Abstract:
A composite component and a plated polymer component are disclosed. The composite component may comprise a body portion formed from an organic matrix composite, a first metal coating applied to a surface of the body portion, and an outer metal layer on the first metal coating that is erosion-resistant. The plated polymer component may comprise a polymer substrate, a metal plating layer applied to a surface of the polymer substrate, and at least one selectively thickened region in the metal plating layer. The at least one selectively thickened region may assist in protecting the plated polymer component against wear and/or erosion.
Abstract:
CURVED VARIABLE PITCH WEDGE RETENTION IN VANE OUTER BASE A method for repairing or replacing a mechanically retained vane is provided. The method comprises the steps of forming an oversized cavity in an outer base, inserting a flared end of a vane in the oversized cavity, and inserting a wedge for mechanically retaining the flared end of the vane in. the oversized cavity. The wedge has a first surface with a constant pitch angle to match the outer base cavity and a second surface with a variable pitch angle to match the vane tip dovetail.
Abstract:
A method for filling cooling holes in a component of a gas turbine engine is disclosed. The component may include a plurality of first cooling holes extending through the wall of the component. The method may comprise the steps of exposing the outer surface of the component, filling the plurality of first cooling holes with a polyimide, curing the polyimide to block the passage of cooling fluid through the plurality of first cooling holes, and applying a thermal bather coating over the outer surface of the component. The method may further include the step of installing a second plurality of cooling holes in the wall of the component wherein the plurality of second cooling holes penetrate the thermal barrier coating and the wall of the component and allow cooling fluid to pass therethrough.
Abstract:
A method for repairing or replacing a mechanically retained vane is provided. The method comprises the steps of forming an oversized cavity (50) in an outer base (52), inserting a flared end (18) of a vane in the oversized cavity (50), and inserting a wedge (70) for mechanically retaining the flared end (18) of the vane in the oversized cavity (50). The wedge (70) has a first surface (72) with a constant pitch angle to match the outer base cavity (50) and a second surface (74) with a variable pitch angle to match the vane tip dovetail.
Abstract:
A method for repairing or replacing a mechanically retained vane is provided. The method comprises the steps of forming an oversized cavity (50) in a support structure (52), inserting a flared end (18) of a vane (22) in the oversized cavity (50), and inserting a wedge (70) for mechanically retaining the flared end (18) of the vane (22) in the oversized cavity (50).
Abstract:
A method for repairing or replacing a mechanically retained vane is provided. The method comprises the steps of forming an oversized cavity (50) in a support structure (52), inserting a flared end (18) of a vane (22) in the oversized cavity (50), and inserting a wedge (70) for mechanically retaining the flared end (18) of the vane (22) in the oversized cavity (50).
Abstract:
A method for filling cooling holes in a component of a gas turbine engine is disclosed. The component may include a plurality of first cooling holes extending through the wall of the component. The method may comprise the steps of exposing the outer surface of the component, filling the plurality of first cooling holes with a polyimide, curing the polyimide to block the passage of cooling fluid through the plurality of first cooling holes, and applying a thermal bather coating over the outer surface of the component. The method may further include the step of installing a second plurality of cooling holes in the wall of the component wherein the plurality of second cooling holes penetrate the thermal barrier coating and the wall of the component and allow cooling fluid to pass therethrough.
Abstract:
a plurality of second cooling holes penetrating the thermal barrier coating and extending between the outer surface and the inner surface, the plurality of second cooling holes allowing cooling fluid to pass therethrough.
Abstract:
A method of applying a wear-resistant coating to aluminum sliding contact wear surfaces is disclosed. The method includes providing a plurality of parts having sliding contact wear surfaces and thermal spray coating at least one of a composite aluminum oxide and PTFE or a blend of aluminum oxide and PTFE. The disclosed method may be used to repair aluminum parts subject to sliding contact wear as well as in the design of new aluminum parts subject to sliding contact wear. Improved compressor bleed valves for gas turbine engines and improved fan exit case assemblies are also disclosed.
Abstract:
A blade (100) has an airfoil (106) having a leading edge (114), a trailing edge (116), a pressure side (118), and a suction side (120) and extending from an inboard end (110) to a tip (112). An attachment root (108) is at the inboard end. The blade comprises an aluminum alloy substrate (102) and a coating at the tip (130). The coating (130) comprises an anodic layer (160) atop the substrate and an aluminum oxide layer (162) atop the anodic layer.