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Turbofan engine with mode adjusting capacity

An adjustment capability, turbofan technology, applied in the direction of machine/engine, gas turbine device, mechanical equipment, etc., can solve the problems of single working state, limited working range, small flight envelope, etc., to reduce fuel consumption and widen the flight envelope. line effect

Pending Publication Date: 2019-06-07
SHENYANG JIANZHU UNIVERSITY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The traditional turbofan engine is mainly composed of high-pressure and low-pressure systems. Both the high-pressure and low-pressure systems include a stator system and a rotor system. The stator systems of the high-pressure and low-pressure systems are connected to each other through components such as casings to form a unified stator system; The rotor systems of the high and low pressure systems are respectively arranged on their respective bearings to form two independent rotating systems. Although the two rotor systems are structurally independent and do not affect each other when they work, the working state of the engine is relatively single, and the flight The envelope is small, although several stages of imported adjustable blades are designed on the fan and compressor of the engine, the overall adjustment ability of the engine is still relatively limited
From the perspective of use requirements and future development trends, traditional turbofan engines are difficult to adapt to the multi-task development requirements of future aircraft due to their limited working range and relatively single working state

Method used

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  • Turbofan engine with mode adjusting capacity
  • Turbofan engine with mode adjusting capacity
  • Turbofan engine with mode adjusting capacity

Examples

Experimental program
Comparison scheme
Effect test

Embodiment approach 1

[0014] Implementation Mode 1: Combining the attached figure 1 with figure 2 , when the aircraft takes off with a full load or requires a large thrust, the first clutch 12 is disconnected, the second clutch 13 is connected, and the low-pressure turbine 9 transmits torque to the fan 2 through the low-pressure turbine shaft 16 to drive it to work. At this time, the engine is in a normal state. In the working mode, the high-pressure system 19 and the low-pressure system 20 work at the same time, and the engine generates thrust simultaneously from the external and internal airflows, and the thrust is maximum.

Embodiment approach 2

[0015] Implementation Mode 2: Combining the attached figure 1 with image 3 , when the aircraft requires the engine to provide a medium thrust level, the first clutch 12 is connected, and the second clutch 13 is disconnected. At this time, the high-voltage system 19 is switched to drive the fan 2. Since the high-voltage system 19 needs to output part of the power to the fan 2, so the high-pressure system 19 will rotate at a reduced speed, and the engine will generate thrust from the high-pressure system 19 and the fan 2.

Embodiment approach 3

[0016] Implementation Mode Three: Combining the Attached figure 1 with Figure 4 , when the aircraft is under light load or low-speed cruise, the engine only needs to provide thrust that meets the minimum requirements. At this time, both the first clutch 12 and the second clutch 13 are disconnected, the fan 2 stops rotating, and only the high-voltage system 19 works alone , the thrust of the engine comes from the internal high-temperature gas flow, and the thrust is the minimum at this time.

[0017] The aircraft engine of the present invention is designed with two clutches such as the first clutch 12 and the second clutch 13 altogether, and both clutches can realize connecting and driving with the fan 2, but the two clutches belong to the high pressure system 19 and the low pressure system 20 respectively. Two different rotor systems, so when the engine is working, it must be ensured that only one of the first clutch 12 and the second clutch 13 can be connected to the fan 2 ...

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Abstract

The invention relates to an aviation power device, in particular to a turbofan engine with a mode adjusting capacity. The technical scheme include the following details that the turbofan engine comprises a high pressure system, a low pressure system and a force bearing system; the high pressure system comprises a high pressure gas compressor, a combustion chamber, a high pressure turbine and a first clutch; the low pressure system comprises a fan, a low pressure turbine and a second clutch; the force bearing system comprises a front machine case, a medium machine case and a turbine rear machine case; the high pressure system forms a rotating system through a third bearing and a fourth bearing; the high pressure gas compressor is connected with one end of the first clutch through a front journal, and the other end of the first clutch is connected wit the fan; the low pressure system forms a rotating system through a first bearing, a second bearing and a fifth bearing; and one end of thesecond clutch is connected with the fan, and the other end of the second clutch is connected with a shaft of the low pressure turbine. The turbofan engine with the mode adjusting capacity has the advantages of being wide in flight envelope, high in adaptability and wide in application range and possessing many working states.

Description

technical field [0001] The invention relates to an aerodynamic device, in particular to a turbofan engine with mode adjustment capability. Background technique [0002] Turbofan engine is an important structural type of aeroengine, which is widely used because of its high propulsion efficiency and high thrust. The traditional turbofan engine is mainly composed of high-pressure and low-pressure systems. Both the high-pressure and low-pressure systems include a stator system and a rotor system. The stator systems of the high-pressure and low-pressure systems are connected to each other through components such as casings to form a unified stator system; The rotor systems of the high and low pressure systems are respectively arranged on their respective bearings to form two independent rotating systems. Although the two rotor systems are structurally independent and do not affect each other when they work, the working state of the engine is relatively single, and the flight The...

Claims

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Application Information

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IPC IPC(8): F02C3/107F02C3/113F02C7/36F02K3/06
Inventor 田大可金路范小东刘士明张宇张岩
Owner SHENYANG JIANZHU UNIVERSITY
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