Fan blade interplatform seal

An interplatform seal 86 for a fan 14 in an axial gas turbine engine 10 comprises a plurality of elastomeric layers (94) which sandwich a stiffener (98) therebetween. The stiffener may comprise stainless steel mesh. The seal also has a raised triangular portion (88) at its forward end for disposal w...

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Bibliographic Details
Main Authors KASPROW, ROBERT F, LESHANE, JEFFREY S, KURZ, PHYLLIS L
Format Patent
LanguageEnglish
French
German
Published 28.10.1998
Edition6
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
ENGINE PLANTS IN GENERAL
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
NON-POSITIVE DISPLACEMENT PUMPS
POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS
PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
STEAM ENGINES
WEAPONS
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Summary:An interplatform seal 86 for a fan 14 in an axial gas turbine engine 10 comprises a plurality of elastomeric layers (94) which sandwich a stiffener (98) therebetween. The stiffener may comprise stainless steel mesh. The seal also has a raised triangular portion (88) at its forward end for disposal within an enlarged region of the gap formed by truncating the leading edge (64) of the blade platform, so as to provide a continuous flow surface. The seal is particularly suited for use with modern impact resistant fan blades which have larger interplatform gaps.
Bibliography:Application Number: EP19980303212