AXIAL FLOW COMPRESSOR, GAS TURBINE WITH THE SAME, AND STATIONARY BLADE OF AXIAL FLOW COMPRESSOR

Japanese Patent JP2017031847

A

PROBLEM TO BE SOLVED: To provide an axial flow compressor capable of achieving improvement of efficiency of the whole compressor and securement of reliability by suppressing corner stall of a blade lattice and simultaneously optimizing inflow conditions of the following blade lattice, a gas turbine with the same, and stationary blades to be used for the same.SOLUTION: An axial flow compressor 1 is provided with: a plurality of rotor blade lattices 12 which are constituted of a plurality of rotor blades and a plurality of stationary blade lattices 14 which are constituted of a plurality of stationary blades arranged in an annular flow channel P on which working fluid circulates, in which a part where at least one of the rotor blade lattices 12 and the stationary blade lattices 14 are located on at least one wall surface on an inner peripheral side and an outer peripheral side of the annular flow channel P has a push-out part 24 curved so that its downstream part pushes out to the annular flow channel P from an upstream side, and the blades of the stationary blade lattices 14 located on a wall surface 23 having the push-out part 24 are constituted so that increase rate of a blade exit angle in a wall surface direction at a blade end on the side of the wall surface 23 having the push-out part 24 becomes larger than increase rate of the blade exit angle in the wall surface direction at an intermediate part of blade height.SELECTED DRAWING: Figure 3

SHIBATA TAKANORI
OMURA NAOTO
MYOREN CHIHIRO
TAKAHASHI YASUO

JP2015150840A

February 09, 2017

July 30, 2015

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MITSUBISHI HITACHI POWER SYS

F04D29/54; F02C3/06; F04D29/66

JP2014505829A

2014-03-06

Kaichi International Patent Office

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