Method and apparatus for assembling gas turbine engines
AssigneeGeneral Electric Company
InventorRollin George Giffin
Life of this patent
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Abstract
A method for assembling a fan assembly for a gas turbine engine includes coupling a plurality of fan blades in a row to a rotor disk, wherein each fan blade includes an airfoil having a first sidewall and a second sidewall connected together at a leading edge and a trailing edge, and wherein each airfoil extends radially between a root and a tip. The method also includes coupling at least one shroud to at least one of the plurality of rows of fan blades, such that the shroud is coupled to at least one fan blade tip extending within the same row of fan blades, and coupling at least one row of rotor blades to the shroud, such that the rotor blades extend radially outward from the shroud.
Claims18
A method for assembling a gas turbine engine, said method comprises:
- coupling a plurality of rows of fan blades in a row to a rotor disk, wherein each fan blade includes an airfoil having a first sidewall and a second sidewall connected together at a leading edge and a trailing edge, and wherein each airfoil extends radially between a root and a tip;
- coupling at least one shroud to at least one of the plurality of rows of fan blades, such that the shroud is coupled to at least one fan blade tip extending within the same row of fan blades;
- coupling at least a first row of rotor blades and a second row of rotor blades to the shroud, such that the rotor blades extend radially outward from the shroud, and wherein each rotor blade includes an airfoil having a first sidewall and a second sidewall connected together at a leading edge and a trailing edge;
- and
- positioning the first row of rotor blades upstream of the second row of rotor blades.
A fan assembly for a gas turbine engine, said fan assembly comprises:
- a plurality of fan blades coupled together such that said fan blades are arranged in a circumferential row extending around a rotor disk, wherein each said fan blade comprises an airfoil comprising a first sidewall and a second sidewall connected together at a leading edge and a trailing edge and extends radially between a root and a tip;
- at least one shroud coupled to at least one of said plurality of fan blade tips and extending circumferentially around the rotor disk;
- and
- at least a first row of rotor blades and a second row of rotor blades extending radially outward from said at least one shroud, said first row of rotor blades is positioned upstream of said second row of rotor blades and each said rotor blade comprises an airfoil comprising a first sidewall and a second sidewall connected together at a leading edge and a trailing edge.
A gas turbine engine comprising:
- a fan blade assembly comprising a plurality of fan blades coupled together such that said fan blades are arranged in a circumferential row extending around a rotor disk, wherein each said fan blade comprises an airfoil comprising a first sidewall and a second sidewall connected together at a leading edge and a trailing edge and extends radially between a root and a tip, at least one shroud coupled to at least one of said plurality of fan blade tips and extending circumferentially around the rotor disk, and at least a first row of rotor blades and a second row of rotor blades extending radially outward from said at least one shroud, wherein said first row of rotor blades is positioned upstream of said second row of rotor blades and each said rotor blade comprises an airfoil comprising a first sidewall and a second sidewall connected together at a leading edge and a trailing edge.
Dependencies are inferred from the claim text.