Abstract: An improved sealing device for use between a transition duct aft frame and turbine inlet is disclosed. The improved sealing device includes a plurality of corrugated metal seals that are secured to the transition duct aft frame along the arc-like sections of the aft frame. The corrugated seals contact both the transition duct aft frame and turbine inlet to provide a more effective seal and to control the amount of compressor discharge air introduced to cool the turbine vane platforms. In the preferred embodiment, the corrugated seals are coated to reduce wear, fretting, and galling and are used in conjunction with a transition duct thermally free aft frame and pivot bearing mounting system. An alternate embodiment of the seal is also disclosed that utilizes an alternate cooling hole pattern for providing additional cooling air to the turbine vane platform. A further alternate embodiment of the seal incorporates a group of wear reduction coatings from which to select.

Abstract: Turbine insulation is disclosed, and comprises blankets, ribs and coupling members. The blankets define, with the turbine, an annular channel in receipt of the turbine vertical joint and a pair of longitudinal channels each in receipt of a respective turbine horizontal joint. A pair of ribs are positioned in each longitudinal channel, in volume-filling relation thereto and overlapping the blankets disposed, respectively, fore and aft of the vertical joint. A pair of ribs are positioned in volume-filling relation to the annular channel and overlapping the blankets disposed, respectively, on the upper and lower arcuate portions of the housing. A coupling member is positioned in each longitudinal channel at its intersection with the annular channel, in volume-filling relation to a void defined by the housing and the ribs and in lapped relation to the ribs.

Abstract: An acoustic-structural LPC splitter assembly which comprises a structural acoustic splitter through which are arranged a plurality of bleed exhaust ports, the acoustic splitter having a first and second end, an inner and outer surface, a front joint for securing the first end, and a slip joint formed at an FEGV interface for securing the second end, wherein the structural acoustic splitter provides support sufficient to maintain concentricity of an LPC inner case.

Abstract: A crossfire tube assembly with telescoping inner and outer crossfire tubes with an enhanced cooling mechanism for connecting adjacent combustors in a gas turbine is disclosed. The enhanced cooling configuration includes a plurality of channels formed in the telescoping region of the inner and outer crossfire tubes of the assembly to improve heat transfer and reduce local operating temperatures such that component life is extended.

Abstract: A bearing housing includes inner and outer shells through which a rotor shaft may extend. A service tube is fixedly joined to the inner shell and extends through a service aperture in the outer shell. A flexible coupling sealingly joins the service tube to the outer shell at the service aperture for permitting differential thermal movement between the inner and outer shells at the service tube.

Abstract: The present invention provides a hollow structure with at least one flange which can eliminate the possibility of creating crackings due to the thermal fatigue, thereby improving the durability thereof. A hollow structure with an flange according to the present invention includes at least one annular flange fixedly attached around the hollow structure which has a temperature gradient in the direction of the thickness of the wall thereof, wherein said at least one annular flange including an outer portion formed of a metal material having a coefficient of linear expansion greater than that of the metal material forming another portion of said at least one annular flange.

Abstract: An apparatus for supporting the recuperator of a microturbine system in a vertical position above a turbine. The apparatus including a plurality of spring supports supporting the recuperator while simultaneously allowing thermal expansion of the turbine with a minimum amount of force being applied thereto. Thermal expansion of the turbine causes it to lift the recuperator while simultaneously decompressing the springs an amount equal to the amount of thermal expansion experienced by the turbine.

Abstract: Interaction between mating gas turbine combustor components due to vibrations and assembly tolerances can cause excessive wear and premature replacement. Typically, wear reduction features, such as hardened materials, are used to minimize the amount of wear or direct such wear to a specific component. The present invention discloses an improved wear reduction device for the interface between a gas turbine combustor transition duct end frame and the turbine inlet. The improved wear reduction device incorporates “L-shaped” wear strip inserts, constructed of a hardened material, and fixed along the sidewalls of the end frame to protect it from wear by the mating turbine inlet seal. The improved wear strip insert provides a cost savings by not requiring costly manufacturing tooling to form the wear strip inserts, unlike previous wear reduction techniques for the same component interface.

Abstract: A combustor dome assembly includes a spectacle plate having an opening formed therein that defines an inner circumferential edge, at least one swirler assembly defining an inner cylindrical surface, and at least one deflector having an outer cylindrical surface. These components are arranged such that the outer cylindrical surface is joined to the inner circumferential edge and to the inner cylindrical surface. One preferred method of manufacturing the combustor dome assembly includes placing a first ring of joining material over the outer cylindrical surface. Then, the outer cylindrical surface is inserted into the spectacle plate opening so that the first ring is sandwiched between a first surface of the spectacle plate and a shoulder formed on the deflector. A second ring of joining material is next placed over the outer cylindrical surface, and a third ring of joining material is inserted into an annular groove formed in the inner cylindrical surface.

Abstract: A head part of an annular combustor for a gas turbine includes an annular bulkhead at the upstream end of the combustor. The bulkhead includes a first annular section integrally, inwardly and radially extending from the outer annular wall of the combustor, and a second annular section integrally, outwardly and radially extending from the annular inner wall of the combustor. The first and second annular sections are overlapped adjacent to the annular inner wall and secured together by segmented heat shields which have integrated threaded studs engaging with self-locking nuts, and cover the downstream side of bulkhead. The first annular section has a plurality of apertures circumferentially spaced apart from one another to receive fuel burners. Each burner is radial-displaceably positioned in the aperture and sealed by a burner collar, which is clamped between the heat shield and the bulkhead wall.

Abstract: The present invention contemplate a seal assembly for reducing the passage of fluid between a combustor liner and a turbine vane segment in a gas turbine engine. In one embodiment, the turbine vane segment has a lip portion defining a sealing surface. A seal element having first and second seal portion is coupled to the turbine vane segment by a support element. The support element urges the first seal portion into engagement with an aft edge of the combustor liner and positions the second seal portion adjacent the sealing surface of the turbine vane segment, while allowing relative movement between the second seal portion and the sealing surface in a direction substantially parallel to the sealing surface.