Abstract:
A means for attaching a metallic component to a non-metallic component using a compliant material having thermal properties intermediate those of the metallic component to a non-metallic component is provided. The method can accommodate CTE mismatches and wear-type problems common to many assemblies of dissimilar materials. In particular, the method provides a sufficient wear surface to accommodate relative motion and provide a durable wear surface that does not excessively wear/gall/mico-weld itself together and provides the necessary damping and motion for proper operation in aeronautical applications.
Abstract:
A compliant attachment for an organic matrix composite component that is configured to interface with a mating component is disclosed. The compliant attachment may comprise an inner surface configured to bond to an interfacing surface of a body portion of the organic matrix component, and an outer surface configured to interface with the mating component. The compliant attachment may have a coefficient of thermal expansion intermediate between a coefficient of thermal expansion of the body portion of the organic matrix composite component and a coefficient of thermal expansion of the mating component.
Abstract:
A method of preparing a casting article for use in manufacturing a gas turbine engine part according to an exemplary aspect of the present disclosure includes, among other things, communicating a powdered material to an additive manufacturing system and preparing a casting article that includes at least one trunk and a skin core that extends from the at least one trunk out of the powdered material.
Abstract:
A compliant attachment for an organic matrix composite component that is configured to interface with a mating component is disclosed. The compliant attachment may comprise an inner surface configured to bond to an interfacing surface of a body portion of the organic matrix component, and an outer surface configured to interface with the mating component. The compliant attachment may have a coefficient of thermal expansion intermediate between a coefficient of thermal expansion of the body portion of the organic matrix composite component and a coefficient of thermal expansion of the mating component.
Abstract:
An example multi-dimensional component building system includes a first chamber having at least one base disposed therein, a second chamber adjacent to and in fluid communication with the first chamber through a first door, and a third chamber adjacent to and in fluid communication with the second chamber through a second door. The second chamber is fluidly sealed from the first chamber if the first door is in a closed position. The second chamber is configured to receive the at least one base via a first transfer mechanism if the fluid parameters of the first chamber are approximately equal to the fluid parameters of the second chamber. The second chamber includes a directed heat source and a build-up material configured to form a component on the at least one base by melting or sintering. The third chamber is fluidly sealed from the second chamber if the first door is in a closed position. The third chamber is configured to receive the at least one base, having a formed component disposed thereon, via a second transfer mechanism if the second door is in an open position. The fluid parameters of the second chamber are not substantially affected by fluid communication with the first chamber or the third chamber.
Abstract:
An airfoil for a gas turbine engine includes a body having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface defined by a perimeter wall. An interior wall is arranged interiorly and adjacent to the perimeter wall to provide a cooling passage there between. A cooling passage with first and second portions is tapered and respectively has first and second thicknesses. The first thickness is greater than the second thickness. The second thickness is less than 0.060 inch (1.52 mm).
Abstract:
An example multi-dimensional component building system includes a first chamber having at least one base disposed therein, a second chamber adjacent to and in fluid communication with the first chamber through a first door, and a third chamber adjacent to and in fluid communication with the second chamber through a second door. The second chamber is fluidly sealed from the first chamber if the first door is in a closed position. The second chamber is configured to receive the at least one base via a first transfer mechanism if the fluid parameters of the first chamber are approximately equal to the fluid parameters of the second chamber. The second chamber includes a directed heat source and a build-up material configured to form a component on the at least one base by melting or sintering. The third chamber is fluidly sealed from the second chamber if the first door is in a closed position. The third chamber is configured to receive the at least one base, having a formed component disposed thereon, via a second transfer mechanism if the second door is in an open position. The fluid parameters of the second chamber are not substantially affected by fluid communication with the first chamber or the third chamber.
Abstract:
An airfoil is disclosed. The airfoil may comprise a body portion having a leading edge, a trailing edge, a pressure side, and a suction side. The airfoil may further comprise a compliant attachment bonded to the body portion and the compliant attachment may be configured to connect to a support structure. The compliant attachment may have a coefficient of thermal expansion intermediate between a coefficient of the thermal expansion of the body portion of the airfoil and a coefficient of thermal expansion of the support structure.
Abstract:
A gas turbine engine includes a plurality of airfoils that are circumferentially arranged to rotate about an engine central axis. Each of the airfoils includes a base and a free tip end. The tip end includes first and second porous abradable elements that are axially spaced apart. The first porous abradable elements of the airfoils circumferentially align with each other, and the second porous abradable elements of the airfoils circumferentially align with each other.
Abstract:
An airfoil includes an airfoil body including a first side wall and a second side wall that is spaced apart from the first side wall. A longitudinally elongated rib connects the first side wall and the second side wall and divides a cavity into a forward section and an aft section. The longitudinally elongated rib includes at least one opening fluidly connecting the forward section and the aft section of the cavity. The opening is located in a lateral central portion of the longitudinally elongated rib with regard to the longitudinal axis such that first and second sections of the longitudinally elongated rib bound respective lateral sides of the at least one opening. The opening defines a maximum dimension along a direction perpendicular to the longitudinal axis. The maximum dimension is greater than a minimum dimension of each of the first and second sections in the same direction.