Abstract: A combustor assembly for a gas turbine engine includes a TOBI module that includes a TOBI housing. The TOBI housing has a slot. A vane includes a dovetail removably received within the slot. The TOBI housing includes an axially extending TOBI nozzle array. The TOBI housing includes a plenum. A cooling passage fluidly connects the plenum to the vane. The TOBI housing includes passages configured to provide cooling fluid to the vane. The TOBI housing includes a first passageway further connecting the TOBI nozzle to the plenum.

Abstract: A fuel fitting assembly includes a monolithic fuel fitting formed by additive manufacturing. The fitting includes a first end, a second end, a conduit extending axially through the fitting from the first end to the second end, and a first sealing element. The first end is to be connected to a fuel line. The second end is to be connected to a device requiring or providing fuel. The first sealing element includes a sealing seat circumferentially surrounding the conduit at the second end of the fitting. The fuel fitting is integrally formed as a stack of layers of material.

Abstract: A cooling arrangement for a turbine engine includes a cooling source and first and second structures. A ceramic-based composite cooling tube fluidly provides a fluid connection between the first and second structures. The cooling tube is configured to transfer a cooling fluid from the cooling source to the second structure.

Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a swirler threaded section defined around a swirler central longitudinal axis. A bulkhead support shell for a combustor of a gas turbine engine includes a swirler boss with a boss threaded section defined around a swirler central longitudinal axis. A combustor of a gas turbine engine includes a bulkhead support shell with a swirler boss. The combustor also includes a swirler mountable to the swirler boss at a threaded interface defined around a swirler central longitudinal axis.

Abstract: A combustor assembly for a gas turbine engine includes a TOBI module that includes a TOBI housing. The TOBI housing has a slot. A vane includes a dovetail removably received within the slot. The TOBI housing includes an axially extending TOBI nozzle array. The TOBI housing includes a plenum. A cooling passage fluidly connects the plenum to the vane. The TOBI housing includes passages configured to provide cooling fluid to the vane. The TOBI housing includes a first passageway further connecting the TOBI nozzle to the plenum.

Abstract: A divergent flap includes a hinge joint to connect the divergent flap to a convergent flap, a plow structure, a first wall, a second wall, and two side walls. The plow structure is at a plow end of the flap opposite the hinge joint. The first wall and the second wall each extend from the hinge joint to the plow end. The second wall is spaced apart from the first wall by the two side walls to form at least one cooling channel extending between the hinge joint and the plow end. The divergent flap is integrally formed in layer-by-layer fashion as a single piece.

Abstract: A combustor assembly for a gas turbine engine includes a TOBI module which includes a TOBI housing. The TOBI housing has a slot. A vane including a dovetail is removably received within the slot.

Abstract: A heat-shielded conduit includes a tube, a heat shield, and a truss structure. The tube has a tube inner diameter and a tube outer diameter. The heat shield radially surrounds the tube. The heat shield has a shield inner diameter greater than the tube outer diameter to form a first gap between the heat shield and the tube. The truss structure is integrally formed together with both of the tube and the heat shield to space the shield inner diameter from the tube outer diameter and maintain the first gap.

Abstract: A structural panel for use with a gas turbine engine includes a first exterior wall, a second exterior wall, and interior walls. The first exterior wall includes a first exterior surface and a first interior surface parallel to the first exterior surface. The second exterior wall includes a second exterior surface and a second interior surface parallel to the second exterior surface. The interior walls extend from the first interior surface to the second interior surface. The interior walls are arranged to form a pattern of hexagonal cells. The pattern of hexagonal cells includes cell groups having a variation in structural strength such that at least one of the cell groups has a structural strength that is not the same as the remaining cell groups.

Abstract: A fuel fitting assembly includes a monolithic fuel fitting formed by additive manufacturing. The fitting includes a first end, a second end, a conduit extending axially through the fitting from the first end to the second end, and a first sealing element. The first end is to be connected to a fuel line. The second end is to be connected to a device requiring or providing fuel. The first sealing element includes a sealing seat circumferentially surrounding the conduit at the second end of the fitting. The fuel fitting is integrally formed as a stack of layers of material.

Abstract: A swirler is provided for a gas turbine engine. The swirler includes a swirler body with a threaded section and a multiple of circumferentially arranged tabs operable to flex radially outward. The multiple of circumferentially arranged tabs are radially displaced from the threaded section.

Abstract: A unitary one-piece hub has first and second rings and a midsection arranged between the first and second rings. The midsection includes a plurality of windows configured to receive a plurality of cross members. The windows include a lip configured to surround the cross members. A gas turbine engine and a method of providing a hub for a gas turbine engine are also disclosed.

Abstract: A method of detecting debris within a lubricant stream, the method includes generating data indicative of debris and sensor system functionality within a lubricant stream with a sensor system. The data is communicated to a controller. Features calculated from the data are indicative of a debris within the lubricant stream. The calculated features are compiled over time during operation. The compiled features are classified. An oil debris monitoring system for a turbine engine is also disclosed.

Abstract: A cooling arrangement for a turbine engine includes a cooling source and first and second structures. A ceramic-based composite cooling tube fluidly provides a fluid connection between the first and second structures. The cooling tube is configured to transfer a cooling fluid from the cooling source to the second structure.

Abstract: A turbine engine includes multiple tierod supports. Each of the tierod supports is connected to an inner frame case of the turbine engine via multiple fasteners and at least one self anti-rotating bushing component.

Abstract: A heat-shielded conduit includes a tube, a heat shield, and a truss structure. The tube has a tube inner diameter and a tube outer diameter. The heat shield radially surrounds the tube. The heat shield has a shield inner diameter greater than the tube outer diameter to form a first gap between the heat shield and the tube. The truss structure is integrally formed together with both of the tube and the heat shield to space the shield inner diameter from the tube outer diameter and maintain the first gap.

Abstract: A fuel fitting assembly includes a monolithic fuel fitting formed by additive manufacturing. The fitting includes a first end, a second end, a conduit extending axially through the fitting from the first end to the second end, and a first sealing element. The first end is to be connected to a fuel line. The second end is to be connected to a device requiring or providing fuel. The first sealing element includes a sealing seat circumferentially surrounding the conduit at the second end of the fitting. The fuel fitting is integrally formed as a stack of layers of material.

Abstract: An effusion-cooled component includes a base portion defining at least one oversized cooling hole preform. A coating is disposed on the base portion and at least partially covers the oversized cooling hole preform to define a cooling hole. The component may be repaired by removing the coating from a component, visually inspecting the resultant base, and re-coating the base with a coating that oversprays to at least partially fill the oversized cooling preforms to define a plurality of cooling holes.

Abstract: A divergent flap includes a hinge joint to connect the divergent flap to a convergent flap, a plow structure, a first wall, a second wall, and two side walls. The plow structure is at a plow end of the flap opposite the hinge joint. The first wall and the second wall each extend from the hinge joint to the plow end. The second wall is spaced apart from the first wall by the two side walls to form at least one cooling channel extending between the hinge joint and the plow end. The divergent flap is integrally formed in layer-by-layer fashion as a single piece.

Abstract: A structural panel for use with a gas turbine engine includes a first exterior wall, a second exterior wall, and interior walls. The first exterior wall includes a first exterior surface and a first interior surface parallel to the first exterior surface. The second exterior wall includes a second exterior surface and a second interior surface parallel to the second exterior surface. The interior walls extend from the first interior surface to the second interior surface. The interior walls are arranged to form a pattern of hexagonal cells. The pattern of hexagonal cells includes cell groups having a variation in structural strength such that at least one of the cell groups has a structural strength that is not the same as the remaining cell groups.