Turbine engine compressor blade

An airfoil for a compressor blade of a gas turbine engine has a chord between a leading edge and a trailing edge and a span between a root and a tip. The airfoil can further include a reduction in local chord from about 75% span to the tip for about a 5% reduction in local solidity. The airfoil can...

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Main Authors Adam, Matthew Ford, Wood, Peter John, Falk, Eric Andrew, Moeckel, Curtis William, Stecher, Mark Joseph
Format Patent
LanguageEnglish
Published 05.03.2019
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Abstract An airfoil for a compressor blade of a gas turbine engine has a chord between a leading edge and a trailing edge and a span between a root and a tip. The airfoil can further include a reduction in local chord from about 75% span to the tip for about a 5% reduction in local solidity. The airfoil can have decreasing sweep angles for the leading edge and the trailing edge from 50% span to the tip and can have decreasing leading and trailing edge dihedral angles from 50% span to the tip.
AbstractList An airfoil for a compressor blade of a gas turbine engine has a chord between a leading edge and a trailing edge and a span between a root and a tip. The airfoil can further include a reduction in local chord from about 75% span to the tip for about a 5% reduction in local solidity. The airfoil can have decreasing sweep angles for the leading edge and the trailing edge from 50% span to the tip and can have decreasing leading and trailing edge dihedral angles from 50% span to the tip.
Author Adam, Matthew Ford
Moeckel, Curtis William
Stecher, Mark Joseph
Falk, Eric Andrew
Wood, Peter John
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Snippet An airfoil for a compressor blade of a gas turbine engine has a chord between a leading edge and a trailing edge and a span between a root and a tip. The...
SourceID epo
SourceType Open Access Repository
SubjectTerms BLASTING
HEATING
LIGHTING
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT PUMPS
POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS
PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
WEAPONS
Title Turbine engine compressor blade
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