Abstract: In one or more embodiments, a luminaire includes a housing, a light source coupled with the housing, an optical sheet coupled with the housing, and a film stabilizer coupled with the housing. The optical sheet includes a first surface and an opposing second surface that are both disposed substantially horizontally when the luminaire is in an installed orientation. The first surface is disposed facing the light source, so that when the light source emits light, the light passes first through the first surface and subsequently through the second surface. The film stabilizer includes a third surface and an opposing fourth surface. The film stabilizer is disposed with the third surface adjacent to the second surface of the optical sheet, and provides mechanical support for the optical sheet.

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case defining a sealed torque box cavity. Multiple spokes protrude radially outward from the inner frame case, and at least one service line is connected to the inner frame case.

Abstract: A luminaire assembly includes a frame and a back plate. In some examples, the frame includes a lip, and the back plate includes a tab. The back plate is positionable within a housing area of the frame such that the tab is engaged with the lip and the back plate is retained within the frame. In other examples, a luminaire assembly includes a wireless module with an antenna positioned adjacent to a module opening of the back plate. The antenna provides wireless transmissions above the top side of the back plate and below the bottom side of the back plate. A luminaire support clip for a luminaire assembly includes a base and a tab. The tab and the base define a receiving area, and the luminaire support clip receives a portion of an edge of a back plate of the luminaire assembly within the receiving area.

Abstract: A case assembly for a gas turbine engine, includes a case with a case boss, said case boss including a peripheral wall that defines a first inner diameter in a first condition to receive a piston seal, and a second inner diameter in a second condition, the second condition including enlargement of the first inner diameter to form a second inner diameter and a bushing mounted within the second inner diameter, an inner diameter of the bushing defines a bushing inner diameter about equivalent to the first inner diameter to receive the piston seal.

Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.

Abstract: In one or more embodiments, a luminaire includes a housing, a light source coupled with the housing, an optical sheet coupled with the housing, and a film stabilizer coupled with the housing. The optical sheet includes a first surface and an opposing second surface that are both disposed substantially horizontally when the luminaire is in an installed orientation. The first surface is disposed facing the light source, so that when the light source emits light, the light passes first through the first surface and subsequently through the second surface. The film stabilizer includes a third surface and an opposing fourth surface. The film stabilizer is disposed with the third surface adjacent to the second surface of the optical sheet, and provides mechanical support for the optical sheet.

Abstract: A heat shield provided with a gas turbine engine includes a heat shield body extending between a first heat shield end and a second heat shield end. The heat shield body has an exterior surface disposed proximate an inner surface of a first case and an interior surface disposed opposite the exterior surface. The interior surface defines a rib that extends towards a combustor vane support lock.

Abstract: A heat shield assembly for an engine case of a gas turbine engine may include a heat shield and a support lock. The heat shield may have an annular shape and a groove formed circumferentially along an inner surface of the heat shield. The support lock may have a tab extending radially outward from a distal surface of the support lock. The groove in the heat shield may be configured to retain the tab of the support lock.

Abstract: A heat shield assembly for an engine case of a gas turbine engine may include a heat shield and a support lock. The heat shield may have an annular shape. The heat shield may define an aperture extending through the heat shield. The support lock may have a tab extending radially outward from a distal surface of the support lock. The aperture in the heat shield may be configured to retain the tab of the support lock.

Abstract: An example diffuser assembly includes a diffuser case, an annular ring, and a retaining tab that is mounted to the annular ring and has an end that engages an inner wall of the diffuser case. The engagement between the second end and the inner wall locks the retaining tab and limits movement of the annular ring along a central longitudinal axis of the diffuser case. Another example diffuser assembly includes a diffuser case, an annular ring, and a snap ring. The snap ring is situated in an annular groove of an inner wall of the diffuser case, and restricts movement of the annular ring along a central longitudinal axis of the diffuser case. A retaining tab is affixed to either the annular ring or the diffuser case, and has an end retaining the annular ring in the annular groove.

Abstract: A combustor panel may comprise a panel wall comprising a proximal surface and a distal surface. A standoff may be formed over the distal surface of the panel wall. An aperture may be formed through the standoff and may extend from a face of the standoff to the proximal surface of the panel wall. The face of the first standoff may be oriented at an angle between 90 degrees and 160 degrees relative to a plane parallel to the distal surface of the panel wall.

Abstract: A luminaire assembly includes a frame and a back plate. In some examples, the frame includes a lip, and the back plate includes a tab. The back plate is positionable within a housing area of the frame such that the tab is engaged with the lip and the back plate is retained within the frame. In other examples, a luminaire assembly includes a wireless module with an antenna positioned adjacent to a module opening of the back plate. The antenna provides wireless transmissions above the top side of the back plate and below the bottom side of the back plate. A luminaire support clip for a luminaire assembly includes a base and a tab. The tab and the base define a receiving area, and the luminaire support clip receives a portion of an edge of a back plate of the luminaire assembly within the receiving area.

Abstract: A combustor panel may include an attachment feature having a central longitudinal axis and extending from a cold side of the combustor panel. The attachment feature may include a tip portion and a base portion and the attachment feature may be configured to extend through a combustor shell such that the tip portion is disposed outward of a diffuser-facing side of the combustor shell. The base portion may be configured to be disposed between the cold side of the combustor panel and the diffuser-facing side of the combustor shell. The attachment feature may define a core passage extending from an inlet opening defined on the tip portion and extending partially through the attachment feature to terminate within the attachment feature. The attachment feature may also define an offshoot passage extending from the core passage to an outlet opening defined on the base portion.

Abstract: A compliant seal assembly that may be for an MTF of a gas turbine engine includes a housing orientated about an axis with a circumferentially extending groove in the housing opened radially outward. An annular carrier of the assembly is constructed and arranged to move radially within the groove, and includes a circumferentially extending channel that is opened radially outward for receipt of a piston ring that may seal to a surrounding cylindrical wall. In operation, the carrier moves radially with respect to the housing to compensate for radial displacement between the housing and the wall, and the piston ring moves axially along the wall to compensate for axial displacement between the housing and the wall.

Abstract: A heat shield assembly for an engine case of a gas turbine engine may include a heat shield having an annular shape. A first groove may be formed circumferentially along an inner surface of the heat shield. A support lock may have a second groove extending radially inward from a distal surface of the support lock. A retention ring may be configured to fit within the first groove of the heat shield and the second groove of the support lock.

Abstract: An assembly includes a case structure, a seal interfacing with the case structure, a first pin, and a main pin hole on one of the seal and the case structure. The first pin extends through the main pin hole and is fixed relative to the other of the seal and the case structure. The assembly also includes a second pin and a secondary pin hole on one of the seal and the case structure. The second pin extends through the secondary pin hole. A cross-sectional gap area between the second pin and the secondary pin hole is greater than a cross-sectional gap area between the first pin and the main pin hole. Also included is a bolt hole on one of the seal and the case structure. The bolt hole is circumferentially located between the main pin hole and the secondary pin hole.

Abstract: A combustor cooling system for a combustor of a gas turbine engine is provided. The combustor cooling system comprising: a heat exchanger fluidly connected to a compressor section of the gas turbine engine, the heat exchanger being configured to receive compressor bleed air from the compressor section and cool the compressor bleed air; and a plenum assembly fluidly connected to the heat exchanger, the plenum assembly configured to receive cooled compressor bleed air from the heat exchanger and distribute the cooled compressor bleed air to one or more areas of the combustor.

Abstract: A method may comprise providing an M-flange of a gas turbine engine, wherein the M-flange may comprise a bolt hole therethrough defined by a bolt hole circumference between an inner diameter and an outer diameter of the M-flange; heating a mandrel; inserting the heated mandrel into the bolt hole such that an outer edge of the heated mandrel contacts the bolt hole circumference; and plastically deforming the bolt hole circumference to strengthen the bolt hole circumference in response to the applying the heated mandrel, producing a plastically deformed bolt hole.

Abstract: A combustor panel may include an attachment feature having a central longitudinal axis and extending from a cold side of the combustor panel. The attachment feature may include a tip portion and a base portion and the attachment feature may be configured to extend through a combustor shell such that the tip portion is disposed outward of a diffuser-facing side of the combustor shell. The base portion may be configured to be disposed between the cold side of the combustor panel and the diffuser-facing side of the combustor shell. The attachment feature may define a core passage extending from an inlet opening defined on the tip portion and extending partially through the attachment feature to terminate within the attachment feature. The attachment feature may also define an offshoot passage extending from the core passage to an outlet opening defined on the base portion.

Abstract: A combustor panel may comprise a panel wall comprising a proximal surface and a distal surface. A standoff may be formed over the distal surface of the panel wall. An aperture may be formed through the standoff and may extend from a face of the standoff to the proximal surface of the panel wall. The face of the first standoff may be oriented at an angle between 90 degrees and 160 degrees relative to a plane parallel to the distal surface of the panel wall.