CN108518284B - Turbojet engine and oil path structure thereof - Google Patents
Turbojet engine and oil path structure thereof Download PDFInfo
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- CN108518284B CN108518284B CN201810346361.XA CN201810346361A CN108518284B CN 108518284 B CN108518284 B CN 108518284B CN 201810346361 A CN201810346361 A CN 201810346361A CN 108518284 B CN108518284 B CN 108518284B
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- oil
- bearing
- housing
- bearing seat
- rotating shaft
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- 239000003921 oil Substances 0.000 claims abstract description 197
- 239000000295 fuel oil Substances 0.000 claims abstract description 44
- 238000007789 sealing Methods 0.000 claims abstract description 43
- 239000000446 fuel Substances 0.000 claims abstract description 41
- 238000002485 combustion reaction Methods 0.000 claims abstract description 17
- 230000002093 peripheral effect Effects 0.000 claims abstract description 15
- 239000010687 lubricating oil Substances 0.000 claims description 14
- 238000005461 lubrication Methods 0.000 abstract description 13
- 230000001050 lubricating effect Effects 0.000 abstract description 11
- 230000000694 effects Effects 0.000 abstract description 5
- 238000001816 cooling Methods 0.000 description 9
- 239000003595 mist Substances 0.000 description 6
- 239000000306 component Substances 0.000 description 5
- 239000007788 liquid Substances 0.000 description 5
- 239000007921 spray Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000013016 damping Methods 0.000 description 2
- 239000000314 lubricant Substances 0.000 description 2
- 230000005514 two-phase flow Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 150000001336 alkenes Chemical class 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000010419 fine particle Substances 0.000 description 1
- 238000005469 granulation Methods 0.000 description 1
- 230000003179 granulation Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- JRZJOMJEPLMPRA-UHFFFAOYSA-N olefin Natural products CCCCCCCC=C JRZJOMJEPLMPRA-UHFFFAOYSA-N 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000009834 vaporization Methods 0.000 description 1
- 230000008016 vaporization Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Sliding-Contact Bearings (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses an oil way structure of a turbojet engine, wherein a rotating shaft penetrates through a bearing seat, an input oil duct which is led into an inner hole of the bearing seat is arranged on the peripheral surface of the bearing seat, a first sealing component which forms a seal with one end of the bearing seat is arranged at one end of the rotating shaft, and at least one output oil duct which is led into the inner hole of the bearing seat is arranged on the peripheral surface of the bearing seat; further comprises: the second sealing assembly is arranged at the other end of the rotating shaft and forms a seal with the other end of the bearing, a closed cavity for receiving fuel oil is formed among the bearing seat, the rotating shaft, the first sealing assembly and the second sealing assembly, and the fuel oil flowing into the closed cavity lubricates a front bearing and a rear bearing arranged in the bearing seat; and an oil delivery assembly for guiding or delivering the fuel oil outputted from the output oil duct to the combustion chamber of the turbojet engine after lubricating the rear bearing and the front bearing. The invention has the advantages of reducing the fuel consumption rate, improving the endurance mileage, improving the lubrication effect of the bearing system and prolonging the service life of the engine.
Description
Technical Field
The invention relates to the technical field of engines, in particular to a turbojet engine and an oil circuit structure thereof.
Background
The miniature turbine engine has the characteristics of small size, light weight, high energy density and large thrust mass ratio, can be used as the thrust power of a miniature unmanned aerial vehicle, can also be used as a core component to be applied to a distributed power generation system and an aircraft auxiliary power device, has wide military and civil prospects, and receives high importance.
For lubrication and cooling of the miniature aero turbine engine bearing, the conventional practice is to spray circulated pressurized lubricating oil onto the rotating bearing to perform lubrication and cooling, but the pressurized oil lubrication mode has a complex structure, and the weight of a lubrication system accounts for 10% -15% of the total weight of the engine. On a miniature and small aeroengine adopting a circulating lubrication system, the weight of the lubrication system is larger than the total weight ratio of the engine, such as a first miniature turbojet engine principle experimental prototype W2P-1 of China developed by the industrial university of northwest in the eighth five period and the thermodynamic engineering system, the circulating lubrication scheme is adopted, wherein the weight of accessories and a speed reducer is 40% of the total weight of the engine, which is the main reason for lower thrust weight of the engine.
The lubricating oil system occupies large volume and mass in the engine, and cannot take care of the specificity of the miniature engine. Therefore, simplifying the structure of the lubrication system and thus reducing the weight of the engine is an effective way to increase the thrust-to-weight ratio of such engines. In recent years, a gas-liquid two-phase flow has been mainly used, in which a small amount of lubricating liquid is mixed with compressed air by a specific device, a gas-liquid two-phase jet is injected from a nozzle into a lubrication cooling area, and the gas-liquid two-phase flow contains only a small amount of lubricating oil which is torn into fine particles, and most of the lubricating oil is air flowing at a high speed. The key is the blowing-off conveying process of the compressed air after oil atomization or oil granulation, but the lubricating effect is not good, and the high-temperature failure rate of the bearing is still high. Another problem is that the air-mixed lubricating oil cannot be recovered and combusted to be utilized, so that certain consumption is caused, and when an engine is started, fuel in the flame tube is not fully combusted due to insufficient air inlet, flame is sprayed out of the tail nozzle, and the flame is aggravated by the lubricating fuel.
For example, the patent application number 201410410174.5 discloses an invention entitled: the patent discloses a miniature aeroengine bearing fuel heat exchange cooling device, which is characterized in that the engine is externally supplied with oil from an oil inlet pipe, and fuel oil (which is used as fuel oil and lubricating oil by adding lubricating oil with a certain proportion into the fuel oil) enters a cooling sleeve through the oil inlet pipe, then enters a fuel oil spray pipe through an oil return pipe, and the fuel oil spray pipe sprays the fuel oil into a flame tube for combustion. And heat generated by the rear bearing can be taken away in the process that the fuel oil flows through the cooling sleeve, so that the rear bearing is cooled. The drawbacks of this patent are as follows:
the flow direction of the fuel oil in the bearing chamber is that the front bearing flows to the rear bearing, so that the lubrication sequence of the fuel oil is as follows: the front bearing is lubricated before the rear bearing is lubricated, however, after the front bearing is lubricated, the lubricating performance of the fuel oil is obviously reduced under the action of high temperature, and when the fuel oil flows to the rear bearing, the fuel oil almost loses the lubricating effect on the rear bearing, so that the rear bearing is almost in a dry state, the rear bearing works in a high-temperature environment of 200 ℃ or more, and in this state, the abrasion of the rear bearing is very large, so that the service life of the rear bearing is short.
And 2. When the fuel oil flows through the cooling sleeve, although the cooling is formed on the rear bearing, the lubricating of the front bearing and the rear bearing still introduces the fuel oil into the bearing chamber, however, the lubricating oil of the front bearing and the rear bearing is not recovered after passing through the bearing chamber and is directly discharged through the rear end of the bearing chamber, so that the lost fuel oil determines that the mileage of the miniature aeroengine during continuous voyage cannot be improved.
Disclosure of Invention
The invention aims to provide an energy-saving turbojet engine capable of improving the endurance mileage and an oil circuit structure thereof.
The technical scheme for solving the technical problems is as follows:
the oil circuit structure of the turbojet engine comprises a rotating shaft and a bearing seat for installing a front bearing and a rear bearing, wherein the rotating shaft penetrates through the bearing seat, an input oil duct which is led into an inner hole of the bearing seat is arranged on the peripheral surface of the bearing seat, a first sealing component which is used for sealing one end of the bearing seat is arranged at one end of the rotating shaft, and at least one output oil duct which is led into the inner hole of the bearing seat is arranged on the peripheral surface of the bearing seat; further comprises:
the second sealing assembly is arranged at the other end of the rotating shaft and forms a seal with the other end of the bearing, a closed cavity for receiving fuel oil is formed among the bearing seat, the rotating shaft, the first sealing assembly and the second sealing assembly, and the fuel oil flowing into the closed cavity lubricates a front bearing and a rear bearing arranged in the bearing seat; and
and the oil delivery assembly is used for guiding or delivering the fuel lubricating oil output from the output oil duct to the combustion chamber of the turbojet engine after lubricating the rear bearing and the front bearing.
A turbojet engine includes an oil passage structure.
By adopting the scheme, the oil way structure of the invention firstly lubricates the front bearing and the rear bearing for supporting the rotating shaft by the fuel lubricating oil, and then guides or conveys the fuel lubricating oil into the combustion chamber of the turbojet engine through the output oil duct and the oil conveying component to be used as fuel for combustion, so that the fuel lubricating oil in the oil way structure is not discharged to the outside of the turbojet engine after lubricating the bearings, but is further used as fuel, thus the fuel consumption rate of the engine can be effectively reduced (compared with the oil way structure in the prior art, the weight of the fuel lubricating oil carried by the turbojet engine can be reduced under the same endurance mileage), the thrust-weight ratio is improved, the endurance mileage is improved, and the preferential oil way structure is also very simple. In addition, the fuel oil continuously flows into the closed cavity to lubricate the front bearing and the rear bearing, the upper heat of the front bearing and the rear bearing is taken away, compared with the prior art that only a small amount of fuel oil can be input to lubricate the bearings, the oil path structure in the invention determines that all the carried fuel oil can sufficiently lubricate and cool the front bearing and the rear bearing, and particularly compared with the prior art, the lubrication effect of the rear bearing is greatly improved and enhanced, and the service life of the whole turbojet engine is further prolonged.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
fig. 2 is a schematic structural view of the turbojet engine according to the present invention;
FIG. 3 is a schematic view of a first housing in the present invention;
FIG. 4 is a schematic view of the structure of the first oil slinger member of the present invention;
FIG. 5 is a schematic view of a second housing in accordance with the present invention;
FIG. 6 is a schematic view of the housing of FIG. 5 assembled with a bearing housing;
FIG. 7 is a schematic view of a second oil slinger member according to the present invention;
FIG. 8 is a schematic view of a third oil slinger member according to the present invention;
FIG. 9 is a schematic view of a fourth oil slinger member according to the present invention;
a is a front bearing, B is a rear bearing, C is a fan blade, and D is a combustion chamber;
10 is a bearing seat, 11 is an input oil duct, 12 is an output oil duct, 13 is a closed cavity, and 14 is a first O-shaped ring;
20 is a rotating shaft, 21 is a nut;
30 is a diffuser, 31 is a shaft sleeve, 32 is a first annular sealing element, 33 is a first sealing ring, and 34 is an annular bulge;
40 is a turbine, 41 is a second annular seal, and 42 is a collar;
50 is a housing, 50a is an oil outlet, 51 is an oil delivery pipe, 52 is an annular oil cavity, 53 is a first assembly hole, 54 is an opening, and 55 is a second assembly hole;
60 is an oil throwing component, 61 is an oil throwing channel, 62 is an inlet, 63 is an outlet, and 64 is an oil carrying groove.
Detailed Description
As shown in fig. 1 to 3, the oil passage structure of the turbojet engine of the present invention includes a bearing housing 10, a rotary shaft 20, a first seal assembly, a second seal assembly, an oil delivery assembly, and an oil slinger 60, and the following details are given with respect to the respective parts and the relationship therebetween:
as shown in fig. 1, the rotating shaft 20 passes through the bearing seat 10, a front bearing a and a rear bearing B are installed in an inner hole of the bearing seat 10, one end of the rotating shaft 20 passes through the front bearing a, the other end of the rotating shaft 20 passes through the rear bearing B, so that the rotating shaft 20 is supported by the front bearing a and the rear bearing B, a compressor fan blade C is installed at one end of the rotating shaft 20, and a turbine 40 is installed at the other end of the rotating shaft 20.
As shown in fig. 1, an input oil duct 11 is provided on the circumferential surface of the bearing housing 10 and is led into the inner bore of the bearing housing, and the fuel oil can be input into the inner bore of the bearing housing 10 through the input oil duct 11 for lubricating the front bearing a and the rear bearing B mounted at both ends of the bearing housing 10.
As shown in fig. 1, at least one output oil duct 12 which is led into the inner hole of the bearing seat is arranged on the peripheral surface of the bearing seat 10, preferably, a plurality of output oil ducts 12 are arranged, more preferably, 8 output oil ducts 12 are arranged, the position of the input oil duct 11 is preferentially set to correspond to the position of the rear bearing B, the position of the output oil duct 12 is preferentially set to correspond to the position of the front bearing a, and as one main function of the fuel is to lubricate the front bearing a and the rear bearing B, when the fuel is input into the inner hole of the bearing seat 10 through the input oil duct 11, the rear bearing B is lubricated first, and then the front bearing a is lubricated, and finally, the fuel is output through the output oil duct 12, so that the utilization rate of the fuel can be improved, and the lubrication effect can be improved.
As shown in fig. 1, one end of the rotating shaft 20 is provided with a first sealing component for forming a seal on one end of the bearing seat 10, and the first sealing component forms a seal on one end of the bearing seat 10 and the rotating shaft 20 so as to prevent the fuel from flowing out from one end of the bearing seat 10.
As shown in fig. 1 and 2, in one or more embodiments, the first seal assembly preferably adopts a structure that: the diffuser comprises a diffuser 30 and a first sealing mechanism, wherein the diffuser 30 is provided with a through hole, the first sealing mechanism is arranged on the rotating shaft 20, and at least one part of the first sealing mechanism is positioned in the through hole of the diffuser 30 to form a seal for the through hole. One end of the rotating shaft 20 passes through the first sealing mechanism and then is connected with the fan blade C of the air compressor.
As shown in fig. 1 and 2, the first sealing mechanism includes a sleeve 31 and a first annular sealing member 32, the sleeve 31 is fixed on the rotating shaft 20 to rotate along with the rotating shaft 20, and the sleeve 31 is located in a through hole provided on the diffuser 30; the sleeve 31 is preferably integrally fixed to the shaft 20 by interference. The first annular sealing member 32 is fixed on the peripheral surface of the shaft sleeve 31, the outer peripheral surface of the first annular sealing member 32 abuts against the hole wall surface of the through hole on the diffuser 30 so as to form a sealing effect on the shaft sleeve 31 and the through hole on the diffuser 30, the first annular sealing member 32 is preferably made of a metal material, the first annular sealing member 32 has elasticity, an annular groove is formed in the peripheral surface of the shaft sleeve 30, the first annular sealing member 32 is embedded in the annular groove, and the outer peripheral surface of the first annular sealing member 32 abuts against the hole wall surface of the through hole on the diffuser 30, so that when the shaft sleeve 31 rotates along with the rotating shaft 30, the first annular sealing member 32 rotates along with the shaft sleeve 31.
As shown in fig. 1 and 2, the first sealing assembly further includes: the first annular groove is formed in the axial end face of the diffuser 30, which faces one end of the bearing seat 10, and the first annular groove is provided with a first sealing ring 33, one end of the bearing seat 10 abuts against the axial end face of the diffuser 30, and after the diffuser 30 is connected and fastened with the bearing seat 10 by adopting a connecting piece, a seal is formed between the axial end face of one end of the bearing seat 10 and the axial end face of the diffuser 30.
As shown in fig. 1 and 2, the second sealing assembly is disposed at the other end of the rotating shaft 20 and forms a seal with the other end of the bearing housing 10, and a closed cavity 13 for receiving the fuel oil is formed among the bearing housing 10, the rotating shaft 20, the first sealing assembly and the second sealing assembly, and the fuel oil flowing into the closed cavity 13 lubricates the front bearing a and the rear bearing B mounted in the bearing housing 10; the second sealing assembly seals the other end of the bearing housing 10 and the rotating shaft 20 to prevent the fuel from flowing out of the other end of the bearing housing 10.
As shown in fig. 1 and 2, the second seal assembly preferably adopts a structure that: the turbine 40 is fixed on the rotating shaft 20, one end of the turbine 40 abuts against the rear bearing B, the other end of the turbine 40 is axially limited through a nut 21 mounted on the rotating shaft 20, a second annular groove is formed in the peripheral surface of the turbine 40, the second annular groove is close to one end of the turbine 40 abutting against the rear bearing B, and the second annular seal 41 is embedded in the second annular groove. One end of the turbine 40 provided with the second annular groove penetrates through the annular sleeve 42, and the annular sleeve 42 is fixedly connected with the bearing seat 10.
As shown in fig. 1 and 2, the collar 42 is fixed on an axial end surface of the other end of the bearing housing 10, and preferably, one end of the collar 42 facing the bearing housing 10 is provided with an annular boss embedded in an inner hole of the bearing housing 10, and the annular boss is in interference fit with the inner hole of the bearing housing 10, so that the tightness of the collar 42 against the inner hole is enhanced. The outer peripheral surface of the second annular seal 41 abuts against the inner peripheral surface of the collar 42, thereby forming a seal against the other end of the bearing housing 10.
As shown in fig. 1 and 2, in one or more embodiments, a third annular groove is provided on the hole wall surface corresponding to the front bearing a in the inner hole of the bearing seat 10, a first O-ring 14 (as shown in fig. 1) is installed in the third annular groove, the first O-ring 14 preferably adopts the first O-ring 14 with elastic performance, the first O-ring 14 is pressed between the front bearing a and the bearing seat 10, the first O-ring 14 can play a role in damping the front bearing a, and the service life of the engine can be improved.
Because the sealed cavity 13 is formed in the invention, the fuel continuously flows into the sealed cavity to lubricate the front bearing and the rear bearing, the upper heat of the front bearing and the rear bearing is taken away, compared with the prior art that only a small amount of fuel can be input to lubricate the bearings, the oil path structure in the invention determines that all the carried fuel can sufficiently lubricate and cool the front bearing A and the rear bearing B, and the temperature at the rear bearing B is reduced to about 100 ℃ after cooling, therefore, in one or more embodiments, a fourth annular groove is arranged on the hole wall surface corresponding to the rear bearing B in the inner hole of the bearing seat 10, a second O-shaped ring (not shown in the figure) is arranged in the fourth annular groove, the second O-shaped ring is preferably pressed between the rear bearing B and the bearing seat 10, and plays a role in damping the rear bearing B through the second O-shaped ring, thereby helping the service life of the engine.
As shown in fig. 1 to 3, the oil delivery assembly guides or delivers the fuel oil delivered from the delivery oil passage 12 to the combustion chamber D of the turbojet engine, the fuel oil being the fuel oil after lubricating the rear bearing and the front bearing, the oil delivery assembly including: the oil delivery pipe comprises a housing 50 and an oil delivery pipe 51, wherein the housing 50 is provided with a containing cavity, one end of the housing 50 is provided with a first assembly hole 53, the other end of the housing 50 is provided with an opening 54, one end of the bearing seat 10 extends into the housing 50 from the first assembly hole 53, an output oil duct 12 on the bearing seat 10 corresponds to the containing cavity of the housing 50, and the housing 50 is provided with an oil outlet 50a. The other end of the housing 50 is connected to or integrally formed with the first seal assembly, preferably, the other end of the housing 50 is integrally formed with the diffuser 30 in the first seal assembly in a manner that facilitates the housing 50 and diffuser 30 to cover the end of the housing 10. A closed annular oil chamber 52 is enclosed between the housing 50 and the first sealing assembly and the bearing housing 10, so that the fuel flowing out of the outlet channel 12 enters the annular oil chamber 52.
As shown in fig. 1 to 3, one end of the oil delivery pipe 51 is connected to the oil outlet 50a of the casing 50, and in one or more embodiments, preferably, the casing 50 has a plurality of oil outlet holes, the oil delivery pipe 51 is also a plurality of oil outlet holes, each oil outlet hole of the casing 50 is connected to one end of one oil delivery pipe 51, and the other end of the oil delivery pipe 51 is connected to the combustion chamber D, so that the lubricated bearing-burning oil is guided or conveyed into the combustion chamber D, and is burned in the olefin combustion chamber to generate high-temperature and high-pressure gas. The lubricant oil from the output oil passage 12 is received through the formed annular oil chamber 52, and when the number of the oil outlets 50a is plural, the lubricant oil is dispersed from the annular oil chamber 52 and flows into the oil outlets 50a.
As shown in fig. 1, 2 and 4, the oil slinger 60 is fixed to the rotating shaft 20 and rotates with the rotating shaft 20, and preferably, the oil slinger 60 is positioned between the shaft sleeve 31 and the front bearing a, one end of the oil slinger 60 abuts against the shaft sleeve 31, and the other end of the oil slinger 60 is low against one end of the front bearing a. In one or more embodiments, the oil slinger 60 is preferably annular in shape, and the oil slinger 60 is fitted over the shaft 20 and secured circumferentially to the shaft 20.
As shown in fig. 1 and 4, at least one oil slinger 61 for accelerating the movement of the fuel into the outlet oil gallery 12 when the oil slinger 60 rotates is provided on the oil slinger 60. Preferably, the circumferential surface of the oil slinger 60 corresponds to the output oil duct 12, when the rotating shaft 20 rotates at a high speed, the oil slinger 60 rotates at a high speed along with the rotating shaft 20, the fuel oil entering the oil slinger 61 is accelerated when the oil slinger 60 rotates at a high speed, so that the flow speed and the pressure of the fuel oil are both increased, the fuel oil changes into a mist form from a liquid state into the output oil duct 12 under the condition of accelerating flow, the mist form of the fuel oil is guided to the combustion chamber D through the oil delivery assembly, and the combustion efficiency of the fuel oil is promoted by the action of the oil slinger 60, so that the endurance mileage of the turbojet engine is promoted due to the fact that the fuel oil forms a mist form in advance. The temperature of the atomized fuel is reduced, and the combustion is facilitated by the vaporization combustion after reaching the combustion chamber D.
As shown in fig. 1 and 4, in one or more embodiments, the oil slinger 61 is arranged along the direction of the centrifugal force generated when the oil slinger 60 rotates, and as a preferred mode of the present invention, since the centrifugal force is generated when the oil slinger 60 rotates, the oil slinger 61 is arranged along the direction of the centrifugal force generated when the oil slinger 60 rotates, so that the flow velocity of the fuel can reach the maximum value, thereby being beneficial to completely forming the mist form of the fuel flowing through the oil slinger 61.
As shown in fig. 1 and fig. 4, in one or more embodiments, the oil slinger 61 is located on an axial end face of the oil slinger 60, and more preferably, the oil slinger is disposed on both axial end faces of the oil slinger 60, so as to disperse the fuel oil to the maximum extent, and effectively form a mist form of the fuel oil, and the number of the oil slinger 61 on each axial end face of the oil slinger 60 is greater than or equal to the number of the output oil channels 12.
As shown in fig. 1 and 4, each oil slinger 61 has a cross-sectional area, and the oil slinger 61 includes an inlet 62 and an outlet 63, preferably the cross-sectional area of the oil slinger increases from the inlet 62 to the outlet 63 of the oil slinger 61, which helps to ensure the pressure rise of the fuel. The inlet 62 is provided at or near the inner periphery of the oil slinger 60, and the outlet 63 is provided at the outer periphery of the oil slinger 60.
As shown in fig. 1 and 4, the oil slinger 60 is provided with an oil carrying groove 64, and the at least one oil slinger channel 61 is communicated with the oil carrying groove 64, so that the fuel oil flows into the oil slinger channel 61 from the oil carrying groove 64, and the shape of the oil carrying groove 64 is preferably annular. After the oil carrier groove 64 is provided on the oil slinger 60, the fuel oil can flow into the oil carrier groove 64 intensively, and then be dispersed into each oil slinger channel 61 from the oil carrier groove 64, so that the fuel oil can be uniformly distributed into each oil slinger channel 61. When the oil-carrying groove 64 is provided in the oil slinger 60, the inlet 62 can be disposed only in the vicinity of the inner periphery of the oil slinger 60.
As shown in fig. 1 and 2, the oil slinger 60 is located between the shaft sleeve 31 and the front bearing a as a preferred mode of the present embodiment, therefore, the oil slinger 60 is also close to the fan blade C of the compressor, since the pressure of the air outlet at the diffuser 30 is low, the pressure of the fuel is increased after the fuel is accelerated by the oil slinger, and the fuel is changed into a mist form in the process of being slinged at high speed, so that under the condition of pressure difference, there is a possibility that the fuel in the bearing housing 10 is sucked out, and therefore, the diffuser 30 is provided with the annular protrusion 34 surrounding the hole opening of the through hole, the annular protrusion 34 is matched in the inner hole of the bearing housing 10 and shields the oil slinger channel 61, and the fuel is prevented from being sucked out by the shielding effect of the annular protrusion 34.
Other embodiments:
while the preferred embodiments of the present invention have been described above, the present invention is not limited to the above embodiments, and various modifications can be made without departing from the spirit of the present invention.
(a) In the above embodiment, the first annular seal 32 may also be made of a rubber material.
(b) In the above embodiment, the shaft sleeve 31 and the first annular seal 32 in the first seal assembly may be directly replaced by the first annular seal 32, and the annular groove is formed in the rotating shaft 20, and the first annular seal 32 is directly fixed in the annular groove formed in the rotating shaft 20, and the outer periphery of the first annular seal 32 abuts against the hole wall surface of the through hole in the diffuser 30.
(c) In the above embodiment, the second sealing assembly may have a structure that: the second seal assembly comprises a second annular seal 32, the second annular seal 32 is sleeved on the rotating shaft, the second annular seal 32 is pressed between the turbine 40 and the rear bearing B, and the outer periphery of the second annular seal 32 abuts against the inner wall of the bearing seat.
Alternatively, the second seal assembly includes a second annular seal member 32 provided on the rotary shaft 20 with a second annular fitting groove in which the second annular seal member 32 is fitted, and the outer periphery of the second annular seal member 32 abuts against the inner wall of the bearing housing.
(d) In the above embodiment, as shown in fig. 5 and 6, the oil delivery assembly may also adopt a structure in which the oil delivery assembly includes a housing 50 and an oil delivery pipe 51, the housing 50 has a receiving cavity, an oil outlet 50a is provided on the housing 50, a first assembly hole 53 is provided at one end of the housing 50, a second assembly hole 55 is provided at the other end of the housing 50, and after one end of the bearing housing 10 extends into the housing 50 from the first assembly hole 53, an output oil duct 12 on the bearing housing 10 corresponds to the receiving cavity of the housing 50, and a closed annular oil cavity 52 is formed between the housing 50 and the bearing housing 10; one end of the oil delivery pipe 51 is connected with an oil outlet 50a on the housing.
(e) In the above embodiment, the structure of the oil delivery assembly may be: the fuel delivery assembly comprises a fuel delivery pipe 51, wherein one end of the fuel delivery pipe 51 is connected with a fuel delivery pipe 12, the other end of the fuel delivery pipe is connected with a combustion chamber D, a plurality of fuel delivery pipes 12 can be arranged, and each fuel delivery pipe 12 is connected with one fuel delivery pipe 51.
(f) In the above embodiment, if the oil slinger 60 is not provided with the oil carrier groove 64, as shown in fig. 7, the inlet 62 is provided on the inner periphery of the oil slinger 60.
(g) In the above embodiment, the oil slinger 61 may be configured as follows: the oil slinger channel 61, which is disposed on the axial end face of the oil slinger member 60, is fan-shaped (as shown in fig. 8).
(h) In the above embodiment, the oil slinger 61 may be configured as follows: the oil slinging passages 61 are arranged in a manner inclined to the radial direction of the oil slinging member 60, and the cross-sectional areas of the oil slinging passages 61 are equal at any two points in the direction from the inlet to the outlet (as shown in FIG. 9).
As shown in fig. 2, the turbojet engine of the present invention includes the oil passage structure according to any of the embodiments described above, and the oil passage structure on an engine such as the one shown in fig. 2 may be replaced with the oil passage structure of the present invention, for example, the oil passage structure on a micro-aeroengine having application number 201410410174.5 may be replaced with the oil passage structure of the present invention.
Claims (8)
1. The oil path structure of the turbojet engine comprises a rotating shaft and a bearing seat for installing a front bearing and a rear bearing, wherein the rotating shaft penetrates through the bearing seat, and an input oil duct which is led into an inner hole of the bearing seat is arranged on the peripheral surface of the bearing seat; further comprises:
the second sealing assembly is arranged at the other end of the rotating shaft and forms a seal with the other end of the bearing, a closed cavity for receiving fuel oil is formed among the bearing seat, the rotating shaft, the first sealing assembly and the second sealing assembly, and the fuel oil flowing into the closed cavity lubricates a front bearing and a rear bearing arranged in the bearing seat; and
the oil delivery assembly is used for guiding or delivering the fuel lubricating oil output from the output oil duct to the combustion chamber of the turbojet engine after the rear bearing and the front bearing are lubricated;
the oil throwing device further comprises an oil throwing part which is fixed on the rotating shaft and rotates along with the rotating shaft, the peripheral surface of the oil throwing part corresponds to the output oil duct, and at least one oil throwing channel which accelerates the fuel oil to move into the output oil duct when the oil throwing part rotates is arranged on the oil throwing part;
the oil slinging passages are arranged in the direction of centrifugal force generated when the oil slinging member rotates.
2. The oil path structure of a turbojet engine according to claim 1, wherein the oil slinger is located on an axial end face of the oil slinger member, the oil slinger having a cross-sectional area, the oil slinger including an inlet and an outlet, the cross-sectional area of the oil slinger increasing from the inlet to the outlet of the oil slinger.
3. The oil path structure of the turbojet engine according to claim 1, wherein the oil slinger is provided with an oil carrying groove, and at least one oil slinger passage is communicated with the oil carrying groove so that the fuel oil flows into the oil slinger passage from the oil carrying groove.
4. The oil passage structure of the turbojet engine of any one of claims 1 to 3 wherein the first seal assembly includes a diffuser having a through hole;
and the first sealing mechanism is arranged on the rotating shaft, and at least one part of the first sealing mechanism is positioned in the through hole of the diffuser to form a seal for the through hole.
5. The oil passage structure of the turbojet engine according to claim 4, wherein the diffuser is provided with an annular protrusion surrounding the through-hole orifice, the annular protrusion being fitted in the bearing housing.
6. The oil passage structure of the turbojet engine according to any one of claims 1 to 3, wherein the second seal assembly includes:
the turbine is fixed on the rotating shaft, and a second annular groove is formed in the peripheral surface of the turbine;
a second annular seal, a portion of which is located in a second annular groove on the turbine;
and one end of the turbine, provided with a second annular groove, penetrates through the annular sleeve, the annular sleeve is fixedly connected with the bearing seat, and the outer circumferential surface of the second annular sealing piece abuts against the inner circumferential surface of the annular sleeve.
7. The oil passage structure of a turbojet engine according to any one of claims 1 to 3, characterized in that the oil delivery assembly includes:
the device comprises a housing with a housing cavity, wherein one end of the housing is provided with a first assembly hole, the other end of the housing is provided with an opening, one end of a bearing seat extends into the housing from the first assembly hole, an output oil duct on the bearing seat corresponds to the housing cavity of the housing, and an oil outlet is arranged on the housing;
the other end of the housing is connected with the first sealing component or integrally formed, and a sealed annular oil cavity is formed between the housing and the first sealing component and between the housing and the bearing seat;
one end of the oil delivery pipe is connected with the oil outlet on the housing.
8. A turbojet engine comprising the oil passage structure according to any one of claims 1 to 7.
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| CN201810346361.XA CN108518284B (en) | 2018-04-18 | 2018-04-18 | Turbojet engine and oil path structure thereof |
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| CN201810346361.XA CN108518284B (en) | 2018-04-18 | 2018-04-18 | Turbojet engine and oil path structure thereof |
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| CN112065586B (en) * | 2020-09-08 | 2021-11-23 | 西安增材制造国家研究院有限公司 | Engine circulating lubrication oil way structure and engine rotating device |
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| CN113309617B (en) * | 2021-07-09 | 2022-06-17 | 常州环能涡轮动力股份有限公司 | Miniature turbojet engine |
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| CN114060152B (en) * | 2021-12-24 | 2022-12-06 | 常州环能涡轮动力股份有限公司 | Fuel oil atomization structure of micro turbojet engine |
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