A hot end structure of an engine

Abstract

The invention discloses an engine hot end structure. The engine hot end structure comprises a turbine machine case arranged between a gas turbine outer ring and a combustion chamber machine case, a combustion chamber outer secondary flow channel is formed by space between the turbine machine case and a combustion chamber inner ring, a turbine machine case inner cavity is formed by space between the turbine machine case and a turbine end component, and a lubricating oil pipeline of a lubricating oil system and / or a gas pipeline of an air system is arranged in the turbine machine case inner cavity. A body of the turbine machine case is a rotation type turbine machine case, bumps are locally arranged on the part, corresponding to the lubricating oil pipeline and / or the gas pipeline, of the circumference of the body of the turbine machine case, the space of the turbine machine case inner cavity is locally enlarged through the bumps, and the radial size of the circumference part except the bumps is smaller than the radial size of the bumps. According to the engine hot end structure, the inner diameter of a combustion chamber can be reduced, and the outer diameter size of an engine can be reduced; and the intermediate diameter of a low-pressure turbine is increased, and the acting capacity of the low-pressure turbine is improved; and the axial length of a low-pressure shaft system of the engine is reduced, the dynamic characteristic of an engine rotor is improved, and the engine performance is improved.

Description

technical field [0001] The invention relates to gas turbines, especially the field of combustion chambers and turbines of high-temperature parts of aero-engines. More specifically, the invention adopts a new type of turbine casing structure, improves the structural layout of the hot end of aero-engines, and makes the engine structure more compact. By adopting this structure, the axial length of the low-pressure shafting system of the engine can be shortened, thereby improving the rotor dynamics characteristics of the engine and improving the engine performance. Background technique [0002] In a gas turbine, especially an aero-engine, the turbine casing is one of its internal important structures. According to different engine structure designs, the main functions of the turbine casing include: supporting the outer ring of the gas turbine and transmitting the axial force of the high-pressure turbine; separating the turbine components and the combustion chamber to form the ma...

AI Technical Summary

Problems solved by technology

In order to meet the requirements of engine outer diameter limitation, low-pressure turbine working ability and lubricating oil pipeline arrangement, the common practice is to move the low-pressure turbine shaft backward to increase the inner cavity space of the turbine case, but this will lengthen the length of the low-pressure shaft system of the engine

Too long low-pressure shafting of the engine will lead to poor rotor dynamics, increase the difficulty of engine design, and also make processing very difficult

The existence of constraints in various aspects limits the further improvement of modern engine performance

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