Patent number 8769814 is assigned to
The following quote was obtained by the news editors from the background information supplied by the inventors: "Components of aircraft engines may develop cracks and other formations that degrade performance of the component and/or cause other more catastrophic failures in the engine. Cracks may form in certain components that must be replaced in their entirety. However, because of the scale, size, complexity, and cost, replacement of such components is fundamentally undesirable. A more advantageous solution would therefore be to repair these components while still in place, thus avoiding costly maintenance and repair."
In addition to the background information obtained for this patent, VerticalNews journalists also obtained the inventors' summary information for this patent: "There is described below embodiments of a device and method for repairing components of gas turbine engines without having to remove the damaged component. The proposed repair includes a supplemental part that is configured with features to improve the mechanical properties of the damaged component in its repaired condition. Such features include, for example, one or more selected dimensions that, while being different than corresponding dimensions of the damaged component, fit within the envelope defined by the damaged component to permit continued operation of the component in its repaired condition.
"Further discussion of these and other features is provided below in connection with one or more embodiments, examples of which appear immediately below:
"In one embodiment, a repair device for a forward frame v-blade in a gas turbine engine on an aircraft, the forward frame v-blade including a v-blade cross-section with an upper v-blade flange and a lower v-blade flange. The repair device comprises a repair part including a repair part web and a pair of stiffening legs extending from the repair part web in manner forming a channel. The repair device also comprises a splice plate disposed in the channel, the spice plate including a splice plate body having a stepped region for engaging the repair part and the forward frame v-blade. The repair device further comprises an array of fasteners coupling the repair part and the splice plate. The repair device further described wherein the stepped region delineates between a repair part engagement area and a v-blade engagement area, wherein the repair part is coupled to the repair part engagement area, and wherein the stiffening legs have a leg thickness that is greater than the thickness of upper v-blade flange and the lower v-blade flange.
"In another embodiment, in a gas turbine engine for an aircraft, a forward frame v-blade comprises a circumferential shape disposed about the gas turbine engine, the circumferential shape having a v-blade cross-section with an upper v-blade flange, a lower v-blade flange, and a v-blade web extending therebetween. The forward frame v-blade also comprises a splice plate coupled to the circumferential shape, the splice plate including a splice plate body having a repair part engagement area and a repair part coupled to the repair part engagement area. The forward frame v-blade further comprises an array of fasteners extending through the repair part, the splice plate, and the circumferential shape. The forward frame v-blade further described wherein the repair part includes a pair of stiffening legs that have a leg thickness that is greater than the thickness of upper v-blade flange and the lower v-blade flange.
"In yet another embodiment, a method for repairing an aircraft engine including a nacelle in which is disposed one or more thrust reversers and a forward frame v-blade subject to damage from the thrust reversers. The method comprises one or more steps for exposing a repair section of the forward frame v-blade, removing a portion of the repair section forming an exposed end of the forward frame v-blade, and coupling a splice plate proximate the exposed end. The method further described wherein a repair part is coupled to the splice plate, wherein an array of fasteners is used to couple the splice plate to the forward frame v-blade and to the repair part, and wherein the repair part includes a repair part web and a pair of stiffening legs which in combination with the splice plate and the fasteners causes a bending stress that does not exceed the bending stress for the forward frame v-blade as measured at the repair part web."
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