METHOD FOR OPERATIONAL DEVELOPMENT OF TURBINE NOZZLE OF GAS TURBINE ENGINE

摘要

FIELD: engine devices and pumps.;SUBSTANCE: method includes placing two-bladed blocks in the circumferential direction. The pitch between the blades in the block and the pitch between the blades of adjacent blocks is constant. Before installation, the blocks are divided into two groups, the first of which is set without changes, and in the second group a portion with a blade is cut from one block before the installation, in the remaining blocks of the second group, the allowance less than the first group of blocks is removed during machining, the value of which is set to ensure the increased uniform pitch between the blades of the adjacent blocks of the second group compared to the first one during their installation. The pitch between the blades in the block remains unchanged as in the first group.;EFFECT: reduction of the excitation oscillations which results in the destruction of the turbine blades of the gas turbine engine at the lock joint, with insignificant change in the nozzle structure at the operational development stage of the gas turbine engine which increases the reliability of the gas turbine engine operation during specified operation life.;2 dwg