Compressor blade having a ratio of leading edge sweep to leading edge dihedral in a range of 1: 1 to 3: 1 along the radially outer portion
J Orosa, M Montgomery - US Patent 8,147,207, 2012 - Google Patents
An airfoil for use as rotor blades in compressors for turbomachines, such as gas turbine
engines. The airfoil includes increased forward sweep and forward dihedral effective to …
engines. The airfoil includes increased forward sweep and forward dihedral effective to …
Advanced booster rotor blade
PJ Wood, EA Falk, LD Dailey - US Patent 7,967,571, 2011 - Google Patents
(57) ABSTRACT A rotor airfoil having a leading edge extending from a root to a tip, an inner
span region and an outer span region the leading edge having a Sweep angle profile Such …
span region and an outer span region the leading edge having a Sweep angle profile Such …
Gas turbine engine airfoil
EJ Gallagher, BR Monzon, L Liu, LS Li… - US Patent …, 2016 - Google Patents
2011/0268.578 A1 11/2011 Praisner et al. US PATENT DOCUMENTS 2011/0286850 A1
11/2011 Micheli et al. 2012, 005.7982 A1 3/2012 O'Hearnet al. 4,431,376 A 2, 1984 …
11/2011 Micheli et al. 2012, 005.7982 A1 3/2012 O'Hearnet al. 4,431,376 A 2, 1984 …
Nonlinearly stacked low noise turbofan stator
WB Schuster, KB Kontos, DS Weir, NA Nolcheff… - US Patent …, 2009 - Google Patents
A nonlinearly stacked low noise turbofan stator vane having a characteristic curve that is
characterized by a nonlinear sweep and a nonlinear lean is provided. The stator is in an …
characterized by a nonlinear sweep and a nonlinear lean is provided. The stator is in an …
Advanced booster system
PJ Wood, EA Falk, LD Dailey - US Patent 8,517,677, 2013 - Google Patents
A compression stage having a plurality of stator vanes and rotor blades coaxial with a
longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that …
longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that …
Airfoil design for rotor and stator blades of a turbomachine
C Clemen - US Patent 8,152,473, 2012 - Google Patents
For the rotor and stator blades of turbomachines, more particularly of gas-turbine engines,
an airfoil design is provided with a defined area of a skeleton line angle distribution for …
an airfoil design is provided with a defined area of a skeleton line angle distribution for …
Transonic blade
C Myoren, Y Takahashi - US Patent 8,425,185, 2013 - Google Patents
(57) ABSTRACT A transonic blade is provided that operates in a flow field where flow has a
transonic speed or higher in an axial-flow rotating machine and that concurrently achieves a …
transonic speed or higher in an axial-flow rotating machine and that concurrently achieves a …
Advanced booster stator vane
PJ Wood, EA Falk, LD Dailey - US Patent 8,087,884, 2012 - Google Patents
US8087884B2 - Advanced booster stator vane - Google Patents US8087884B2 - Advanced
booster stator vane - Google Patents Advanced booster stator vane Download PDF Info …
booster stator vane - Google Patents Advanced booster stator vane Download PDF Info …
Aerofoil members for a turbomachine
NW Harvey, MR Stokes, DA Bagshaw - US Patent 8,192,153, 2012 - Google Patents
US8192153B2 - Aerofoil members for a turbomachine - Google Patents US8192153B2 - Aerofoil
members for a turbomachine - Google Patents Aerofoil members for a turbomachine Download …
members for a turbomachine - Google Patents Aerofoil members for a turbomachine Download …
Advanced booster system
PJ Wood, EA Falk, LD Dailey - US Patent 8,292,574, 2012 - Google Patents
A compression stage having a plurality of stator vanes and rotor blades coaxial with a
longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that …
longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that …