Abstract: A combustor liner (230) for a gas turbine engine combustor (200) comprises an inner wall (232), an outer wall (238), a cooling air flow channel (244) formed there between, and a flow control ring (246). The flow control ring (246) is sealingly attached to the downstream ends of the inner wall (232) and the outer wall (238), and comprises a plurality of holes (250) that, during gas turbine engine operation, may regulate a flow of cooling air that passes through the cooling air flow channel (244). One or more surfaces may be coated with a thermal barrier coating (237) to provide additional protection from thermal damage.

Abstract: A thermal shield for reducing thermal stress induced proximate to a first joint formed between adjacent engine casing components in a gas turbine engine. The thermal shield includes a cover structure for covering a radially inner portion of at least one of the engine casing components. The cover structure is disposed proximate to the first joint and attached to the respective engine casing component so as to limit exposure of a covered inner portion of the engine casing component to hot gases in an interior volume defined by the engine casing components. A thermally insulating layer is disposed between the cover structure and the engine casing component for effecting a reduced amount of heat transfer to the covered inner portion of the engine casing component from the hot gases in the interior volume defined by the engine casing components.

Abstract: A combustor liner (231) for a gas turbine engine combustor (200) comprises an inner wall (232), an outer wall (238), a flow channel (244) formed there between, and an end-capping ring (246). The end-capping ring (246) is sealingly attached to the downstream end of the inner wall (232). In operation air passes within the end-capping ring (246), into the flow channel (244), and through holes (250) disposed in the inner wall (232). In some embodiments, an end-capping ring variation, a flow-diverting ring (357) comprises a plurality of holes (360) that, during gas turbine engine operation, may additionally dispense a flow of cooling air. One or more surfaces may be coated with a thermal barrier coating (237) to provide additional protection from thermal damage.

Abstract: A combustor liner (231) for a gas turbine engine combustor (200) comprises an inner wall (232), an outer wall (238), a flow channel (244) formed there between, and an end-capping ring (246). The end-capping ring (246) is sealingly attached to the downstream end of the inner wall (232). In operation air passes within the end-capping ring (246), into the flow channel (244), and through holes (250) disposed in the inner wall (232). In some embodiments, an end-capping ring variation, a flow-diverting ring (357) comprises a plurality of holes (360) that, during gas turbine engine operation, may additionally dispense a flow of cooling air. One or more surfaces may be coated with a thermal barrier coating (237) to provide additional protection from thermal damage.

Abstract: A thermal shield for reducing thermal stress induced proximate to a first joint formed between adjacent engine casing components in a gas turbine engine. The thermal shield includes a cover structure for covering a radially inner portion of at least one of the engine casing components. The cover structure is disposed proximate to the first joint and attached to the respective engine casing component so as to limit exposure of a covered inner portion of the engine casing component to hot gases in an interior volume defined by the engine casing components. A thermally insulating layer is disposed between the cover structure and the engine casing component for effecting a reduced amount of heat transfer to the covered inner portion of the engine casing component from the hot gases in the interior volume defined by the engine casing components.

Abstract: A secondary fuel delivery system for delivering a secondary stream of fuel and/or diluent to a secondary combustion zone located in the transition piece of a combustion engine, downstream of the engine primary combustion region is disclosed. The system includes a manifold formed integral to, and surrounding a portion of, the transition piece, a manifold inlet port, and a collection of injection nozzles. A flowsleeve augments fuel/diluent flow velocity and improves the system cooling effectiveness. Passive cooling elements, including effusion cooling holes located within the transition boundary and thermal-stress-dissipating gaps that resist thermal stress accumulation, provide supplemental heat dissipation in key areas.

Abstract: A fuel/air mixing apparatus, such as a main swirler assembly (400) comprising a sleeve (410), provides for additional air entry around the perimeter of a bore (440) through which passes a fuel/air mixture. The additional air reduces or eliminates flashback during operation of a gas turbine comprising the assembly (400). In some embodiments, a plurality of gaps (464) exists between spaced apart tabs (462) along a downstream end (460) of the sleeve (410). During gas turbine operation, air flows through both a flashback annulus (411) and the gaps (464). In other embodiments, a plurality of holes are placed upstream and in line with the tabs (1004) to supplement the air flow through gaps (1006). In yet other embodiments, rows (1102) of holes (1104) are provided to supplement the airflow. Downstream ends (460,1218) may interface with a downstream-oriented lip (460) or with an upstream-oriented lip (1224). The interfacing may comprise a fit effective to damp vibration and to increase the natural frequency.

Abstract: A secondary fuel delivery system for delivering a secondary stream of fuel and/or diluent to a secondary combustion zone located in the transition piece of a combustion engine, downstream of the engine primary combustion region is disclosed. The system includes a manifold formed integral to, and surrounding a portion of, the transition piece, a manifold inlet port, and a collection of injection nozzles. A flowsleeve augments fuel/diluent flow velocity and improves the system cooling effectiveness. Passive cooling elements, including effusion cooling holes located within the transition boundary and thermal-stress-dissipating gaps that resist thermal stress accumulation, provide supplemental heat dissipation in key areas.

Abstract: An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal may include an inner housing and an outer housing. The inner housing or the outer housing, or both, may be shortened relative to conventional clips and may include a cooling channel proximate to a point of attachment to the combustor basket.

Abstract: An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine clip seal may include an inner housing and an outer housing. The inner housing or the outer housing, or both, may include one or more tapered leaves forming a portion of the spring clip seal. At least one leaf may include a flared end for limiting gas from passing through the slots in the spring clip seal. In at least one embodiment, the turbine clip seal may include a center sealing member positioned between the inner and outer housings.

Abstract: An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine clip seal may include an inner housing and an outer housing. The inner housing or the outer housing, or both, may include one or more tapered leaves forming a portion of the spring clip seal. At least one leaf may include a flared end for limiting gas from passing through the slots in the spring clip seal. In at least one embodiment, the turbine clip seal may include a center sealing member positioned between the inner and outer housings.

Abstract: A turbo machinery assembly, having a natural frequency outside of the range of operational vibrational forces and further having increased damping capability, comprises a turbo machinery component and a plate having an elongated opening defining an inner surface. The turbo machinery component has a first end and a second end; the second end having an outer profile that extends inside the opening, contacting portions of the inner surface and extending peripherally to regions of clearance with the inner surface. The second end of the turbo machinery component may also extend beyond the inner surface. The turbo machinery component may further include a sleeve having a proximal end and a distal end. The second end of the turbo machinery component extends into the sleeve through the proximal end. The distal end of the sleeve defines the second end of the turbo machinery component extending inside the inner surface.

Abstract: A turbo machinery assembly, having a natural frequency outside of the range of operational vibrational forces and further having increased damping capability, comprises a turbo machinery component and a plate having an elongated opening defining an inner surface. The turbo machinery component has a first end and a second end; the second end having an outer profile that extends inside the opening, contacting portions of the inner surface and extending peripherally to regions of clearance with the inner surface. The second end of the turbo machinery component may also extend beyond the inner surface. The turbo machinery component may further include a sleeve having a proximal end and a distal end. The second end of the turbo machinery component extends into the sleeve through the proximal end. The distal end of the sleeve defines the second end of the turbo machinery component extending inside the inner surface.

Abstract: A combustor for a gas turbine having a centrally located fuel nozzle and inner, middle and outer concentric cylindrical liners, the inner liner enclosing a primary combustion zone. The combustor has an air inlet that forms two passages, each of which has a circumferential array of individually rotatable swirl vanes. The swirl vanes are mounted on axially oriented primary fuel pegs that extend through the air inlet passages. The middle and outer liners form an outer annular passage in which radially oriented secondary fuel pegs are disposed. The middle and inner liners form an inner annular passage that is supplied with cooling air. A perforated circumferentially extending baffle is locating in the inner annular passage and directs the cooling air to flow over the inner liner.

Abstract: Apparatus for retro-fitting low NOx combustors in a conventional gas turbine using the existing openings in the cylinder casing and without any significant alteration of the turbine apparatus. Each one of the low NOx combustors is mounted by a nozzle block to the cylinder casing over an existing opening sized for a conventional combustor, the nozzle block having a plurality of fuel nozzles for spraying fuel into said combustor. The nozzle block has a pilot nozzle aperture and a plurality of annular fuel passages such that when the nozzle block is mechanically connected to the combustor the nozzles are in flow communication with the fuel passages. The nozzle block is sized such that one end can be flushly mounted to the cylinder casing over the existing opening.

Abstract: A plate for spreading bolt loading around the horizontal joint flanges of a turbomachine, such as a steam turbine, is provided. The plate is contoured so that its surface area substantially matches that of the surface of the steam turbine flange against which the compressive load associated with the joint bolt preloading is applied. The plate is disposed between the flange and the nuts on the joint bolts and is made from a high yield strength material so that the locally high stresses under the nuts do not cause creeping or yielding of the plate. The plate serves to distribute the compressive joint loading around the entire surface of the flange, thereby eliminating the locally high compressive stresses that can cause creep and yielding in the flange. Spherical counter bores are machined in the plate bolt holes and spherical washers are installed between the plate and the nuts so that misalignment of bolt holes does not cause the nuts to impose bending forces on the bolts.

Abstract: A utility vest with a pair of straps running through the shoulder areas of the vest and terminating in loops that extend proximate to the outer surface of the garment. These straps are engageable with a belt and thereby transfer the weight of items clipped or otherwise attached to the belt to the shoulders of the user, preventing the belt from riding low or sliding down around the user's hips. Additionally, there are a number of pleated and unpleated pockets disposed about the inner and outer surfaces of the vest. On the rear panel of the vest, one of these pockets has contained within it a folded backpack that is integrally attached to the vest. The backpack has a pair of loops on its anterior surface that cooperate with the belt, thus holding the deployed backpack substantially stationary relative to the vest.

Abstract: A thermal shield for a steam turbine inner cylinder surrounding a plurality of turbine blade stages and having an outer cylinder substantially enclosing the inner cylinder. A steam inlet is connected to the inner cylinder through an outer cylinder for admitting high temperature steam into the inner cylinder to effect rotation of the turbine blade stages and a steam exit emits cooled steam from the inner cylinder into a space between the inner and outer cylinders. The shield reduces thermal stress on the inner cylinder from contact on an inner surface with the high temperature steam and contact on an outer surface with the cooled steam. The thermal shield is attached to the outer surface of the inner cylinder and spaced therefrom by a predetermined spacing. The thermal shield extends about all surfaces of the inner cylinder and forms a substantially closed inner space between the shield and the inner cylinder to prevent the flow of the cooled steam over the outer surface of the inner cylinder.

Abstract: A steam turbine is disclosed which eliminates the transfer of thermal deformation from the inner cylinder to the stationary blade assemblies. A dual plane bolted connection and a free floating tongue and groove interface formed between the outer ring of the stationary blade assemblies and the turbine inner cylinder provided the clearance necessary to remove the deformation associated with the stationary blade assemblies, while supporting them within the turbine assembly. The outer ring of the stationary blade assemblies may either be formed as an integral component of formed from two sections which are then welded together. The present invention also permits the rotational blades of the turbine to be placed in close proximity to the outer ring of the stationary blade assemblies and the positioning of the flow guide on the outer ring, since the deformations due to the thermal deformation of the inner cylinder are now isolated and the deformation due to the stationary blade assemblies is eliminated.

Abstract: A nozzle chamber assembly comprising an upper nozzle chamber resting on a lower nozzle chamber wherein the nozzle chambers are neither bolted nor pinned at their horizontal juncture but are held together by gravitational and pressure forces. A removable bolt which passes through the upper portion of the inner cylinder during assembly of the turbine and threads into the upper portion of the nozzle chamber to fasten the upper nozzle chamber in the upper portion of the inner cylinder during assembly and is removable once the inner cylinder is assembled. The inlet nozzles for the turbine and nozzle chambers are slidably received and sealed in a common bore which extends through the inner cylinder.