Lubricating oil system of aviation turbojet engine for missile

Abstract

The invention relates to the technical field of lubrication, and discloses a lubricating oil system of an aviation turbojet engine for a missile. The lubricating oil system of the missile aviation turbojet engine comprises a lubricating oil sleeve and a lubricating oil base, the lubricating oil sleeve comprises a first installation sleeve, a boss is fixedly arranged on one side of the peripheral side face of the first installation sleeve in a sleeving mode, an oil guide groove is formed in the peripheral side face of the boss, and the oil guide groove penetrates through the other end of the boss and the peripheral side face of the first installation sleeve; the lubricating oil seat comprises an oil guide sleeve, a lantern ring and a connecting strip connected between the oil guide sleeve and the lantern ring, an oil guide cavity is formed in the oil guide sleeve, a first hole and a second hole are formed in the oil guide sleeve and communicated with the oil guide cavity, an oil channel is formed in the connecting strip, an oil outlet hole is formed in the lantern ring, the oil channel is communicated with the oil guide cavity and the oil outlet hole, and the oil outlet hole is communicated with the oil guide cavity. Lubricating oil has kinetic energy and generates centrifugal force through rotation of a shaft of the aviation turbojet engine, and the lubricating oil is thrown to a bearing under the action of the centrifugal force to lubricate the bearing.

Description

Technical Field

[0001] The present invention relates to the technical field of lubrication, and specifically to an oil system for an air-breathing turbojet engine used in missiles. Background Art

[0002] An air-breathing turbojet engine used in missiles is a short-life, single-use aeroengine specially designed for unmanned aerial vehicles such as missiles. Compared with the turbojet engines of aircraft, missile engines have the characteristics of long-term storage, rapid start-up, small size, light weight, simple structure, and little or no maintenance. To reduce the cost of the engine and its weight, the design requirements for each system of the engine are to simplify the structure, reduce the number of parts and assembly times, and make the processing method as economical and applicable as possible.

[0003] The basic function of an aeroengine oil system is to supply oil to the working surfaces of bearings and gears, carry away the frictional heat generated under high-speed rotation and the heat transferred from surrounding high-temperature parts, and form a continuous oil film between the raceways of the bearings and the rotors and between the meshing tooth surfaces, thereby playing a lubricating role, reducing the wear and frictional losses of these working surfaces, and preventing the corrosion of parts. At present, most aeroengine oil systems consist of an oil supply system and an oil return system. The oil supply system uses a booster pump to supply the oil in the oil tank to each nozzle, and the oil is sprayed from the nozzle onto friction pairs such as bearings; the oil return system uses an oil return pump to pump the lubricated oil back from the oil in each bearing cavity, cools it through a radiator, and then returns it to the tank for recycling.

[0004] At present, the structural design of aeroengine oil systems is complex. The main components include an oil tank, an oil pump, an oil filter, a pressure regulating valve, a fuel-oil radiator, an oil nozzle, a bypass valve, a centrifugal ventilator, etc. The number of parts is large, the occupied space is large, the cost is high, the assembly process is numerous, and the maintenance is inconvenient, which does not meet the design requirements of air-breathing turbojet engines used in missiles. Summary of the Invention

[0005] (1) Technical Problems to be Solved

[0006] Aiming at the deficiencies of the prior art, the present invention provides an oil system for an air-breathing turbojet engine used in missiles, which can effectively solve the problems raised in the background art.

[0007] (2) Technical Solutions

[0008] To achieve the above object, the present invention provides the following technical solution: A lubricating oil system for an aviation turbojet engine for a missile, comprising a lubricating oil sleeve and a lubricating oil seat. The lubricating oil sleeve includes a first mounting sleeve. On one side of the outer peripheral surface of the first mounting sleeve, a boss is fixedly sleeved. At one end of the boss, a second mounting sleeve is fixedly connected. An oil guiding groove is formed on the outer peripheral surface of the boss, and the oil guiding groove penetrates through the other end of the boss and the outer peripheral surface of the first mounting sleeve. The lubricating oil seat includes an oil guiding sleeve, a collar, and a connecting strip connected between the oil guiding sleeve and the collar. An oil guiding cavity is formed in the oil guiding sleeve. A first hole is formed at the end of the oil guiding sleeve away from the collar, and a second hole is formed at the end of the oil guiding sleeve facing the collar. Both the first hole and the second hole communicate with the oil guiding cavity. An oil passage is provided in the connecting strip, and an oil outlet hole is formed in the collar. The oil outlet hole penetrates through the end of the collar away from the connecting strip. The oil passage communicates the oil guiding cavity and the oil outlet hole; the oil guiding sleeve is sleeved on the boss, and the oil guiding cavity communicates with the oil guiding groove; the boss is embedded in the first hole, and a gap is left between the outer peripheral surface of the boss and the wall surface of the first hole; the first mounting sleeve passes through the second hole, and the collar is sleeved on the first mounting sleeve.

[0009] Preferably, the number of the oil guiding grooves, the connecting strips, and the oil outlet holes is the same and at least one is provided.

[0010] Compared with the prior art, the present invention provides a lubricating oil system for an aviation turbojet engine for a missile, which has the following beneficial effects:

[0011] 1. For the lubricating oil system of the aviation turbojet engine for a missile, in combination with the working characteristics of the missile engine with a short service life and single use, a lubricating oil sleeve that can be installed on the shaft of the aviation turbojet engine and a lubricating oil seat that is sleeved on the lubricating oil sleeve are provided. During the rotation of the shaft of the aviation turbojet engine, the lubricating oil in the oil guiding cavity and the oil guiding groove has kinetic energy and generates centrifugal force. Under the action of the centrifugal force, the lubricating oil in the oil guiding cavity and the oil guiding groove enters the oil passage and is ejected through the oil outlet hole, and is ejected towards the bearing to lubricate the bearing, so that the system can cancel all external oil supply and oil return pipelines while meeting the lubrication of the engine bearing, and the lubricating oil is lubricated in a closed manner in the bearing cavity, simplifying the lubricating oil system and improving the engine integration.

[0012] 2. The lubricating oil system of the aviation turbojet engine for a missile is suitable for lubricating the front bearing of the aviation turbojet engine for a missile. The bearing can be arranged at the position of the air inlet flow passage close to the compressor. The bearing transfers the heat generated during the working process to the intake casing, and the intake casing then transfers the heat to the air at the inlet to dissipate heat and cool the lubricating oil. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0014] Figure 2 It is a schematic diagram of the overall structure of the present invention from another perspective;

[0015] Figure 3 is a schematic cross-sectional structure diagram of the present invention;

[0016] Figure 4 is a schematic cross-sectional structure diagram of the lubricating oil sleeve of the present invention;

[0017] Figure 5 is a schematic cross-sectional structure diagram of the lubricating oil seat of the present invention;

[0018] Figure 6 is a schematic installation diagram of the present invention on the shaft of an aero-turbojet engine;

[0019] Figure 7 is another schematic installation diagram of the present invention on the shaft of an aero-turbojet engine.

[0020] Wherein: 1, lubricating oil sleeve; 2, lubricating oil seat; 11, first installation sleeve; 12, boss; 121, oil guiding groove; 13, second installation sleeve; 14, installation hole; 15, connecting thread; 21, oil guiding sleeve; 211, oil guiding cavity; 212, first hole; 213, second hole; 22, connecting bar; 221, oil passage; 23, collar; 231, oil outlet hole; 3, shaft of aero-turbojet engine; 31, installation thread; 32, driving key; 4, bearing. Specific embodiments

[0021] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0022] Embodiment 1

[0023] Please refer to Figures 1-6, a lubricating oil system for an aero-turbojet engine used in ammunition, which can be installed on the aero-turbojet engine shaft 3 through the mounting thread 31 on the aero-turbojet engine shaft 3 and introduce lubricating oil into the bearing 4 on the aero-turbojet engine shaft 3 to achieve lubrication of the bearing 4. It includes a lubricating oil sleeve 1 and a lubricating oil seat 2. The lubricating oil sleeve 1 includes a first mounting sleeve 11. On one side of the outer peripheral side of the first mounting sleeve 11, a boss 12 is fixedly sleeved. At one end of the boss 12, a second mounting sleeve 13 is fixedly connected. An oil guiding groove 121 is formed on the outer peripheral side of the boss 12. The oil guiding groove 121 penetrates through the other end of the boss 12 and the outer peripheral side of the first mounting sleeve 11. The lubricating oil seat 2 includes an oil guiding sleeve 21, a collar 23, and a connecting strip 22 connected between the oil guiding sleeve 21 and the collar 23. An oil guiding cavity 211 is formed in the oil guiding sleeve 21. A first hole 212 is formed at one end of the oil guiding sleeve 21 away from the collar 23. A second hole 213 is formed at one end of the oil guiding sleeve 21 facing the collar 23. Both the first hole 212 and the second hole 213 communicate with the oil guiding cavity 211. An oil passage 221 is arranged in the connecting strip 22. An oil outlet hole 231 is formed in the collar 23. The oil outlet hole 231 penetrates through the end of the collar 23 away from the connecting strip 22. The oil passage 221 communicates the oil guiding cavity 211 and the oil outlet hole 231. The oil guiding sleeve 21 is sleeved on the boss 12, and the oil guiding cavity 211 communicates with the oil guiding groove 121. The boss 12 is embedded in the first hole 212, and there is a gap between the outer peripheral side of the boss 12 and the wall surface of the first hole 212. Lubricating oil can enter the oil guiding cavity 211 and the oil guiding groove 121 through the gap between the boss 12 and the first hole 212. The first mounting sleeve 11 passes through the second hole 213. The collar 23 is sleeved on the first mounting sleeve 11, and the collar 23 is in interference fit with the first mounting sleeve 11. The collar 23 can move synchronously with the first mounting sleeve 11. The first mounting sleeve 11 is fixedly sleeved on the aero-turbojet engine shaft 3 and can rotate with the rotation of the aero-turbojet engine shaft 3. After the first mounting sleeve 11 is fixed on the aero-turbojet engine shaft 3, the oil outlet hole 231 corresponds to the bearing 4 on the aero-turbojet engine shaft 3. During the rotation of the lubricating oil sleeve 1 with the aero-turbojet engine shaft 3, under the action of centrifugal force, the lubricating oil in the oil guiding cavity 211 and the oil guiding groove 121 enters the oil passage 221 and is ejected through the oil outlet hole 231, and is ejected towards the bearing 4 to lubricate the bearing 4. The number of the oil guiding grooves 121, the connecting strips 22, and the oil outlet holes 231 is the same and at least one is provided.

[0024] On one side of the inner circumferential surface of the first mounting sleeve 11 away from the boss 12, a connecting thread 15 is provided. The first mounting sleeve 11 is sleeved on the aero-turboprop engine shaft 3 through the threaded fit of the connecting thread 15 and the mounting thread 31. The tightening direction of the connecting thread 15 on the mounting thread 31 is opposite to the rotation direction of the aero-turboprop engine shaft 3, so that the lubricating oil sleeve 1 rotates with the aero-turboprop engine shaft 3 during the rotation of the aero-turboprop engine shaft 3. An installation hole 14 is formed at one end of the first mounting sleeve 11 facing the second mounting sleeve 13. The installation hole 14 is a prismatic hole. Specifically, the installation hole 14 is a hexagonal prismatic hole and can be matched with an internal hexagonal wrench. After the connecting thread 15 is screwed onto the mounting thread 31, the internal hexagonal wrench is inserted into the second mounting sleeve 13 from one end of the second mounting sleeve 13 away from the first mounting sleeve 11 and inserted into the installation hole 14. The internal hexagonal wrench is rotated to rotate the lubricating oil sleeve 1, so that the connecting thread 15 is tightened on the mounting thread 31.

[0025] Embodiment 2

[0026] Please refer to Figure 7, A lubricating oil system for an aero-turbojet engine used in ammunition can be installed on the aero-turbojet engine shaft 3 through a drive key 32 and introduce lubricating oil into the bearing 4 on the aero-turbojet engine shaft 3 to achieve lubrication of the bearing 4. It includes a lubricating oil sleeve 1 and a lubricating oil seat 2. The lubricating oil sleeve 1 includes a first mounting sleeve 11. On one side of the outer peripheral side of the first mounting sleeve 11, a boss 12 is fixedly sleeved. At one end of the boss 12, a second mounting sleeve 13 is fixedly connected. An oil guiding groove 121 is formed on the outer peripheral side of the boss 12. The oil guiding groove 121 penetrates through the other end of the boss 12 and the outer peripheral side of the first mounting sleeve 11. The lubricating oil seat 2 includes an oil guiding sleeve 21, a collar 23, and a connecting strip 22 connected between the oil guiding sleeve 21 and the collar 23. An oil guiding cavity 211 is formed in the oil guiding sleeve 21. A first hole 212 is formed at one end of the oil guiding sleeve 21 away from the collar 23. A second hole 213 is formed at one end of the oil guiding sleeve 21 facing the collar 23. Both the first hole 212 and the second hole 213 communicate with the oil guiding cavity 211. An oil passage 221 is provided in the connecting strip 22. An oil outlet hole 231 is formed in the collar 23. The oil outlet hole 231 penetrates through the end of the collar 23 away from the connecting strip 22. The oil passage 221 communicates the oil guiding cavity 211 and the oil outlet hole 231; The oil guiding sleeve 21 is sleeved on the boss 12, and the oil guiding cavity 211 communicates with the oil guiding groove 121; The boss 12 is embedded in the first hole 212, and there is a gap between the outer peripheral side of the boss 12 and the wall surface of the first hole 212. Lubricating oil can enter the oil guiding cavity 211 and the oil guiding groove 121 through the gap between the boss 12 and the first hole 212; The first mounting sleeve 11 passes through the second hole 213, the collar 23 is sleeved on the first mounting sleeve 11, and the collar 23 is in interference fit with the first mounting sleeve 11. The collar 23 can move synchronously with the first mounting sleeve 11. The first mounting sleeve 11 is fixedly sleeved on the aero-turbojet engine shaft 3 and can rotate with the rotation of the aero-turbojet engine shaft 3. After the first mounting sleeve 11 is fixed on the aero-turbojet engine shaft 3, the oil outlet hole 231 corresponds to the bearing 4 on the aero-turbojet engine shaft 3; During the rotation of the lubricating oil sleeve 1 with the aero-turbojet engine shaft 3, under the action of centrifugal force, the lubricating oil in the oil guiding cavity 211 and the oil guiding groove 121 enters the oil passage 221 and is ejected through the oil outlet hole 231, and is ejected towards the bearing 4 to lubricate the bearing 4. The number of the oil guiding groove 121, the connecting strip 22, and the oil outlet hole 231 is the same and at least one is provided.

[0027] The first mounting sleeve 11 is sleeved on the aero-turbojet engine shaft 3, and the drive key 32 is embedded in the outer peripheral side of the aero-turbojet engine shaft 3 and the inner peripheral side of the first mounting sleeve 11. The drive key 32 is used to install and fix the first mounting sleeve 11 on the aero-turbojet engine shaft 3 and achieve the transmission of motion.

[0028] It should be noted that in the specific implementation process, the connection method between the first mounting sleeve 11 and the aero-turbine engine shaft 3 is not limited to the threaded connection and key connection mentioned in the above embodiments. The threaded connection and key connection are just two preferred options.

[0029] It should be noted that for an engine applying the lubricating oil system of an aero-turbine engine for ammunition, during use, the lubricating oil in the engine needs to cover the rollers below the bearing 4. When the engine is working, the rotation direction of the aero-turbine engine shaft 3 is counterclockwise along the course. The lubricating oil sleeve 1 and the lubricating oil seat 2 rotate with the rotation of the aero-turbine engine shaft 3. With the high-speed rotation of the lubricating oil sleeve 1 and the lubricating oil seat 2, the lubricating oil in the oil guiding cavity 211 and the oil guiding groove 121 has kinetic energy and generates centrifugal force. The lubricating oil in the oil guiding cavity 211 and the oil guiding groove 121 enters the oil passage 221 and is ejected through the oil outlet hole 231, and is ejected towards the bearing 4 to lubricate the bearing 4.

[0030] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principle and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A lubricating oil system for an aviation turbojet engine used in a missile can be installed on the aviation turbojet engine shaft (3) through the installation thread (31) on the aviation turbojet engine shaft (3) or through a drive key (32), and lubricating oil is introduced into the bearing (4) on the aviation turbojet engine shaft (3) to achieve lubrication of the bearing (4). Characterized in that: It includes a lubricating oil sleeve (1) and a lubricating oil seat (2). The lubricating oil sleeve (1) includes a first installation sleeve (11). On one side of the outer peripheral side of the first installation sleeve (11), a boss (12) is fixedly sleeved. At one end of the boss (12), a second installation sleeve (13) is fixedly connected. An oil guiding groove (121) is opened on the outer peripheral side of the boss (12). The oil guiding groove (121) penetrates through the other end of the boss (12) and the outer peripheral side of the first installation sleeve (11). The lubricating oil seat (2) includes an oil guiding sleeve (21), a collar (23), and a connecting strip (22) connected between the oil guiding sleeve (21) and the collar (23). An oil guiding cavity (211) is opened in the oil guiding sleeve (21). A first hole (212) is opened at one end of the oil guiding sleeve (21) away from the collar (23). A second hole (213) is opened at one end of the oil guiding sleeve (21) facing the collar (23). Both the first hole (212) and the second hole (213) are communicated with the oil guiding cavity (211). An oil passage (221) is arranged in the connecting strip (22). An oil outlet hole (231) is opened in the collar (23). The oil outlet hole (231) penetrates through the end of the collar (23) away from the connecting strip (22). The oil passage (221) communicates the oil guiding cavity (211) and the oil outlet hole (231); the oil guiding sleeve (21) is sleeved on the boss (12), and the oil guiding cavity (211) is communicated with the oil guiding groove (121); the boss (12) is embedded in the first hole (212), and there is a gap between the outer peripheral side of the boss (12) and the wall surface of the first hole (212); the first installation sleeve (11) passes through the second hole (213), and the collar (23) is sleeved on the first installation sleeve (11).

2. The lubricating oil system for an aviation turbojet engine used in a missile according to claim 1, Characterized in that: On the inner peripheral side of the first installation sleeve (11) on the side away from the boss (12), a connecting thread (15) is provided. The first installation sleeve (11) is sleeved on the aviation turbojet engine shaft (3) through the thread fit of the connecting thread (15) and the installation thread (31).

3. The lubricating oil system for an aviation turbojet engine used in a missile according to claim 2, Characterized in that: The tightening direction of the connecting thread (15) on the installation thread (31) is opposite to the rotation direction of the aviation turbojet engine shaft (3).

4. The lubricating oil system for an aviation turbojet engine used in a missile according to claim 3, Characterized in that: An installation hole (14) is opened at one end of the first installation sleeve (11) facing the second installation sleeve (13). The installation hole (14) is a prismatic hole.

5. A lubricating oil system for an air - breathing turbojet engine for a missile, according to claim 5, characterized in that: the first mounting sleeve (11) is sleeved on the air - breathing turbojet engine shaft (3), and the transmission key (32) is embedded in the outer peripheral side of the air - breathing turbojet engine shaft (3) and the inner peripheral side of the first mounting sleeve (11).

6. A lubricating oil system for an air - breathing turbojet engine for a missile, according to claim 1, characterized in that: the number of the oil guiding grooves (121), the connecting strips (22) and the oil outlet holes (231) is the same and at least one is provided.

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