Abstract: A dirt blocker including a support structure disposed within a gas turbine engine, the support structure defining an upstream control volume proximate a forward portion of the gas turbine engine and a downstream control volume proximate an aft portion of the gas turbine engine, the downstream control volume being opposite the upstream control volume relative to the support structure, a flow passage formed through the support structure, the flow passage configured to fluidly couple the upstream control volume with the downstream control volume; a radial contact wall formed from the support structure in fluid communication with the upstream control volume, the radial contact wall configured to intercept debris entrained within cooling air within the gas turbine engine; and a stagnation zone fluidly coupled with the flow passage, the stagnation zone configured to reduce momentum of the debris.

Abstract: The present disclosure relates to diagnostic test devices that provide improved communication to a user of one or both of proper functioning of the test device and an analog test result that is provided by the test device. The diagnostic test devices particularly can include one or more sensors effective to indicate application of a sufficient volume of a test fluid and/or can include one or more light sources positioned to illuminate an analog test result for improved visibility and understanding of the analog test result.

Abstract: The present disclosure relates to diagnostic test devices that provide improved communication to a user of one or both of proper functioning of the test device and an analog test result that is provided by the test device. The diagnostic test devices particularly can include one or more sensors effective to indicate application of a sufficient volume of a test fluid and/or can include one or more light sources positioned to illuminate an analog test result for improved visibility and understanding of the analog test result.

Abstract: A dirt blocker including a support structure disposed within a gas turbine engine, the support structure defining an upstream control volume proximate a forward portion of the gas turbine engine and a downstream control volume proximate an aft portion of the gas turbine engine, the downstream control volume being opposite the upstream control volume relative to the support structure, a flow passage formed through the support structure, the flow passage configured to fluidly couple the upstream control volume with the downstream control volume; a radial contact wall formed from the support structure in fluid communication with the upstream control volume, the radial contact wall configured to intercept debris entrained within cooling air within the gas turbine engine; and a stagnation zone fluidly coupled with the flow passage, the stagnation zone configured to reduce momentum of the debris.

Abstract: A system for filling a chambered package includes a carrying mechanism travelling in a machine direction and having chambered recesses defined about a surface thereof, a first dispensing nozzle configured to dispense a quantity of a medium onto the surface of the carrying mechanism for direction into the chambered recesses in a first group of the chambered recesses defined about the surface of the carrying mechanism, and a first wiper blade disposed along the carrying mechanism in the machine direction after the first dispensing nozzle, the first wiper blade defining a curvilinear surface having crests configured to direct the quantity of the medium into the chambered recesses in the first group of the chambered recesses and troughs configured to direct the quantity of the medium away from entering the chambered recesses in the second group of the chambered recesses.

Abstract: A gas turbine engine component includes a wall that has an inner surface and an outer surface. An inlet is defined by the inner surface. At least one non-rectangular slot is defined by the outer surface and includes at least one protrusion extending into the slot. A slot passage fluidly connects the inlet to the at least one non-rectangular slot. The slot passage comprises an inlet portion that extends through the wall from the inlet to an intermediate portion. An outlet portion extends through the wall from the intermediate portion to the at least one non-rectangular slot.

Abstract: The present disclosure relates to diagnostic test devices that provide improved communication to a user of one or both of proper functioning of the test device and an analog test result that is provided by the test device. The diagnostic test devices particularly can include one or more sensors effective to indicate application of a sufficient volume of a test fluid and/or can include one or more light sources positioned to illuminate an analog test result for improved visibility and understanding of the analog test result.

Abstract: A process for manufacturing a composite rotor blade includes manufacturing an oversized root region of a root region of a composite rotor blade; fixturing the CMC blade into a machining fixture at a primary Y and Z axis datum located at an attachment fillet radii of the root region; machining V-notches into the oversized root region to form a Y? and Z? axis datum of a sacrificial datum system in relation to the primary Y and Z axis datum; applying an oversized coating layer over the attachment fillet radii of the root region; fixturing the CMC blade into a machining fixture at the Y? and Z? axis datum of the sacrificial datum system; machining the oversized coating layer to a machined coating layer forming a Y? and Z? axis datum with respect to the Y? and Z? axis datum of the sacrificial datum system; fixturing the CMC blade into a machining fixture at the Y? and Z? axis datum; and machining off the sacrificial datum system removing the V-notches.

Abstract: A system for filling a chambered package includes a carrying mechanism travelling in a machine direction and having chambered recesses defined about a surface thereof, a first dispensing nozzle configured to dispense a quantity of a medium onto the surface of the carrying mechanism for direction into the chambered recesses in a first group of the chambered recesses defined about the surface of the carrying mechanism, and a first wiper blade disposed along the carrying mechanism in the machine direction after the first dispensing nozzle, the first wiper blade defining a curvilinear surface having crests configured to direct the quantity of the medium into the chambered recesses in the first group of the chambered recesses and troughs configured to direct the quantity of the medium away from entering the chambered recesses in the second group of the chambered recesses.

Abstract: A process for manufacturing a composite rotor blade includes manufacturing an oversized root region of a root region of a composite rotor blade; fixturing the CMC blade into a machining fixture at a primary Y and Z axis datum located at an attachment fillet radii of the root region; machining V-notches into the oversized root region to form a Y? and Z? axis datum of a sacrificial datum system in relation to the primary Y and Z axis datum; applying an oversized coating layer over the attachment fillet radii of the root region; fixturing the CMC blade into a machining fixture at the Y? and Z? axis datum of the sacrificial datum system; machining the oversized coating layer to a machined coating layer forming a Y? and Z? axis datum with respect to the Y? and Z? axis datum of the sacrificial datum system; fixturing the CMC blade into a machining fixture at the Y? and Z? axis datum; and machining off the sacrificial datum system removing the V-notches.

Abstract: A gas turbine engine component includes a wall that has an inner surface and an outer surface. An inlet is defined by the inner surface. At least one non-rectangular slot is defined by the outer surface and includes at least one protrusion extending into the slot. A slot passage fluidly connects the inlet to the at least one non-rectangular slot. The slot passage comprises an inlet portion that extends through the wall from the inlet to an intermediate portion. An outlet portion extends through the wall from the intermediate portion to the at least one non-rectangular slot.

Abstract: A core for gas turbine engine component comprises a body extending between first and second ends to define a length, and extending between first and second edges to define a width. A plurality of core extensions are formed as part of the body. The plurality of core extensions are positioned to be staggered relative to each other such that at least two adjacent core extensions are variable relative to each other in at least one dimension. A gas turbine engine component is also disclosed.

Abstract: A hanger for mounting an exhaust liner to an exhaust duct is provided. The hanger includes at least one cable, a cable flange, and a J-shaped flange. The at least one cable extends lengthwise between a first end and a second end. The cable flange has at least one cable aperture configured to receive a portion of the cable. The J-shaped liner flange is configured for attachment to the exhaust liner. The liner flange and cable flange are configured to mate with one another to prevent substantial relative motion between the cable flange and the liner flange in a first direction and in a second direction. The first and second directions are substantially orthogonal to one another.

Abstract: A component for a gas turbine engine includes a wall that has an exterior surface and an interior surface spaced from the exterior surface. A cooling circuit extends from the interior surface to the exterior surface. The cooling circuit includes a feed passage that has a first end defining an inlet at the interior surface and a second end spaced from the first end. At least one second passage is in fluid communication with the feed passage. At least one slot passage is in fluid communication with the second end of the feed passage and a cooling slot in the exterior surface.

Abstract: An airfoil for a gas turbine engine includes an airfoil including spaced apart pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface that extends in a radial direction from a platform to a tip. A cavity is provided between the pressure and suction side walls near the trailing edge. The cavity includes an interior region bounded by first and second exit regions arranged at angle relative to one another. The first and second exit regions are respectively in low and high pressure regions relative to one another. First and second pedestal groups respectively are arranged at the first and second exit regions. The second pedestal group has first and second pedestals each terminating in an end. The ends of the second pedestals extend beyond the ends of first pedestals.

Abstract: Core assemblies and methods for manufacturing components of gas turbine engines include a first core body having a first trunk configured to attach to a first location of a cavity core structure, a first branch extending from the first trunk and configured to form a first portion of a first cooling circuit, the first branch having a first joining surface, and a second core body having a second trunk configured to attach to a second location of a cavity core structure, a first branch of the second core body extending from the second trunk and configured to form a first portion of a second cooling circuit in the component. The first branches of the core bodies joined to form a junction. The junction defines a merger of the first cooling circuit and the second cooling circuit proximate to an exit of the first and second cooling circuits.

Abstract: A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a body with at least one internal cavity defined by a cavity wall. A plurality of cooling holes formed within the cavity wall, wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet, and wherein the cooling holes are positioned relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.

Abstract: A turbomachine component includes a body defining an interior cooling channel in fluid communication with the exterior of the body for fluid communication with a cooling flow source. At least one flow modifying pedestal is disposed within the interior cooling channel extending in a first direction. The flow modifying pedestal includes at least one flow feature that extends from the pedestal in a second direction.

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a reference plane extending in a spanwise direction along a surface of the internal wall, a first cavity and a second cavity separated by the internal wall, and a plurality of crossover passages within the internal wall and connecting the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The passage axis of each of the plurality of crossover passages is arranged at a radial angle relative to a localized region of the reference plane such that the radial angle of at least some of the plurality of crossover passages differs in the spanwise direction.