Abstract: An integrated cable support, the support comprising a grommet portion for enclosing at least one first elongated cable and a bracket portion for securing at least one second elongated cable in spaced and substantially fixed relation to said at least one first elongated cable. The at least one first elongated cable and the at least one second elongated cable are in a non-parallel orientation.

Abstract: A method for assembling a combustor for use in a turbine engine is provided. The method includes providing at least one support leg, forming at least one opening in the support leg, wherein the at least one opening has a perimeter defined only by a plurality of non-linear segments, and coupling the support leg to the combustor.

Abstract: A method for assembling a combustor for use in a turbine engine is provided. The method includes providing at least one support leg, forming at least one opening in the support leg, wherein the at least one opening has a perimeter defined only by a plurality of non-linear segments, and coupling the support leg to the combustor.

Abstract: A gas turbine engine component has an annular flange arm, a backing plate mounted to the flange arm and a bypass circuit formed between the flange arm and the backing plate. The bypass circuit includes one or more channels formed in one of the flange arm or the backing plate. When more than one channels are used, at least one connecting slot is provided between the channels. At least one inlet passage extends through the flange arm in fluid communication with the forward-most channel, and at least one outlet slot is formed between the flange arm and the backing plate in fluid communication with the aft-most channel.

Abstract: A turbine assembly includes a shroud for being mounted around a last stage of the low pressure turbine rotor. The shroud includes an arcuate body having spaced-apart forward and aft ends and spaced-apart circumferential ends. Attachments are provided for securing the shroud body to the surrounding engine case. An arcuate extension member protrudes rearward from the aft end of the shroud body. The extension member has an inner surface which defines a portion of the gas flowpath through the engine. Seals may be provided to prevent leakage between adjacent shroud segments. The shroud is especially useful for protecting a downstream turbine frame from debris and thermal stress.

Abstract: A gas turbine engine strut segment includes a strut, which may be hollow, extending radially between co-annular radially inner and outer platforms, axially spaced apart inner platform flanges extending radially inwardly from the inner platform, and axially spaced apart outer platform flanges extending radially outwardly from the inner platform. At least one inner set of coaxial tapered inner holes extend axially through the inner platform flanges and at least one outer set of coaxial tapered outer holes extend axially through the outer platform flanges. The inner set of coaxial inner holes define an inner conical surface and the outer set of coaxial outer holes define an outer conical surface. Each of the axial spaced apart platform flanges may be circumferentially continuous or scalloped having spaced circumferentially apart lugs. The strut may have two inner sets of coaxial tapered inner and outer holes extending axially through the inner and outer platform flanges, respectively.

Abstract: A gas turbine engine component has an annular flange arm, a backing plate mounted to the flange arm and a bypass circuit formed between the flange arm and the backing plate. The bypass circuit includes one or more channels formed in one of the flange arm or the backing plate. When more than one channels are used, at least one connecting slot is provided between the channels. At least one inlet passage extends through the flange arm in fluid communication with the forward-most channel, and at least one outlet slot is formed between the flange arm and the backing plate in fluid communication with the aft-most channel.

Abstract: An annular air baffle disposed in a cavity of a rotatable gas turbine engine part includes an annular split ring supporting a plurality of circumferentially spaced apart fins. The cavity is closed at a radially outer diameter and open at a radially inner diameter of the part. The ring and the fins may be integrally formed in one piece. The fins may have common surfaces with the ring and the common surfaces may be circular cross-sectional surfaces of the ring and radially outer rounded corners of the fins. The fins may have triangular cross-sectional shapes with first, second, and third sides, rounded first radially inner corners between the first and second sides, rounded second radially inner corners between the second and third sides, and the radially outer rounded corners between the first and third sides. The fins may extend radially inwardly from the annular split ring.

Abstract: A gas turbine engine strut segment includes a strut, which may be hollow, extending radially between co-annular radially inner and outer platforms, axially spaced apart inner platform flanges extending radially inwardly from the inner platform, and axially spaced apart outer platform flanges extending radially outwardly from the inner platform. At least one inner set of coaxial tapered inner holes extend axially through the inner platform flanges and at least one outer set of coaxial tapered outer holes extend axially through the outer platform flanges. The inner set of coaxial inner holes define an inner conical surface and the outer set of coaxial outer holes define an outer conical surface. Each of the axial spaced apart platform flanges may be circumferentially continuous or scalloped having spaced circumferentially apart lugs. The strut may have two inner sets of coaxial tapered inner and outer holes extending axially through the inner and outer platform flanges, respectively.

Abstract: A stiffener system includes a stiffener and a fastener means. The stiffener includes an extruded body that includes a plurality of projections. The stiffener couples to the apparatus to facilitate increasing a structural integrity of the apparatus. The fastener means secures the stiffener to the apparatus.

Abstract: A gas turbine engine includes a non-rotatable member that includes a honeycomb seal that reduces wear to rotor seal teeth disposed within the gas turbine engine. The gas turbine engine also includes a rotatable annular member including a sealing assembly disposed between rotor and stator components. The rotatable annular member includes seal teeth that extend radially outward from the rotatable annular member. The stator components include a non-rotatable member that includes a honeycomb seal that extends radially inward. The honeycomb seal is fabricated from a material that has a melting temperature less than approximately 2000° F.

Abstract: A fan casing for a gas turbine engine is provided which combines the functions of blade containment and noise suppression. The fan casing has an annular metallic inner shell with a plurality of holes are formed therethrough. An acoustic absorber, such as a cellular resonator, is disposed around the inner shell.

Abstract: The present invention provides a seal for a gas turbine engine, comprising an annular ring with an L-shaped cross-section having a radially extending leg and an axially extending leg. A plurality of corrugations are formed in the axial leg so as to make it compliant in the circumferential direction.

Abstract: A frame for a gas turbine engine is provided comprising a central hub having a circumferentially extending flowpath surface enclosing an interior cavity and an annular outer casing connected to the hub by a plurality of struts extending radially from the hub to the casing, wherein the flowpath surface has a plurality of inlets disposed in flow communication with the interior cavity and a plurality of outlets disposed in flow communication with the interior cavity. A flowpath member for a turbine frame hub is also provided having a plurality of inlets and outlets formed therein.

Abstract: A fan casing for a gas turbine engine is provided which combines the functions of blade containment and noise suppression. The fan casing has an annular metallic inner shell with a plurality of holes are formed therethrough. An acoustic absorber, such as a cellular resonator, is disposed around the inner shell.

Abstract: A frame for a gas turbine engine is provided comprising a central hub having a circumferentially extending flowpath surface enclosing an interior cavity and an annular outer casing connected to the hub by a plurality of struts extending radially from the hub to the casing, wherein the flowpath surface has a plurality of inlets disposed in the in flow communication with the interior cavity and a plurality of outlets disposed in flow communication with the interior cavity. A flowpath member for a turbine frame hub is also provided having a plurality of inlets and outlets formed therein.

Abstract: The present invention provides a seal for a gas turbine engine, comprising an annular ring with an L-shaped cross-section having a radially extending leg and an axially extending leg. A plurality of corrugations are formed in the axial leg so as to make it compliant in the circumferential direction.

Abstract: A gas turbine frame has inner and outer annular bands, respectively, joined together by generally radially extending struts therebetween. A radially outer conical support arm extends radially outwardly from the outer band and a radially inner conical support arm extends radially inwardly from the inner band. Circumferentially spaced apart inner and outer openings are disposed in the inner and outer conical support arms, respectively. Each of the struts has at least one radially extending hollow passage which extends through the inner and outer bands. The frame is a single piece integral casting. The inner and outer conical support arms have an equal number of the inner and outer circumferentially spaced apart openings. The inner circumferentially spaced apart openings are equi-angularly spaced apart and the outer circumferentially spaced apart openings are equi-angularly spaced apart.

Abstract: A gas turbine frame has inner and outer annular bands, respectively, joined together by generally radially extending struts therebetween. A radially outer conical support arm extends radially outwardly from the outer band and a radially inner conical support arm extends radially inwardly from the inner band. Circumferentially spaced apart inner and outer openings are disposed in the inner and outer conical support arms, respectively. Each of the struts has at least one radially extending hollow passage which extends through the inner and outer bands. The frame is a single piece integral casting. The inner and outer conical support arms have an equal number of the inner and outer circumferentially spaced apart openings. The inner circumferentially spaced apart openings are equi-angularly spaced apart and the outer circumferentially spaced apart openings are equi-angularly spaced apart.

Abstract: Multiple tubes are connected to steam supply and spent cooling steam return manifolds for supplying cooling steam to buckets and returning spent cooling steam from the buckets to the manifolds, respectively. The tubes are prevented from axial movement in one direction by flanges engaging end faces of the spacer between the first and second-stage wheels. Retention sleeves are disposed about cantilevered ends of the tubes. One end of the retention sleeve engages an enlarged flange on the tube, while an opposite end is spaced axially from an end face of the adjoining wheel, forming a gap, enabling thermal expansion of the tubes and limiting axial displacement of the tube in the opposite direction.