Abstract: A nacelle structure for a gas turbine engine includes an outer nacelle surrounding a fan section and defining an outer boundary of a bypass flow passage and an inner nacelle surrounding a core engine section and defining an inner boundary of the bypass flow passage. A panel of the inner nacelle is moveable between an open position providing access to the core engine section and a closed position. A lock is supported within the inner nacelle proximate the panel. The lock includes an electric actuator for moving a locking pin between a locked position and an unlocked position. The lock prevents opening and limits deflection of the panel when in the locked position.

Abstract: A method of inhibiting ice accretion within a turbine engine, including the steps: (a) operating the turbine engine at a predetermined engine speed; and (b) driving the compressor of the turbine engine at an elevated speed which is greater than the nominal speed of the compressor at the predetermined engine speed so as to inhibit ice accretion within the compressor.

Abstract: A bleed air duct joint insulation means is disclosed in which a leak vent comprises valve means.

Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a fan drive turbine and a second turbine. The fan drive turbine includes a plurality of turbine rotors. A fan includes a plurality of blades rotatable about an axis and a ratio between the number of fan blades and the number of fan drive turbine rotors is between about 2.5 and about 8.5. A speed change system is driven by the fan drive turbine for rotating the fan about the axis. The fan drive turbine has a first exit area at a first exit point and rotates at a first speed. The second turbine section has a second exit area at a second exit point and rotates at a second speed, which is faster than the first speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

Abstract: A method is provided for operating a gas turbine power plant with flue gas recirculation, in which the flue gases are split into a first flue gas flow for recirculation into an intake flow of the gas turbine and into a second flue gas flow for discharging to the environment. The first flue gas flow is cooled in a recooler before its mixing with ambient air for forming the intake flow. The recirculation flow, after being recooled, is reheated in order to avoid condensation of vaporous water contained in the recycled flue gases during cooling as a result of the mixing with the ambient air. A gas turbine power plant is provided with flue gas recirculation, which includes a heat exchanger for reheating the recirculation flow after being recooled.

Abstract: A combustor having a combustion chamber is provided with an external flow sleeve and a combustor liner surrounding the combustion chamber. A plurality of flow channels are provided on the combustor liner and a plurality of nozzles are disposed at predetermined locations on the flow channels. The locations of the nozzles are selected to provide different mixing times for fuel injected through the nozzles.

Abstract: A heat shield is disclosed. The heat shield may comprise a body having a back surface and an opposite front surface, wherein an opening in the body communicates through the front and back surfaces. The heat shield may further comprise at least one radial rail disposed on the back surface and extending radially outward from the opening for directing cooling air flow.

Abstract: Methods and devices for anticipating a surge in a gas turbine engine. Controlled pressure signal(s) may be compared with reference pressure signal(s), each of the controlled pressure signal(s) and reference pressure signal(s) having an associated time value. If the controlled pressure signal(s) are less than the reference pressure signal(s), a controlled pressure curve may be fitted through a predetermined number of points based on the controlled pressure value(s) and associated time value(s). A reference pressure curve may be fitted through the predetermined number of points based on the reference pressure value(s) and associated time value(s). A time to compressor surge may be estimated based on an intersection of the controlled pressure curve and the reference pressure curve.

Abstract: A combustor liner which reduces cooling flow to a combustion chamber and augments pressure drop split between impingement holes and effusion holes is disclosed. The combustor liner may further include accelerating channels, trip strips, pedestals, and cone-shaped effusion holes to provide further cooling of the liner. The combustor liner may reduce NOx production and the temperature of the combustion chamber of a gas turbine engine or the like.

Abstract: A hanger for suspending a liner within an exhaust duct of a gas turbine engine exhaust system comprises a connector assembly, a cable and a bracket. The connector assembly is for connecting to an exhaust duct of the gas turbine exhaust system. The cable extends from the connector assembly and is configured to extend into the exhaust duct. The bracket is for connecting to an exhaust duct liner of the gas turbine exhaust system. The bracket is connected to the cable.

Abstract: A method is provided for operating a gas turbine plant, in which compressed air is extracted from a compressor and for cooling is directed in an internal cooling passage through thermally loaded components to the combustion chamber and/or to the turbine, then re-cooled, and added to the compressor main flow in the compressor. At least a portion of the recirculated air is supersaturated, or partially saturated, with drops of water during or before recirculation into the compressor and a cooling mist is created. A gas turbine plant is provided with a closed cooling circuit which, for implementing the method, includes an injection arrangement for introducing water into the recirculated cooling air.

Abstract: A gas turbomachine includes a casing having a first casing half including first and second edge portions and a second casing half including first and second edge sections. The first edge portion is configured and disposed to be joined to the first edge section to form a first horizontal joint and the second edge portion is configured and disposed to be joined to the second edge section to form a second horizontal joint. At least one of the first edge portion and the first edge section including a first fluid passage, and at least one of the second edge portion and second edge section including a second fluid passage. The first and second fluid passages are configured and disposed to guide heated fluid along respective ones of the first and second horizontal joints.

Abstract: An industrial gas turbine engine (10), including: a can annular combustion assembly (80), having a plurality of discrete flow ducts configured to receive combustion gas from respective combustors (82) and deliver the combustion gas along a straight flow path at a speed and orientation appropriate for delivery directly onto the first row (56) of turbine blades (62); and a compressor diffuser (32) having a redirecting surface (130, 140) configured to receive an axial flow of compressed air and redirect the axial flow of compressed air radially outward.

Abstract: A scoop inlet for use in a gas turbine engine nacelle has a scoop inlet, and a tab extending forwardly of the scoop inlet. The scoop communicates with a downstream flowpath. The tab has at least one opening at a location upstream of the scoop inlet. A nacelle and a gas turbine engine are also disclosed.

Abstract: A method of producing a pulsatile jet flow from a substantially constant flow primary jet in a way that is mechanically efficient, easy to implement, and allows direct control over pulse duration and pulsing frequency is disclosed herein. The invention includes at least two components: (a) a constant flow fluid jet produced by any normal method (e.g., propeller) that can be directionally vectored fluidically, mechanically, or electromagnetically and (b) a nozzle with multiple outlets (orifices) through which the vectored jet may be directed. By alternately vectoring the jet through different outlets, a transient (pulsatile) flow at an outlet is obtained even with a substantially constant primary jet flow. Additionally, the nozzle outlets may be oriented in different directions to provide thrust vectoring, making the invention useful for maneuvering, directional control, etc.

Abstract: A substantially wedge-shaped sector nozzle includes a nozzle body having inner and outer arcuate segments connected by diverging radial side plates and a nozzle plate at an aft end of the nozzle body formed with an array of fuel orifices. One of the diverging radial side plates supports a radially-oriented leaf seal assembly adapted to seal against a flat plate of an adjacent similarly-shaped sector nozzle.

Abstract: A process for reducing CO2 emissions from combined cycle power generation processes utilizing a gaseous hydrocarbon feed, which includes splitting the hydrocarbon feed into two portions; a first portion ?45% by volume of the feed and a second portion ?55% by volume of the feed, feeding the first portion to an autothermal reforming process to generate a hydrogen-containing gas and a carbon dioxide stream, combining the hydrogen-containing stream with the second portion, combusting the resulting hydrogen-containing fuel stream with oxygen containing gas in a gas turbine to generate electrical power and passing the exhaust gas mixture from the gas turbine to a heat recovery steam generation system that feeds one or more steam turbines to generate additional electrical power. The captured carbon dioxide stream may be fed to storage or enhanced oil recovery processes. The process may be retrofitted into existing combined cycle processes.

Abstract: A fuel system for an aircraft comprises a boost pump, a main fuel pump and a motive pump. The boost pump receives fuel from a storage unit. The main fuel pump receives fuel from the boost pump and delivers fuel to a distribution system. The motive fuel pump receives fuel from the boost pump, routes fuel through the storage unit, and delivers fuel to an actuator. A method for delivering fuel in an aircraft comprises pumping fuel from a fuel tank to a distribution system using a main pump, pumping fuel from a fuel tank to an actuator using a motive pump, and routing fuel from the actuator to the main pump.

Abstract: An example method of thermal energy exchange within a turbomachine includes heating a liquid using thermal energy from compressed air, injecting the liquid into a first portion of a turbomachine, and using the compressed air to cool a second portion of the turbomachine.

Abstract: An ignition system includes a housing defining an interior and an exhaust outlet. The housing is configured and adapted to be mounted to a combustor to issue flame from the exhaust outlet into the combustor for ignition and flame stabilization within the combustor. A fuel injector is mounted to the housing with an outlet of the fuel injector directed to issue a spray of fuel into the interior of the housing. An igniter is mounted to the housing with an ignition point of the igniter proximate the outlet of the fuel injector for ignition within the interior of the housing.