Abstract: A diffuser case support structure for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case. A sliding joint is formed between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing.

Abstract: A diffuser case assembly for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.

Abstract: A nut strip assembly is provided that includes a carrier and a plurality of nuts. The carrier includes a base, a plurality of first tabs and a plurality of second tabs. The base is configured with a plurality of apertures. Each of the first tabs is connected to and project out from a first side of the base. Each of the second tabs is connected to and projects out from a second side of the base. The nuts are secured to the carrier. Each of the nuts are aligned with a respective one of the apertures. Each of the nuts is captured between the base and a respective one of the first tabs. Each of the nuts captured between the base and a respective one of the second tabs.

Abstract: A diffuser case support structure for a gas turbine engine is disclosed. The diffuser case support structure includes a fairing disposed circumferentially about a longitudinal axis. The fairing forms at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. The fairing defines a plurality of apertures extending through the fairing. At least one spoke extends through at least one respective aperture of the plurality of apertures. The at least one spoke is configured to couple an inner diffuser case and an outer diffuser case of the gas turbine engine.

Abstract: Combustor mounting structures for gas turbine engines are described. The combustor mounting structures include a shell portion defining an outer ring arranged at an outer radius relative to a central axis, a combustor connection element defining an inner ring arranged at an inner radius that is less than the outer radius relative to the central axis, and a plurality of struts extending radially between and connecting the shell portion to the combustor connection element, wherein one or more flow apertures are defined between the shell portion and the combustor connection element in a radial direction and between adjacent struts of the plurality of struts in a circumferential direction.

Abstract: A diffuser case support structure for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case. A sliding joint is formed between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing.

Abstract: A pre-diffuser fairing for a gas turbine engine is disclosed. In various embodiments, the pre-diffuser fairing includes a first side wall, a first radially inward portion and a first radially outward portion and a second side wall, a second radially inward portion and a second radially outward portion. The first side wall and the second side wall are spaced apart to form a cavity configured to receive a strut.

Abstract: A system for an engine defined about an axial centerline includes an inner case that includes a bushing, a duct case radially outward of the inner case with respect to the axial centerline, and a seal located on the duct case. The system further includes a borescope plug assembly that traverses the seal and the bushing in mounting to the inner case. The borescope plug assembly includes a spring, a housing sleeve, and a washer sleeve at least partially nested within the housing sleeve. The spring is isolated from the seal by the housing sleeve and the washer sleeve such that the spring is contact-free with respect to the seal.

Abstract: A diffuser case assembly for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.

Abstract: A diffuser case support structure for a gas turbine engine is disclosed. The diffuser case support structure includes a fairing disposed circumferentially about a longitudinal axis. The fairing forms at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. The fairing defines a plurality of apertures extending through the fairing. At least one spoke extends through at least one respective aperture of the plurality of apertures. The at least one spoke is configured to couple an inner diffuser case and an outer diffuser case of the gas turbine engine.

Abstract: A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A method of cooling a wall assembly for a combustor of a gas turbine engine is also provided. This method includes a step of directing cooling air into at least one convergent passage between the support shell and a multiple of liner panels.

Abstract: An assembly for a turbine engine includes a combustor bulkhead, a swirler and a mounting strap. The swirler includes a mounting lug and a tubular swirler body that extends along an axis. The mounting lug projects radially out from the swirler body. The mounting strap is attached to the combustor bulkhead. The mounting lug is axially restrained between the combustor bulkhead and the mounting strap.

Abstract: A gas turbine engine includes a bushing that is non-round in cross-section, the bushing receivable within an aperture. A fastener passes through the bushing to retain a second component to a third component with respect to the first component.

Abstract: A nut strip assembly is provided that includes a carrier and a plurality of nuts. The carrier includes a base, a plurality of first tabs and a plurality of second tabs. The base is configured with a plurality of apertures. Each of the first tabs is connected to and project out from a first side of the base. Each of the second tabs is connected to and projects out from a second side of the base. The nuts are secured to the carrier. Each of the nuts are aligned with a respective one of the apertures. Each of the nuts is captured between the base and a respective one of the first tabs. Each of the nuts captured between the base and a respective one of the second tabs.

Abstract: A borescope assembly comprises a spring, a housing sleeve, a washer sleeve at least partially nested within the housing sleeve, and a plug coupled to the housing sleeve, where the spring is completely contained within the housing sleeve and the washer sleeve. A system for an engine defined about an axial centerline comprises an inner case that includes a bushing, a duct case radially outward of the inner case with respect to the axial centerline, a seal located on the duct case, and a borescope assembly that traverses the seal and the bushing in mounting to the inner case, the borescope assembly including: a spring, a housing sleeve, and a washer sleeve at least partially nested within the housing sleeve, where the spring is isolated from the seal by the housing sleeve and the washer sleeve such that the spring is contact-free with respect to the seal.

Abstract: A pre-diffuser fairing for a gas turbine engine is disclosed. In various embodiments, the pre-diffuser fairing includes a first side wall, a first radially inward portion and a first radially outward portion and a second side wall, a second radially inward portion and a second radially outward portion. The first side wall and the second side wall are spaced apart to form a cavity configured to receive a strut.

Abstract: An iso-grid composite component according to an exemplary aspect of the present disclosure includes a spacer transverse to a uni-tape ply bundle, the spacer interrupted by the uni-tape ply bundle.

Abstract: A wall assembly is provided for a gas turbine engine. This wall assembly includes a support shell with a contoured region; and a multiple of liner panels mounted to the support shell. At least one of the multiple of liner panels includes an end rail. The contoured region is deformable to selectively contact at least a portion of the end rail. A method of assembling a wall assembly within a gas turbine engine is also provided. This method includes locating a stud that extends from a cold side of a liner panel through a support shell; and attaching a fastener onto the stud to at least partially close a gap defined between the panel and shell.

Abstract: A combustor floatwall panel includes a stack of layers of a sintered material forming in the aggregate a panel, an attachment stud, and a cooling flow passageway. The panel has a first surface and a second surface parallel to the first surface. The attachment stud projects from the second surface. The cooling flow passageway includes a feeder hole extending through the attachment stud, and at least one effusion cooling hole extending to the first surface. The effusion cooling hole is fluidly connected to the feeder hole. The effusion cooling hole extends along a first axis where the effusion cooling hole meets the first surface. The feeder hole extends along a second axis. The first axis is at a first angle relative to the first surface. The second axis is at a second angle relative to the first surface. The second angle is greater than the first angle.

Abstract: An annular seal includes an annular outer casing, a plurality of seal segments, and a plurality of spring components. The plurality of seal segments is coupled to the annular outer casing to cumulatively form an annular sealing surface, the annular sealing surface is configured to face a rotating structure to inhibit fluid leakage between the rotating structure and the annular sealing surface, and each seal segment of the plurality of seal segments is configured for independent radial movement relative to other seal segments of the plurality of seal segments. In various embodiments, the plurality of spring components are configured to bias the plurality of seal segments relative to the radial movement.