Abstract: A method for assembling a gas turbine engine includes coupling a first structure within the gas turbine engine, wherein the first structure includes a plurality of sockets extending from a radially outer surface of the first structure, and coupling a second structure to the first structure by inserting a radial pin through the second structure and into each respective socket such that the first structure is aligned axially, circumferentially, and with respect to an engine centerline axis extending through the gas turbine engine, where the position of the pins relative to the second structure is adjustable.

Abstract: A method for assembling a gas turbine engine includes coupling an axisymmetric structure within the gas turbine engine, wherein the axisymmetric structure includes at least one mounting bushing extending from a radially outer surface of the axisymmetric structure, and inserting a pin having a crowned surface at least partially into the mounting bushing such that the pin provides both axial and tangential support to the axisymmetric structure, and securing the pin to the gas turbine engine utilizing a retaining assembly.

Abstract: A method for exchanging heat between a first fluid and a second fluid. The method includes providing a heat exchanger having a stack of at least two layers of support structures, wherein each support structure layer is formed from a lattice of support members, and substantially fluidly separating the at least two support structure layers using at least one barrier such that each layer defines a fluid passageway. The method also includes directing a flow of first fluid through a first of the fluid passageways, and directing a flow of second fluid through a second of the fluid passageways that is adjacent the first fluid passageway to facilitate exchanging heat between the first and second fluids.

Abstract: A method for assembling a gas turbine engine includes coupling an outer structure within the gas turbine engine, wherein the outer structure includes a socket extending from a radially inner surface of the outer structure, and coupling an inner structure to the outer structure by inserting a radial pin through the inner structure and into the socket such that the inner structure is aligned axially, circumferentially, and with respect to an engine centerline axis extending through the gas turbine engine.

Abstract: A turbomachine frame member including an annular inner hub and a concentric annular outer casing that is spaced radially outwardly from the inner hub to define an annular flow passageway. A plurality of substantially radially-extending, circumferentially-spaced struts interconnect the inner hub and outer casing. The struts are connected to the outer casing by respective pairs of connecting bolts that pass through the outer casing and into the struts to engage barrel nuts.

Abstract: A turbomachine frame member including an annular inner hub and a concentric annular outer casing that is spaced radially outwardly from the inner hub to define an annular flow passageway. A plurality of substantially radially-extending, circumferentially-spaced struts interconnect the inner hub and outer casing. The struts are connected to the outer casing by respective pairs of connecting bolts that pass through the outer casing and into the struts to engage barrel nuts.

Abstract: A method for exchanging heat between a first fluid and a second fluid. The method includes providing a heat exchanger having a stack of at least two layers of support structures, wherein each support structure layer is formed from a lattice of support members, and substantially fluidly separating the at least two support structure layers using at least one barrier such that each layer defines a fluid passageway. The method also includes directing a flow of first fluid through a first of the fluid passageways, and directing a flow of second fluid through a second of the fluid passageways that is adjacent the first fluid passageway to facilitate exchanging heat between the first and second fluids.

Abstract: A centerbody for a gas turbine engine includes a thermal control system which minimizes the thermal stresses between the centerbody and at least one stiffener. The centerbody stiffener extends radially inward from a centerbody shell. A cavity is defined within each centerbody stiffener. The thermal control system includes a plurality of openings circumferentially disposed around the centerbody. Each opening extends through the centerbody shell into each cavity. The openings include pairs of entrance openings and exit openings which permit circumferential flow to develop within the centerbody cavity.

Abstract: A low pressure turbine shroud includes an arcuate backsheet having opposite mounting rails for engaging a surrounding annular case. The backsheet includes a thicker blade containment shield extending between the rails in a unitary construction. And, a honeycomb rub strip is fixedly joined to the backsheet between the rails.

Abstract: A fan case for a turbofan engine having a fan including plurality of fan blades mounted to a rotor disk and a decoupler that fails in response to a predetermined load includes a substantially annular shell. The shell has a forward section, an intermediate section, and an aft section. The fan case further includes an aft facing step formed at the forward end of the intermediate section to prevent blade fragments from being ejected forward. The intermediate section is axially aligned with the fan and has a large inside diameter. The intermediate section thus defines an annular space around the fan blades that is sufficiently large to allow the fan to orbit when the decoupler fails. The intermediate section and the aft section are aligned radially to allow blade fragments to be ejected aft, avoiding additional secondary blade damage.

Abstract: A casing for a gas turbine engine having a longitudinal axis extending therethrough, including a first casing portion having a substantially arcuate section and a split-line flange extending from each end thereof and a second casing portion having a substantially arcuate section and a split-line flange extending from each end thereof. The first and second casing portions are mated at each end by connecting together respective pairs of the split-line flanges. A channel is formed in at least one mating surface of the split-line flanges to provide an axial passage therethrough so that air flow provided to the axial passage reduces a temperature gradient between the arcuate sections and the flanges of the first and second casing portions.

Abstract: An improved containment structure for use with turbomachinery, such as turbofan engines. A casing is provided with at least one impact resistant section of a thickness sufficient to resist being pierced upon impact by a blade. The impact resistant section has a smoothly contoured thickness along its axial length and is free from features likely to cause a local failure in the event of impact by a blade released from a rotating disk.

Abstract: A low pressure turbine shroud includes an arcuate backsheet having opposite mounting rails for engaging a surrounding annular case. The backsheet includes a thicker blade containment shield extending between the rails in a unitary construction. And, a honeycomb rub strip is fixedly joined to the backsheet between the rails.

Abstract: A low profile joint is provided for a strut tube extending radially through a strut extending between an outer casing and an inner hub in a gas turbine engine frame. The strut tube has a longitudinal axis and a closed distal end. A sideseat is spaced from the distal end and is disposed substantially perpendicularly to the longitudinal axis to define a flow orifice. A secondary tube has a ballnose at a distal end thereof disposed in abutting contact with the sideseat for channeling fluid therebetween. A fastener joins together the strut and secondary tubes in compression between the ballnose and sideseat to maintain sealed contact therebetween for channeling fluid between the strut and secondary tubes.

Abstract: A turbine frame includes outer and inner coaxially disposed annular casings having a plurality of circumferentially spaced apart struts extending therebetween is provided with at least one and preferably two axially spaced apart polygonal stiffening rails, a forward rail and an aft rail, circumferentially disposed on the outer annular casing. The rails have at least a first section with a constant cross-sectional area normal to the casing in a circumferential direction around the outer casing, a linear centroid distribution of the cross-sections in the circumferential direction, and the centroids lie in a first plane P1 which is parallel to and spaced apart from a second plane P2 that is tangential to the outer casing mid-way between adjacent struts.

Abstract: A turbine flowpath assembly includes a plurality of circumferentially spaced apart airfoils disposed within an annular outer casing. Each of the airfoils includes outer and inner integral bands. A plurality of flowpath outer and inner panels are disposed between adjacent ones of the bands and circumferentially overlap the bands. The panels and bands are joined together at the respective overlaps using tripod plates and fasteners therethrough for allowing circumferential movement therebetween while providing sealing.

Abstract: A blade containment system is disclosed which includes an annular casing positioned radially outward of the blades and in surrounding relationship therewith, the annular casing including a plurality of composite tapes bonded to the outer or inner radial surfaces thereof, wherein the composite tapes limit the propagation of cracks and holes formed in the annular casing.

Abstract: A turbine flowpath assembly includes a plurality of circumferentially spaced apart airfoils disposed within an annular outer casing. Each of the airfoils includes outer and inner integral bands. A plurality of flowpath outer and inner panels are disposed between adjacent ones of the bands and circumferentially overlap the bands. The panels and bands are joined together at the respective overlaps for allowing circumferential movement therebetween while providing sealing.

Abstract: A structural frame assembly for use in a gas turbine engine includes an annular inner hub, an annular outer casing and a plurality of circumferentially-spaced and radially extending hollow struts connected to the inner hub and outer casing. Hot gases are extracted from the engine primary flowpath, using a scoop attached to each strut, and are directed through the struts to the inner hub interior for the purpose of reducing a bulk temperature differential between the outer casing and the inner hub and for providing a uniform temperature distribution within the inner hub. A first portion of the hot gases entering the inner hub flows continuously through passages extending through the inner hub forward wall and scrubs an exterior of the forward wall, using an annular shield attached to the inner hub, before re-entering the engine flowpath.

Abstract: A turbine frame includes first and second coaxially disposed rings having a plurality of circumferentially spaced apart struts extending therebetween. A plurality of clevises join respective first ends of the struts to the first ring for removably joining the struts thereto. Each of the clevises includes a base removably fixedly joined to the first ring, and a pair of legs extending away from the base and spaced apart to define a U-shaped clevis slot receiving the strut first end. The first strut end is removably fixedly joined to the clevis legs by a pair of expansion bolts. The clevis base includes a central aperture aligned with a first port in the first ring for providing access therethrough. And, the strut first end abuts the first ring for carrying compressive loads therebetween and providing a seal therewith.