Abstract: Disclosed herein is a rotary engine a supply flow passage provided in the housing to allow the lubricating oil to move therethrough, a sealing part arranged to contact the rotor to selectively close the supply flow passage, and an elastic part configured to press the sealing part toward the combustion chamber.

Abstract: An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: at least one coolant feed channel fluidly coupled to a supply of cooling fluid; and an interconnected circuit of cooling channels, including: an interconnected circuit of cooling channels embedded within an exterior wall of the component; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling a supply of cooling fluid to the interconnected circuit of cooling channels; wherein the cooling fluid flows through the plurality of feed tubes into the interconnected circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels.

Abstract: A radial compressor has an iris diaphragm mechanism for a pressure-charging device of an internal combustion engine. The radial compressor has a bearing assembly, in which a rotor shaft is rotatably mounted, having a compressor impeller arranged in a compressor housing for conjoint rotation on the rotor shaft and having a fresh air supply channel for carrying a fresh air mass flow to the compressor impeller. The iris diaphragm mechanism is upstream of the compressor impeller, allowing variable adjustment of a flow cross section for the fresh air mass flow for admission to the compressor impeller, at least over a partial region. The iris diaphragm mechanism has a plurality of blades, each having at least one first and one second blade section, wherein an offset is formed between the first blade section and the second blade section of the respective blade.

Abstract: A rotary internal combustion engine with a housing having a fluid passage defined therethrough opening into a portion of its inner surface engaging each peripheral or apex seal of the rotor. An injector has an inlet for fluid communication with a pressurized lubricant source and a selectively openable and closable outlet in fluid communication with the fluid passage for delivering the pressurized lubricant to each seal through the fluid passage. A housing for a Wankel engine and a method of lubricating peripheral seals of a rotor in an internal combustion engine are also discussed.

Abstract: An embodiment of Horizontal and Vertical Axis Wind Generator (HVAWG) concept with the rotating wings, the gearbox, repulsive magnets attached to the wings and the wind tunnel cover with the same pole magnets or repulsive magnets is described. This feature allows for a number of improvements over the current state of the art including damage protection and the ability to remain operational during high wind conditions. In addition, the invention described here is scalable for cars, boats, motor cycles, camping cars, homes, offices, and power plants.

Abstract: Aircraft turbomachine with mechanical reducer and counter-rotating turbine are described. The turbomachine includes a fan driven in rotation by a fan shaft, a mechanical reducer with epicyclic gear train, a gas generator comprising a counter-rotating turbine, a first turbine shaft of which is coupled to an input shaft of the reducer and to a pin, and a second turbine shaft of which is coupled to the fan shaft. The guidance of the reducer input shaft is provided by a first ball bearing, the guidance of the pin is provided by a second roller bearing, and the guidance of the first shaft is provided by a third roller bearing axially interposed between the first and second bearings.

Abstract: An epicyclic gear system includes a sun gear, a ring gear, and two or more star gear assemblies enmeshed between the sun gear and the ring gear. Each star gear assembly includes a star gear and a journal bearing supportive of the star gear. The journal bearing includes one or more lubricant passageways to deliver a flow of lubricant to a selected location of the star gear assembly, wherein a first cross-sectional area of a lubricant passage of a first journal bearing of the two or more star gear assemblies is greater than a second cross-sectional area of the corresponding lubricant passage of a second journal bearing of the two or more star gear assemblies.

Abstract: A turbomachine includes a low-pressure shaft that drives a fan shaft in rotation by a coupling assembly including a first shaft on which are formed plural first axial grooves, a second shaft on which are formed plural second axial grooves, and a coupling device including rolling elements and an annular cage positioned between the first shaft and the second shaft. The rolling elements are positioned between one of the first axial grooves and one of the second axial grooves to couple in rotation the first and the second shaft. Each first and second groove has a first and a second substantially planar surface inclined with respect to one another and extending along the axis.

Abstract: A turbine or compressor wheel mounted in a housing. The wheel is carried on two radial bearings both mounted in a wall of the housing. The wall has a venting orifice that is not impeded by moving parts such as bearings. The wall also has a circular seal member extending toward a back-disk of the wheel with only a very small clearance. The seal member is composed of a material significantly softer than the material of the wheel.

Abstract: The invention relates to a method for controlling a turbocharger system (10) fluidly connected to an exhaust manifold (102) of a combustion engine (100). The turbocharger system comprises a tank (40) with pressurized gas, and a turbocharger turbine (22) operable by exhaust gases from the exhaust manifold. The tank is fluidly connectable to the turbocharger turbine. The method comprises the steps of: determining a first operational mode in which zero fuel, or only a predetermined low amount of fuel, is injected to the combustion engine, for a predetermined time period; and, after the predetermined time period, injecting pressurized gas from the tank to drive the turbocharger turbine, such that the turbocharger turbine is activated by the pressurized gas.

Abstract: A gas turbine engine component includes a first member, a second member rotatable relative to the first member about an axis, and a seal assembly that includes a seal supported by the first member and a seal runner that rotates with the second member relative to the seal. The seal runner includes at least one internal passage to direct cooling fluid flow through the seal runner. A restriction is associated with the at least one internal passage to restrict flow through the at least one internal passage in response to an engine condition.

Abstract: An apparatus and method for an engine component for a turbine engine comprising an outer wall having an outer surface and bounding an interior, the outer wall defining a pressure side and a suction side, extending axially between a leading edge and a trailing edge to define a chord-wise direction, and extending radially between a root and a tip to define a span-wise direction, at least one cooling supply conduit provided in the interior, and at least one cooling passage fluidly coupling the at least one cooling supply conduit to the outer surface of the outer wall, the at least one cooling passage comprising an outlet opening onto the outer surface along the leading edge, an inlet fluidly coupled to the at least one cooling supply conduit, and a curved passage defining a curvilinear centerline.

Abstract: A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in the turbine blade according to the coordinates of Table 1 and at least some of the plurality of cooling holes are located in an airfoil of the turbine blade.

Abstract: A guide vane for a variable turbine geometry and a turbine assembly provided with same are described. The guide vane has an outer face that is at least partly concave in design. The inner face opposite the outer face may also be at least partly concave in design. This gives the guide vane a good functional capability when arranged in a vane ring of a turbine, since an overflow through the gap between the guide vane and the neighboring walls is reduced.

Abstract: A gas turbine engine has a compression system blade ratio defined as the ratio of the height of a fan blade to the height of the most downstream compressor blade in the range of from 45 to 95. 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.

Abstract: A housing for a rotary engine has: a peripheral wall defining two end faces and an inner face transverse to the two end faces; two side walls sealingly engaged to the two end faces of the peripheral wall, a core of a side wall of the two side walls having a core face, the core face having a cavity section facing the rotor cavity and an abutment section annularly extending around the cavity section, the abutment section facing an end face of the two end faces, the abutment section having a flared portion flaring away from the end face; and a coating on the core face, the coating made of a material harder than a material of the core of the side wall, the coating covering the cavity section and ending at a coating edge located on the flared portion, the coating edge free of contact with the end face.

Abstract: A centrifugal compressor includes: a housing; an impeller rotatably disposed within the housing; a rotational shaft connected to the impeller; and a bearing member supporting the rotational shaft in the housing. An oil flow passage through which oil flows is formed in the housing. The oil flow passage includes a lubricating oil passage through which the oil flows as lubricating oil to be supplied to the bearing member, and a cooling oil passage through which the oil flows as cooling oil for heat exchange with a fluid compressed by the impeller. The cooling oil passage is configured so that the oil flows into the cooling oil passage as the cooling oil without passing through the bearing member.

Abstract: A rotary engine comprised of a pair of counterrotating rotors within a non-rotating outer housing. Each of the rotors is coupled to a common power shaft, one directly and the other through a reversing gear arrangement. Both are driven by the hyper-expansion of combustion gases in a repeating combustion cycle. Each has a generally circular, nearly frictionless working surface perpendicular to the power shaft axis. Each rotor surface defines chambers which rotate past each other. Within such chambers, compressed air and fuel are introduced, mixed, ignited, allowed to hyper-expand (and thus cause the rotation) and exhausted. The power shaft may be connected to a conventional clutch, torque converter, gearbox, differential, alternator or a similar system.

Abstract: A gas turbine engine according to an exemplary aspect of this disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The gas turbine engine further includes a seal assembly including a static structure and a rotatable structure configured to meet to form a contact area. The seal assembly includes an abradable coating on one of the static structure and the rotatable structure, and the seal assembly further includes a cutter on the other of the static structure and the rotatable structure.

Abstract: There is disclosed a rotor for a turbocharger, wherein the rotor has a rotor shaft, a carrier sleeve, a bearing collar and an oil diverting ring. The oil diverting ring is arranged on the carrier sleeve and is spaced apart from the rotor shaft in the radial direction by means of the carrier sleeve.