Gas-compressor multistage stationary-blade regulating mechanism allowing gear transmission

Abstract

The invention provides a gas-compressor multistage stationary-blade regulating mechanism allowing gear transmission in the technical field of aero-engines. The gas-compressor multistage stationary-blade regulating mechanism comprises a casing, a driving mechanism and a transmission mechanism, wherein the casing is provided with an output mechanism, and the driving mechanism and the transmission mechanism are fixedly installed on the outside of the casing. One end of the output mechanism is radially installed in the casing, the other end of the output mechanism is connected with the transmission mechanism located outside the casing, and the driving mechanism is axially installed outside the casing, is connected with the transmission mechanism and transmits power. The gas-compressor multistage stationary-blade regulating mechanism not only is compact and small in required motion space, and rocker arms will not deform in motion processes, so that the service life of the gas-compressor multistage stationary-blade regulating mechanism is prolonged, and accuracy of the gas-compressor multistage stationary-blade regulating mechanism is improved.

Description

technical field [0001] The invention relates to a device in the field of aero-engine technology, in particular to a multi-stage vane adjustment mechanism for a compressor with gear transmission. Background technique [0002] With the continuous improvement of aircraft requirements for aero-engines, the performance indicators of compressor components are also continuously improved. Especially in the case of ensuring a certain stable working margin, the substantial increase in load level and efficiency requirements makes the design extremely difficult. When an aero-engine is working at a non-design point, there will be a mismatch between adjacent stages of the axial flow compressor, causing airflow instability, and in extreme cases, even surge, which may cause serious mechanical damage. In engineering applications, using adjustable inlet guide vanes and vanes to delay compressor stall and expand the stability margin can not only achieve the purpose of panting prevention, but ...

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Problems solved by technology

[0004] After searching the existing technology, it is found that the existing compressor stator blade adjustment mechanism (such as patent document number EP1724471A3, US20050135926A1, US20050135926A1, US2999630, US20110182715) has the following problems: the linkage ring and the stationary blade rocker are connected by a flexible rocker, that is, The rocker arm is deformed during the movement, which not only reduces the accuracy of the blade adjustment structure, but also reduces the life and reliability of the mechanism; the driving mechanism of the linkage ring occupies a large movement space

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