Abstract: A gas turbine combustor (10) comprises a base plate (12) from which protrude a plurality of lips (36) that surround respective apertures (16) into which are positioned downstream ends (19) of main swirler assemblies (18). The apertures (16) are arranged about a centrally positioned pilot cone (22) that comprises an inner cone (23) and an outer cone (25), defining a space (31) there between. A number of laterally directed apertures (60) are disposed along the outer cone (25) so as to direct a flow of fluid toward a near portion (38) of each lip (36), thereby perturbing pockets of high fuel-to-air mixtures between the outer cone (25) and the near region (38). The provision of such laterally directed apertures (60) reduces or eliminates flashback between the outer cone (25) and the near region (38) through such action.

Abstract: A gas turbine combustor (10) comprises a base plate (12) from which protrude a plurality of lips (36) that surround respective apertures (16) into which are positioned downstream ends (19) of main swirler assemblies (18). The apertures (16) are arranged about a centrally positioned pilot cone (22) that comprises an inner cone (23) and an outer cone (25), defining a space (31) there between. A number of laterally directed apertures (60) are disposed along the outer cone (25) so as to direct a flow of fluid toward a near portion (38) of each lip (36), thereby perturbing pockets of high fuel-to-air mixtures between the outer cone (25) and the near region (38). The provision of such laterally directed apertures (60) reduces or eliminates flashback between the outer cone (25) and the near region (38) through such action.

Abstract: Embodiments of the invention relate to a combustor flow sleeve for a turbine engine. According to aspects of the invention, the flow sleeve can be attached to one of the components in the combustor head-end by a plurality of fasteners. In one embodiment, the flow sleeve can be attached directly to the combustor head-end component by a plurality of bolts. The bolted flow sleeve can reduce the time to install or remove the flow sleeve. In certain areas, it may not be possible to directly attach the flow sleeve to the combustor component. A flow sleeve according to aspects of the invention can be adapted to facilitate indirect attachment to the combustor head-end component. The flow sleeve can further be adapted to include thermal relief slots to accommodate any differential thermal expansion or contraction between the flow sleeve and the component to which the flow sleeve is attached.

Abstract: Aspects of the invention are directed to a sealing system for the interface between a combustor liner and transition duct. The system includes a spring clip seal. A first end of the spring clip seal operatively engages the inner peripheral surface of the transition duct. A second end of the spring clip seal is indirectly attached to the liner by an insert disposed therebetween. The spring clip seal can be attached to the insert by any kind of welding process that does not involve melting of the spring clip seal and the insert, such as fillet welding. The insert and the liner can be attached in a similar manner. Because fillet welds are relatively easy to cut, the spring clip, insert and liner can be separated without the need for cutting any of these individual components. Thus, the system can facilitate the repair, disassembly and reassembly of the interface.

Abstract: Aspects of the invention are directed to a sealing system for the interface between a combustor liner and transition duct. The system includes a spring clip seal. A first end of the spring clip seal operatively engages the inner peripheral surface of the transition duct. A second end of the spring clip seal is indirectly attached to the liner by an insert disposed therebetween. The spring clip seal can be attached to the insert by any kind of welding process that does not involve melting of the spring clip seal and the insert, such as fillet welding. The insert and the liner can be attached in a similar manner. Because fillet welds are relatively easy to cut, the spring clip, insert and liner can be separated without the need for cutting any of these individual components. Thus, the system can facilitate the repair, disassembly and reassembly of the interface.

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: Aspects of the invention are directed to a system for improving the damping performance of an acoustic resonator. According to aspects of the invention, a resonator, such as a Helmholtz resonator, can be attached to a surface of a combustor component in a turbine engine. The combustor component includes a region in which a plurality of passages extend through the thickness of the component. The resonator is attached to the component so as to enclose at least some of the passages. The passages are in fluid communication with a cavity defined between the component surface and the resonator. Resonator performance is a function of the length of the passages in the component. According to aspects of the invention, resonator performance can be improved by reducing the length of the passages in the component by reducing the thickness of the component in a region that includes the plurality of passages.

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: A pilot nozzle heat shield includes a generally cylindrical body having a first end for receiving a pilot nozzle. The body includes a plurality of radial retention pin cavities for receiving retention pins. A frustoconical flow tip is located at a second end of the body that includes a proximal periphery and a distal periphery. A plurality of flow jets are circumferentially spaced about the proximal periphery of the frustoconical flow tip which further includes a plurality of slots extending distally from the plurality of flow jets. The plurality of slots define a plurality of tangs and the plurality of tangs define an aperture at the distal periphery of the flow tip. At least two of the tangs are connected about the distal periphery of the flow tip and the pilot nozzle heat shield generally includes at least two sets of connected tangs.

Abstract: A gas turbine combustor (10) comprises a main swirler assembly (400) comprising an annulus casting (410) itself comprising a modified downstream end (418) fitted into an reversed-edge base plate (450) that comprises an opening (453) defined by a lip (452) oriented upstream. The lip (452) comprises an upstream surface (457), an outboard surface (458) and an inboard surface (459). In certain embodiments the modified downstream end (418) has a shape to fit against the upstream surface (457) and the outboard surface (458) so as to increase the natural frequency of the main swirler assembly (400) to above the natural frequency of the combustion in the gas turbine combustor (10).

Abstract: Aspects of the invention are directed to a sealing system for the interface between a combustor liner and transition duct. The system includes a spring clip seal. A first end of the spring clip seal operatively engages the inner peripheral surface of the transition duct. A second end of the spring clip seal is indirectly attached to the liner by an insert disposed therebetween. The spring clip seal can be attached to the insert by any kind of welding process that does not involve melting of the spring clip seal and the insert, such as fillet welding. The insert and the liner can be attached in a similar manner. Because fillet welds are relatively easy to cut, the spring clip, insert and liner can be separated without the need for cutting any of these individual components. Thus, the system can facilitate the repair, disassembly and reassembly of the interface.

Abstract: Embodiments of the invention relate to a combustor flow sleeve for a turbine engine. According to aspects of the invention, the flow sleeve can be attached to one of the components in the combustor head-end by a plurality of fasteners. In one embodiment, the flow sleeve can be attached directly to the combustor head-end component by a plurality of bolts. The bolted flow sleeve can reduce the time to install or remove the flow sleeve. In certain areas, it may not be possible to directly attach the flow sleeve to the combustor component. A flow sleeve according to aspects of the invention can be adapted to facilitate indirect attachment to the combustor head-end component. The flow sleeve can further be adapted to include thermal relief slots to accommodate any differential thermal expansion or contraction between the flow sleeve and the component to which the flow sleeve is attached.

Abstract: Aspects of the invention are directed to a system for improving the damping performance of an acoustic resonator. According to aspects of the invention, a resonator, such as a Helmholtz resonator, can be attached to a surface of a combustor component in a turbine engine. The combustor component includes a region in which a plurality of passages extend through the thickness of the component. The resonator is attached to the component so as to enclose at least some of the passages. The passages are in fluid communication with a cavity defined between the component surface and the resonator. Resonator performance is a function of the length of the passages in the component. According to aspects of the invention, resonator performance can be improved by reducing the length of the passages in the component by reducing the thickness of the component in a region that includes the plurality of passages.

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: 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 gas turbine combustor (10) comprises a main swirler assembly (400) comprising an annulus casting (410) itself comprising a modified downstream end (418) fitted into an reversed-edge base plate (450) that comprises an opening (453) defined by a lip (452) oriented upstream. The lip (452) comprises an upstream surface (457), an outboard surface (458) and an inboard surface (459). In certain embodiments the modified downstream end (418) has a shape to fit against the upstream surface (457) and the outboard surface (458) so as to increase the natural frequency of the main swirler assembly (400) to above the natural frequency of the combustion in the gas turbine combustor (10).

Abstract: A pilot nozzle heat shield includes a generally cylindrical body having a first end for receiving a pilot nozzle. The body includes a plurality of radial retention pin cavities for receiving retention pins. A frustoconical flow tip is located at a second end of the body that includes a proximal periphery and a distal periphery. A plurality of flow jets are circumferentially spaced about the proximal periphery of the frustoconical flow tip which further includes a plurality of slots extending distally from the plurality of flow jets. The plurality of slots define a plurality of tangs and the plurality of tangs define an aperture at the distal periphery of the flow tip. At least two of the tangs are connected about the distal periphery of the flow tip and the pilot nozzle heat shield generally includes at least two sets of connected tangs.

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.