Abstract: Embodiments of a turbine nozzle assembly are provided for deployment within a gas turbine engine (GTE) including a first GTE-nozzle mounting interface. In one embodiment, the turbine nozzle assembly includes a turbine nozzle flowbody, a first mounting flange configured to be mounted to the first GTE-nozzle mounting interface, and a first radially-compliant spring member coupled between the turbine nozzle flowbody and the first mounting flange. The turbine nozzle flowbody has an inner nozzle endwall and an outer nozzle endwall, which is fixedly coupled to the inner nozzle endwall and which cooperates therewith to define a flow passage through the turbine nozzle flowbody. The first radially-compliant spring member accommodates relative thermal movement between the turbine nozzle flowbody and the first mounting flange to alleviate thermomechanical stress during operation of the GTE.

Abstract: A mounting system for locating a combustor and a fuel manifold of a gas turbine engine within a gas generator casing thereof is described. The mounting system comprises at least three support pin assemblies which extend radially inwardly from the gas generator casing. The support pin assemblies support both the fuel manifold and at least an upstream end of the combustor and maintaining engagement between the fuel manifold and the combustor during operation of the gas turbine engine.

Abstract: Fuel injector assemblies with frictionally damped fuel supply members, including fuel feed strips. More particularly, the invention provides friction dampers and/or assemblies that frictionally damp movement of fuel supply members in at least one direction. Some of the embodiments provide a friction damper that is easily serviceable, and can be installed after final assembly of a fuel injector. Aspects of the invention are applicable to other components of fuel injectors and gas turbine engines in addition to fuel supply members.

Abstract: A transition duct assembly with a thermally free aft frame and mounting system for use in a gas turbine engine are disclosed. The aft frame is capable of adjusting to thermal gradients while the mounting system provides for at least transverse movement of the transition duct during engine assembly. The mounting system also provides a means for raising the natural frequency of the transition duct outside of the engine's dynamic excitation ranges.

Abstract: A sliding connection between components of dissimilar materials includes a first mating surface formed on a first component and a second mating surface formed on a second component and configured to mate with the first mating surface. The first component is connected to the second component at the first and the second mating surfaces by a fastener including a shank, a sleeve received by the shank, and a resilient member received by the shank and contained by the sleeve. The resilient member is configured to press the first mating surface and the second mating surface against one another and to permit the first mating surface to slide against the second mating surface.

Abstract: A device for guiding an element in an orifice in a wall of a turbomachine combustion chamber is disclosed. The device includes a coaxial ring and bushing mounted one inside the other. The bushing includes two coaxial annular parts that are fastened to each other by welding and that define a groove for guiding a rim of the ring. Welding zones between the parts of the bushing are situated away from the path of the rim of the ring when moved along a privileged transverse direction of ring movement relative to the bushing when the combustion chamber is in operation.

Abstract: An apparatus is provided for coupling a first portion of a gas turbine transition duct to a second portion of a gas turbine transition duct to reduce vibratory deflection. The apparatus may comprise: at least one first support structure attached to the gas turbine transition duct first portion; at least one second support structure attached to the gas turbine transition duct second portion; and at least one coupling mechanism configured to couple the at least one first support structure to the at least one second support structure so as to allow sliding movement between the at least one first support structure and the at least one second support structure when a movement force of the at least one first support structure and the at least one second support structure exceeds a predefined frictional force threshold value.

Abstract: A gas turbine engine sealing arrangement which includes a combustor liner establishing a combustion area and a turbine nozzle configured to receive a portion of a combustor liner. A sealing ring arrangement is configured to seal with the turbine nozzle to control fluid flow from the combustion area and reduce leakage.

Abstract: A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections, and a reinforcement member positioned between two of the plurality of corrugate sections.

Abstract: An igniter assembly (10) of a gas turbine (12) is presented, including an igniter (14) disposed within an igniter housing (16). The igniter is extendable from the igniter housing through an opening (18) in a combustion liner (19) to an extended position, and is retractable from the extended position back through the opening to a retracted position (22). The igniter assembly further includes a compressible assembly (24) disposed between a base (26) of the igniter housing and the combustion liner to form a sealed interface (15) with a perimeter (28) of the opening (18). The compressible assembly is configured to restrict an air flow from passing between the igniter housing base and the perimeter of the opening. The compressible assembly is variable in length to accommodate a respective variation in a separation between the igniter housing base (26) and the opening (18).

Abstract: An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.

Abstract: An improved floating collar assembly for gas turbine combustion units consists of a sheet metal collar with a flat flange and an E seal that is pre-compressed within a block of epoxy. The collar fits over a corresponding fuel nozzle burner tube and is retained on a cap assembly by a flat plate. During assembly, the collar is loose so that it floats, which makes cap assembly easy. During operation, the epoxy used to pre-compress the E seal heats up and burns off, whereupon the E seal opens up and produces a seating load between the collar and plate that is high enough to keep the collar from rotating and thereby reduce collar wear.

Abstract: The present invention are directed towards a system and method for providing a way of reducing the vibrations and wear between mating components of a gas turbine combustor. The gas turbine combustor includes a flow sleeve having a plurality of liner stops and a combustion liner located radially within the flow sleeve. Spring dampers are positioned between the combustion liner and the flow sleeve to restrict the relative movement between the flow sleeve and the combustion liner and dampen vibrations at their assembly location. The spring dampers are capable of compressing to permit thermal growth between the combustion liner and flow sleeve.

Abstract: An annular combustion chamber for a turbomachine is disclosed. The combustion chamber includes radially internal and radially external cylindrical walls which are fixed by bolting at their upstream ends to an internal and an external annular flange of an annular chamber end wall, and an annular fairing extending in the upstream direction from the chamber end wall. The internal and external annular ends are fixed by bolting to the flanges of the chamber end wall in axial alignment with the annular ends of the walls of the chamber.

Abstract: An inflatable sealing assembly for sealing between an intake section of a turbine engine and an air inlet ring of a vehicle. The inflatable sealing assembly including a seal holder coupled to the intake section of the engine and having a first inflatable seal, a second inflatable seal, and a closed cell foam material disposed therein. The first inflatable seal and the second inflatable seal are configured when inflated to provide a seal between the intake section of the turbine engine and the air inlet ring of the vehicle and prevent foreign object debris and/or water from entering the turbine engine.

Abstract: Provided is a seal structure, according to the present invention, for sealing opposite surfaces of flanges between adjacent tail ducts, which can be prevented from being worn or aged deteriorated due to a thermal deformation in a high temperature atmosphere or vibration of a gas turbine combustor, and which can maintain a satisfactory sealing function for a long time.

Abstract: There is provided a gas turbine capable of improving the durability of a main shaft by absorbing the deformation of a casing due to heat and pressure and suppressing stresses acting on the main shaft. A link plate 31 of a movable supporting leg 30 that supports a casing 26 of a gas turbine 20 on the turbine 24 side is installed beforehand in an inclined manner at an angle ?1, whereby the displacement X of a lower casing 26L in the height direction; which occurs between a pin 31a in a top end portion of the link plate 31 and a top surface of a lower casing 26L when the operation status of the gas turbine 20 shifts from a stop condition to an operating condition is compensated for. This prevents a main shaft 25 from changing in the height direction in the part of the movable supporting leg 30 and suppresses bending stresses acting on the main shaft 25.

Abstract: Apparatus for channeling combustion gases to a turbine in a gas turbine engine. The engine has a compressor for providing compressed air, a combustor for combusting fuel with the compressed air to provide combustion gases, and a radial inflow turbine having an inlet configured to receive the combustion gases. The turbine is rotatable about an axis for expanding the combustion gases to produce work. The apparatus includes a subassembly of plurality of nozzle guide vanes fixed between a pair of spaced apart, ring-shaped sidewalls. A pair of spaced apart supports is configured to position the subassembly therebetween, concentric with the axis, and adjacent the turbine inlet. The apparatus further includes a plurality of bolt assemblies extending axially through the pair of supports, apertures in the sidewalls, and holes in the guide vanes.

Abstract: The turbine engine assembly has a frame and a turbine engine spool. A strut couples the frame to the spool and an actuator couples the strut to the frame. The actuator has a spring.

Abstract: A hot gas duct, such as a combustion casing in a gas turbine engine, includes a duct splitter held within the hot gas duct in at least three, preferably four, locations spaced around a peripheral edge of the duct splitter. At least one, preferably two, of the holding locations each comprise a generally cylindrical mounting that projects through a wall of the hot gas duct to engage an edge portion of the duct splitter by means of a slot formed in a circular face of the mounting. Mutually contacting surfaces of the slot and the duct splitter comprise hard face coatings to combat wear due to vibration and differential thermal expansion and contraction. The mountings have cooling holes that penetrate the mounting, so that coolant can flow through the mountings and into the interior of the hot gas duct to cool the mountings and the hard face coatings.

Abstract: An air metering apparatus for a secondary air system of gas turbine engine includes a metering gap defined between surfaces comprised of one or more metals having one of similar coefficients of thermal expansion or similar thermal expansions at an operating temperature. Provided is an air metering gap which undergoes thermal growth in a way which provides a suitable air metering gap during engine running conditions.

Abstract: A fuel injector for a gas turbine engine is disclosed that includes an injector body having a bore, a fitting at an inlet end of the injector body for receiving fuel, an atomizer at an outlet end of the injector body for delivering atomized fuel to a combustor of the gas turbine engine, a fuel tube disposed within the bore of the injector body for delivering fuel from the fitting to the atomizer, the fuel tube having an inlet end portion adjacent the fitting and an outlet end portion joined to the atomizer, and structure joined to the inlet end portion of the fuel tube to compensate for thermal growth of the injector body relative to the fuel tube during engine operation.

Abstract: The interturbine duct (ITD) directs hot combustion gases from a high pressure turbine stage outlet to a low pressure turbine stage inlet in a gas turbine engine. The ITD comprises an outer wall and a heat resistant non-metallic resilient annular seal provided around an end of the outer wall that is adjacent to the high pressure turbine stage outlet.

Abstract: An arrangement for a turbomachine combustion chamber is disclosed. The arrangement includes a chamber end wall pierced by at least one substantially circular opening, a deflector mounted from the downstream side of the chamber end wall in the opening by an annulus, an injector system associated with the opening and including an annular bowl that is flared downstream, passing through the opening, and a pinch ring that cooperates with the annulus to allow the injector system to shift off-center relative to the chamber end wall. The deflector includes an annular collar extending radially inwards. The bowl of the injector system includes at its downstream end an outwardly-open annular groove radially in alignment with the collar of the deflector in such a manner as to enable it to retract into said groove when the injector system shifts off-center relative to the chamber end wall.

Abstract: An expansion joint for use between a turbine duct and an exhaust duct. The expansion joint may include a flange attached to the turbine duct and a number of plates attached to the exhaust duct that extend towards the flange. The plates and the flange may include a gap therebetween, the gap being narrower when the turbine duct is hot than when the turbine duct is cold.

Abstract: Provided is a seal structure, according to the present invention, for sealing opposite surfaces of flanges between adjacent tail ducts, which can be prevented from being worn or aged deteriorated due to a thermal deformation in a high temperature atmosphere or vibration of a gas turbine combustor, and which can maintain a satisfactory sealing function for a long time.

Abstract: A sacrificial liner is provided for an injector access aperture in a combustor casing. The liner has an outer annular surface and an eccentric inner annular surface. The liner serves to protect the combustor outer casing from wear by a series of piston rings mounted in a seal carrier. The eccentricity of the surfaces prevent excess contact pressure between the piston rings and the seal carrier to improve the life of these components.

Abstract: In a combustor section, having a forward sleeve is disposed to encircle a leading end of an impingement sleeve including first and second impingement sleeve parts abutted along a longitudinal junction thereof, a retainer member disposed to overlie the longitudinal junction. The retainer member is welded to the forward sleeve and/or to the impingement sleeve. The retainer member has first and second axial end edges disposed transverse to the longitudinal junction, and at least one of the axial end edges has a cutout defined therein and disposed to overlie the longitudinal junction.

Abstract: Turbomachine with an annular combustion chamber including at its upstream end an annular chamber bottom, and attached at its downstream end by annular flanges to a radially inner casing and outer casing, wherein the upstream end of the chamber is connected to the inner casing or outer casing by elastically deformable bridges.

Abstract: An inflatable sealing assembly for sealing between an intake section of a turbine engine and an air inlet ring of a vehicle. The inflatable sealing assembly including a seal holder coupled to the intake section of the engine and having a first inflatable seal, a second inflatable seal, and a closed cell foam material disposed therein. The first inflatable seal and the second inflatable seal are configured when inflated to provide a seal between the intake section of the turbine engine and the air inlet ring of the vehicle and prevent foreign object debris and/or water from entering the turbine engine.

Abstract: An improved inlet bleed heat system for a gas turbine engine is disclosed. The inlet bleed heat system provides improved mixing in an inlet region while permitting the engine to be operated at lower power settings. The inlet bleed heat system comprises a supply conduit, a plurality of feed tubes extending from the supply conduit, and a guide tube for receiving opposing ends of the feed tubes. The plurality of feed tubes each have a plurality of injection orifices and the feed tubes are oriented such that the injection orifices generally face into a flow of oncoming air with the feed tubes being positioned forward of a plurality of sound attenuating baffles.

Abstract: A gas turbine component (20) with a layer of ceramic material (22) defining a wear surface (21), in which an array of cross-shaped depressions (26A, 26B) formed in the wear surface (21) define a continuous labyrinth of orthogonal walls (28, 30) of the ceramic material, and reduce the area of the wear surface (21) by about 50%. Within a representative area (36) of the wear surface (21), the depressions (26A, 26B) provide a ratio of a lineal sum of depression perimeters (27) divided by the representative area (36) of the wear surface of least 0.9 per unit of measurement for improved abradability characteristics of the wear surface (21).

Abstract: The manifold includes supports which slidably engage a heat shield to floatingly suspend it around the manifold. The manifold is part of a heat shield assembly inside a gas turbine engine. The assembly comprises a plurality of radially-extending supports extending from a casing of the engine to the manifold. A heat shield encloses the manifold. The heat shield has openings through which the supports pass to slidably engage the heat shield. The supports floatingly suspend the heat shield relative to the manifold.

Abstract: A mounting system for a liner within a combination chamber of a gas turbine, where the liner is secured at one upstream end to a burner and at an opposite downstream end to a transition duct, the mounting system comprising: a first elastic head comprised of a first ring-shaped housing having first and second pluralities of radially spaced, axially extending teeth, with a first annular groove between said first and second pluralities of teeth, wherein said first elastic head is secured to said upstream end of said liner, with an end portion of said liner received within said first annular groove; and a second elastic head comprised of a second ring-shaped housing having third and fourth pluralities of radially-spaced, axially-extending teeth, with a second annular groove between said third and fourth pluralities of teeth, wherein said second elastic head is secured to said downstream end of said liner, with an opposite end portion of said liner received within said second annular groove.

Abstract: A method for assembling a gas turbine engine includes coupling an axisymmetric structure within the gas turbine engine, wherein the axisymmetric structure includes a plurality of mounting bushings extending from a radially outer surface of the axisymmetric structure, inserting a first quantity of fixed pins at least partially into a respective mounting bushing to facilitate securing the axisymmetric structure within the gas turbine engine, and inserting a second quantity of floating pins at least partially into a respective mounting bushing to facilitate each floating pin moving in both an axial and tangential direction with respect to a gas turbine engine centerline axis.

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: An expansion joint for use between a turbine duct and an exhaust duct. The expansion joint may include a flange attached to the turbine duct and a number of plates attached to the exhaust duct that extend towards the flange. The plates and the flange may include a gap therebetween, the gap being narrower when the turbine duct is hot than when the turbine duct is cold.

Abstract: This invention refers to a labyrinth seal for a gas turbine engine incorporating from upstream to downstream ends, a high pressure compressor with a rotor, a diffuser and a fixed wall element forming at least one part of the internal envelope of the combustion chamber said seal comprising a stator part mounted on the wall element by virtue of an attaching part with flanges and supporting an annular wearing part said wearing part working jointly with a rotor element provided with at least one circumferential tooth integral with rotor of the compressor to form the labyrinth seal. It is characterized by the fact that at least one of the flanges of said attaching means is heavy enough to harmonize the rate of dilatation of the stator part with respect to the dilatation rate of the rotor element during engine accelerations. In conformity with another characteristic, ventilation orifices are arranged in the wall element.

Abstract: A cowl structure (18) for a gas turbine engine (10) comprises an outer skin (26) defining a first path for a load applied to the engine (10). The cowl structure (18) includes an inner skin (24) defining a second path for the load. The inner and outer skins (24, 26) are constructed such that a major proportion of the load is transmitted along the first path.

Abstract: The invention pertains to a seal element for sealing a gap, in particular within a turbo-machinery, between a first component and a second components spaced apart from each other, said first component having a first surface and said second component having an opposing second surfaces. The seal element comprises a support structure and a sealing structure covering at least partially said support structure. The support structure comprises at least two contacting members, each contacting member serves for putting a portion of the sealing structure in contact with one of the surfaces and being capable of following a deformation of said surface. The invention further pertains to a combustion turbine, wherein a gap is formed between a first surface and a second surface, which gap is sealed off by said seal element.

Abstract: The invention relates to the sealing of the cavity from which air is bled off to the cabin, which cavity is delimited, on the one hand, by the external shell of the compressor and an annular structure connected to the shell, and, on the other hand, by the external casing of the diffuser grating and a strut connected to said external casing and to an external engine casing shell fastened to the annular structure. A first seal is fitted in a first groove provided around the upstream part of the external casing of the diffuser grating, the strips of this first seal bearing on the downstream end of a first projection integral with the annular structure. A second seal is fitted in a second groove provided under said annular structure, the strips of this second seal bearing on the downstream end of a second projection integral with said annular structure and on the end of a third projection formed on the upstream part of the external casing of the diffuser.

Abstract: A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and relative to the turbine scroll. The pivoting liner has the ability to control and minimize air leakage from part to part, for example, from the liner to the turbine scroll and liner to the surrounding structures, during various operating conditions. Additionally, the liner provides for easy assembly with no flow path steps. Finally, the pivoting liner tolerates thermal and mechanical stresses and minimizes thermal wear.

Abstract: An expansion turbine stage for compressed gases has a housing and a turbine rotor. The housing has flow guide channels for feeding the compressed gas to the turbine rotor. The turbine rotor, which is over-mounted and has centripetal flow through it, is followed by an out-flow diffuser enclosed by the housing, to delay the cold expanded gas. The out-flow diffuser is arranged in a holder bore in the housing, as a separate component. For thermal insulation of the housing relative to the cold expanded gas stream, the out-flow diffuser is made of a non-metallic material having a low heat conductivity.

Abstract: A bypass duct sealing grommet, for sealing between an opening in a gas turbine engine bypass duct wall and the external surface of a projection extending through the opening, where the grommet has an annular body with a central aperture having an interior periphery adapted to sealingly engage the external surface of the projection. A first flange and second flanges define an external slot about an exterior periphery of the body adapted to receive and seal the bypass duct wall between the flanges.

Abstract: An assembly for mounting an igniter in a gas turbine engine combustor between an outer casing and an outer liner, wherein a longitudinal centerline axis extends through the gas turbine engine. The igniter mounting assembly includes a first spring member encircling a portion of said igniter and being positioned between a surface adjacent the outer casing and an outer surface of the outer liner, a first ring member connected to a first end of the first spring member adjacent the outer surface of the outer liner, and a second ring member connected to a second end of the first spring member adjacent the surface adjacent the outer casing. Accordingly, the igniter is able to maintain substantial alignment with respect to an opening in the outer liner while moving radially and/or axially with respect to the outer liner as the outer casing experiences thermal growth greater than the outer liner.

Abstract: A crossfire tube assembly is provided having an increased resistance to wear and oxidation. This increased resistance is provided by the application of coatings to the mating surfaces between the crossfire tube and crossfire tube clip. In the preferred embodiment, a physical vapor deposition (PVD) Titanium Aluminum Nitride coating is applied to the outer walls of the crossfire tubes which is used in combination with an air plasma spray (APS) Aluminum Bronze coating applied to the crossfire tube clip open end that mates with the crossfire tubes. The coating combination serves to protect the components from frictional wear and extend their life. In an alternate embodiment, the crossfire tubes also contain a plurality of air purge holes that provide a layer of cooling air along the crossfire tube inner wall.

Abstract: A cowl structure (18) for a gas turbine engine (10) comprises an outer skin (26) defining a first path for a load applied to the engine (10). The cowl structure (18) includes an inner skin (24) defining a second path for the load. The inner and outer skins (24, 26) are constructed such that a major proportion of the load is transmitted along the first path.

Abstract: A floating collar assembly for damping vibration and sealing between a combustor and a fuel nozzle of a gas turbine engine. The combustor has a nozzle opening with an outer peripheral abutment surface and the nozzle is integral with an internal fuel manifold that is secured to the engine core relative to the combustor. The nozzle has a cylindrical body aligned with the nozzle opening and has a shoulder laterally extending from the nozzle body. An annular floating collar has a combustor face adapted for radial sliding engagement with the abutment surface, a central aperture adapted for axial sliding engagement with the cylindrical body and an outer bearing surface. A wave spring is disposed between the outer bearing surface of the floating collar and an inner surface of the nozzle shoulder, for maintaining sealing engagement, for damping vibration, and for impeding relative rotation between the nozzle and the combustor, while accommodating axial and radial relative displacement.

Abstract: A gas turbine engine (40) having an active combustion control system (54) including a sensor element (44) positioned proximate the combustion chamber (46) as part of a sensor assembly (84) including a spring-action bellows (74). The sensor assembly is installed through an opening (69) in the casing (48) of the engine to make contact with the combustor wall (62). The bellows is compressed from its resting position by tightening mounting bolts (70) against a mounting flange (66) of the sensor assembly. The spring action of the bellows ensures contact between the sensing assembly and the combustor wall in spite of differential thermal growth between the casing and the combustor. The sensor element may be replaced by simply removing the mounting bolts without further disassembly of the engine.

Abstract: A catalytic section of a combustor is formed from a spaced tandem array of corrugated panels. The exterior top and bottom surfaces of the panels are coated with a catalyst and the space between panels defines a passage for a fuel-rich/air mixture. The interior of the corrugated panels define cooling air passages for maintaining the catalyst and substrate on which it is formed, at acceptable temperatures.