Floating structure of high-temperature hot end connector of aero-engine
A technology of aero-engine and floating structure, which is applied in the direction of engine components, machines/engines, mechanical equipment, etc., can solve the problems of thermal expansion and deformation of aero-engine hot-end connectors, and achieve improved test pass rate, reliable operation, and safe and reliable use Effect
Inactive Publication Date: 2017-03-08
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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[0003] This invention designs a floating connection structure of high-temperature hot-end parts of aero-engines to solve the problem of thermal expansion and deformation of hot-end connectors of aero-engines
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[0025] The connector structure has a floating function in the high temperature working state. The core components of the floating function are the floating bracket 1 and the spacer bushing 2; a certain amount of thermal expansion gap is reserved for the initial assembly of the floating bracket 1 and the spacer bushing 2 in the stationary state of the engine. The internal thin-walled part 3 is in a high-temperature environment and expands due to thermal deformation. The thin-walled part 3 and the floating bracket 1 float along the axial direction of the reserved gap. As the ambient temperature rises, the floating amount continues to increase until the ambient temperature increases. The temperature reaches the maximum and no longer changes, the thin-walled part 3 and the floating support 1 float to the maximum position, and after the engine stops working, the connecting part returns to the starting position again.
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The invention discloses a floating structure of a high-temperature hot end connector of an aero-engine. The floating structure mainly comprises a floating support, a distance bushing, a thin-wall part, a case, a gasket, a bolt and a nut; the distance bushing is of an annular structure with a limiting plate and a fastening plate, the diameter of the limiting plate is greater than the diameter of a round opening of the floating support, the annular width of the limiting plate is equal to the up-down floating gap, and a left-right floating gap is reserved between the limiting plate and the fastening plate; the round opening is formed in the middle of the floating support, and the fastening plate penetrates through the round opening so that the floating support can be arranged on the distance bushing in a sleeving mode and stopped on the limiting plate; the floating support 1 can float up and down within the up-down floating gap or float in the left-right direction within the left-right floating gap; the distance bushing is fixed to the case through the gasket, the bolt and the nut; and the floating support is a trapezoidal supporting arm and is connected to the thin-wall part through rivets in a riveted mode. The floating structure is reliable in work and easy to disassemble and assemble. According to the structural scheme, the test run qualification rate of the aero-engine can be increased, and the cost of the manufacturing step and the assembling step can be saved.
Description
technical field [0001] The invention belongs to the technical field of structural design of hot-end parts of aero-engines, and relates to a floating structure design of hot-end connectors of aero-engines. Background technique [0002] The working environment temperature of high-temperature hot-end parts of aero-engine is high, basically above 1000°C, the load is complicated, and it is also corroded by fuel and gas, and the working conditions are harsh. This puts forward higher requirements for the material selection and structural design of the hot-end parts Require. In terms of material selection, superalloy materials with good high temperature oxidation resistance and gas corrosion resistance, sufficient instantaneous and lasting strength, good cold and heat fatigue performance, high creep resistance and low cycle fatigue performance are generally selected. In addition to selecting materials with good performance for the hot-end parts, the key is to solve the problem of t...
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IPC IPC(8): F02C7/00F01D25/00
CPCF02C7/00F01D25/00
Inventor 王邦赛林成蓝天霞李丹王维东
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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