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US 11,043,146 B2Granted
Fan blade refurbishment training device
AssigneeRaytheon Technologies Corporation
InventorsDelbert Laughery, Dennis J. Ryckman
Life of this patent
Estimating the term…
Abstract
A training apparatus is provided that includes a stand and at least one gas turbine engine fan stage. The at least one gas turbine engine fan stage has a plurality of fan rotor blades attached to a disk. The at least one gas turbine engine fan stage has an axially extending centerline, and the disk is mounted for rotation about the axially extending centerline. The stand is configured to support the at least one gas turbine engine fan stage.
Claims18
A training apparatus, comprising:
- at least one gas turbine engine fan stage having a plurality of fan rotor blades attached to a disk, the at least one gas turbine engine fan stage having an axially extending centerline, and the disk mounted for rotation about the axially extending centerline;
- and
- a stand configured to support the at least one gas turbine engine fan stage;
- wherein the plurality of fan rotor blades includes at least one learning fan rotor blade having an airfoil, the airfoil has a geometric configuration with at least one preexisting geometric deviation, the at least one preexisting geometric deviation being deviant from a design geometric configuration of a reference fan rotor blade.
1 more element
A training apparatus, comprising:
- a first gas turbine engine fan stage having a plurality of first fan rotor blades attached to a first disk, the first gas turbine engine fan stage having a first axially extending centerline, and the first disk mounted for rotation about the first axially extending centerline;
- and
- a second gas turbine engine fan stage having a plurality of second fan rotor blades attached to a second disk, the second gas turbine engine fan stage having a second axially extending centerline, the second disk mounted for rotation about the second axially extending centerline;
- wherein the first gas turbine engine fan stage is independent of the second gas turbine engine fan stage;
- a stand configured to support the first gas turbine engine fan stage and the second gas turbine engine fan stage;
- wherein the first gas turbine engine fan stage and the second gas turbine engine fan stage are oppositely positioned;
- and
- a casing that at least partially encloses the first gas turbine engine fan stage and the second gas turbine engine fan stage;
- wherein at least one of the plurality of first fan rotor blades or the plurality of second fan rotor blades, includes at least one learning fan rotor blade having an airfoil, the airfoil has a geometric configuration with at least one preexisting geometric deviation, the at least one preexisting geometric deviation being deviant from a design geometric configuration of a reference fan rotor blade.
6 more elements
A training apparatus, comprising:
- at least one gas turbine engine fan stage having a plurality of fan rotor blades attached to a disk, the at least one gas turbine engine fan stage having an axially extending centerline, and the disk mounted for rotation about the axially extending centerline;
- a stand configured to support the at least one gas turbine engine fan stage;
- and
- a fan stage rotational resistance device, which device is configured to adjustably resist rotation of the at least one gas turbine engine fan stage.
1 more element
Dependencies are inferred from the claim text.