Abstract: A gas turbine engine for an aircraft comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module, with a first electric machine being rotationally connected to the turbine module. The first electrical machine is configured to generate a maximum electrical power PEM1 (W), and the gas turbine engine is configured to generate a maximum dry thrust T (N); and a ratio S of: S = ( Maximum ? Electrical ? Power ? Generated = P E ? M ? 1 ) ( Maximum ? Dry ? Thrust = T ) is in a range of between 2.0 and 10.0.

Abstract: A system and process for restarting a turbomachine includes a shutdown cooldown protection process implemented by a plant level control system or direct control system of the turbomachine. The system and process for restarting ensure rotating components are cooled as expected prior to a unit restart. This system and process for restarting will lockout an ability to restart if an improper cooldown of rotating components is detected. If this lockout is enabled, delaying restart for the rotating components to cool naturally is needed, or the operator could decide to force cool the components.

Abstract: In a fastening structure that fastens an exhaust manifold to a cylinder head of an engine, a bolt that extends through a flange is inserted into and fixed to a bolt hole of the cylinder head. The flange includes a contact surface that contacts a coupling surface of the cylinder head, and an inclined surface that is inclined with respect to the contact surface. A clearance is provided between the bolt and the cylinder head inside the bolt hole in a range extending from the coupling surface of the cylinder head to a specified length.

Abstract: An air turbine starter that includes a housing. The housing can circumscribe a turbine coupled that is coupled to a gear train in a gear box via a drive shaft. The gear train can couple to an output shaft via at least a carrier. The air turbine starter can include at least a first bearing assembly and a second bearing assembly to rotatably support the drive shaft and the output shaft.

Abstract: An exhaust gas recirculation (EGR) system for an internal combustion (IC) engine. The EGR system has a first cooler configured to cool exhaust from an exhaust system of the IC and to drain exhaust liquid formed by the cooling. The EGR system has a mixture chamber configured to mix exhaust cooled by the first cooler with intake air to form an exhaust-air mixture. The EGR system has a second cooler configured to cool the exhaust-air mixture. The EGR system has a heat exchange system for circulating and cooling coolant fluid used by the first and second coolers, and includes a split valve configured to divide coolant fluid flow between the first and second coolers. The EGR system has an engine control module configured to adjust the split valve based on comparing a temperature of the exhaust-air mixture to a determined dewpoint temperature of the exhaust-air mixture.

Abstract: A dozer valve bracket includes a first member to secure to a rail. A second member receives a dozer valve. A pivot couples the first and second members with one another for pivotal movement with respect to one another. A stop in the second member contacts the rail to provide a second position to enable the second member to pivot away from the first member on another side of the rail to enable installation of an exhaust system.

Abstract: A turbine engine includes a compressor section, a combustion section, and a turbine section, and an airfoil with an outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a mean camber line. A first thickness is defined between the pressure side and the suction side at a first location along the mean camber line.

Abstract: An air blower includes an impeller rotatable about a central axis extending vertically, a motor to rotate the impeller, and a holder to hold the motor. The air blower is a centrifugal air blower which generates a radial airflow perpendicular to the central axis. The holder includes a base supporting the motor, attachments on a radial directional-outer side of the impeller, arms connecting the base and each of the attachments, and a wall surface on a side of the impeller, between the base and each attachment, and opposing a radial-directional inner side. An axial lower end of the impeller is located below an axial upper end of the wall surface.

Abstract: An exhaust duct of an aircraft engine includes an annular inlet conduit having an inlet central axis, and at least two outlet conduits in flow communication with the inlet conduit. The at least two outlet conduits are located non-parallel to the inlet central axis. Each of the at least two outlet conduits include an outlet port defining a distal end of each of the two outlet conduits. At least one of the outlet ports is non-circular in cross-sectional shape.

Abstract: A catalyst device includes a catalyst carrier serving as a heating element that generates heat when energized. The catalyst device includes a guide pipe that guides exhaust into the case. The catalyst device includes a connecting pipe that connects the guide pipe to the case. The case has an end that is an insulative portion and projects further upstream, in the direction in which exhaust flows, from an end surface of the catalyst carrier. A temperature difference inducing structure, which induces a state in which the connecting pipe is relatively lower in temperature than the end of the case, includes a heat shield, encompassing an outer circumferential surface of the connecting pipe and having an opening in part of a portion opposing the outer circumferential surface of the connecting pipe, and a stay fixing the outer circumferential surface of the connecting pipe to an internal combustion engine.

Abstract: A turbine engine may include a compressor section of the turbine engine. The turbine engine may include a combustion section of the turbine engine. The combustion section may be downstream of the compressor section. The turbine engine may include a turbine section of the turbine engine. The turbine section may be downstream of the combustion section. The turbine engine may include a sensor for speed detection. The sensor may be disposed at an upstream segment of the turbine section. The sensor may include a cooling jacket. The cooling jacket may encase at least a portion of the sensor. A cooling fluid may be in fluid communication with the cooling jacket and an outer surface of the sensor. The cooling jacket may be shaped to direct cooling fluid around the sensor.

Abstract: Provided is a rotary compressor excellent in energy saving performance and reliability that can suppress over-compression of a compressed refrigerant compressed in a compression chamber. A rotary compressor includes a discharge port provided on an end plate and partially located outside a cylinder inner wall and a discharge groove provided on the cylinder inner wall and communicating with a compression chamber and the discharge port, the compression chamber compressing a refrigerant by contracting as an annular piston revolves, in which the discharge port faces an end portion of a vane groove on the cylinder inner wall on the compression chamber side.

Abstract: A fuel management system includes: a fuel tank; a fuel supply line that supply fuel from the fuel tank to a combustor of the gas turbine engine; a reheat fuel supply line that supply fuel from fuel tank to a reheat of the gas turbine engine, the reheat fuel supply line extending from a reheat branching point on the fuel supply line to the reheat; a fuel supply pump disposed along fuel supply line upstream of the reheat branching point; a reheat pump disposed along reheat fuel supply line, the reheat pump that pressurise fuel to a reheat delivery pressure for delivery to the reheat; and a reheat recirculation line that recirculate fuel from the reheat fuel supply line to a location upstream of fuel supply pump, the reheat recirculation line extending from a reheat recirculation branching point on the reheat fuel supply line downstream of the reheat pump.

Abstract: An aircraft power system comprises a turbocharger, the turbocharger including a compressor for supplying combustion air to an internal combustion engine, a turbine operatively connected to an internal combustion engine to receive an exhaust flow from the internal combustion engine and convert energy of the exhaust flow into rotational power and, a turbo shaft operatively connecting the turbine to the compressor to transfer at least some of the rotational power to the compressor. A generator is operatively connected to the turbo shaft to receive at least some of the rotational power from the turbo shaft for generating electrical power. At least one electrically powered air-mover is electrically connected to the generator to receive at least some of the electrical power to produce thrust.

Abstract: A method for heating a catalytic converter includes a) switching on a compressor; b) at least partially opening an injection valve; c) setting a combustion-air/fuel ratio of ?<1 in combustion chambers; d) detecting an actual value of the oxygen content in the exhaust gas; and e) comparing the actual value with a target value, where the target value corresponds to an exhaust-gas oxygen content that would be set in a region of the catalytic converter if the combustion-air/fuel ratio in the combustion chambers is approximately ?=1, where a manipulated variable output by a controller on a basis of a deviation of the actual value from the target value is kept constant when the actual value reaches one of two limit values of a value range within which the target value is ranged, and where the two limit values deviate from the target value by approximately 3%.

Abstract: An entryway system includes a divided volute turbocharger having variable turbine geometry (VTG). The turbocharger includes a turbine housing, first and second volutes separated by a wall having a first and second tongue, and a turbine housing outlet. The system also includes a turbine wheel disposed in the turbine housing and a vane ring disposed in the turbine housing between the turbine wheel and the volutes. The system includes design modifications of one or more of the VTG components and/or locations of such components to manipulate the aerodynamic forces and/or subsequent mechanical loads in the VTG mechanism of the entryway system to mitigate VTG component wear during normal usage.

Abstract: The invention relates to a method for operating a power plant (1) for generating electrical energy for delivery to at least one consumer (16) by combustion of a carbonaceous combustible, wherein carbon dioxide (19) is separated from the flue gas (7) of the power plant (1), the separated carbon dioxide (19) is converted at least in part into a fuel (20), characterized in that the fuel (20) is combusted at least temporarily in at least one heat engine (4) so as to form a waste gas (8), and electrical energy is generated by the heat engine (4) and is delivered to at least one consumer (16), at least some of the thermal energy of the waste gas (8) being used in at least one of the following processes: a) for heating combustion air (10) of a power plant (1); b) for heating a process medium (14) of the power plant (1); c) in a drying of the combustible of the power plant (1); and d) in carbon dioxide separation.

Abstract: A method of operation is provided during which buffer air flows into a buffer cavity in a turbine engine. The buffer cavity surrounds a bearing compartment in the turbine engine. Leakage air flows across a buffer seal device in the turbine engine. The buffer air and the leakage air are combined to provide combined air. The combined air is vented to a pressure sink such that: a pressure of the buffer air within the buffer cavity is maintained at or below a maximum buffer air threshold during operation of the turbine engine; and a flowrate of the leakage air across the buffer seal device is maintained at or above a minimum leakage air threshold during the operation of the turbine engine.

Abstract: A sealing system for sealing between components. The sealing system includes a first component, a second component, and a seal assembly including a seal member. The first component includes a first component surface, and the second component includes a second component surface. The second component surface is oriented in a direction transverse to the first contact surface. The seal member has a plurality of contact surfaces including a first contact surface and a second contact surface. The first contact surface is configured to contact the first component surface and to slide relative to the first component surface. The second contact surface is configured to contact the second component surface and to slide relative to the second component surface. The second contact surface is oriented in a direction transverse to the first contact surface.

Abstract: Apparatus and methods are disclosed which apply inorganic particles to a plugged honeycomb body comprising porous walls, an inlet end and an outlet end. The apparatus comprises a particle counter and the method comprises counting a selected portion of the inorganic particles from a first sampling port upstream from the plugged honeycomb body and a second sampling port downstream from the plugged honeycomb body. The selected portion of the inorganic particles are in a preselected inorganic particle size range. Filtration efficiency can be determined while inorganic particles are being deposited, for example to increase filtration efficiency.