A gas turbine engine for an aircraft includes: a flow path boundary, which delimits the flow path through the engine radially on the outside, and a lining, which lines the flow path boundary on the inside, at least along an axial section. Here, the lining includes a plurality of panels, which, in the circumferential direction of the flow path boundary, adjoin each other and which together line a circumferential area of 360, wherein each panel has two end faces, which each adjoin an end face of an adjacent panel. The panels are of beveled design at their end faces, such that two mutually adjoining panels form a V-shaped gap between them, the minimum clearance of which is realized at the inside of the panels. The panels can be sound-absorbing panels. Also disclosed is a panel for a gas turbine engine.

An intershaft seal assembly for maintaining separation between a piston ring and a pair of mating rings is presented. The assembly includes a piston ring interposed between forward and aft mating rings and a plurality of hydrodynamic grooves disposed along a sealing face of each mating ring. Each hydrodynamic groove further includes at least two adjoining steps wherein each step is defined by a base wall arranged to decrease depthwise in the direction opposite to rotation of an inner shaft. Two adjoining base walls define a base shoulder which locally redirects potion of a longitudinal flow within the groove to form an outward flow in the direction of the piston ring. Base walls are bounded by and intersect a pair of side walls with at least one side shoulder thereon which narrows the groove widthwise and locally redirects portion of the longitudinal flow to form a lateral flow from one side wall toward another side wall. Outward and lateral flows cooperate, with or without the longitudinal flow, to increase fluid pressure and maintain separation between the piston ring and the mating rings.

A seal includes a seal body disposed about a seal axis and configured to be mounted to a first component at a second axial end of the seal body. The seal body includes an interior surface defining a seal gland circumferentially extending about the seal axis. A packing is disposed within the seal gland. A retaining ring is in communication with a second radial side of the packing and is disposed within the seal gland. A plurality of exciter springs are mounted to a second radial side of the retaining ring. The plurality of exciter springs are biased against the interior surface of the seal body and are configured to center the packing within the seal body. The packing is configured to receive a second component and form a seal interface between the packing and the second component. The seal body is configured to form a portion of a passage.

A fan module is provided. The fan module includes a housing and an impeller. The housing includes a cover plate. The impeller is disposed in the housing and configured to rotate around an axis. The cover plate has an outer outline away from the axis. A tangent line of an endpoint on the outer outline intersects with the axis to form an angle, and the angle is not a right angle.

A blade body of a turbine blade, which defines an interior cavity fluidly communicative with coolant, is provided. The blade body includes an interior surface and one or more pins extending from the interior surface. The interior surface and the one or more pins are disposable to thermally interact with the coolant. At least one of the one or more pins includes a first section and a second section interposed between the first section and the interior surface. The first section has a larger cross-sectional area than the second section.

Wind funnel and gas combustion turbine systems are disclosed. Air travels through a wind funnel where it is compressed, and then flows into a compression section of a gas turbine that is fueled by a hydrocarbon fuel source such as natural gas. Compressed air from the wind funnel enters the compressor section of the gas turbine at relatively high density and force, and then flows to the combustion section of the gas turbine where oxygen from the wind-compressed air is used to combust the hydrocarbon fuel supplied to the gas turbine. The combustion section drives a power output generator having first and second generators that are selectively engageable and disengageable from each other. During periods when compressed air from the wind funnel is delivered to the compression section of the gas combustion turbine, the first and second generators may be drivingly engaged with each other by a generator coupling mechanism.

A vacuum pump comprises: a pump rotor portion configured such that multiple rotor blade stages including stacking portions formed in a ring shape and turbine blades radially formed on an outer peripheral side of the stacking portions are stacked on each other; a rotor shaft to which inner peripheral surfaces of the stacking portions of the multiple rotor blade stages stacked on each other are fixed; and a communication path allowing communication between a clearance space between the rotor shaft and each stacking portion and a pump exhaust path in which the turbine blades are arranged and discharging gas in the clearance space through the pump exhaust path.

A blast fan includes: a tubular frame having a first opening and a second opening to pass airflow through between the first opening and the second opening. The first opening has a first reverse tapered portion expanding from inside to outside of the frame, and the first reverse tapered portion has a surface having first convex portions projecting to the inside of the frame.

A component is provided and includes a substrate comprising an outer and an inner surface, where the inner surface defines at least one hollow, interior space. The component defines one or more grooves, where each groove extends at least partially along the outer surface of the substrate and has a base and a top. The base is wider than the top, such that each groove comprises a re-entrant shaped groove. One or more access holes are formed through the base of a respective groove, to connect the groove in fluid communication with the respective hollow interior space. Each access hole has an exit diameter D that exceeds the opening width d of the top of the respective groove. The diameter D is an effective diameter based on the area enclosed. The component further includes at least one coating disposed over at least a portion of the surface of the substrate, wherein the groove(s) and the coating together define one or more re-entrant shaped channels for cooling the component. A method for manufacturing the component is also provided. A method for manufacturing a component is also provided, where the groove and the access hole(s) are machined as a single continuous process, such that the groove and the access hole(s) form a continuous cooling passage.

A centrifugal blower has a first housing section and a second housing section separated by a width of the centrifugal blower. The centrifugal blower also has an intake port extending through the first housing section and the second housing section along the width, and an outlet port formed by the first housing section and the second housing section. A dimension of the width continuously decreases as the outlet port is approached along a length of the centrifugal blower.