Abstract: An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal is composed of inner and outer housings and a center sealing member disposed between the inner and outer housings. The center sealing member is flexible and prevents a fluid, such as air, from leaking through the seal. In operation, the center sealing member flexes and is sealed against the outer housing by a pressure differential that is created by the relatively higher pressure on the inner housing side and the relatively lower pressure on the outer housing side.

Abstract: A method of controlling a gas turbine engine to provide protection against damaging pressure transients in the combustion process and to ensure compliance with emission requirements. Pressure fluctuations are monitored in a plurality of frequency ranges, and unacceptable pressure transients in different frequency ranges trigger different corrective actions. Unacceptable pressure transients in low and intermediate frequency ranges trigger a change in the pilot fuel fraction of a dual-mode combustor, while unacceptable pressure transients in a high frequency range trigger immediate power reduction in the engine. A control system for a gas turbine engine includes a plurality of timers for defining consecutive time periods for alternate monitoring of pressure transients and not monitoring pressure transients. Corrective action is taken only if unacceptable pressure transients are detected in each of the monitored time periods.

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 method of controlling a gas turbine engine to provide protection against damaging pressure transients in the combustion process and to ensure compliance with emission requirements. Pressure fluctuations are monitored in a plurality of frequency ranges, and unacceptable pressure transients in different frequency ranges trigger different corrective actions. Unacceptable pressure transients in low and intermediate frequency ranges trigger a change in the pilot fuel fraction of a dual-mode combustor, while unacceptable pressure transients in a high frequency range trigger immediate power reduction in the engine. A control system for a gas turbine engine includes a plurality of timers for defining consecutive time periods for alternate monitoring of pressure transients and not monitoring pressure transients. Corrective action is taken only if unacceptable pressure transients are detected in each of the monitored time periods.

Abstract: A flame-holding nozzle for a combustion turbine engine is disclosed. The nozzle includes several elongated sleeves in a substantially concentric arrangement. The sleeves cooperatively provide distinct passageways for fluids to move through the nozzle. The nozzle includes conduits that advantageously direct fluids to designated regions of the nozzle, allowing fuel and cooling fluid to move within the nozzle without becoming commingled. Portions of the nozzle sleeves are also strategically arranged to transmit fluids in a manner that provides substantially-uniform thermal expansion, thereby reducing the need for sliding joints or bellows arrangements.

Abstract: A method of controlling a gas turbine engine to provide protection against damaging pressure transients in the combustion process and to ensure compliance with emission requirements. Pressure fluctuations are monitored in a plurality of frequency ranges, and unacceptable pressure transients in different frequency ranges trigger different corrective actions. Unacceptable pressure transients in low and intermediate frequency ranges trigger a change in the pilot fuel fraction of a dual-mode combustor, while unacceptable pressure transients in a high frequency range trigger immediate power reduction in the engine. A control system for a gas turbine engine includes a plurality of timers for defining consecutive time periods for alternate monitoring of pressure transients and not monitoring pressure transients. Corrective action is taken only if unacceptable pressure transients are detected in each of the monitored time periods.

Abstract: A flame-holding nozzle for a combustion turbine engine is disclosed. The nozzle includes several elongated sleeves in a substantially concentric arrangement. The sleeves cooperatively provide distinct passageways for fluids to move through the nozzle. The nozzle includes conduits that advantageously direct fluids to designated regions of the nozzle, allowing fuel and cooling fluid to move within the nozzle without becoming commingled. Portions of the nozzle sleeves are also strategically arranged to transmit fluids in a manner that provides substantially-uniform thermal expansion, thereby reducing the need for sliding joints or bellows arrangements.

Abstract: A method of controlling a gas turbine engine to provide protection against damaging pressure transients in the combustion process and to ensure compliance with emission requirements. Pressure fluctuations are monitored in a plurality of frequency ranges, and unacceptable pressure transients in different frequency ranges trigger different corrective actions. Unacceptable pressure transients in low and intermediate frequency ranges trigger a change in the pilot fuel fraction of a dual-mode combustor, while unacceptable pressure transients in a high frequency range trigger immediate power reduction in the engine. A control system for a gas turbine engine includes a plurality of timers for defining consecutive time periods for alternate monitoring of pressure transients and not monitoring pressure transients. Corrective action is taken only if unacceptable pressure transients are detected in each of the monitored time periods.

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 dual fuel injection system for a low Nox combustor in which separate gaseous and liquid fuel manifolds are integrally joined to form manifold assemblies. Each manifold assembly extends circumferentially around the inlet of an annular fuel and air mixing passage. The gaseous fuel manifolds have a number of gas discharge ports spaced around their circumferences. The liquid fuel manifolds have a number of fuel nozzles spaced around their circumferences. The gaseous fuel discharge ports and liquid fuel nozzles are oriented so as to inject fuel into the annular passages in a manner that will facilitate mixing of the fuel and air. Separate gaseous and liquid fuel supply tubes are connected to each manifold.

Abstract: A fuel mixer for a gas turbine combustor is provided. The fuel mixer has a substantially cylindrical body with a flared end and a tapered end. The flared end is adapted for receiving compressed air and for channeling the compressed air into the fuel mixer. The fuel mixer has a fuel/air mixing disk disposed within the body proximate the flared end. A disk axis of the fuel/air mixing disk is substantially parallel to the axis of the fuel mixer body. The fuel/air mixing disk has a plurality of holes parallel to the disk axis. The fuel/air mixer reduces NO.sub.x and CO emissions in a gas turbine combustor by providing more evenly distributed fuel/air mixtures without increasing the risk of flame holding or flashback.

Abstract: An apparatus and method for establishing a stable pilot flame at a wide range of operating conditions, having a main fuel tube, an outer tube concentrically enclosing the main fuel tube, a swirler located downstream from the outer tube, an ignitor, and several fuel manifold tubes connected to the main fuel tube, are disclosed. The fuel manifold tubes direct a portion of the pilot gas fuel stream radially outward from the remainder of the pilot fuel. The axial momentum of the radially displaced fuel stream is greater than the average axial momentum of the remainder of the pilot gas streams. This relationship between the axial momenta of the gas steams promotes flame recirculation and stabilizes the pilot flame over a wide range of operating conditions.

Abstract: A multi-swirl combustor plate is disclosed. The multi-swirl combustor plate contains a plurality of swirlers arranged around an interior section of the combustor plate, and a plurality of non-swirled holes arranged around an exterior section of the plate that had been cast as a solid section. The swirlers are preferably arranged in concentric circles, and the non-swirled holes are also preferably created in concentric circles disposed outside of the swirlers. In accordance with the present invention, each of the swirlers also preferably comprises an outer wall having a thickness greater than that of the multi-swirl plate and is an extension of the multi-swirl plate disposed in the downstream direction. Similarly, the swirler hub also has a thickness greater than that of the plate is an extension disposed in the downstream direction.