Load compressor configuration

By designing independent rotor support structure and volute shell optimization, the problem of load compressor components cannot be independently designed and have poor stability is solved, and efficient production and stability and lightweight of the rotor system are achieved.

CN116538131BActive Publication Date: 2025-08-29AECC HUNAN AVIATION POWERPLANT RES INST
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Patent Information

Application Number
CN202310469555.X
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2023-04-27
Publication Date
2025-08-29
Estimated Expiration
2043-04-27

AI Technical Summary

Technical Problem

The existing load compressor components are not designed as independent component units and cannot be independently produced, assembled, transported and sold. The rotor system is weak in rigidity, poor stability, and the volute shell design leads to a large weight.

Method used

A load compressor mechanism is designed, and a rotor assembly is used to form a simple supporting structure with independent bearing receivers and intake receivers. The rotor assembly is supported by front and rear bearings, equipped with a tie rod assembly and a sealing ring disc. The volute and intake receiver are integrated to form an independent rotor system and optimize the volute cross-section design.

Benefits of technology

The independent unit body design is realized, adaptability and production efficiency are improved, the rigidity and stability of the rotor system are enhanced, and weight and preparation costs are reduced.

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Abstract

The present invention discloses a load compressor configuration, comprising: a rotor assembly, and a first bearing casing and an air intake casing relatively spaced apart and installed on the outer circles at both ends of the rotor assembly. The power input end of the rotor assembly is supported on the first bearing casing through a front bearing, and the power output end of the rotor assembly is supported on the air intake casing through a rear bearing to form an independent rotor support structure. The power input end of the rotor assembly can also be detachably connected to the upstream power input system, and the power output end of the rotor assembly can also be detachably connected to the downstream power output system to ensure the input and output of the load compressor power. The present invention can form an independent rotor system, ensure an independent unit design, and then can be quickly adapted to auxiliary power units of different models and powers, with a wide range of adaptability; the rotor assembly has a short fulcrum span and strong rigidity, ensuring that the rotor system has sufficient critical speed margin.
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