CN215566269U - Medium conveying device of micro turbojet engine - Google Patents

Abstract

The utility model discloses a medium conveying device of a micro turbojet engine, which comprises a gas compressor, a turbine, a combustion chamber, a medium throwing-out assembly and a medium conveying assembly connected with the gas compressor, wherein a first spacing space is formed between the gas compressor and the turbine, the medium conveying assembly is positioned in the first spacing space, one end of the medium conveying assembly is provided with an accommodating cavity and a first channel corresponding to the accommodating cavity, and the medium throwing-out assembly corresponds to the accommodating cavity. The utility model can convey the lubricating oil and the compressed gas.

Description

Medium conveying device of micro turbojet engine

Technical Field

The utility model relates to the technical field of aero-engines, in particular to a medium conveying device of a micro turbojet engine.

Background

The micro turbine engine has the characteristics of small size, light weight, high energy density and large mass-to-thrust ratio, can be used as the propulsion power of a micro unmanned aerial vehicle, can also be used as a core component to be applied to a distributed power generation system and an auxiliary power device of an airplane, has wide military and civil prospects, and therefore receives high attention.

The utility model patent application No. 2014104101745 discloses a method named: the patent of the cooling device for the heat exchange of the bearing fuel oil of the miniature aero-engine is that the fuel oil is supplied to an oil inlet pipe from the outside of the engine, and the fuel oil (lubricating oil which is added into the fuel oil in a certain proportion and is used as the fuel oil and the lubricating oil) enters a cooling jacket through the oil inlet pipe, then enters a fuel oil spray pipe through an oil return pipe, and is sprayed into a flame tube for combustion through the fuel oil spray pipe. The 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 patent has the following disadvantages:

1, the flowing direction of the fuel in the bearing chamber is from the front bearing to the rear bearing, so that the lubricating sequence of the fuel is as follows: the front bearing is lubricated first and then the rear bearing is lubricated, however, the flame tube surrounds the bearing chamber, the temperature generated by the flame tube is conducted to the transmission shaft and the bearing through the turbine guider and the turbine, so that the temperature in the bearing chamber is very high, the lubricating performance of the fuel oil is obviously reduced under the action of high temperature after the front bearing is lubricated, 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 more than 200 degrees centigrade, under the state, the abrasion of the rear bearing is very large, the service life of the bearing is influenced by the excessively high temperature, the rotating speed of the micro-turbojet engine is high and often reaches 12 ten thousand revolutions per minute or even higher, and the working condition is very bad.

2, when the fuel oil flows through the cooling sleeve, although the rear bearing is cooled, the front bearing and the rear bearing are lubricated by introducing the fuel oil into the bearing chamber, however, the oil lubricated by the front bearing and the rear bearing is still not recovered after passing through the bearing chamber and is directly discharged through the rear end of the bearing chamber, so that the mileage of the miniature aero-engine, which is determined by the lost fuel oil, cannot be increased.

3, in the existing micro aero-engine, a starting motor is usually installed at the front end of the whole engine, and the starting motor does not work any more after being started.

SUMMERY OF THE UTILITY MODEL

The utility model provides a medium conveying device of a micro turbojet engine, which is convenient for conveying lubricating oil and compressed gas.

The technical scheme for solving the technical problems is as follows:

the medium conveying device of the micro turbojet engine comprises a gas compressor, a turbine, a combustion chamber, a medium throwing-out assembly and a medium conveying assembly connected with the gas compressor, a first interval space is formed between the gas compressor and the turbine, the medium conveying assembly is located in the first interval space, one end of the medium conveying assembly is provided with an accommodating cavity and a first channel corresponding to the accommodating cavity, and the medium throwing-out assembly corresponds to the accommodating cavity.

The utility model has the following advantages: the structure of the utility model utilizes the matching relationship of the medium throwing-out component and the medium conveying component to convey the fuel oil and the compressed gas, thereby being beneficial to simplifying the structure of the product and lightening the weight of the product.

Drawings

FIG. 1 is a schematic cross-sectional view of a micro turbojet engine according to the present invention;

FIG. 2 is a schematic view of the compressor of the present invention;

FIG. 3 is a schematic structural diagram of a casing according to the present invention;

FIG. 4 is a schematic cross-sectional view of a media transport assembly of the present invention;

FIG. 5 is a schematic perspective view of a media transport assembly of the present invention;

FIG. 6 is a schematic perspective view of the media transport assembly of the present invention in another orientation;

FIG. 7 is a schematic diagram of a portion of a media transport assembly of the present invention;

FIG. 8 is a schematic view of a media throw-out assembly;

reference numbers in the drawings:

the gas compressor 1, a pressure shell 1a, a pressure gas wheel 1b, a diffuser 1c, a gas guide cylinder 1e, a second exhaust passage 1f, a gas guide passage 1g, a gas guide hole 1h, a relief notch 1i, a rotating shaft 2, a turbine 3, a combustion chamber 4, a first spacing space 5, a front bearing 6, a rear bearing 7, a medium throwing-out component 8, a disc-shaped part 8a, an oil throwing part 8b, a gas throwing part 8c, an annular boss 8d, a containing groove 8e, a medium driving part 8f, an oil pipe 9, a casing 10, a first oil channel 10a, a second oil channel 10b, a bearing containing cavity 10c, a rotor 11, a stator 12 and an inner cylinder 13, the device comprises an oil guide plate 14, an end cover 15, an outer cylinder 16, an air supply channel 17, a connecting part 18, a first sealing part 19, an airflow guide part 20, a first tubular part 20a, a first guide block 20B, a bleed air channel 21, an accommodating cavity A and a first channel B;

Detailed Description

The present invention will be described in detail with reference to the accompanying drawings 1 to 8.

The micro turbojet engine shown in fig. 1 comprises a compressor 1, a rotating shaft 2, a turbine 3, a combustion chamber 4, a motor, a front bearing 6, a rear bearing 7, a medium throwing-out component 8, an oil pipe 9 and a medium conveying component connected with the compressor 1, wherein the compressor 1, the turbine 3, the combustion chamber 4 and the medium throwing-out component 8 form a medium conveying device for lubricating oil, and each part and the relationship among the parts are described in detail below:

the compressor 1 is fixed at the front end of the rotating shaft 2, the turbine 3 is fixed at the rear end of the rotating shaft 2, the compressor 1 comprises a pressure shell 1a, a pressure wheel 1b, a diffuser 1c and an air guide cylinder 1e, the pressure wheel 1b is located in the pressure shell 1a, the pressure wheel 1b is fixed with the rotating shaft 2, the diffuser 1c is sleeved on the rotating shaft 2 and the front bearing 6, and a first exhaust channel 1d is formed between the diffuser 1c and the pressure shell 1 a.

The front bearing 6 and the rear bearing 7 are respectively arranged on the rotating shaft 2, a first spacing space 5 is formed between the compressor 1 and the turbine 3, the motor, the front bearing 6, the rear bearing 7 and the medium conveying assembly are all located in the first spacing space 5, and the motor is respectively matched with the rotating shaft 2, the front bearing 6 and the rear bearing 7.

The motor comprises a casing 10, a rotor 11 and a stator 12, wherein the casing 10 is matched with a front bearing 6 and a rear bearing 7, the rotor 11 is fixed with the rotating shaft 2, the stator 12 is fixed with the casing 10, a first oil duct 10a is arranged on the circumferential surface of the casing 10, a second oil duct 10b which is radially arranged along the casing 10 is arranged on the axial end surface of the casing 10, the first oil duct 10a is communicated with the second oil duct 10b, and the second oil duct 10b corresponds to the front bearing 6.

According to the structure of the motor, in the starting stage of the micro turbojet engine, a battery loaded on the micro turbojet engine supplies power to the motor, the motor works to drive the rotating shaft 2 to rotate, and the rotating shaft 2 drives the air compressor 1 and the turbine 3 to rotate, so that the micro turbojet engine is started to work. When the micro turbojet engine works normally, the electric energy supplied to the motor by the battery is cut off, the rotating shaft 2 is driven by the turbine 3 to rotate, and the rotor 11 is driven by the rotating shaft 2 to work, so that the motor becomes a generator.

After the medium conveying assembly is sleeved on the motor, an oil path extending to the front bearing 6 and the rear bearing 7 is formed between the motor, the medium conveying assembly and the compressor 1, a bearing accommodating cavity 10c is formed at one end of the casing 10, at least one part of the front bearing 6 is located in the bearing accommodating cavity 10c, and after one end of the casing 10 is fixed with the compressor 1, the second oil path 10b is located between the compressor 1 and the casing 10. The fuel enters the bearing accommodating chamber 10c through the first oil passage 10a and the second oil passage 10b, and cools and lubricates the front bearing 6.

One end of the medium conveying assembly is provided with a containing cavity A and a first channel B corresponding to the containing cavity A, the medium throwing-out assembly 8 is installed on the rotating shaft 2 and matched with the rear bearing 7, the medium throwing-out assembly 8 corresponds to the containing cavity A, the containing cavity A is communicated with the first oil duct 10a, and the fuel oil enters the containing cavity A through the first oil duct 10a and cools and lubricates the rear bearing 7 in the containing cavity A. The medium throwing-out component 8 is fixed with the rotating shaft 2, one end of the medium throwing-out component 8 abuts against the axial end face of the rear bearing 7, and the other end of the medium throwing-out component 8 abuts against a shaft shoulder arranged on the bearing 2. The structure of the utility model ensures that the front bearing 6 and the rear bearing 7 form oil bath lubrication, the service life is longer, meanwhile, the lubricating oil passes through the casing 10 of the motor to form a cooling effect on the motor, and the temperature of the motor can be reduced.

The medium throwing assembly 8 comprises a disc-shaped part 8a provided with a mounting hole, an oil throwing part 8b and a gas throwing part 8c, wherein the disc-shaped part 8a is arranged on the rotating shaft 2, the disc-shaped part 8a is sleeved on the rotating shaft 2 and is fixed with the rotating shaft 2 into a whole, the oil throwing part 8b is arranged on the axial end face, facing the rear bearing 7, of the disc-shaped part 8a, and the gas throwing part 8c is arranged on the axial end face, facing the combustion chamber 4, of the disc-shaped part 8 a. In this embodiment, get rid of oily part 8b and get rid of gas part 8c and all include cyclic annular boss 8d, and the recess forms a plurality of holding tanks 8e on cyclic annular boss 8 d's global, and the part between two adjacent holding tanks 8e is medium drive portion 8f, and in this embodiment, holding tank 8e preferentially adopts the arc wall.

The fuel oil entering the accommodating cavity a cools and lubricates the rear bearing 7, flows to the medium throwing-out assembly 8 and enters the accommodating groove 8e, and is thrown into the first channel B by the fuel throwing-out component 8B because the medium throwing-out assembly 8 rotates. Similarly, the gas-throwing component 8c throws high-pressure gas output by the compressor 1 into the first passage B, so that the fuel and the gas are mixed in the first passage B to improve the combustion efficiency of the fuel in the combustion chamber. After the fuel oil cools and lubricates the front bearing 6 and the rear bearing 7, the temperature of the fuel oil can rise, so that the fuel oil is preheated in the cooling and lubricating processes, the fuel oil is favorable for evaporation, and the evaporation effect is good and the combustion efficiency can be improved.

The one end of oil pipe 9 is connected behind the medium transport assembly and is cooperated with the output of first passageway B, and the other end of oil pipe 9 stretches into in the combustion chamber 4, and the one end and the medium transport assembly of combustion chamber 4 are connected, and the other end of combustion chamber 4 extends to pivot 2 rear and makes this combustion chamber 4 wholly keep away from front bearing 6 and rear bearing 7, and the waste gas delivery outlet of combustion chamber 4 is located around turbine 3.

The combustion chamber 4 is arranged at the rear part, is far away from the front bearing 6 and the rear bearing 7, and can greatly reduce the temperature transmitted to the front bearing 6 and the rear bearing 7 by the combustion chamber 4, so that the structure of the utility model is not only beneficial to reducing the temperature of the front bearing 6 and the rear bearing 7, but also can reduce the temperature of combustion lubrication, and the fuel oil can keep the original lubricating effect and combustion efficiency.

The medium conveying assembly comprises an inner cylinder body 13, an oil guide plate 14 and an end cover 15, wherein the inner cylinder body 13 is sleeved on the motor, the accommodating cavity A is formed in one end of the inner cylinder body 13, the oil guide plate 14 is formed in one end of the inner cylinder body 13, and an oil guide groove 14a communicated with the accommodating cavity A is formed in the oil guide plate 14; the end cover 15 and the oil guide plate 14 form the first channel B after being matched.

The medium conveying assembly further comprises an outer cylinder 16 and a connecting part 18, after the outer cylinder 16 surrounds the oil guide plate 14, a gas supply channel 17 is formed between the outer cylinder 16 and the oil guide plate 14, and the input end of the gas supply channel 17 is connected with the gas output end of the compressor 1; one end of the connecting member 18 is connected to the inner cylinder 13 and/or the oil guide plate 14, and the other end of the connecting member 18 is connected to the outer cylinder 16. The air guide cylinder 1e is provided with a relief notch 1i, and the relief notch 1i is matched with the connecting part 18 to avoid the connecting part 18.

One end of the air guide cylinder body 1e is connected with the diffuser 1c, the other end of the air guide cylinder body 1e penetrates through the outer cylinder body 16 to be matched with the outer peripheral surface of the oil guide plate 14, and a second exhaust passage 1f communicated with the first exhaust passage 1d is formed between the air guide cylinder body 1e and the outer cylinder body 16, so that the air supply passage 17 is communicated with the second exhaust passage 1 f. The compressed gas generated between the pressure turbine 1b and the diffuser 1c passes through the first exhaust passage 1d and the second exhaust passage 1f in this order to reach the gas supply passage 17. The structure of the utility model utilizes the medium conveying component to convey both the fuel and the lubricating oil and the compressed gas, thereby being beneficial to simplifying the structure of the product and reducing the weight of the product.

The utility model also comprises a first sealing part 19, the first sealing part 19 is arranged between the front bearing 6, the rear bearing 7 and the motor, the diffuser 1c is provided with an air entraining channel 1g, the medium conveying assembly and the motor are provided with air entraining holes 1h communicated with the interior of the motor, the air entraining holes 1h are communicated with the air entraining channel 1g, part of high-pressure gas generated by the compressor 1 is introduced into the motor through the air entraining channel 1g and the air entraining holes 1h, and the high-pressure gas resists the oil pressure applied to the first sealing part 19. With the structure, because the pressure on the two sides of the first sealing part 19 is equal, a gap between the first sealing part 19 and the motor can be avoided, and the sealing of the motor is ensured.

The utility model also comprises a plurality of airflow guide parts 20, after the airflow guide parts 20 are arranged between the medium conveying assembly and the combustion chamber 4, the medium conveying assembly, the combustion chamber 4 and the airflow guide parts 20 form a bleed air channel 21, the bleed air channel 21 is communicated with the accommodating cavity A, and oil and gas are mixed in the first channel B under the action of the medium throwing-out assembly 8.

The airflow guide member 20 includes a first tubular member 20a and a first guide block 20b, the first tubular member 20a is penetrated by the oil supply pipe 9, the first guide block 20b is disposed on the circumferential surface of the first tubular member 20a, one ends of the first tubular member 20a and the first guide block 20b are fixed to the medium delivery assembly, and one ends of the first tubular member 20a and the first guide block 20b abut against the axial end of the combustion chamber 4.

Claims (7)

1. The medium conveying device of the micro turbojet engine comprises a gas compressor (1), a turbine (3), a combustion chamber (4) and a medium throwing-out assembly (8), and is characterized by further comprising a medium conveying assembly connected with the gas compressor (1), a first spacing space (5) is formed between the gas compressor (1) and the turbine (3), the medium conveying assembly is located in the first spacing space (5), one end of the medium conveying assembly is provided with an accommodating cavity (A) and a first channel (B) corresponding to the accommodating cavity (A), and the medium throwing-out assembly (8) corresponds to the accommodating cavity (A).

2. The medium delivery apparatus of a micro turbojet engine according to claim 1, wherein the medium delivery assembly comprises:

the inner cylinder (13) is sleeved on the motor, and the accommodating cavity (A) is arranged at one end of the inner cylinder (13);

the oil guide plate (14), the oil guide plate (14) is arranged at one end of the inner cylinder body (13), and the oil guide plate (14) is provided with an oil guide groove (14a) communicated with the accommodating cavity (A);

and the end cover (15), the end cover (15) and the oil guide plate (14) are matched to form the first channel (B).

3. The micro turbojet engine media delivery device of claim 2, wherein the media delivery assembly further comprises:

the outer cylinder (16), after the outer cylinder (16) surrounds the oil guide plate (14), an air supply channel (17) is formed between the outer cylinder (16) and the oil guide plate (14), and the input end of the air supply channel (17) is connected with the gas output end of the compressor (1);

one end of the connecting part (18) is connected with the inner cylinder (13) and/or the oil guide plate (14), and the other end of the connecting part (18) is connected with the outer cylinder (16).

4. The medium delivery device of a micro turbojet engine according to claim 3, wherein the compressor (1) comprises:

a press shell (1 a);

the pressure wheel (1b), the pressure wheel (1b) is positioned in the pressure shell (1a), and the pressure wheel (1b) is fixed with the rotating shaft (2);

the diffuser (1c) is sleeved on the rotating shaft (2) and the front bearing (6), and a first exhaust channel (1d) is formed between the diffuser (1c) and the pressure shell (1 a);

one end of the air guide cylinder body (1e) is connected with the diffuser (1c), the other end of the air guide cylinder body (1e) penetrates through the outer cylinder body (16) to be matched with the outer peripheral surface of the oil guide plate (14), and a second exhaust channel (1f) communicated with the first exhaust channel (1d) is formed between the air guide cylinder body (1e) and the outer cylinder body (16).

5. The medium conveying device of the micro turbojet engine according to claim 1, further comprising a plurality of air flow guide members (20), wherein the air flow guide members (20) are arranged between the medium conveying assembly and the combustion chamber (4), the medium conveying assembly, the combustion chamber (4) and the air flow guide members (20) form a bleed air channel (21), and the bleed air channel (21) is communicated with the accommodating cavity (A) and enables oil and gas to be mixed in the first channel (B) under the action of the medium throwing-out assembly (8).

6. The medium delivery apparatus of a micro turbojet engine according to claim 1 or 5, wherein the medium ejection assembly (8) comprises:

a disk member (8a) provided with a mounting hole, the disk member (8a) being provided on the rotary shaft (2);

an oil slinging member (8b), the oil slinging member (8b) being provided on an axial end face of the disc-shaped member (8a) facing the rear bearing (7);

and a gas-throwing part (8c), wherein the gas-throwing part (8c) is arranged on the axial end face of the disc-shaped part (8a) facing the combustion chamber (4).

7. The medium delivery device of the micro turbojet engine according to claim 5, wherein the airflow guide member (20) comprises a first tubular member (20a) and a first guide block (20b), the first tubular member (20a) is penetrated by the oil supply pipe (9), the first guide block (20b) is arranged on the peripheral surface of the first tubular member (20a), one end of the first tubular member (20a) and one end of the first guide block (20b) are fixed to the medium delivery assembly, and one end of the first tubular member (20a) and one end of the first guide block (20b) abut against the axial end of the combustion chamber (4).

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