembled and reassembled to meet uniformity requirements. Conventional nozzle assemblies have many disassembled parts, complex disassembly and assembly processes, and high debugging costs. Summary of the Invention

[0004] The purpose of this invention is to provide a main combustion chamber nozzle for aircraft engines, which can reduce the risk of the entire fuel manifold assembly being scrapped, improve the reliability of the fuel nozzle, enable efficient disassembly and assembly and debugging of fuel flow uniformity on the fuel manifold assembly, and facilitate use and maintenance.

[0005] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows:

[0006] A main combustion chamber nozzle for an aircraft engine, comprising:

[0007] A nozzle holder, wherein the holder is provided with a mounting hole and a flow passage hole, and the flow passage hole communicates with the mounting hole;

[0008] The injection shaft is fixed in the mounting hole by a threaded section. The injection shaft has fuel injection holes along the axial direction and an oil passage hole that connects the mounting hole and the fuel injection holes. A sealing ring and a sealing retainer are also provided between the outer wall of the injection shaft and the inner wall of the mounting hole. The sealing ring and the sealing retainer are located on both sides of the threaded section, and the sealing ring is installed on the outer wall of the injection shaft near the flow hole.

[0009] A necking section is located on the outer wall of the injection shaft between the flow hole and the threaded section.

[0010] The oil inlet is located on the nozzle mounting base, and the oil outlet end of the oil inlet is located on the inner wall of the mounting hole corresponding to the necked section.

[0011] Furthermore, the outer wall of the necked section of the injection shaft is provided with an annular boss, which is located between the oil passage hole and the oil outlet end of the oil inlet. The annular boss divides the cavity between the necked section and the mounting hole into a first cavity and a second cavity. The first cavity is connected to the fuel injection hole through the oil passage hole, and the second cavity is connected to the oil outlet end of the oil inlet through the gap between the annular boss and the oil outlet end of the oil inlet.

[0012] Furthermore, the number of oil passage holes on the injection shaft is 2 to 3, and the oil passage holes are evenly distributed along the circumference of the injection shaft.

[0013] Furthermore, the diameter of the oil passage hole is Φ0.4~Φ0.6mm, the corresponding fuel injection hole diameter range is Φ0.3~Φ0.5mm, the flow passage hole diameter range is Φ0.8~Φ1.0mm, and the gap between the annular boss and the mounting hole ranges from 0.1 to 0.2mm.

[0014] Furthermore, it also includes a plug, wherein the injection shaft has a machining hole along the axial direction, the machining hole is connected to the fuel injection hole, the plug is fixed in the machining hole and used to seal the machining hole; the oil passage hole is located on the side wall of the injection shaft between the plug and the fuel injection hole.

[0015] Furthermore, a locking plate is installed on the nozzle holder, the locking plate is installed at the end of the nozzle holder away from the flow hole, the locking plate is in contact with the spray shaft, and the nozzle holder is provided with a punch locking hole that cooperates with the locking plate to limit the spray shaft within the mounting hole.

[0016] Furthermore, the nozzle holder is also provided with an oil collecting chamber that communicates with the oil inlet, and the oil collecting chamber is used to connect the oil inlet pipeline.

[0017] Compared with the prior art, the beneficial effects of this invention are as follows: This invention enables the detachable installation and fixation of the injection shaft with fuel injection holes and the nozzle mounting seat, avoiding the problem of excessive flow caused by extrusion deformation during the assembly process of conventional fuel nozzle mounting seats using sealed ball heads. This reduces the risk of the entire fuel manifold assembly being scrapped and improves the reliability of the fuel nozzle. Moreover, by controlling the nozzle flow characteristics through the fuel injection holes on the detachable injection shaft, efficient disassembly and adjustment of fuel flow uniformity can be achieved on the fuel manifold assembly, which is also convenient for use and maintenance. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the main combustion chamber nozzle structure for an aero-engine in the embodiment;

[0019] Figure 2 A schematic diagram of the installation structure of the main combustion chamber nozzle on the fuel inlet pipe;

[0020] The components include: 1. Nozzle holder; 101. First chamber; 102. Second chamber; 103. Flow hole; 104. Punch point locking hole; 105. Sealing ball head; 2. Injection shaft; 201. Fuel injection hole; 202. Oil passage hole; 203. Neck section; 204. Annular boss; 3. Sealing ring; 4. Sealing retainer ring; 5. Oil inlet; 6. Plug; 7. Locking plate; 8. Oil collection chamber; 9. Oil inlet pipeline. Detailed Implementation

[0021] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0022] Example

[0023] See Figure 1 and Figure 2 A main combustion chamber nozzle for an aircraft engine, comprising:

[0024] Nozzle holder 1, the holder is provided with a mounting hole and a flow passage 103, the flow passage 103 is connected to the mounting hole;

[0025] The injection shaft 2 is fixed in the mounting hole by a threaded section. The injection shaft 2 has a fuel injection hole 201 along the axial direction and an oil passage hole 202 that connects the mounting hole and the fuel injection hole 201. A sealing ring 3 and a sealing retainer 4 are also provided between the outer wall of the injection shaft 2 and the inner wall of the mounting hole. The sealing ring 3 and the sealing retainer 4 are located on both sides of the threaded section, and the sealing ring 3 is installed on the outer wall of the injection shaft 2 near the flow hole 103.

[0026] The necking section 203 is located on the outer wall of the jet shaft 2 between the flow hole 103 and the threaded section.

[0027] Oil inlet 5 is provided on nozzle fixing seat 1, and the oil outlet end of oil inlet 5 is located on the inner wall of the mounting hole corresponding to the necked section 203.

[0028] In this embodiment, by moving the fuel nozzle orifice 201 from the nozzle mounting seat 1 to the injection shaft 2, and fixing the injection shaft 2 to the mounting hole via a threaded section, the injection shaft 2 with the fuel nozzle orifice 201 is detachably installed and fixed to the nozzle mounting seat 1. This avoids the problem of flow deviation caused by extrusion deformation during the assembly process of the conventional fuel nozzle mounting seat 1 using the sealing ball head 105, reduces the risk of the entire fuel manifold assembly being scrapped, and improves the reliability of the fuel nozzle. Moreover, by using the fuel nozzle orifice 201 on the detachable injection shaft 2 as a throttling orifice to control the nozzle flow characteristics, efficient disassembly, replacement, and adjustment of fuel flow uniformity can be achieved on the fuel manifold assembly. This also facilitates use and maintenance, enabling the fuel manifold with the main combustion chamber nozzle to meet the low-cost and high-reliability requirements of small aero engines, improving the flow adjustment process and efficiency, and solving the problems of complex disassembly and assembly and poor economy of conventional nozzle assemblies.

[0029] In this embodiment, an annular boss 204 is provided on the outer wall of the constricted section 203 of the injection shaft 2. The annular boss 204 is located between the oil passage 202 and the oil outlet end of the oil inlet 5. The annular boss 204 divides the cavity between the constricted section 203 and the mounting hole into a first chamber 101 and a second chamber 102. The first chamber 101 is connected to the fuel injection hole 201 through the oil passage 202, and the second chamber 102 is connected to the oil outlet end of the oil inlet 5 through the gap between the annular boss 204 and the oil outlet end. This can play a role in adjusting the pressure balance of the first chamber 101 and the second chamber 102, making the fuel volume of the fuel injection hole 201 more uniform. In addition, the gap between the annular boss 204 and the oil outlet end of the oil inlet 5 can be made by using a small gap fit with a cylindrical surface circumferential seam, which also plays a role in oil filtering and can effectively prevent the fuel injection hole 201 of the injection shaft 2 from becoming blocked.

[0030] To facilitate the precise machining of the fuel injection holes 201 on the injection shaft 2, this embodiment opens a machining hole along the axial direction of the injection shaft 2, and then further processes the machining hole to open a fuel injection hole 201 with precise dimensions. Then, a plug 6 is used to seal the machining hole; and the oil passage hole 202 is located on the side wall of the injection shaft 2 between the plug 6 and the fuel injection hole 201 to ensure normal flow of oil.

[0031] The nozzle is bolted to the outer casing of the engine combustion chamber and sealed by a sealing ball head 105 that mates with a conical surface on the outer casing. Fuel ultimately enters the guide pipe through the flow hole 103 on the sealing ball head 105 of the nozzle holder 1, and finally enters the combustion chamber flame tube through the guide pipe. In this embodiment, a locking plate 7 is installed on the nozzle holder 1. The locking plate 7 is installed at the end of the nozzle holder 1 away from the flow hole 103. The locking plate 7 contacts the injection shaft 2. The injection shaft 2 is locked by the locking plate 7 at the locking hole on the nozzle holder 1, thereby limiting the injection shaft 2 within the mounting hole. The locking method is simple, reliable, and easy to disassemble and maintain.

[0032] In this embodiment, to ensure fuel uniformity, the number of fuel passage holes 202 on the injection shaft 2 is 2 to 3, and the fuel passage holes 202 are evenly distributed along the circumference of the injection shaft 2. Furthermore, the diameter of the fuel passage holes 202 is Φ0.4 to Φ0.6 mm, the corresponding fuel injection hole 201 diameter ranges from Φ0.3 to Φ0.5 mm, the flow passage hole 103 diameter ranges from Φ0.8 to Φ1.0 mm, and the gap between the annular boss 204 and the mounting hole ranges from 0.1 to 0.2 mm, thus serving to throttle and control the fuel flow characteristics of the nozzle.

[0033] The nozzle mounting base 1 is also provided with an oil collecting chamber 8 that communicates with the oil inlet 5. The oil collecting chamber 8 is used to connect with the oil inlet pipeline 9. In this embodiment, the oil collecting chamber 8 is cylindrical, with an inner diameter ranging from Φ6 to Φ9 mm and a depth of 6 to 7 mm.

[0034] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A main combustion chamber nozzle for an aircraft engine, characterized in that, include: Nozzle holder (1), the holder is provided with a mounting hole and a flow passage (103), the flow passage (103) is connected to the mounting hole; A fuel injection shaft (2) is fixed in the mounting hole by a threaded section. The fuel injection shaft (2) has a fuel injection hole (201) along the axial direction. The flow hole (103) is coaxially arranged with the fuel injection hole (201) and the flow hole (103) is located downstream of the outlet of the fuel injection hole (201). The fuel injection shaft (2) has an oil passage hole (202) that connects the mounting hole and the fuel injection hole (201). A sealing ring (3) and a sealing retainer (4) are also provided between the outer wall of the fuel injection shaft (2) and the inner wall of the mounting hole. The sealing ring (3) and the sealing retainer (4) are located on both sides of the threaded section, and the sealing ring (3) is installed on the outer wall of the fuel injection shaft (2) near the flow hole (103). A necked section (203) is provided on the outer wall of the injection shaft (2) between the fuel injection hole (201) and the threaded section, and the oil passage hole (202) is located in the necked section (203). Oil inlet (5) is provided on nozzle fixing seat (1), and the oil outlet end of the oil inlet (5) is located on the inner wall of the mounting hole corresponding to the necking section (203).

2. The main combustion chamber nozzle for an aero-engine according to claim 1, characterized in that, The outer wall of the constricted section (203) of the injection shaft (2) is provided with an annular boss (204). The annular boss (204) is located between the oil passage (202) and the oil outlet end of the oil inlet (5). The annular boss (204) divides the cavity between the constricted section (203) and the mounting hole into a first chamber (101) and a second chamber (102). The first chamber (101) is connected to the fuel injection hole (201) through the oil passage (202). The second chamber (102) is connected to the oil outlet end of the oil inlet (5) through the gap between the annular boss (204) and the oil outlet end of the oil inlet (5).

3. The main combustion chamber nozzle for an aero-engine according to claim 2, characterized in that, The number of oil passage holes (202) on the injection shaft (2) is 2 to 3, and the oil passage holes (202) are evenly distributed along the circumference of the injection shaft (2).

4. The main combustion chamber nozzle for an aero-engine according to claim 3, characterized in that, The oil passage hole (202) has a diameter of Φ0.4~Φ0.6mm, the corresponding fuel injection hole (201) has a diameter range of Φ0.3~Φ0.5mm, the flow passage hole (103) has a diameter range of Φ0.8~Φ1.0mm, and the gap between the annular boss (204) and the mounting hole is 0.1~0.2mm.

5. The main combustion chamber nozzle for an aero-engine according to claim 1, characterized in that, It also includes a plug (6), the injection shaft (2) has a machining hole along the axial direction, the machining hole is connected to the fuel injection hole (201), and the plug (6) is fixed in the machining hole to seal the machining hole.

6. The main combustion chamber nozzle for an aero-engine according to claim 1, characterized in that, A locking plate (7) is installed on the nozzle holder (1). The locking plate (7) is installed at the end of the nozzle holder (1) away from the flow hole (103). The locking plate (7) is in contact with the spray shaft (2). The nozzle holder (1) is provided with a punch locking hole (104) that cooperates with the locking plate (7) to limit the spray shaft (2) in the mounting hole.

7. The main combustion chamber nozzle for an aero-engine according to claim 1, characterized in that, The nozzle mounting base (1) is also provided with an oil collecting chamber (8) that communicates with the oil inlet (5), and the oil collecting chamber (8) is used to connect the oil inlet pipeline (9).

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