Search patents:
Gas turbine engine combustor with integrated combustor vane
Filed: January 1st, 1970 [Granted]
Patent Number: WO2014099074A3
A combustor section for a gas turbine engine includes a combustor vane which extends at least partially into a combustion chamber.
Airfoil assembly with paired endwall contouring
Filed: January 1st, 1970 [Granted]
Patent Number: WO2014105270A3
An airfoil assembly is disclosed. The airfoil assembly may comprise a series of airfoils such as vanes radially extending between an ID endwall ...
Gas turbine engine asymmetric nozzle guide vanes
Filed: January 1st, 1970 [Granted]
Patent Number: WO2014099077A3
A gas turbine engine includes a multiple of Nozzle Guide Vanes (NGVs) arranged asymmetrically and a multiple of NGVs clocked with respect ...
Nacelle scoop inlet
Filed: January 1st, 1970 [Granted]
Patent Number: WO2014077922A3
A scoop inlet for use in a gas turbine engine nacelle has a scoop inlet, and a tab extending forwardly of the scoop inlet. The scoop ...
Post processing of components that are laser peened
Filed: January 1st, 1970 [Granted]
Patent Number: WO2014065921A3
A method of post processing a laser peened component to remove a laser remelt layer is proposed. The post processing includes a series of ...
Hybrid core assembly for a casting process
Filed: January 1st, 1970 [Granted]
Patent Number: EP2532457A3
A hybrid core assembly (46) for a casting process includes a ceramic core portion (48), a refractory metal core portion (50) and a plate (62) ...
Gas turbine engine geared architecture axial retention arrangement
Filed: January 1st, 1970 [Granted]
Patent Number: WO2014007881A3
A support assembly for a geared architecture includes an engine static structure. A flex support is secured to the engine static structure and ...
Hybrid core assembly
Filed: January 1st, 1970 [Granted]
Patent Number: EP2554294A3
A hybrid core assembly (46) for a casting process includes a ceramic core portion (48) and a refractory metal core portion (50) that interfaces ...