Abstract: A combustor for a gas turbine engine includes an annular combustor shell, the annular combustor shell defining a combustion chamber, and a fuel injector extending at least partially into the combustion chamber, and configured to deliver a flow of fuel and a flow of combustion air into the combustion chamber for combustion. The fuel injector includes a swirler with a swirler exit having a circumferential width along a circumferential axis greater than a radial width along a radial axis. A swirler for a gas turbine engine includes a swirler entrance and a swirler exit. The swirler exit has a circumferential width along a curvilinear circumferential axis greater than a radial width along a radial axis.

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 borescope plug assembly includes a borescope plug having a shaft section and a tip section, a bushing engageable with the shaft section and a seal engageable with the tip section.

Abstract: A sealing arrangement has a turbine static structure with contact surfaces, a bearing compartment with contact surfaces, and a cavity between the turbine static structure and the bearing compartment. There are also two seals, wherein each seal is configured to contact the turbine static structure and the bearing compartment.

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: An interface within a gas turbine engine includes a sealing surface defined by a portion of a vane platform. A seal is in contact with said sealing surface. A barrier is transverse to the sealing surface.

Abstract: A combustor panel of a combustor may include a combustion facing surface and a cooling surface opposite the combustion facing surface. An attachment feature may extend from the cooling surface. The attachment feature may define a first channel extending through the attachment feature to the combustion facing surface. The combustor channel may be formed by additive manufacturing.

Abstract: A seal system is provided. The seal system may comprise a first duct having an annular geometry, a second duct overlapping the first duct in a radial direction, and a seal disposed between the first duct and the second duct. The seal may comprise a groove defined by the first duct and a piston configured to slideably engage the groove.

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 casting mold assembly includes an airfoil defining section and a casting core. The airfoil defining section includes an outer mold wall and a direct-shelled inner mold wall. The direct-shelled inner mold wall is disposed within a forward chordwise portion of the airfoil defining section. The direct-shelled inner mold wall includes an aft end having an external radius measuring more than about 0.075 in. (1.9 mm). The casting core is secured within an aft chordwise portion of the airfoil defining section, and includes an aft end with an external radius measuring less than about 0.075 in. (1.9 mm). A cast component and a method for making the casting mold assembly are also disclosed.

Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract: A minidisk for a rotor system may comprise a balance flange defining a hole array, which may include a first hole having a first width. The first hole may be configured to receive a balance weight. A second hole and a third hole may have a second width. The second hole and the third hole may be disposed adjacent to the first hole. The second width may be greater than the first width.

Abstract: A seal system is provided. The seal system may comprise a first duct having an annular geometry, a second duct overlapping the first duct in a radial direction, and a seal disposed between the first duct and the second duct. The seal may comprise a groove defined by the first duct and a piston configured to slideably engage the groove.

Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange. A method of cooling a portion of a gas turbine engine is also disclosed.

Abstract: According to one embodiment of the present invention, a sealing arrangement includes a turbine static structure with an inner case and a seal ring each having contact surfaces. The sealing arrangement also has a bearing compartment with a contact surface. A piston seal is positioned between the inner case, the seal ring, and the bearing compartment and is configured to contact the contact surfaces.

Abstract: A sealing arrangement for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a groove that extends between an upstream rail and a downstream rail, a complementary static structure spaced from the groove, and a seal positioned within the groove and configured to seal a clearance between at least one of the upstream rail and the downstream rail and the complementary static structure.

Abstract: Inspection systems for a gas turbine engine (20) are provided. The inspection systems may comprise an inspection port (106), a bore-scope plug (100), a seal seat (108) and a seal (110A/110B). The bore-scope plug (100) may comprise a shaft (102A/102B) having a uniform or stepped profile. The seal (110A/110B) may be a multi-part seal (110A) or a piston seal (110B). Moreover, the bore-scope plug (100) may be configured to support, carry, and/or stabilize one or more internal structures such as, for example, a mid-turbine frame vane 82. In various embodiments, the inspection systems described herein may provide for increased inspection efficiency during development, qualification, maintenance, and event inspections.

Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange and between adjacent spokes. A method of cooling a portion of a gas turbine engine is also disclosed.

Abstract: A rotor disc assembly includes a rotor disc and a minidisc. The rotor disc has a first extension member, a first finger, and a second finger. The first extension member axially extends from a disc body disposed about an axis. The first finger extends axially from the first extension member. The second finger is circumferentially spaced apart from the first finger. The second finger extends axially from the first extension member. Each of the first finger and the second finger has a first portion and a second portion that extends radially from a distal end of the first portion. The minidisc is operatively connected to the rotor disc. The minidisc has an interlocking finger that radially extends from a minidisc body and is disposed between the first finger and the second finger. The interlocking finger, the first portion, and second portion define a ring groove.

Abstract: A seal land for a gas turbine engine can include a seal body circumferentially extending about a longitudinal centerline axis. The seal body includes at least one sealing surface that extends in a plane that is transverse to the longitudinal centerline axis.