CN216198528U - Case contra-rotating turbofan aircraft engine - Google Patents

Abstract

A kind of case contra-rotating turbofan aircraft engine, does not need to increase the rotational speed while improving the engine thrust, its high-pressure shaft is fitted on the outside of low-pressure shaft coaxially, intake cone, fan and disk motor are installed on engine air suction end axis body of the low-pressure shaft from outside to inside; the low-pressure turbine and the tail cone are arranged on an engine exhaust end shaft body of the low-pressure shaft from outside to inside; the air compressor is arranged on an engine air suction end shaft body of the high-pressure shaft; the high-pressure turbine is arranged on an engine exhaust end shaft body of the high-pressure shaft; the inner culvert casing is coaxially sleeved on the outer side of the high-pressure shaft, and the gas compressor, the high-pressure turbine, the low-pressure turbine and the tail cone are positioned on the inner side of the inner culvert casing; the outer culvert casing is coaxially sleeved on the outer side of the front part of the inner culvert casing, and the rear part of the air inlet cone, the fan and the disc type motor are positioned on the inner side of the outer culvert casing; the outer culvert casing opposite to the disc motor is provided with an annular slit, and the rotatable casing is coaxially sleeved on the outer side of the disc motor and is positioned in the annular slit; the root of the contra-rotating guide blade is fixedly connected with the outer rotor of the disc motor, and the tip of the contra-rotating guide blade is fixedly connected with the rotatable casing.

Description

Case contra-rotating turbofan aircraft engine

Technical Field

The utility model belongs to the technical field of design and manufacture of aero-engines, and particularly relates to a case contra-rotating turbofan aero-engine.

Background

The turbofan engine can provide larger thrust compared with other types of engines, and the turbofan engine with a high bypass ratio can have lower fuel consumption, and the thrust generated by a fan of the turbofan engine with the high bypass ratio can reach more than 78%. The sum of the aerodynamic forces of the air flow flowing through the interior of the engine on the engine is known as the thrust, and then according to the impulse theorem, the thrust is equal to the mass multiplied by the speed, so that the essence of improving the thrust is two aspects, namely improving the mass flow Q of the air flowing through the engine in unit time, improving the speed difference v of the air flow flowing through the engine before and after the speed difference is improved, and improving the rotating speed of the engine. For increasing the mass flow, the flow can be increased by only increasing the airflow inlet area S and the fan diameter of the engine, so that the air flow of the engine is mainly increased by increasing the size of the blades of the engine at present. However, the size of the fan is a limiting factor and there is a fatal drawback in that the low pressure turbine must be made large in order to have sufficient rim work because the fan is directly mechanically connected to the low pressure turbine and thus rotates at the same speed. It is known that the increase of the low pressure turbine makes the slip between the high pressure and the low pressure too large and the flow passage between the high pressure and the low pressure turbine becomes steep or else a long transition section is used, which inevitably worsens the rotordynamic performance, and the larger the inlet diameter, the larger the whole engine and therefore the larger the engine weight. This therefore limits the possibility of an infinite increase of the low-pressure turbine. In addition, the tangential velocity of the blade tip is also easily supersonic, and the shock wave brought by the supersonic velocity generates high noise, which obviously has adverse effects on the personnel in the aircraft and the environment around an airport. At the present stage, the turbofan engines of the existing models overcome the limiting factor of the tangential speed of the blade tips as much as possible, but the rotating speed of the engine is reduced while the propelling efficiency is improved, and the problem of high noise caused by high rotating speed of the turbofan engines of the existing models is not solved all the time.

SUMMERY OF THE UTILITY MODEL

Aiming at the problems in the prior art, the utility model provides a box contra-rotating turbofan aircraft engine, which improves the thrust of the engine without increasing the rotating speed of the engine, and further solves the problem of high noise caused by high rotating speed.

In order to achieve the purpose, the utility model adopts the following technical scheme: a case contra-rotating turbofan aircraft engine comprises a low-pressure shaft, a high-pressure shaft, an air inlet cone, a fan, a disc type motor, contra-rotating guide blades, a rotatable case, an outer culvert case, an inner culvert case, a gas compressor, a high-pressure turbine, a low-pressure turbine and a tail cone; the high-pressure shaft is coaxially sleeved on the outer side of the low-pressure shaft, and the air inlet cone, the fan and the disc type motor are sequentially arranged on a shaft body at the air suction end of the engine of the low-pressure shaft from outside to inside; the low-pressure turbine and the tail cone are sequentially arranged on an engine exhaust end shaft body of the low-pressure shaft from outside to inside; the compressor is arranged on an engine air suction end shaft body of the high-pressure shaft; the high-pressure turbine is arranged on an engine exhaust end shaft body of the high-pressure shaft; the inner culvert casing is coaxially sleeved on the outer side of the high-pressure shaft, and the gas compressor, the high-pressure turbine, the low-pressure turbine and the tail cone are all positioned on the inner side of the inner culvert casing; the outer culvert casing is coaxially sleeved on the outer side of the front part of the inner culvert casing, and the rear part of the air inlet cone, the fan and the disc type motor are all positioned on the inner side of the outer culvert casing; the outer culvert casing opposite to the disc motor is provided with an annular slot, and the rotatable casing is coaxially sleeved on the outer side of the disc motor and is positioned in the annular slot of the outer culvert casing; the blade root part of the contra-rotating guide blade is fixedly connected with an outer rotor of the disc type motor, and the blade tip part of the contra-rotating guide blade is fixedly connected with the inner surface of the rotatable casing.

The utility model has the beneficial effects that:

the case contra-rotating turbofan aircraft engine provided by the utility model has the advantages that the thrust of the engine is improved, the rotating speed of the engine is not required to be increased, and the problem of high noise caused by high rotating speed is further solved.

Drawings

FIG. 1 is a schematic structural view of a case-to-case turbofan aircraft engine of the present invention;

in the figure, 1-low pressure shaft, 2-high pressure shaft, 3-inlet cone, 4-fan, 5-disc motor, 6-contra-rotating guide vane, 7-rotatable casing, 8-outer culvert casing, 9-inner culvert casing, 10-compressor, 11-high pressure turbine, 12-low pressure turbine, 13-tail cone.

Detailed Description

The utility model is described in further detail below with reference to the figures and the specific embodiments.

As shown in fig. 1, a casing contra-rotating turbofan aircraft engine comprises a low-pressure shaft 1, a high-pressure shaft 2, an air inlet cone 3, a fan 4, a disc motor 5, contra-rotating guide blades 6, a rotatable casing 7, an outer culvert casing 8, an inner culvert casing 9, an air compressor 10, a high-pressure turbine 11, a low-pressure turbine 12 and a tail cone 13; the high-pressure shaft 2 is coaxially sleeved on the outer side of the low-pressure shaft 1, and the air inlet cone 3, the fan 4 and the disc type motor 5 are sequentially arranged on an engine air suction end shaft body of the low-pressure shaft 1 from outside to inside; the low-pressure turbine 12 and the tail cone 13 are sequentially arranged on an engine exhaust end shaft body of the low-pressure shaft 1 from outside to inside; the compressor 10 is arranged on an engine air suction end shaft body of the high-pressure shaft 2; the high-pressure turbine 11 is mounted on an engine exhaust end shaft body of the high-pressure shaft 2; the culvert casing 9 is coaxially sleeved on the outer side of the high-pressure shaft 2, and the compressor 10, the high-pressure turbine 11, the low-pressure turbine 12 and the tail cone 13 are all positioned on the inner side of the culvert casing 9; the culvert casing 8 is coaxially sleeved on the outer side of the front part of the culvert casing 9, and the rear part of the air inlet cone 3, the fan 4 and the disc motor 5 are all positioned on the inner side of the culvert casing 8; an annular slit is formed in the culvert casing 8 opposite to the disc motor 5, and the rotatable casing 7 is coaxially sleeved on the outer side of the disc motor 5 and is positioned in the annular slit of the culvert casing 8; the root part of the contra-rotating guide blade 6 is fixedly connected with the outer rotor of the disc motor 5, and the tip part of the contra-rotating guide blade 6 is fixedly connected with the inner surface of the rotatable casing 7.

The one-time use process of the present invention is described below with reference to the accompanying drawings:

in order to increase the thrust of the engine, during the operation of the engine, the disc motor 5 is started, the counter-rotating guide blades 6 and the rotatable casing 7 are driven by the disc motor 5 to rotate synchronously, and the counter-rotating guide blades 6 need to rotate relative to the front fan 4, during the relative rotation of the counter-rotating guide blades 6 and the fan 4, the front fan 4 is used for sucking air, and the rear counter-rotating guide blades 6 are used for blowing out the incoming flow again, so as to increase the relative rotation speed of the fan 4. The disc motor 5 is controlled independently of the main engine power system.

In the practical application process, the too high or too low rotating speed of the rear contra-rotating guide blades 6 relative to the front fan 4 may affect the performance of the engine, so that the rotating speed of the contra-rotating guide blades 6 and the rotating speed of the fan 4 need to be constantly ensured to be in optimal fit, and the performance of the engine can be ensured to be in the most stable state. Specifically, the rotation speed of the front fan 4 is represented as N1, the rotation speed of the rear counter-rotating guide blades 6 is represented as N2, and N2 is equal to T/Tmax · N1, where T is the current thrust of the engine and Tmax is the maximum thrust provided by the engine.

Through the rotational speed of control contra-rotating guide vane 6 that disk motor 5 can be convenient, make the engine performance more stable, when the engine need increase thrust, only need start disk motor 5 and drive contra-rotating guide vane 6 rotate can, compare with traditional turbofan engine, need not obtain bigger thrust through pure increase engine speed, avoid increasing the load of engine.

In addition, compared with the traditional turbofan engine, the thrust of the engine can be increased only by relatively rotating the rotary guide blades 6 and the fan 4 without increasing the rotating speed of the engine, so that the noise cannot be increased in the thrust increasing process of the engine, the oil consumption cannot be increased while the performance is improved, and compared with the traditional turbofan engine, about 30% of oil consumption is saved under the same engine thrust, so that the power consumption of the turbofan engine is lower.

Furthermore, the engine thrust is increased while the engine rotating speed is not required to be increased, so that the overall level of the rotating speed of the engine is reduced, the service life of the engine is prolonged, and the requirements on the strength of the relevant structure of the engine are correspondingly reduced, so that the relevant structure of the engine can be replaced by a light material, the structural part is lightened and thinned while the strength and the rigidity are ensured, the weight of the engine can be further reduced, and the thrust-weight ratio of the engine can be finally improved.

The embodiments are not intended to limit the scope of the present invention, and all equivalent implementations or modifications without departing from the scope of the present invention are intended to be included in the scope of the present invention.

Claims (1)

1. The utility model provides a machine casket is to rotating turbofan aircraft engine which characterized in that: the device comprises a low-pressure shaft, a high-pressure shaft, an air inlet cone, a fan, a disc type motor, counter-rotating guide blades, a rotatable casing, an outer culvert casing, an inner culvert casing, a gas compressor, a high-pressure turbine, a low-pressure turbine and a tail cone; the high-pressure shaft is coaxially sleeved on the outer side of the low-pressure shaft, and the air inlet cone, the fan and the disc type motor are sequentially arranged on a shaft body at the air suction end of the engine of the low-pressure shaft from outside to inside; the low-pressure turbine and the tail cone are sequentially arranged on an engine exhaust end shaft body of the low-pressure shaft from outside to inside; the compressor is arranged on an engine air suction end shaft body of the high-pressure shaft; the high-pressure turbine is arranged on an engine exhaust end shaft body of the high-pressure shaft; the inner culvert casing is coaxially sleeved on the outer side of the high-pressure shaft, and the gas compressor, the high-pressure turbine, the low-pressure turbine and the tail cone are all positioned on the inner side of the inner culvert casing; the outer culvert casing is coaxially sleeved on the outer side of the front part of the inner culvert casing, and the rear part of the air inlet cone, the fan and the disc type motor are all positioned on the inner side of the outer culvert casing; the outer culvert casing opposite to the disc motor is provided with an annular slot, and the rotatable casing is coaxially sleeved on the outer side of the disc motor and is positioned in the annular slot of the outer culvert casing; the blade root part of the contra-rotating guide blade is fixedly connected with an outer rotor of the disc type motor, and the blade tip part of the contra-rotating guide blade is fixedly connected with the inner surface of the rotatable casing.

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