CN218760158U - Engine with variable bypass ratio realized by motor with rotating booster stage - Google Patents

Abstract

The utility model discloses an engine that changes duct ratio is realized to pressure boost level by motor area, include, the utility model discloses a main part, air inlet, fan, pressure boost level, motor, high pressure compressor, core machine, interior duct, combustion chamber, low pressure turbine and spray tube, the utility model discloses a set up the motor in pressure boost level bottom, rotate through the rotational speed that drives pressure boost level by motor independence, reduced low pressure turbine's load to make the engine adapt to different flight status through the rotational speed that control motor drove pressure boost level, reached and reduced holistic complexity, reduced low pressure turbine's load simultaneously, and effectively reduced complete machine weight, reduced whole machine size to and the mode of independent control motor area change pressure boost level is favorable to the beneficial effect of unsteady state processes such as complete machine start, acceleration and deceleration, especially air start very much.

Description

Engine with variable bypass ratio realized by motor with rotating booster stage

Technical Field

The utility model relates to an engine correlation field specifically is an engine that changes bypass ratio is realized to pressure boost level by motor area.

Background

The engine is a machine capable of converting other forms of energy into mechanical energy, and comprises an internal combustion engine (a reciprocating piston engine), an external combustion engine (a stirling engine, a steam engine and the like), a jet engine, an electric motor and the like, wherein the internal combustion engine converts chemical energy into mechanical energy, and the engine is suitable for a power generation device and can also refer to the whole machine comprising a power device (such as a gasoline engine and an aeroengine), and one of the variable bypass engines is the engine.

The variable ducted engine greatly improves the design difficulty due to the very complicated structure, and meanwhile, the variable ducted engine has large control difficulty, and the low-pressure turbine of the variable cycle engine needs to convert partial kinetic energy into mechanical energy for driving a fan, so that the load of the voltage turbine is increased, the volume of the whole engine is improved, and the design difficulty of the low-pressure turbine is also increased.

SUMMERY OF THE UTILITY MODEL

Therefore, in order to solve the above-mentioned insufficiency, the utility model discloses it changes bypass ratio's engine to provide a pressure boost level by the motor area here.

The utility model discloses a realize like this, construct one kind and change the engine that the duct ratio was compared by motor area change booster stage, the device includes main part, air inlet, fan and low pressure turbine, the inboard rotation of main part installs the booster stage, the air inlet sets up in the inboard left end of main part, and the air inlet link up in interior duct inboard, the fan is installed in the main part left end in, the booster stage is connected on motor top output shaft, and the booster stage is located the high pressure compressor left side, the motor fastens in the main part bottom, the high pressure compressor is installed inside interior duct, and the high pressure compressor sets up in the core machine outside, the core machine sets up inside the combustion chamber, interior duct sets up right-hand member in the main part inboard, the combustion chamber sets up in the inboard right-hand member of interior duct, and the combustion chamber link up with the spray tube inboard mutually, low pressure turbine installation main part inboard right-hand member, and low pressure turbine are located the spray tube left side, the spray tube fastens in the main part right-hand member.

Preferably, the middle of the bottom end face of the booster stage and the output shaft at the top of the motor are located on the same Z axis.

Preferably, the nozzle and the fan are arranged coaxially.

Preferably, the inner side of the air inlet is tapered from left to right.

Preferably, a generator may be disposed outside the main body, and the generator is connected to the motor.

Preferably, the inner side of the spray pipe is tapered from left to right.

The utility model has the advantages of as follows: the utility model discloses an improve and provide an engine that is changed the bypass ratio by the motor area changes the booster stage and realizes here, compare with equipment of the same type, have following improvement:

an engine that changes duct ratio is realized to pressure boost level by motor area, through having set up the motor in pressure boost level bottom, rotate through independently driving pressure boost level by the motor, the load of low pressure turbine has been reduced, and the rotational speed that drives pressure boost level through the control motor makes the engine adapt to different flight status, reached and reduced holistic complexity, reduce low pressure turbine's load simultaneously, and effectively reduced complete machine weight, the whole machine size has been reduced, and the mode of independent control motor area commentaries on classics pressure boost level, be favorable to the complete machine to start very much, add the deceleration, especially the beneficial effect of unsteady state processes such as aerial start.

Drawings

Fig. 1 is a schematic structural view of the present invention.

Wherein: the device comprises a main body-1, an air inlet-2, a fan-3, a booster stage-4, a motor-5, a high-pressure compressor-6, a core machine-7, an inner duct-8, a combustion chamber-9, a low-pressure turbine-10 and a spray pipe-11.

Detailed Description

The present invention will be described in detail with reference to the accompanying fig. 1, and the technical solutions in the embodiments of the present invention will be clearly and completely described, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

The utility model discloses a realize like this, construct one kind and realize the engine that becomes the duct ratio by motor area commentaries on classics booster stage, the device includes main part 1, air inlet 2, fan 3 and low pressure turbine 10, 1 inboard rotation in main part installs booster stage 4, air inlet 2 sets up in 1 inboard left end in main part, and air inlet 2 link up in interior duct 8 inboardly, fan 3 installs the left end in 1 inside of main part, booster stage 4 is connected in on motor 5 top output shaft, and booster stage 4 is located high pressure compressor 6 left side, motor 5 fastens in 1 bottom of main part, high pressure compressor 6 installs inside interior duct 8, and high pressure compressor 6 sets up in the core machine 7 outside, core machine 7 sets up inside combustion chamber 9, interior duct 8 sets up right-hand member in main part 1 inboard, combustion chamber 9 sets up in interior duct 8 inboard right-hand member, and combustion chamber 9 link up with 11 inboard mutually in spray tube, low pressure turbine 10 installs the inboard right-hand member of main part 1, and low pressure turbine 10 is located spray tube 11 left sides, spray tube 11 right-hand members in spray tube 11.

Furthermore, the middle part of the bottom end face of the booster stage 4 and the output shaft at the top of the motor 5 are positioned on the same Z axis, so that the motor 5 can drive the booster stage 4 to stably rotate.

Furthermore, the nozzle 11 and the fan 3 are coaxially arranged, so that the air can flow in the fan 3 and the nozzle 11 conveniently.

Further, the inner side of the air inlet 2 is tapered from left to right, and a larger amount of air enters the air inlet 2.

Furthermore, a generator can be arranged outside the main body 1 and connected to the motor 5, so that the motor 5 can be started independently.

Furthermore, the inner side of the spray pipe 11 is tapered from left to right, so that high-temperature and high-pressure gas can be discharged outwards conveniently.

The utility model provides an engine which realizes variable bypass ratio by the motor with a pressure boosting stage through improvement, and the working principle is as follows;

firstly, the engine can be integrally arranged at a designated position on an external airplane, and a generator can be arranged on the device and connected with the motor 5;

secondly, in the use process of the engine, external gas can be introduced into the inner duct 8 through the gas inlet 2, the temperature and the pressure of the gas are raised through the booster stage 4 and the high-pressure compressor 6, the gas is mixed and combusted with fuel in the combustion chamber 9 to form high-temperature and high-pressure gas, the high-temperature and high-pressure gas enters the gas turbine and the free turbine to expand, the gas turbine drives the high-pressure compressor 6, the low-pressure turbine 10 drives the fan, the motor 5 drives the booster stage 4 to rotate, and meanwhile, the configuration can be provided with a generator, and the generator can directly provide electricity needed by the motor 5;

thirdly, in the use process of the engine, the rotating speed of the motor 5 can be adjusted to adjust the rotating speed of the booster stage 4, so that the flow of the inner duct 8 is changed, and further the duct ratio of the engine is changed, when the engine climbs, accelerates and flies at supersonic speed, the rotating speed of the motor is increased to increase the flow of the inner duct 8, so that the duct ratio of the engine is reduced, the duct ratio is as small as possible to approach the performance of a turbojet engine, and the thrust of the engine is increased; during takeoff and subsonic flight, the bypass ratio of the engine is improved by reducing the rotating speed of the motor 5 and reducing the flow of the inner bypass 8, the oil consumption of the airplane is reduced, and the range of the airplane is improved.

The utility model discloses an improve and provide an engine that changes bypass ratio is realized to pressure boost level by motor area commentaries on classics, rotate through by motor 5 independent drive pressure boost level 4, the load of low pressure turbine 10 has been reduced, and drive the rotational speed of pressure boost level 4 through control motor 5 and make the engine adapt to different flight states, reached and reduced holistic complexity, reduce low pressure turbine 10's load simultaneously, and effectively reduced complete machine weight, the whole machine size has been reduced, and the mode of independent control motor 5 area commentaries on classics pressure boost level, be favorable to the complete machine to start very much, add the deceleration, especially the beneficial effect of unsteady state processes such as aerial start.

The basic principle and the main characteristics of the utility model and the advantages of the utility model have been shown and described above, and the utility model discloses the standard part that uses all can purchase from the market, and dysmorphism piece all can be customized according to the record of the description with the drawing, and the concrete connection mode of each part all adopts conventional means such as ripe bolt rivet among the prior art, welding, and machinery, part and equipment all adopt prior art, conventional model, and conventional connection mode in the prior art is adopted in addition to circuit connection, and the details are not repeated here.

The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims (6)

1. The utility model provides an engine that changes bypass ratio is realized to pressure boost level by the motor area which characterized in that: the structure of the high-pressure gas turbine engine comprises a main body (1), a gas inlet (2), a fan (3) and a low-pressure turbine (10), wherein a boosting stage (4) is rotatably mounted on the inner side of the main body (1), the gas inlet (2) is arranged at the left end of the inner side of the main body (1), the gas inlet (2) is communicated with the inner side of an inner duct (8), the fan (3) is mounted at the left end of the inner portion of the main body (1), the boosting stage (4) is connected to an output shaft at the top of a motor (5), the boosting stage (4) is located at the left side of a high-pressure gas compressor (6), the motor (5) is fastened to the bottom of the main body (1), the high-pressure gas compressor (6) is mounted inside the inner duct (8), the high-pressure gas compressor (6) is arranged on the outer side of a core machine (7), the core machine (7) is arranged inside a combustion chamber (9), the inner duct (8) is arranged at the right end of the inner side of the main body (1), the combustion chamber (9) is arranged at the right end of the inner duct (8), the combustion chamber (9) is fastened to the inner side of the main body (10), the low-pressure turbine engine (1), the left end face of the main body (11) is arranged at the right end face of the main body (11), and the low-pressure turbine engine (1).

2. The engine with the variable bypass ratio realized by the motor with the boost pressure stage according to claim 1 is characterized in that: the middle part of the bottom end surface of the booster stage (4) and an output shaft at the top of the motor (5) are positioned on the same Z axis.

3. The engine with the variable bypass ratio realized by the motor driven pressure boosting stage according to claim 1 is characterized in that: the spray pipe (11) and the fan (3) are coaxially arranged.

4. The engine with the variable bypass ratio realized by the motor with the boost pressure stage according to claim 1 is characterized in that: the inner side of the air inlet (2) is gradually reduced from left to right.

5. The engine with the variable bypass ratio realized by the motor with the boost pressure stage according to claim 1 is characterized in that: the outer side of the main body (1) can be provided with a generator which is connected with the motor (5).

6. The engine with the variable bypass ratio realized by the motor driven pressure boosting stage according to claim 1 is characterized in that: the inner side of the spray pipe (11) is gradually reduced from left to right.

Images