Common cavity type aero-engine bearing seat and aero-engine with same

Abstract

The invention discloses a common cavity type aero-engine bearing seat and an aero-engine with the same, the bearing seat is of a rotary body structure, a bearing cavity is formed between the bearing seat and a first rotating shaft and between the bearing seat and a second rotating shaft, and the first rotating shaft and the second rotating shaft are sequentially arranged on the axis of the bearing cavity; the bearing seat comprises a first bearing set and a second bearing set which are arranged on the first rotating shaft and the second rotating shaft in a sleeving mode respectively and used for supporting the first rotating shaft and the second rotating shaft. By reducing the number of bearing pedestals of the aviation gas turbine engine, multiple sets of bearing pedestals in the prior art are integrated into one bearing pedestal, the overall structure size and weight of the engine can be effectively controlled, the structure is simplified, maintenance is convenient, and cost input is reduced; meanwhile, the complexity and the load of a lubricating system can be reduced through the simplified bearing seat structure, the using amount of sealing cold air is reduced, and then the power and the efficiency of an engine are indirectly improved.

Description

technical field [0001] The invention belongs to the technical field of gas turbine engines, and in particular relates to a common-cavity aero-engine bearing seat and an aero-engine with the same. Background technique [0002] Existing gas turbine engines belong to high-temperature, high-pressure and high-rotational rotary power machines. In order to ensure the high-speed rotation of the engine rotor, support bearings must be used at the front and rear ends of the rotor; correspondingly, bearing seats are required to install the bearings, accept the rotor and stator, and transmit the rotor load. At the same time, the bearing seat also needs to undertake the functions of lubricating the bearing, sealing and cooling. [0003] Most of the current gas turbine engines have a double-rotor or even three-rotor structure, with a large number of bearings and a compact space distribution. A single bearing seat only supports one bearing or a bloated structure that supports the bearings ...

AI Technical Summary

Problems solved by technology

[0003] Most of the current gas turbine engines have a double-rotor or even three-rotor structure, with a large number of bearings and a compact space distribution. A single bearing seat only supports one bearing or a bloated structure that supports the bearings on the same rotor. It is difficult to meet the increasing power of the engine, thrust-to-weight ratio and lower emission requirements

First of all, multiple bearings require multiple bearing housings to support the structure, which increases the number of stator parts, increases the weight of the engine, complicates the assembly, increases the cost, and reduces the maintainability

Each bearing cavity needs to meet separate lubrication, sealing and ventilation functions, and needs to be equipped with independent oil supply and oil return structures, which increases the load and complexity of the accessory lubricating oil system; additional sealing required for multiple bearing seats The bleed air consumes the compression work of the engine, reduces the gas flow in the main channel, and then reduces the power and efficiency of the engine

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