Damper for compressor blade feet

Intermediate part (1) located in a circumferential groove (4) of a drum (6) where blades (2) are inserted, the intermediate part (1) being located between two adjacent compressor blades (2, 20) in a high pressure axial compressor, presenting in its rest position certain degree of pre-bending (A) pro...

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Bibliographische Detailangaben
Hauptverfasser:	ARKHIPOV, ALEXANDRE, EBELING, WILHELM, MATZ, CHARLES RAYMOND, KARABAN, VLADIMIR, PUTCHKOV, IGOR
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	Intermediate part (1) located in a circumferential groove (4) of a drum (6) where blades (2) are inserted, the intermediate part (1) being located between two adjacent compressor blades (2, 20) in a high pressure axial compressor, presenting in its rest position certain degree of pre-bending (A) provided by the elastic properties of the material of which the cited intermediate part (1) is made. The invention also refers to a gas turbine (100) with a high pressure axial compressor, such that an intermediate part (1) as cited above is located between each two adjacent compressor blades (2, 20).