GUIDE BLADE SEGMENT OF GAS-TURBINE ENGINE, COMPRESSION STAGE, COMPRESSOR AND GAS-TURBINE ENGINE Russian patent published in 2011 - IPC F01D5/14 F01D9/04 

FIELD: engines and pumps.

SUBSTANCE: guide blade segment of gas-turbine engine includes at least one guide blade connected to external and internal rings and having radial internal and external parts, lower and upper surfaces, as well as front and rear edges. Radial external part is divided into intermediate and linking parts connected to each other, and intermediate part is located between linking and radial internal parts. Radial internal part includes the first zone connected to radial external part of transition zone. Each blade is connected to external ring only with its linking part, and its intermediate part is located radially inside external ring. Rear edge attaching lower and upper surfaces has curvature radius gradually increasing in blade transition zone and reaches the maximum at the level of connection between transition zone and intermediate part, and then it remains constant in intermediate part and in linking part. One more invention refers to compression stage including grid of guide blade segments and movable wheel, in which segment grid includes at least one above mentioned guide blade segment. Other inventions of the group refer to compressor including the above compression stage and gas-turbine engine including such compressor.

EFFECT: inventions allow improving reliability of guide blade segment owing to reducing stresses in the seam connecting the blade to its external ring.

10 cl, 6 dwg