Abstract: TURBINE WITH SOLAR COLLECTOR OR TURBOCHARGER, which is designed to originate innovative turbine kinetic energy through solar irradiation, irradiated by heliostats, parabolic or possibly to function with other types of fuel when not no solar radiation. With a heat exchanger through which passes the residual thermal energy is achieved in a higher efficiency than conventional turbines. In this set of turbine exchanged, collector and collector, its components are located so that the drop of the thermal fluid is the minimum possible. The team has been solar collector incorporated a radial type where the sunlight is irradiated, which in the collector, the heated fluid flowing through it which comes from the compressor, through the heat exchanger, and that the empty on the blades of the turbine motor generating a kinetic energy of a mechanical element that needs a turning force or power generators.

Abstract: A turbine blade for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates.

Abstract: A method for managing temperatures in an aftertreatment system positioned downstream of an engine. The method includes (1) combusting a rich air/diesel mixture in a cylinder of the engine, and then (2) combusting a lean air/diesel mixture in the cylinder, in the next combustion event in the cylinder, after combusting the rich air/diesel mixture therein. The method further includes repeating steps (1) and (2) in the cylinder and basing a frequency thereof on a desired aftertreatment system temperature.

Abstract: A blade outer air seal for a gas turbine engine includes a gas path surface exposed to exhaust gas flow, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, and a plurality of film cooling holes disposed on at least one of the gas path surface. The first side and the second side, the film cooling holes are disposed at locations described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin. A gas turbine engine is also disclosed.

Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.

Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. A retention flange extends from the leading edge portion and a leaf seal contacts the retention flange.

Abstract: The invention relates to a method for starting a steam turbine. The method involves pre-warming the steam turbine with a steam in which 65% of an energy used to pre-warming the steam turbine is derived from a latent heat energy of the steam.

Abstract: The invention relates to a device (11) for cooling oil for a turbine engine, such as an aircraft turbojet or turboprop engine, characterized in that it comprises a duct (12) for circulating a flow of cold air (F1), means (16) for injecting oil into the duct, and means (19) for extracting the oil mixed with the flow of cold air (F1), located in the duct (12), downstream from the injection means (16).

Abstract: An abradable seal comprises an organic matrix composite comprising an additive and an organic component, the additive is configured to prevent adhesion of the organic component onto an abrasive blade tip.

Abstract: The present disclosure is directed to a sump housing for a gas turbine engine. The sump housing includes a base portion and a first wall extending outwardly from the base portion. The first wall and the base portion at least partially define an inner chamber. A second wall is positioned outwardly from the first wall and extends outwardly from the base portion. The base portion, the first wall, and the second wall at least partially define an outer chamber positioned outwardly from the inner chamber. A projection extending inwardly from the first wall engages a bearing assembly. The base portion, the first wall, the second wall, and the projection are integrally coupled together.

Abstract: The present disclosure is directed to a shroud assembly for a gas turbine engine that includes a first shroud segment, a second shroud segment spaced from the first shroud segment, and a third shroud segment spaced from the first shroud segment. The first and the second shroud segments define a gap therebetween, and the first and the third shroud segments define a gap therebetween. A first seal portion is positioned at least partially on the first and the third shroud segments and at least partially covers the gap defined by the first and the third shroud segments. A second seal portion is positioned at least partially on the first and the second shroud segments and at least partially covers the gap defined by the first and the second shroud segments. A third seal portion extends between and couples the first and the second seal portions.

Abstract: A floating collar assembly for a gas turbine engine combustor includes a ferrule having a peripheral wall and a recessed surface bounded by the peripheral wall, the recessed surface of the ferrule including a particulate collecting groove adjacent the peripheral wall, and a cap secured to the peripheral wall of the ferrule. The recessed surface of the ferrule, an interior surface of the cap and the peripheral wall of the ferrule define a cavity. A floating collar is disposed within the cavity and includes a peripheral flange inwardly spaced a distance from the peripheral wall of the ferrule.

Abstract: The present invention relates to a method for lubricant heating during starting up of a thermodynamic cycle device, wherein the cycle device comprises a working medium with a working substance and a lubricant, an evaporator for evaporating the working substance, a lubricant separator for separating at least part of the lubricant from the working medium which is supplied by the evaporator, an expansion machine which is to be lubricated with the lubricant, and a condenser device with a condenser, and wherein the method comprises the following steps: delivery of lubricant from the lubricant separator to the condenser device and/or to the evaporator during shutdown of the cycle device, as a result of which a working medium which is enriched with lubricant is provided in the condenser device and/or in the evaporator; and heating of the working medium which is enriched with lubricant in the evaporator during starting up of the cycle device.

Abstract: An acoustic damping device is provided that includes a resonating tube defining a resonating cavity with a predetermined characteristic length and a tube end defining a cavity opening, as well as a case configured to reversibly secure the tube end in fluidic communication with a fluid volume enclosed by a liner. The cavity opening is connected with the resonating cavity. The case includes a vented ferrule adpressed over a perforated region of the liner. The vented ferrule defines a ferrule opening that is aligned with the perforated region of the liner and the cavity opening to form the fluidic communication between the fluid volume and the resonating cavity.

Abstract: Provided is a system and a method which allow hydrogen to be produced both efficiently and in a stable manner when using exhaust gas produced by power generation as a heat source for the dehydrogenation reaction, controlling the temperature of the dehydrogenation reaction within an appropriate range.

Abstract: The present disclosure is directed to an airfoil for a gas turbine rotor blade. The airfoil includes a pressure side wall and a suction side wall connected to the pressure side wall at a leading edge portion and a trailing edge portion. The pressure side wall and the suction side wall collectively define an internal cavity within the airfoil. A plurality of pins is disposed within the internal cavity. The trailing edge portion defines a first cooling passage having a first inlet spaced apart from a first outlet by a first length and a second cooling passage comprising a second inlet spaced apart from a second outlet by a second length. The first length is greater than the second length.

Abstract: An electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine and an electronic module of the electromechanical component connected to the mechanical component by a module cable. The electronic module is inserted through a module opening in the firewall from the first side to a second side, the second side having a lower operating temperature than the first side. A cover plate is installed over the module opening after the electronic module is inserted therethrough.

Abstract: A tandem tip blade includes a main blade body, a front blade and a rear blade. The front blade extends from a main body end. Each of a front blade pressure and a front blade suction side extends between a front blade leading edge and a front blade trailing edge and a front blade tip extending from the front blade pressure side to the front blade suction side. The rear blade extends from the main body end. Each of a rear blade pressure side and a rear blade suction side extends between a rear blade leading edge and a rear blade trailing edge, and a rear blade tip extending from the rear blade pressure side to the rear blade suction side.

Abstract: A gas turbine engine clearance control system includes a cooling air passage extending from a cooling air inlet port to a cooling air outlet port. The cooling air inlet port and outlet port are formed within an external surface of a compressor casing of a compressor and are also axially spaced on the external surface of the compressor casing. The cooling air passage extends from the cooling air inlet port radially inwardly to at least one of a flange joint, a radially outer surface of a compressor casing ring, and a radially outer surface of a connector case. The cooling air passage further extends aftward along the radially outer surfaces of the connector case and the compressor casing ring. The cooling air passage further extends radially outward to the cooling air outlet port.

Abstract: A turbomachine combustion chamber, comprises a fuel injector nozzle and an injection system. The injection system comprises a sliding traverse, means for maintaining the sliding traverse and a supporting sole for the sliding traverse. The injection system comprises means for recalling the sliding traverse configured to stress the supporting sole against axial displacements of the sliding traverse relatively to the means for maintaining. The outer connection surface of the injector nozzle and/or at least one portion of the internal centring surface of the sliding traverse narrow in the downstream direction, in such a way as to retain the injector nozzle relatively to the sliding traverse axially in the downstream direction.