AXIAL FLOW COMPRESSOR AND GAS TURBINE ENGINE

PROBLEM TO BE SOLVED: To enlarge the operational area of an axial flow compressor 1 on the low flow rate side at a high level while achieving the stable operation of the axial flow compressor 1.SOLUTION: Each stationary blade 9A in one of compressor stators 5 is divided into a first variable segment...

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Bibliographic Details
Main Authors OKIRI KUNIO, PALLOT GUILLAUME
Format Patent
LanguageEnglish
Published 29.03.2012
Subjects
BLASTING
HEATING
LIGHTING
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT PUMPS
POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS
PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
WEAPONS
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Summary:PROBLEM TO BE SOLVED: To enlarge the operational area of an axial flow compressor 1 on the low flow rate side at a high level while achieving the stable operation of the axial flow compressor 1.SOLUTION: Each stationary blade 9A in one of compressor stators 5 is divided into a first variable segment blade 17, which is oscillated around the axis core in the radial direction, and a second variable segment blade 19, which is arranged on the downstream side of the first variable segment blade 17 and oscillated around the axis core in the radial direction, and can be changed into an integrated state, in which the first variable segment blade 17 and the second variable segment blade 19 show a common blade shape, and a disintegrated state, in which the first variable segment blade 17 and the second variable segment blade 19 show an independent blade shape.
Bibliography:Application Number: JP20100206765