Aecc Commercial Aircraft Engine Co., Ltd.

Aecc Shanghai Commercial Aircraft Engine Manufacturing Co., Ltd.

Chuanjun Cao

Jiaguang Wang

Fan Wu

Bin Zhu

Zhiqing Wu

Zeyong Yin

Jibao Li

Miaomiao Zhang

Haomai Gao

Shuhui Hu

Jinchun Wang

Yixuan Jiang

Wen Qin

Zhilong Zhai

Xiaoshi Zhang

A method includes simplifying flowing of airflow at root of a rotor blade into flowing of free jet, and determining an airflow expansion angle according to Mach number of incoming flow at root of a stator vane; calculating a radial height difference between a first end point on a leading edge of a stator platform and a trailing edge of an adjacent rotor platform by using an axial distance thereof, the angle and a deviation coefficient; determining position of the first end point with radial height difference; determining intersection point of the leading edge and the stator platform as position of a second end point on the leading edge; and determining a profile line between the points by bridging spline curves, so that the tail end thereof is tangent to the intersection line, and the starting end thereof is kept on same plane as side wall of the leading edge.

Method for configuring a leading edge of a compressor stator platform and the corresponding stator platform

A rotor blade tip clearance control method and a rotor blade manufactured using same. The control method includes: coinciding, along an axial direction of an aircraft engine, a center of gravity of a rotor blade with a center of gravity of a rotor wheel disk supporting the rotor blade; rotating the rotor wheel disk to measure a leading edge deformation amount of the rotor blade; measuring a trailing edge deformation amount of the rotor blade; comparing the deformation amounts; and adjusting the center of gravity of the rotor wheel disk until the leading edge deformation amount tends to be approximately equal to the trailing edge deformation amount. The method can effectively improve or even solve the problem of inconsistent radial displacements of a leading edge and a trailing edge during the operation.

Method for rotor blade tip clearance control and rotor blade manufactured by the method

An adjustable stator blade position maintaining structure for an aero-engine compressor, which keeps an adjustable stator blade at a preset position when a compressor works. The adjustable stator blade position maintaining structure includes a positioning section, a limiting section and a force transmission section The positioning section is mounted in a mounting hole in a casing; the limiting section is cone-shaped and thus fits into a conical hole in the top of a journal of the adjustable stator blade; and the force transmission section is connected between the positioning section and the limiting section so as to transmit a load from the limiting section to the positioning section.

Aeroengine compressor and position holding structure of adjustable stator vane

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Shanghai, China

Chuanjun Cao