Abstract: A damper for damping vibration of a structural member of a gas turbine engine is disclosed. The damper may include a first metal mesh pad which abuts an outer circumferential surface of the structural member, and a garter spring which abuts the first metal mesh pad. Both the metal mesh pad and the garter spring may completely or partially encircle the structural member. Alternatively, the damper may include a damper cover which encloses the first metal mesh pad and the garter spring and which abuts the outer surface of the structural member. A second metal mesh pad may be inserted between the damper cover and the garter spring. A gas turbine engine which comprises such a damper is also disclosed.

Abstract: A wall assembly includes a wall that extends axially along a centerline, and circumferentially at least partially around the centerline. The wall assembly also includes a plurality of mounting brackets arranged circumferentially around the centerline, and a plurality of wall brackets. Each of the mounting brackets includes a groove that extends axially into the respective mounting bracket. Each of the wall brackets includes a tongue and a base. The tongue extends axially from the base into the groove of a respective one of the mounting brackets. The base is connected to the wall.

Abstract: A heat shield for a mid-turbine frame has a conical body, including at least one axial retention feature, at least one circumferential retention feature, and at least one radial retention feature.

Abstract: The present invention discloses a novel apparatus and way for altering the airflow to a gas turbine combustion system. The apparatus comprises a flow divider mechanism which splits the airflow surrounding a combustion liner into two distinct portions, one directed towards a pilot and one directed towards a main stage combustion. The flow divider mechanism is interchangeable so as to provide a way of altering airflow splits between stages of the combustion system.

Abstract: A support hanger is provided for a turbine engine. The support hanger includes a pin with a pin head, a retainer and a flexible seal. The retainer is pivotally connected to the pin head. The retainer includes a seal bearing surface facing towards the pin head. The seal includes a retainer bearing surface sealingly engaging the seal bearing surface.

Abstract: A device for filtering intake air of an internal combustion engine, including at least one filtering element including an inlet for air being treated, a first clean air outlet toward the engine, and a second air outlet toward the outside, and a ventilation mechanism driving the air from the second air outlet. The ventilation mechanism includes a fan wheel driven by a turbine set into motion by a gas flow taken from the engine.

Abstract: Gas-turbine combustion chamber with a combustion chamber head made from a metallic material and mounting at least one burner, and with a combustion chamber wall made from a ceramic material, where at least one igniter plug or other combustion chamber attachment is arranged in a recess of the combustion chamber wall, and where in the area of the recess a seal is arranged that is mounted by a metallic holding mechanism from another component than the combustion chamber wall.

Abstract: A disclosed hanger assembly for supporting a liner within a gas turbine engine exhaust nozzle includes a first mount for attachment to a case and a second mount for attachment to the liner. A u-joint assembly is attached between the first and second mounts and includes a first yoke and a second yoke aligned transverse to the first yoke. A pivot block is includes a first set of pins received by the first yoke and a second set of pins received by the second yoke. The u-joint assembly accommodates relative movement between the liner and case.

Abstract: A combustor includes a breech end, a fuel nozzle connected to the breech end and extending downstream from the breech end, and a shroud that circumferentially surrounds the fuel nozzle inside the combustor. A support extends radially inside at least a portion of the shroud, and a flexible coupling is between the support and the fuel nozzle. An adjustable tensioner is configured to engage with the flexible coupling and constrain longitudinal extension of the flexible coupling.

Abstract: A combustor includes a breech end, a plurality of fuel nozzles connected to the breech end and extending downstream from the breech end, and a shroud that circumferentially surrounds the plurality of fuel nozzles inside the combustor. A support extends radially inside at least a portion of the shroud. A leaf spring is between the support and one or more of the plurality of fuel nozzles, wherein each leaf spring includes at least three leaves.

Abstract: This invention relates to an aft pylon fairing (30) for a suspension system of an aircraft engine, comprising two side panels (44) assembled to each other by inner cross stiffening ribs (46) spaced at intervals from each other along a longitudinal direction (X) of the fairing, and also comprising a heat protection deck (32) designed to delimit an engine core flow (36). According to the invention, it also comprises two longitudinal connecting walls (58) offsetting the deck (32) from the ribs (46), each of these two longitudinal walls (58) being provided with a first side end (62) fixed to one or the other of the two side ends (60, 60) of the deck (32), and a second side end (64) rigidly fixed to the ribs (46).

Abstract: A bushing for assembling an exhaust duct liner with an exhaust duct in a gas turbine engine comprises a body, a bushing opening and a first tab. The body is insertable into a duct opening in an exhaust duct. The bushing opening extends through the body to receive a shaft of a liner fastener. The first tab protrudes from the body to extend into an interior of the duct to prevent rotation of a head of the liner fastener.

Abstract: A bleed valve module for mounting to a support structure within an aircraft includes a pipe, a plurality of bleed valves connected to the pipe, a plurality of pneumatic actuators connected to the plurality of bleed valves, and a vibration isolating element. The pipe contains a flow of bleed air and includes a plurality of inlets and an outlet. The plurality of bleed valves controls the flow of bleed air in the pipe. The plurality of pneumatic actuators actuate the plurality of bleed valves. The vibration isolating element connects the bleed valve module to the support structure within the aircraft and isolates the bleed valve module from vibration.

Abstract: A gas turbine device includes an inlet casing and a stator diaphragm provided inside the inlet casing. The stator diaphragm has an integral inner stator shroud and an outer stator shroud and a plurality of stator vanes provided in a circumferential arrangement between the inner stator shroud and the outer stator shroud. A plurality of key slots is provided in a circumferential arrangement on the stator diaphragm and a corresponding plurality of key slots is provided in a circumferential arrangement on the inlet casing. The key slots provided on the stator diaphragm are aligned with the plurality of key slots provided on the inlet casing. A key is inserted into each of the plurality of key slots provided to prevent rotation of the stator diaphragm with respect to the inlet casing. The stator diaphragm is secured in an axial direction by a stator shear ring.

Abstract: A hanger for a gas turbine exhaust system includes an exhaust duct attachment structure associated with an exhaust duct and a liner attachment structure associated with a liner spaced radially inwardly of the exhaust duct. The exhaust duct attachment structure and the liner attachment structure cooperate to suspend the liner within the exhaust duct such that the exhaust duct and liner are movable relative to each other. At least one resilient member generates a resilient biasing force between the exhaust duct attachment structure and the liner attachment structure.

Abstract: A hanger for suspending a liner within an exhaust duct of a gas turbine engine comprises a bracket, a washer, a rod and a cap. The bracket is for connection to an exhaust duct liner of a gas turbine exhaust system. The washer is connected to the bracket at a slip joint. The rod is connected to the washer at a ball joint. The cap for is for connecting to an exhaust duct of the gas turbine exhaust system. The cap is connected to the rod.

Abstract: A hanger for suspending a liner within an exhaust duct of a gas turbine engine exhaust system comprises a connector assembly, a cable and a bracket. The connector assembly is for connecting to an exhaust duct of the gas turbine exhaust system. The cable extends from the connector assembly and is configured to extend into the exhaust duct. The bracket is for connecting to an exhaust duct liner of the gas turbine exhaust system. The bracket is connected to the cable.

Abstract: A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis. The support assembly further includes an annular contact member extending from the transition duct. The contact member is configured to allow movement of the transition duct about at least one axis.

Abstract: A gas turbine engine assembly includes a rotor shaft having a threaded portion, a rotor stack support positioned radially outward from the rotor shaft, and a locking nut. The locking nut includes a body portion, a threaded portion located on a radially inner surface of the body portion, and a lug portion extending from the body portion. The rotor stack support radially rests upon the body portion of the locking nut, and the rotor stack support axially rests against the lug portion of the locking nut. The threaded portion of the locking nut and the threaded portion of the rotor shaft are engaged together.

Abstract: A structural frame for a turbomachine, such as an intermediate frame or an exhaust frame, the frame including at least two coaxial rings, an inner ring and an outer ring, together with radial arms interconnecting the rings. At least one of these elements includes a plurality of parts that are fastened together by bolting.

Abstract: A compressor assembly of a gas turbine engine includes a case including at least one opening and a stator assembly supported within the case. A lug assembly is secured to the case and sets a position of the stator assembly relative to the case. The lug assembly includes a lug engaging the stator assembly and a boss extending from the lug through the opening in the case. The boss including a threaded hole receiving a threaded member holding the lug assembly to the case and defines a seat for the threaded member that is spaced apart from an outer surface of the case.

Abstract: A pressure-loss adjusting-member installation tool having pressure-loss adjusting-member grippers that are configured to freely grip or release a pressure-loss adjusting member which is arranged at a position between a lower nozzle arranged at one end of a fuel assembly having a relatively small pressure-loss when a primary coolant flows and a lower core support plate, and which can cause the primary coolant to pass therethrough in a state with a pressure-loss being increased more than that of when the primary coolant passes through only core support plate flow holes formed on the lower core support plate; and a holding unit that holds the pressure-loss adjusting-member grippers in a same positional relationship as a relative positional relationship between the fuel assemblies arranged in plural on the lower core support plate.

Abstract: In a gas turbine engine, a fan rotor and a compressor rotor are connected to a joint which is attached to a shaft. The fan rotor is connected to the joint by a plurality of fasteners extending through mounting openings in the joint and through apertures in the fan rotor. A standard retaining ring is attached to the joint to cover a portion of an enlarged head of each of the respective fasteners in order to prevent removal of the respective fasteners from the mounting openings in the joint before the respective fasteners are connected to the fan rotor.

Abstract: A bracket for an augmentor assembly of a gas turbine engine includes a first mount attachable to a support structure. A second mount is attachable to an augmentor pilot assembly and extends radially inward of the support structure. First and second spring members attach on a first end to the first mount and on a second end to the second mount. The first and second spring members include a center spring portion spaced apart from one another to allow sufficient relative radial and circumferential movement to accommodate differential thermal expansions throughout operation of the augmentor.

Abstract: The present invention proposes a structural unit for an aircraft engine having at least one fuel pump of a fuel circuit and at least one hydraulic fluid pump of a hydraulic fluid circuit, where the structural unit can be coupled to an accessory gearbox shaft of an accessory gearbox of the engine.

Abstract: A liner stop for retaining a flow sleeve relative to a combustion liner in a combustor is disclosed. The liner stop includes a female component defining a recess and a male component comprising a protrusion, the protrusion insertable in the female component. The liner stop further includes an insert disposable between the female component and the male component, the insert comprising a surface protrusion configured to interfere with one of the female component or the male component.

Abstract: A system includes a gas turbine engine and a multipurpose gas turbine engine support frame couple to the gas turbine engine. The multipurpose gas turbine support frame is configured to support the gas turbine engine during both operation and transport of the gas turbine engine.

Abstract: A gas turbine engine includes a combustor, a first turbine section in fluid communication with the combustor, a second turbine section in fluid communication with the first turbine section, and a mid-turbine frame located axially between the first turbine section and the second turbine section. An oil system includes a first oil system component that houses oil. A first connector mechanically connects the first oil system component to the mid-turbine frame.

Abstract: A gas turbine engine includes a combustor, a first turbine section in fluid communication with the combustor, a second turbine section in fluid communication with the first turbine section, and a mid-turbine frame located axially between the first turbine section and the second turbine section. The mid-turbine frame includes a first frame case, a second frame case, a vane positioned between the first frame case and the second frame case, and a spoke extending through the vane and connecting the first frame case to the second frame case. The spoke includes a tie rod having a first end connected to the first frame case at a keyed connection.

Abstract: A corrugated shield comprises a mounting base and a corrugated ring section. The mounting base is disposed at an aft end of the ring section for securing the shield ring section within a generally annular cavity. The generally annular cavity is defined at least in part by a hot fluid flow path boundary wall, and a radially adjacent and spaced apart cold fluid flow path boundary wall. The corrugated ring section is configured to substantially block a line of sight between the hot fluid flow path boundary wall and the cold fluid flow path boundary wall.

Abstract: A thermal radiation shield comprises a first mounting base and a ring section. The first mounting base is disposed at a first axial end of the ring section for securing the shield ring section within a generally annular cavity defined at least in part by a hot fluid flow path boundary wall, and a radially adjacent and spaced apart cold fluid flow path boundary wall. The ring section is configured to substantially block a line of sight between the hot fluid flow path boundary wall and the cold fluid flow path boundary wall.

Abstract: A coupling assembly for an engine core of a turbomachine is provided. The coupling assembly comprises a duct having a substantially circular shape and surrounding the engine core, and a plurality of coupling struts, each coupling strut extending only in a substantially vertical direction relative to the direction of gravity when the engine core is at a rest position with zero pitch and zero roll, each of the plurality of coupling struts coupling the engine core to the duct.

Abstract: A suspension rudder bar has the shape of a bar with a transversal axis (Y?Y), symmetrical with respect to a plane (PS) intersecting the rotation axis (X?X) of the engine, and includes links with transmission connecting rods between a rear casing for ejecting gases and a front casing hub of the fan, and a central link to a fastening fixation to an engine fastening pylon. The links of the rudder bar to the transmission connecting rods are arranged on the transversal ends of the rudder bar, and the rudder bar extends, perpendicularly to the axis of the bar (Y?Y), with spars over a sufficient portion and at a determined distance from the edges of the plate to act as an abutment to the plate in the case of a torsion around the central link or of a connecting rod breaking.

Abstract: A system for moving an auxiliary component of a gas turbine engine is disclosed. The system may have a mobile support platform configured to support the auxiliary component during operation of the gas turbine engine. The system may further have at least one guide assembly operably connected to the mobile support platform and configured to guide movement of the mobile support platform. The system may also have a drive assembly operably connected to the mobile support platform and configured to impart movement of the mobile support platform between an elevated position and a lowered position.

Abstract: A method is provided for fuel injection in a sequential combustion system comprising a first combustion chamber and downstream thereof a second combustion chamber, in between which at least one vortex generator is located, as well as a premixing chamber having a longitudinal axis downstream of the vortex generator, and a fuel lance having a vertical portion and a horizontal portion, being located within said premixing chamber. The fuel injected is an MBtu-fuel. In said premixing chamber the fuel and a gas contained in an oxidizing stream coming from the first combustion chamber are premixed to a combustible mixture. The fuel is injected in such a way that the residence time of the fuel in the premixing chamber is reduced in comparison with a radial injection of the fuel from the horizontal portion of the fuel lance.

Abstract: A structural attachment system for the outlet of a transition duct includes a structural attachment member that has a step over portion with an outer flange at one end thereof and an inner flange at the other end thereof. The step over portion can project away from the inner and outer flanges and can define an open area. The step over portion can have a cross-section that is generally u-shaped, v-shaped, c-shaped, semi-circular, semi-oval, parabolic, or bowed. A portion of the outlet of a transition duct is received within the step over portion of the structural attachment member. Because of such arrangement, the structural attachment member is not constrained circumferentially to fitting in between two neighboring transition ducts. The structural attachment member can manage the thermal displacements that can occur between the transitions, rotor shaft cover and first row of blades during transient engine operation.

Abstract: An assembly for use in a gas turbine engine has an underlying metal sheet, and at least one ceramic matrix composite tile attached to the underlying metal sheet with at least one fastener assembly. The panel fastener assembly includes a fastener having a threaded portion extending rearwardly from a head, which has a frustoconical surface facing the threaded portion. The frustoconical surface is received in a frustoconical bore in the ceramic matrix composite panel. A bushing is positioned on an opposed side of the metal sheet from the ceramic matrix composite panel. The bushing has a flange extending away from the metal sheet. A sleeve is received about the threaded portion of the fastener, and extends away from the panel, beyond the metal sheet. The sleeve has a lip extending radially outwardly toward the flange on the bushing, such that the flange on the bushing extends beyond a space defined between the lip and a seating surface on the bushing. A wave spring is received within the cavity.

Abstract: A fuel nozzle assembly for use with a combustor is provided. The fuel nozzle assembly includes a fuel nozzle including a discharge end. A cap is coupled adjacent to the nozzle discharge end, wherein the cap includes an outer surface. At least one dampener mechanism is coupled to the cap outer surface to facilitate reducing vibrations induced to the fuel nozzle.

Abstract: The present invention relates to a silent hair dryer (3) comprising at least one casing (30) comprising an inlet end (33) and an outlet end (31) and enclosing at least one turbine (T) sucking in air via at least one admission orifice (330) upstream of the turbine (T) and expelling it downstream via at least one outlet orifice (310), and generating determined sound frequencies, characterized in that it comprises a silencer comprising at least one chamber (10) upstream of the admission orifice (330) and comprising an inlet orifice (110) for aspiration of air upstream of the chamber (10), the diameter of the chamber (10) being greater than the diameter of the admission orifice (330) and the diameter of the inlet orifice (110), the length (L) and the diameter (Dc) of the chamber (10) being of such a size so as to define a volume tuned as a function of said determined sound frequencies.

Abstract: Setting in place of one or several coolers in the wall of a secondary flow of a bypass turbomachine. The wall extends from an intermediate casing toward a leading edge of a separator nose between a primary flow and the secondary flow. The wall includes a series of support arms attached to an intermediate casing, distributed over the perimeter of the wall and directed upstream. A series of surface air-oil heat exchangers forming wall segments are arranged end-to-end on the support arms, so as to form an annular wall. A shroud having a leading edge is arranged and fixed in the area of the upstream edges of the heat exchangers, so as to complete the wall. The support arms include hydraulic connectors connected to one another on each arm, adapted to cooperate with corresponding connectors in the area of the heat exchangers and in the area of the intermediate casing.

Abstract: An exemplary gear assembly support for use in a gas turbine engine includes a support member having a portion that is configured to be coupled to a gear assembly. Another portion of the support member is configured to be coupled to a housing in a gas turbine engine. The support member includes a plurality of removal features that each have a plurality of engaging surfaces to facilitate a pulling force on the support member in a direction parallel to an axis through a center of the support member. The engaging surfaces on each of the removal features are oriented relative to each other to resist any bending moment on the support member during application of the pulling force.

Abstract: An exemplary gear assembly support for use in a gas turbine engine includes a support member having a portion that is configured to be coupled to a gear assembly. Another portion of the support member is configured to be coupled to a housing in a gas turbine engine. The support member includes a plurality of removal features that each have a plurality of engaging surfaces to facilitate a pulling force on the support member in a direction parallel to an axis through a center of the support member. The engaging surfaces on each of the removal features are oriented relative to each other to resist any bending moment on the support member during application of the pulling force.

Abstract: A device for assembly of a connecting rod on the casing of a turbo-engine including: a clevis fixed to the casing and including at least two coaxially bored lugs; a shaft traversing the bores of the lugs to which the suspension member is fixed, in a manner which is mobile in radial rotation, via a ball joint surrounding the shaft; and a connecting device which holds the shaft in place in the lugs of the clevis and is capable of being driven in rotation about the axis of the bores, is disclosed. The ball joint and the connecting device are configured such that the rotation of the connecting device about the axis of the bore of the lugs causes an offset of the axis of rotation of the connecting rod in a direction perpendicular to the axis of the bores.

Abstract: A precision counter-swirl combustor that includes an annular combustor having a forward end, an aft end opposite the forward end, and an interior. The aft end being proximal to a gas turbine. The combustor further includes a fuel inlet and swirler operatively connected to the forward end and at least one air inlet. The air inlet is equipped with a chute that extends into the interior of said combustor. The combustor is secured to a fixed structure proximate the forward end of the combustor.

Abstract: A burner having two ignition electrodes and a bracket is provided. The bracket is arranged on the outer surface of the burner and the ignition electrodes are held, at in each case three points of their periphery, in a fixed position using the bracket. A gas turbine with the burner is also provided.

Abstract: Certain embodiments include a first individual sector configured to fit together with a plurality of individual sectors to form a combustor cap assembly of a turbine combustor, wherein the first individual sector is configured to fixedly attach to a first fuel nozzle of a plurality of fuel nozzles, the first individual sector comprises a first substantially enclosed cavity configured to surround the first fuel nozzle, and the first substantially enclosed cavity is configured to receive a cooling air flow.

Abstract: A combustor is provided for mounting a fuel injector to a gas turbine engine. The combustor comprises an engine casing having an aperture formed therein. The system further comprises a fuel injector having a flange for mounting the fuel injector to the casing at the aperture so that the fuel injector extends into the engine. The flange is dismountably sealed to an inner side of the casing. The aperture and flange are configured so that, when dismounted, the fuel injector can be rotated into an orientation relative to the aperture which allows the flange to pass though the aperture and the fuel injector to be withdrawn from the casing.

Abstract: A hanger system includes a pin with a head section which defines a pin axis. A clip assembly captures the head section to permit movement of the pin within a hanger in a direction transverse to the pin axis. A fastener which retains the clip assembly to the hanger.

Abstract: A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one of the airfoils have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the midspan plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°.

Abstract: A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions.