Abstract: A system and method for blade health monitoring is provided. The system and method may improve health diagnostic capabilities for engine blades, thus reducing the risk of blade failure during engine operation, increasing the useful life of each engine blade, and allowing for more accurate maintenance and/or inspection schedules of engine blades. The system may include a health monitoring processor, an excitation actuator, and a health monitoring sensor. The excitation actuator may pulse a force against an engine blade to cause non-integral vibratory excitations in engine blades. The health monitoring sensor may measure the vibratory excitations. The health monitoring processor may analyze the vibratory excitations to determine the health of the engine blade.

Abstract: A tubing assembly for fluid delivery to a bearing system may comprise a fitting having an inner surface defining an inner flow path and having an outer surface defining a first mating surface. A first tube may be coupled to the fitting. The fitting may be disposed within a bearing housing of the bearing system. The bearing housing may include a second mating surface in sealing contact with the first mating surface of the fitting.

Abstract: A main shaft bearing compartment seal system is described herein. The modified ring groove geometry creates two distinct cavities or steps for a piston ring and a wave spring. This concept provides a separate groove cavity for the spring independent of the fool-proofing and clearance cavity. This modified ring groove geometry increases first face coverage and reduces exposure risk for eccentricity of wave spring to piston ring, to avoid potential disengagement and improve function and performance of the seal assembly and engine. A piston ring may comprise a first face configured to form a first seal between the piston ring and a cylindrical ID bore, a second face configured to form a second seal between the piston ring and a carbon seal assembly, and a third face configured to interface with a surface of a spring, wherein the third face is longer than the surface of the spring.

Abstract: A mid-turbine frame for a gas turbine engine may comprise a bearing system including a bearing housing. A first tube may define a first fluid passage configured to carry a first fluid to the bearing system. An outer sleeve may be disposed around the first tube and may define a chamber between the first tube and the outer sleeve. A first fitting may be coupled to the first tube and to the outer sleeve. The first fitting may comprise an inner portion having an inner surface further defining the first fluid passage. An outer portion may be disposed around the inner portion and may further define the chamber therebetween. The chamber may be configured to contain a fluid. An outer surface may have a first mating surface comprising a frustoconical shape. A flange may extend radially outward from the outer surface.

Abstract: A compressor assembly may include a compressor case disposed about an axis. A bleed valve may be disposed about the compressor case to translate axially and/or rotationally relative to the compressor case. A first seal may be disposed in a forward seal housing of the bleed valve a first radial distance from the axis. A first sealing wall may be fixed relative to the compressor case and configured to engage the first seal. A second seal may be disposed in an aft seal housing of the bleed valve at a second radial distance from the axis. The first radial distance may be substantially equal to the second radial distance. A second sealing wall may be fixed relative to the compressor case and configured to engage the second seal.

Abstract: A fitting for a double wall tube may comprise an inner portion defining an inner fluid passage. An outer portion may be disposed concentrically around the inner portion and may define an outer fluid passage between the outer portion and the inner portion. The outer portion may define a first aperture disposed through a sidewall of the outer portion.

Abstract: A method is disclosed for manufacturing a blade tip coating. The blade tip coating (152) comprising an abrasive (156) and a matrix (154). The method comprises forming a mixture comprising the abrasive, a precursor of the matrix, and an additional particulate (158). The mixture is pressed, the additional particulate acting as a stop to limit thickness reduction of the mixture.

Abstract: A multiwall tubing assembly for fluid delivery to a bearing system may comprise a first tube defining an inner fluid passage configured to carry a first fluid. A second tube may be disposed around the first tube and may define an outer fluid passage between the first tube and the second tube. The outer fluid passage may be configured to carry a second fluid. A fitting may be coupled to the first tube and the second tube. The fitting may comprise an inner portion fluidly coupled to the inner fluid passage and configured to carry the first fluid. An outer portion may be disposed around the inner portion and fluidly coupled to the outer fluid passage. The outer portion may be configured to carry the second fluid. The fitting may be configured to fluidly isolate the first fluid from the second fluid.

Abstract: A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed.

Abstract: An inner diffuser case for a gas turbine engine may include a pre-diffuser including a plurality of struts. At least one of the struts may include an aperture therethrough. A cone may have a downstream end coupled to the pre-diffuser downstream of, and proximate to, the aperture. A skirt may have a forward end coupled to the pre-diffuser downstream of, and proximate to, the aperture. The forward end of the skirt may be axially aligned with the downstream end of the cone.

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a platform and a feed cavity that feeds a cooling fluid inside of the platform. The feed cavity includes a leg portion and a main body portion that extends from the leg portion inside of the platform. A cooling cavity is inside the platform and in fluid communication with the feed cavity.

Abstract: A turbine engine is provided that includes a turbo-compressor and a combustor section. The turbo-compressor includes a compressor section and a turbine section. The combustor section is fluidly coupled between the compressor section and the turbine section. The compressor section includes a first number of stages. The turbine section includes a second number of stages that is different than the first number.

Abstract: A casting article according to an exemplary aspect of the present disclosure includes, among other things, a circuit forming portion and an interior channel formed inside of the circuit forming portion. The interior channel defines a leaching path that extends at least partially through the circuit forming portion.

Abstract: A system for providing a seal between a combustor and a turbine vane. The system includes a flange configured to extend radially from the combustor, and a seal. The flange includes a flange surface configured to face in an axial direction toward a surface of the vane. The seal is configured to be axially loaded between the flange surface and the surface of the vane.

Abstract: The gas turbine component showerhead cooling hole layouts described herein include minimal lateral cooling hole exit diffusion on the middle showerhead cooling hole rows and interior facing sides of outer rows. In this way, rows of cooling holes may be placed close together. Stated another way, the outer showerhead cooling hole rows substantially only include lateral cooling hole exit diffusion in the direction away from the other rows to again allow the rows to be placed close together.

Abstract: This disclosure relates to a gas turbine engine including a blade outer air seal (BOAS) having at least one attachment hook adjacent one of a leading edge and a trailing edge thereof. The BOAS further includes at least one radial standoff axially aligned with the at least one attachment hook.

Abstract: A compound fillet radii cutter may have a shaft having a cylindrical member, frustoconical cutting surface, a small radius cutting surface having an arc length of a first circle, and a large radius cutting surface having an arc length of a second circle. The frustoconical cutting surface may be disposed between the cylindrical member and the small radius cutting surface. The small radius cutting surface may be disposed between the frustoconical cutting surface and the large radius cutting surface, and a juncture of the large radius cutting surface and the small radius cutting surface may form a tangential union. In this manner, a single cutter may cut radii of various sizes or cut compound radii.

Abstract: A fuel delivery system is provided for a turbine engine. This fuel delivery system includes a variable orifice jet configured to spray fuel received from a spray bar fuel conduit. The variable orifice jet includes a flexible body and a pintle that extends through a sidewall of the flexible body. An area of an orifice between the sidewall and the pintle is variable.

Abstract: An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots.

Abstract: A method of monitoring performance of an auxiliary pump is provided. A monitoring system measures a first pressure at a location supplied by a main pump and the auxiliary pump while the auxiliary pump is operated at a first speed. The monitoring system measures a second pressure at the location while the auxiliary pump is operated at a second speed. The monitoring system calculates performance of the auxiliary pump based on a difference between the first pressure and the second pressure divided by a difference between the first speed and the second speed. The monitoring system tracks the performance of the auxiliary pump over time by repeating the measuring and calculating over time.