90-degree nozzle structure
By designing interval-distributed fuel chamber and cyclone in the 90 nozzle structure, flexible adjustment and stability of nozzle oil supply are achieved, the problem of insufficient oil supply adjustment in the prior art is solved, and the fuel fuel of the engine is improved Usage efficiency and overall performance.
Patent Information
- Application Number
- CN202323404973.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2023-12-13
- Publication Date
- 2024-12-17
- Estimated Expiration
- 2033-12-13
AI Technical Summary
The existing 90 engine nozzles cannot be effectively met under various flight conditions and working conditions, resulting in inefficient fuel use.
A 90 nozzle structure is designed, including a base, a housing, a nozzle and a cyclone, with a spaced first and second fuel chambers arranged in the base, and the fuel is injected through the cyclone and when required Oil supply separately or jointly to meet the oil supply needs under different working conditions.
It improves the adjustment range of nozzle oil supply, reduces fuel waste, enhances the stability and sealing effect of nozzles, facilitates adapting to different working needs, extends service life and simplifies assembly and maintenance processes.
Smart Images
Figure CN222187013U_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the field of fuel nozzles, and in particular to a 90° nozzle structure. Background Art
[0002] 90 The engine nozzle, also called the fuel nozzle, scatters the fuel into the combustion chamber through the flow channel constraint, mixes with the air, burns and expands to do work, and propels the aircraft into the air. The fuel nozzle is an important component of the engine combustion chamber. The fuel passes through the nozzle flow channel constraint under high pressure, is sprayed in the form of atomization, and is mixed and burned with compressed air in a certain proportion to form the engine working source.
[0003] The fuel nozzles used in aircraft engines include centrifugal nozzles, pneumatic nozzles, evaporative nozzles and oil-slinging plate nozzles. Among them, the 90 engine uses a centrifugal nozzle, and a swirler and a nozzle are installed at the liquid outlet of the centrifugal nozzle. The swirler allows the fuel to enter the nozzle cavity along the tangential direction hole under the action of oil pressure, and then it is sprayed out from the nozzle at a high speed in the form of droplets, so that the fuel has a better combustion efficiency in the combustion chamber.
[0004] However, the fuel supply required by the engine under various flight conditions and operating states currently varies greatly. Therefore, in order to adapt to the fuel supply adjustment needs, the effectiveness of the nozzle needs to be improved. Utility Model Content
[0005] In order to improve the use effect of the nozzle in the engine, the present application provides a 90 nozzle structure.
[0006] The 90° nozzle structure provided in this application adopts the following technical solution:
[0007] A 90 nozzle structure comprises a base, a shell, a nozzle and a swirler, wherein a first fuel chamber and a second fuel chamber are provided in the base and are spaced apart from each other, and a plurality of oil ports are provided in the first fuel chamber and the second fuel chamber. The shell is mounted on the base, and the nozzle is mounted on the shell. The swirler is connected to the nozzle, and the swirler simultaneously connects the first fuel chamber and the second fuel chamber, and the fuel in the first fuel chamber and the second fuel chamber can pass through the swirler and then be sprayed out from the nozzle.
[0008] By adopting the above technical scheme, when in use, the fuel in the base will first pass through the swirler and then be sprayed out from the nozzle, so that the fuel is sprayed outward in the form of droplets; when the engine is working at a low speed and a small amount of oil is required, the fuel can be transported only through the first fuel chamber (or the second fuel chamber) to meet the fuel supply demand of the engine in this state, and it is not easy to cause fuel waste; when the fuel supply needs to be increased, the second fuel chamber (or the first fuel chamber) can be synchronously transported to the fuel, so that the first fuel chamber and the second fuel chamber are jointly supplied with fuel to meet the high fuel supply demand of the engine under this working condition; thereby increasing the adjustment range of the fuel supply of the nozzle in the engine, making it easier to adapt to different working requirements and improving the use effect of the nozzle in the engine.
[0009] Optionally, an installation cavity with an opening at one end is defined inside the base, the shell is detachably connected to the base and covers the opening of the installation cavity, a supporting top column is installed in the installation cavity, and the upper end of the supporting top column abuts against the cyclone; an area in the installation cavity corresponding to the outer wall of the supporting top column is a first fuel cavity, and an area in the installation cavity corresponding to the bottom of the supporting top column is a second fuel cavity, and the interior of the supporting top column is a hollow structure and is connected to the second fuel cavity.
[0010] By adopting the above technical solution, when in use, the support top column can reinforce the installation of the cyclone, so that the stability of the cyclone and the nozzle during use is better; and the support top column can also divide the internal area of the installation cavity into a first fuel cavity and a second fuel cavity, reducing the possibility of mutual interference between the first fuel cavity and the second fuel cavity.
[0011] Optionally, an annular overlapping portion is formed between the first fuel chamber and the second fuel chamber, and a separator is fixed to the bottom of the supporting top column, and the separator abuts against the overlapping portion.
[0012] By adopting the above technical solution, during installation, it is only necessary to insert the supporting top column into the installation cavity so that the dividing sheet is clamped on the overlapping portion, thereby separating the internal area of the installation cavity into the first fuel cavity and the second fuel cavity.
[0013] Optionally, an inner seat is installed on the inner side of the shell, the inner seat covers the opening of the installation cavity, the inner seat is clamped between the base and the shell, the nozzle is installed on the inner seat, the cyclone and the supporting top column are both located on the inner side of the inner seat, and the shell is provided with an avoidance opening corresponding to the liquid outlet end of the nozzle.
[0014] By adopting the above technical solution, during installation, the nozzle and the cyclone are first installed on the inner seat, and then the inner seat is installed on the base, and then the shell is closed, thereby realizing the overall assembly of the nozzle; and the shell has a better protective effect on the internal nozzle and cyclone, and at the same time can push the inner seat to tightly abut the edge of the opening of the installation cavity, thereby ensuring the sealing effect of the installation cavity.
[0015] Optionally, a sealing ring is installed on the side of the inner seat facing the base, the sealing ring extends around the opening edge of the installation cavity, and the sealing ring is clamped between the base and the inner seat.
[0016] By adopting the above technical solution, the provided sealing ring can improve the sealing effect after the inner seat is installed, and reduce the possibility of fuel in the installation cavity leaking outwards.
[0017] Optionally, the inner seat is formed with an annular plug-in flange, and the plug-in flange is plug-fitted into the opening end of the installation cavity.
[0018] By adopting the above technical solution, when installing the inner seat, the sealing ring is first sleeved on the plug-in flange, and then the plug-in flange is plugged into the opening of the installation cavity, thereby having a better positioning effect on the installation of the inner seat; and, when the sealing ring is clamped between the inner seat and the base, the plug-in flange has a better supporting effect on the sealing ring, reducing the possibility of deformation of the sealing ring.
[0019] Optionally, the side wall of the supporting top column is formed with an abutting section abutting against the inner wall of the inner seat, and the side wall of the abutting section is provided with a plurality of fuel channels, one end of the fuel channel is connected to the first fuel cavity, and the other end is connected to the cyclone.
[0020] By adopting the above technical solution, after the support top column is installed in the installation cavity, the support top column is connected to the cyclone and can also be supported by the inner seat, so that the support top column is more stable in use.
[0021] Optionally, the base is provided with a plurality of connection holes, and the shell is provided with a plurality of connection screws, and the connection screws pass through the shell and are threadedly connected to the connection holes.
[0022] By adopting the above technical solution, the connecting screws can detachably fix the shell to the base, making the assembly and maintenance process of the entire nozzle more convenient.
[0023] In summary, the present application includes at least one of the following beneficial technical effects:
[0024] 1. When the engine is working at a low speed and requires less fuel, fuel can be delivered only through the first fuel chamber (or the second fuel chamber) to meet the fuel supply demand of the engine in this state without causing fuel waste; when the fuel supply needs to be increased, the first fuel chamber and the second fuel chamber can be used to supply fuel together to meet the high fuel supply demand of the engine under this working condition; thereby increasing the adjustment range of the fuel supply of the nozzle in the engine, facilitating adaptation to different working requirements and improving the use effect of the nozzle in the engine;
[0025] 2. The support top column can reinforce the installation of the cyclone, making the cyclone and the nozzle more stable during use; the support top column can also divide the internal area of the installation cavity into a first fuel cavity and a second fuel cavity, reducing the possibility of mutual interference between the first fuel cavity and the second fuel cavity. BRIEF DESCRIPTION OF THE DRAWINGS
[0026] Figure 1 It is a cross-sectional view of the nozzle structure of Example 90 of the present application.
[0027] Explanation of the reference numerals: 1. base; 11. first fuel chamber; 12. second fuel chamber; 13. overlap; 14. connection hole; 2. shell; 21. avoidance port; 3. nozzle; 4. swirler; 5. supporting top column; 51. partition plate; 52. abutment section; 521. fuel channel; 6. inner seat; 61. plug-in flange; 7. sealing ring; 8. connecting screw. DETAILED DESCRIPTION
[0028] The following is combined with Figure 1 This application is described in further detail.
[0029] The present application embodiment discloses a 90 nozzle structure. Figure 1 The nozzle structure includes a base 1, a shell 2, a nozzle 3, a swirler 4, a support top column 5 and an inner seat 6. The base 1 is provided with an upper opening mounting cavity, in which a first fuel cavity 11 and a second fuel cavity 12 are arranged, the second fuel cavity 12 is located below the first fuel cavity 11, and the first fuel cavity 11 and the second fuel cavity 12 are provided with a plurality of oil ports. An overlap portion 13 is formed on the inner wall of the mounting cavity, and the overlap portion 13 is located between the first fuel cavity 11 and the second fuel cavity 12.
[0030] Reference Figure 1 The inner seat 6 covers the opening of the installation cavity, and the housing 2 is sleeved on the inner seat 6. The housing 2 is provided with a plurality of connecting screws 8, and the base 1 is provided with a plurality of connecting holes 14, and the connecting screws 8 pass through the housing 2 and are threadedly connected to the connecting holes 14, so that the inner seat 6 is clamped by the housing 2.
[0031] Reference Figure 1 The nozzle 3 is embedded in the upper end of the inner seat 6, and the cyclone 4 is installed at the lower end of the nozzle 3. The cyclone 4 includes a main body and a plurality of capillary spray holes opened on the main body. The capillary spray holes extend along a spiral track, one end of the capillary spray holes is connected to the installation cavity, and the other end points to the hole on the nozzle 3. Alternatively, the cyclone 4 is set to be hollow inside, and an inlet extending along a tangential direction is opened at one end facing the installation cavity, and an outlet is provided at one end facing the nozzle 3.
[0032] The fuel inside the installation cavity can pass through the swirler 4 and have a tendency to rotate before entering the nozzle and then being sprayed out. At this time, a avoidance port 21 is provided at the portion of the shell 2 corresponding to the nozzle 3. The support top column 5 extends vertically, the upper end of the support top column 5 is supported on the swirler 4, and a separator 51 is fixed on the lower end, and the separator 51 abuts against the overlap portion 13. The gap between the outer wall of the support top column 5 and the inner wall of the inner seat 6 is the first fuel cavity 11, so that the fuel in the first fuel cavity 11 can be transported toward the swirler 4. The interior of the support top column 5 is set as a hollow structure, and one end of the hollow area inside the support top column 5 is connected to the second fuel cavity 12, and the other end is connected to the swirler 4, so that the fuel in the second fuel cavity 12 can also be transported toward the swirler 4.
[0033] When in use, the fuel in the base 1 will first pass through the swirler 4 to make the fuel rotate at high speed, and then spray out from the nozzle 3, so that the fuel is sprayed outward in the form of droplets. When the engine is working at a low speed and requires less oil, the fuel can be transported only through the first fuel chamber 11 (or the second fuel chamber 12) to meet the fuel supply demand of the 90 engine in this state, and it is not easy to cause fuel waste. When the fuel supply needs to be increased, the second fuel chamber 12 (or the first fuel chamber 11) can be synchronously transported to make the first fuel chamber 11 and the second fuel chamber 12 supply fuel together to meet the high fuel supply demand of the 90 engine. Thereby increasing the adjustment range of the fuel supply of the nozzle in the 90 engine, it is convenient to adapt to different working requirements and improve the use effect of the nozzle in the 90 engine.
[0034] The shell 2 has a better protective effect on the inner seat 6, the nozzle 3 and the cyclone 4, and increases the service life of the nozzle as a whole. In addition, the shell 2 pushes the inner seat 6 to closely abut the edge of the opening of the installation cavity, so that the sealing effect of the installation cavity is better. In addition, the shell 2, the nozzle 3, the cyclone 4, the support top column 5 and the inner seat 6 can be disassembled by removing the connecting screws 14, making the assembly and maintenance process of the nozzle as a whole more convenient.
[0035] When the supporting top column 5 is installed, the partition sheet 51 and the overlapping portion 13 abut against each other, so that the first fuel chamber 11 and the second fuel chamber 12 can be separated by the partition sheet 51, ensuring the possibility of the two chambers interfering with each other during use.
[0036] Reference Figure 1The side wall of the support pillar 5 is formed with an abutting section 52 that abuts against the inner wall of the inner seat 6, and the side wall of the abutting section 52 is provided with a plurality of fuel channels 521. The fuel channels 521 extend along the length direction of the support pillar 5, and one end of the fuel channels 521 is connected to the first fuel cavity 11, and the other end is connected to the cyclone 4. After the support pillar 5 is installed in the installation cavity, the support pillar 5 is connected to the cyclone 4 and can also be supported by the inner seat 6, so that the stability of the support pillar 5 is better. The fuel in the first fuel cavity 11 can flow normally to the cyclone 4 through the fuel channels 521, ensuring the normal injection of the fuel.
[0037] Reference Figure 1 A sealing ring 7 is installed on the side of the inner seat 6 facing the base 1. The sealing ring 7 extends around the opening edge of the installation cavity and is clamped between the base 1 and the inner seat 6. An annular plug-in flange 61 is formed on one end of the inner seat 6 facing the base 1. The plug-in flange 61 is plugged into the opening end of the installation cavity, and the sealing ring 7 is sleeved on the plug-in flange 61.
[0038] The provided sealing ring 7 can improve the sealing effect after the inner seat 6 is installed, and reduce the possibility of fuel leakage from the installation cavity. When the inner seat 6 is installed, the sealing ring 7 is first sleeved on the plug-in flange 61, and then the plug-in flange 61 is plugged and matched with the opening of the installation cavity, thereby having a better positioning effect on the installation of the inner seat 6. The sealing ring 7 is clamped between the inner seat 6 and the base 1, and the plug-in flange 61 also has a better supporting effect on the sealing ring 7, so that the sealing ring 7 is more stable when used, and the possibility of deformation of the sealing ring 7 is reduced.
[0039] The implementation principle of a 90 nozzle structure in the embodiment of the present application is as follows: when in use, when the engine is operating at a low speed and requires less oil, fuel can be delivered only through the first fuel chamber 11 (or the second fuel chamber 12) to meet the fuel supply demand of the 90 engine in this state, and it is not easy to cause fuel waste. When it is necessary to increase the fuel supply, the second fuel chamber 12 (or the first fuel chamber 11) can be used to deliver fuel synchronously, so that the first fuel chamber 11 and the second fuel chamber 12 can supply fuel together to meet the high fuel supply demand of the 90 engine under this working condition. Thereby increasing the adjustment range of the fuel supply of the nozzle in the 90 engine, making it easier to adapt to different working requirements and improving the use effect of the nozzle in the 90 engine.
[0040] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.
Claims
1. A 90 nozzle structure, characterized in that: The invention comprises a base (1), a shell (2), a nozzle (3) and a swirler (4); the base (1) is provided with a first fuel chamber (11) and a second fuel chamber (12) which are arranged at intervals; the first fuel chamber (11) and the second fuel chamber (12) are both provided with a plurality of oil ports; the shell (2) is mounted on the base (1); the nozzle (3) is mounted on the shell (2); the swirler (4) is connected to the nozzle (3); the swirler (4) is connected to the first fuel chamber (11) and the second fuel chamber (12); the fuel in the first fuel chamber (11) and the second fuel chamber (12) can pass through the swirler (4) and then be sprayed out from the nozzle (3).
2. The 90 nozzle structure according to claim 1, characterized in that: The base (1) has an installation cavity with an opening at one end, the shell (2) is detachably connected to the base (1) and covers the opening of the installation cavity, a support column (5) is installed in the installation cavity, and the upper end of the support column (5) abuts against the cyclone (4); the area in the installation cavity corresponding to the outer wall of the support column (5) is a first fuel cavity (11), and the area in the installation cavity corresponding to the bottom of the support column (5) is a second fuel cavity (12), and the interior of the support column (5) is a hollow structure and is connected to the second fuel cavity (12).
3. The 90 nozzle structure according to claim 2, characterized in that: An annular overlapping portion (13) is formed between the first fuel chamber (11) and the second fuel chamber (12), a separator (51) is fixed to the bottom of the supporting top column (5), and the separator (51) abuts against the overlapping portion (13).
4. The 90 nozzle structure according to claim 2, characterized in that: An inner seat (6) is installed on the inner side of the shell (2), and the inner seat (6) covers the opening of the installation cavity. The inner seat (6) is clamped between the base (1) and the shell (2), and the nozzle (3) is installed on the inner seat (6). The cyclone (4) and the supporting top column (5) are both located on the inner side of the inner seat (6). The shell (2) is provided with an avoidance opening (21) corresponding to the liquid outlet end of the nozzle (3).
5. The 90 nozzle structure according to claim 4, characterized in that: A sealing ring (7) is installed on the side of the inner seat (6) facing the base (1), the sealing ring (7) extends around the opening edge of the installation cavity, and the sealing ring (7) is clamped between the base (1) and the inner seat (6).
6. The 90 nozzle structure according to claim 5, characterized in that: The inner seat (6) is formed with an annular plug-in flange (61), and the plug-in flange (61) is plug-fitted into the opening end of the installation cavity.
7. The 90 nozzle structure according to claim 4, characterized in that: The side wall of the supporting top column (5) is formed with an abutting section (52) that abuts against the inner wall of the inner seat (6), and the side wall of the abutting section (52) is provided with a plurality of fuel channels (521), one end of the fuel channel (521) is connected to the first fuel cavity (11), and the other end is connected to the cyclone (4).
8. The 90 nozzle structure according to claim 4, characterized in that: The base (1) is provided with a plurality of connection holes (14), the shell (2) is provided with a plurality of connection screws (8), and the connection screws (8) pass through the shell (2) and are threadedly connected to the connection holes (14).