Abstract: Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to a combustor by supplying fuel to a first fuel manifold and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and supplying pressurized air to the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.

Abstract: A multi-engine system includes a first gas turbine engine that includes a first compressor and a first turbine. The multi-engine system may further include a second gas turbine engine that has a second compressor and a second turbine. Still further, the multi-engine system may include a first crossover cooling network configured to route a first crossover airflow from the first compressor of the first gas turbine engine to the second turbine of the second gas turbine engine and a second crossover cooling network configured to route a second crossover airflow from the second compressor of the second gas turbine engine to the first turbine of the first gas turbine engine.

Abstract: A combustor including a combustor lining, a tile including a recess at an end defining a receiving surface, and a tile holder. The tile holder includes an elongate retaining head having a combustor surface configured to face a combustion chamber of a combustor, and a securing portion extending from the head, the securing portion being configured to secure the head to a combustor lining. The retaining head extends laterally with respect to an elongate direction of the retaining head to define a retaining surface laterally adjacent to the securing portion; and the retaining surface cooperates with the receiving surface of the tile to retain the tile against the combustor lining. There is also disclosed a tile holder and a tile.

Abstract: A combustor having bundled tube fuel nozzles is provided. At least one of the fuel nozzles has a dynamics-mitigating adapter removably coupled thereto. The adapter includes a mounting body defining at least one flow passage aligned with an inlet of at least one tube of the at least one fuel nozzle. The at least one flow passage extends an axial length of the at least one tube. The adapter may include extenders aligned with each tube of the fuel nozzle, and the extenders may have identical or different lengths. Adapters may be used for each fuel nozzle of the combustor. The mounting body may be a monolithic unit through which the flow passages are defined or may include a plurality of extenders affixed to and extending upstream of the mounting body.

Abstract: A method for operating a gas turbine at a desired gas turbine production value. The method includes setting a desired gas turbine production value based on a schedule of a reference gas turbine shaft speed with respect to ambient temperature and an exhaust temperature; comparing values of a gas turbine shaft speed to the reference gas turbine shaft speed to determine whether a difference between the gas turbine shaft speed and the reference gas turbine shaft speed is within or outside of a predetermined range; and in response to the difference being outside of the predetermined range, initiating a change in gas turbine shaft speed to cause the gas turbine to operate approximately at the desired gas turbine production value.

Abstract: A propulsion system is provided and includes a solid hydride storage unit from which gaseous hydrogen fuel is drawn, an engine comprising a combustion chamber and a piping system to draw the gaseous hydrogen fuel from the solid hydride storage unit, the piping system being interposed between the solid hydride storage unit and the combustion chamber. The combustion chamber is receptive of the gaseous hydrogen fuel drawn from the solid hydride storage unit by the piping system and is configured to combust the gaseous hydrogen fuel to drive an operation of the engine.

Abstract: Systems and methods are disclosed for controlling surge margin in the compressor section of a gas turbine engine. A first compressor section and a second compressor section are in fluid communication with a bypass conduit. An auxiliary turbine and discharge conduit are positioned in the bypass conduit. Fluid flow from the compressor sections into the bypass conduit is controlled by bypass control valves.

Abstract: A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first threshold is met. The first threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.

Abstract: A fuel conditioning and control system provides dynamic control and steady state operations of a gas turbine provided fueled by supercritical liquefied petroleum gas (LPG). The fuel conditioning and control system comprises a storage for LPG fuel; a fuel delivery sub-system connecting the storage to turbomachinery; and a control system. The gas turbine includes a gas turbine core control that provides at least one operational data of the gas turbine to the control system. The fuel delivery sub-system includes at least one sensor for sensing at least one property of the LPG fuel in the fuel delivery sub-system, where the at least one sensor providing data on the at least one property of the LPG fuel to the control system. The control system analyzes the data on the at least one property of the LPG fuel and at least one operational data of the gas turbine for dynamic control of LPG fuel to the gas turbine under dynamic and steady state conditions.

Abstract: The present disclosure provides devices for guiding an element in a combustion chamber wall opening. Between the welds or brazes joining a bushing with a cup and the trajectory of the ring edge, an intermediate space is reserved in an internal annular groove for said welds or brazes to protrude into, so that said welds or brazes lie outside the trajectory of the ring edge.

Abstract: A gas turbine engine for an aircraft comprises a high-pressure (HP) spool comprising an HP compressor and a first electric machine driven by an HP turbine; a low-pressure (LP) spool comprising an LP compressor and a second electric machine driven by an LP turbine; a combustion system comprising a fuel metering unit; and an engine controller configured to, in response to a change of a throttle lever angle setting indicative of an acceleration event, increase fuel flow to the combustion system by the fuel metering unit, and to operate the first electric machine in a motor mode to increase the HP spool rotational speed and engine core mass flow.

Abstract: A system for generating electricity, heat, and desalinated water having a gas turbine system connected to a first electric generator, a waste heat recovery boiler (WHRB) system, a combined heat and power (CHP) generation system connected to a second electric generator, one or more solar powered energy systems, and a desalination system. The desalination system is connected to the CHP generation system and the WHRB system. The gas turbine system generates electricity and heat, the WHRB system is connected to and uses the exhaust of the gas turbine system to provide heat and steam power to the CHP generation system. The CHP generation system produces and provides electricity and heat to the desalination system, which produces product water, and at least one solar powered energy system provides thermal energy to one or more of the gas turbine system, the WHRB system, the CHP generation system, and the desalination system.

Abstract: A system for generating electricity, heat, and desalinated water having a gas turbine system connected to a first electric generator, a waste heat recovery boiler (WHRB) system, a combined heat and power (CHP) generation system connected to a second electric generator, one or more solar powered energy systems, and a desalination system. The desalination system is connected to the CHP generation system and the WHRB system. The gas turbine system generates electricity and heat, the WHRB system is connected to and uses the exhaust of the gas turbine system to provide heat and steam power to the CHP generation system. The CHP generation system produces and provides electricity and heat to the desalination system, which produces product water, and at least one solar powered energy system provides thermal energy to one or more of the gas turbine system, the WHRB system, the CHP generation system, and the desalination system.

Abstract: A fuel supply assembly for a gas turbine engine comprises a plurality of fuel injectors configured for mounting circumferentially to an engine casing of the gas turbine engine and to be serially interconnected. At least one pair of the plurality of the fuel injectors has a first fuel injector including a first manifold adapter having a first outlet defined around a first outlet axis, and a first stem connected to the first manifold adapter at the first outlet and extending longitudinally along a first stem axis; and a second fuel injector including a second manifold adapter having a second outlet defined around a second outlet axis, and a second stem connected to the second manifold adapter at the second outlet, the first and second outlet axes being disposed circumferentially between the first and second stem axes.

Abstract: The present disclosure relates to systems and methods that are useful in control of one or more aspects of a power production plant. More particularly, the disclosure relates to power production plants, methods of starting power production plants, and methods of generating power with a power production plant wherein one or more control paths are utilized for automated control of at least one action. The present disclosure more particularly relates to power production plants, control systems for power production plants, and methods for startup of a power production plant.

Abstract: A method for controlling the fuel injection of a turbine engine using a fuel supply circuit. The supply circuit includes a pilot injection line and a main injection line. During a transition of the supply distribution between the pilot injection line and the main supply line, the method includes the following steps: a) determining at least a minimum value to be maintained for a pressure value; b) determining at least one hydraulic quantity of the supply circuit; c) based on the determined hydraulic quantity of the supply circuit, calculating a calculated fuel supply distribution value corresponding to the minimum value to be maintained; and switching the fuel supply distribution to the calculated fuel distribution value.

Abstract: A highly efficient gas turbine engine includes the fan of the gas turbine engine driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

Abstract: A method of starting a gas turbine and related apparatus, the method including keeping a main fuel line in a sealed state while allowing fuel to flow from a fuel source to at least one nozzle of a nozzle array via an auxiliary fuel line; firing a gas turbine while keeping the main fuel line in the sealed state; and after combustion has started: opening the main fuel line to commence a flow of fuel from the fuel source to the at least one nozzle of the nozzle array via the main fuel line, sealing the auxiliary fuel line, and after the auxiliary fuel line is sealed, increasing the flow of fuel from the fuel source to the at least one nozzle of the nozzle array via the main fuel line.

Abstract: In one embodiment, an apparatus includes a first seal and a perforated cover. The first seal may comprise one or more inlet apertures and be located proximate to an opening into an interior of a nacelle. The perforated cover may be slidably engaged with the first seal and configured to vary an amount of air allowed into the interior of the nacelle.

Abstract: A gas turbine engine that has improved fuel burn provides operability and/or maintenance requirements when installed on an aircraft. The gas turbine engine is provided with a core compressor that includes twelve, thirteen or fourteen rotor stages. The gas turbine engine has a ratio of a core compressor aspect ratio divided by a core compressor pressure ratio is in the range of from 0.03 to 0.09. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.