Abstract: A flexible shield for fluid connectors of a gas turbine engine is disclosed. The flexible shield may comprise a flexible sleeve adapted to surround the fluid connector, and a coupling configured to secure the flexible sleeve onto a fluid tube proximate the fluid connector. A gas turbine engine employing such a flexible shield is also disclosed, as is a method of enclosing a fluid connector in a gas turbine engine using such a flexible shield.

Abstract: A fuel delivery system for use with a flow of heavy fuel oil for a gas turbine engine may include one or more fuel lines in communication with the gas turbine engine and a magnesium mixing system positioned upstream of the one or more fuel lines. The magnesium mixing system may include a flow of magnesium and a flow of a carrier fluid, a carrier mixing chamber to mix the flow of magnesium and the flow of the carrier fluid to form a mixed carrier flow, and a heavy fuel oil mixing chamber to mix the flow of heavy fuel oil and the mixed carrier flow.

Abstract: According to one embodiment of the disclosure, a system for accelerating droop response in a combined cycle power plant may include a controller and a processor communicatively coupled to the controller. The processor may be configured to receive frequency variation data associated with a frequency variation of an electrical grid, determine, based at least in part on the frequency variation data, a target operational level of the combined cycle power plant and the droop response associated with the target operational level, calculate a variable compensation value, and apply the variable compensation value to the droop response until the target operational level is reached.

Abstract: A combustor liner defining a combustor chamber is included. Also included is a cover sleeve spaced radially outwardly from and at least partially surrounding an aft end of the combustor liner, the cover sleeve and the combustor liner defining a cooling annulus. Further included is at least one aperture extending through the cover sleeve for routing a cooling flow to the cooling annulus. Yet further included is a perforated sleeve disposed between the cover sleeve and the combustor liner, wherein the perforated sleeve comprises a plurality of holes for impinging the cooling flow toward the combustor liner.

Abstract: A process for the conversion of a hydrocarbon to CO2 and electrical power is described which includes subjecting a gas mixture of a hydrocarbon feed stream and steam to an integrated reforming process including stages of steam reforming in a gas-heated reformer and secondary reforming to generate a reformed gas mixture, increasing the hydrogen content of the reformed gas mixture by subjecting it to one or more water-gas-shift stages, cooling the resulting hydrogen-enriched reformed gas and separating condensed water therefrom, passing the resulting de-watered hydrogen-enriched reformed gas to one or more stages of carbon dioxide separation to recover carbon dioxide, combusting the remaining hydrogen-containing fuel stream with an 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.

Abstract: The present invention proposes a structural unit for an aircraft engine having at least one fuel pump of a fuel circuit and at least one hydraulic fluid pump of a hydraulic fluid circuit, where the structural unit can be coupled to an accessory gearbox shaft of an accessory gearbox of the engine.

Abstract: A system and method for controlling bleed air flow into an air cycle machine that includes a bleed air inlet and a conditioned air outlet is provided. The system and method include discharging bleed air from an operating gas turbine engine, sensing exhaust gas temperature (EGT) of the gas turbine engine, sensing conditioned air temperature at the conditioned air outlet, and controlling bleed air flow into the air cycle machine based on the sensed EGT and on the sensed conditioned air temperature.

Abstract: The present invention relates to a method of increasing the safety of a power plant (10) provided with at least one heat engine (1, 2) and a gearbox (BTP), said engine (1, 2) driving said gearbox (BTP), said gearbox (BTP) having a lubrication system implemented using an aqueous medium stored in a reserve (30), in which method a fluid comprising water is injected into said heat engine (1, 2) to increase the power developed by the heat engine (1, 2) without increasing the temperature of a member of the heat engine (1, 2), or to decrease said temperature without modifying the power developed by the engine (1, 2), said fluid being taken from said reserve (30).

Abstract: A gas turbine system includes a compressor, a fuel source, a combustor, and a turbine. The compressor is configured to compress air. The fuel source is configured to supply fuel to a plurality of fuel manifolds. The combustor is configured to receive the air from the compressor, to receive the fuel from the plurality of fuel manifolds, and to combust the air and the fuel into combustion products. The turbine is configured to extract work from the combustion products. A fuel control valve is disposed within each of the plurality of fuel manifolds and is configured to throttle the fuel to the combustor when the gas turbine system is operating in an electrical island mode.

Abstract: A swirler for mixing fuel and air is provided. The swirler includes a plurality of vanes arranged on a reference circle diameter which, together with a first longitudinal end face of the vanes disposed on a first wall and a second wall disposed on an opposing second longitudinal end face of the vanes, form a flow channel. In this arrangement at least one injection orifice in the first wall and at least one further injection orifice in the second wall open into a flow channel. The arrangement of the at least two mutually opposing injection orifices in the wall of the swirler makes for a homogeneous distribution of the fuel in the flow channel and ensures a uniform mixing of the air with the fuel. This results in uniform and low-NOx combustion of the fuel/air mixture in a burner.

Abstract: Provided is a gas turbine combustion burner capable of uniformly ejecting fuel from ejection holes for reduced NOx emissions of gas turbine combustors. The gas turbine combustion burner includes a plurality of swirling vanes (20) for ejecting fuel from fuel ejection holes (23, 24) into air or a mixture of air and fuel flowing from an upstream side while applying a swirling force to form a swirling mixed airflow and a nozzle (21) having the swirling vanes (20) arranged radially on an outer circumferential surface thereof and having a first fuel passage (26), through which the fuel is guided to the fuel ejection holes (23, 24), provided therein, a cavity (25) communicating with the fuel ejection holes (23, 24) is provided in each swirling vane (20), and at least two second fuel passages (27) are provided between the cavity (25) and the first fuel passage (26) along an axial direction.

Abstract: A system and method for reducing combustion dynamics includes first and second combustors, and each combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. Each fuel nozzle includes an axially extending center body, a shroud that circumferentially surrounds at least a portion of the axially extending center body, a plurality of vanes that extend radially between the center body and the shroud, a first fuel port through at least one of the plurality of vanes at a first axial distance from the combustion chamber, the plurality of vanes being located at a second axial distance from the combustion chamber. A second fuel port is provided through the center body at a third axial distance from the combustion chamber. The system further includes structure for producing a combustion instability frequency in the first combustor that is different from the combustion instability frequency in the second combustor.

Abstract: An engine system includes a thrust chamber that has a cooling channel. The cooling channel is adapted to provide sustained cracking conditions for a fluid at steady-state operating conditions. A turbine has an input in fluid communication with an output of the cooling channel. A pump is mechanically coupled with the turbine and is in fluid communication with the cooling channel.

Abstract: A fuel supply device of a gas turbine engine is provided. The fuel supply device includes a fuel divider which divides fuel supplied from a collecting fuel passage to feed the fuel to a pilot fuel passage and to a main fuel passage. The fuel divider includes a movable member which is movable according to fuel pressure at the fuel entrance and opens and closes pilot ports and main ports according to a distance of the movement of the movable member. When the fuel pressure at the fuel entrance is not higher than a predetermined value, the fuel is supplied only to the pilot fuel passage, while when the fuel pressure at the fuel entrance is higher than the predetermined value, the fuel is supplied to the pilot fuel passage and to the main fuel passage.

Abstract: A can-annular gas turbine engine combustion arrangement (10), including: a combustor can (12) comprising a combustor inlet (38) and a combustor outlet circumferentially and axially offset from the combustor inlet; an outer casing (24) defining a plenum (22) in which the combustor can is disposed; and baffles (70) configured to divide the plenum into radial sectors (72) and configured to inhibit circumferential motion of compressed air (16) within the plenum.

Abstract: A locking system for a cascade thrust reverser on a bypass turbofan is disclosed. The locking system includes a translating sleeve configured to move between a stowed position and a deployed position. A lock member is mounted to a beam and has a locking portion which contacts a roller on the translating sleeve to retract the locking portion when the translating sleeve moves to the stowed position.

Abstract: A hydraulic fluid transfer coupling has a stator, a first coaxial rotor, and a second coaxial rotor. The first rotor is radially inwards of the stator, the second rotor is radially outwards of the stator, at least part of the first rotor axially overlapping with the stator, and at least part of the second rotor axially overlapping with the stator. The first rotor carries one or more first rotating fluid lines, and the second rotor carries one or more second rotating fluid lines. The stator carries one or more first static fluid lines and second static fluid lines. Each pair of a first rotating fluid line and the corresponding first static fluid line are fluidly coupled and each pair of a second rotating fluid line and the corresponding second static fluid line are fluidly coupled. Hydraulic fluid is transferable between each static fluid line and the corresponding rotating fluid line.

Abstract: An aircraft powerplant is disclosed that can be operated in at least three modes including as a gas turbine engine, as an engine having a ramburner, and as an engine having a forward compression combustor engine such as a ramjet and/or scramjet. An airflow valve is provided to direct air to a downstream portion of the aircraft engine and can be positioned as a function of the aircraft operating modes. The valve can be used to cocoon the gas turbine engine.