FLUTTER INHIBITING INTAKE FOR GAS TURBINE PROPULSION SYSTEM

FLUTTER INHIBITING INTAKE FOR GAS TURBINE PROPULSION SYSTEM

Disclosed is flutter damper (102) including a first cavity (168) having a radially inner side in fluid communication with a flow path (164), and a second cavity (170) having a radially inner side in fluid communication with a radially outer side of the first cavity, and the flutter damper having an...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: SADEGHI, Mani, MORIN, Bruce L, GYSLING, Daniel L
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
ACOUSTICS
ACOUSTICS NOT OTHERWISE PROVIDED FOR
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING,NOISE OR OTHER ACOUSTIC WAVES IN GENERAL
MUSICAL INSTRUMENTS
PHYSICS
SOUND-PRODUCING DEVICES
WEAPONS
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Beschreibung
Zusammenfassung:Disclosed is flutter damper (102) including a first cavity (168) having a radially inner side in fluid communication with a flow path (164), and a second cavity (170) having a radially inner side in fluid communication with a radially outer side of the first cavity, and the flutter damper having an impedance characteristic at one or more target frequencies defined as f target = f S , ND + © ‹ ND wherein f S,ND is a resonance frequency corresponding to a structural mode of a rotating component, ND is a nodal diameter count of the structural mode, and © is a rotational speed of the rotating component, and wherein the flutter damper has the following impedance characteristic at the one or more targeted frequencies R ‰¥ 2 Ác ˆ’ 3 Ác ‰¤ X ‰¤ ˆ’ 0.6 Ác wherein R is the real part of the impedance characteristic, X is the imaginary part of the impedance characteristic, Á is air density, and c is speed of sound.