A rotary seal seals a high-pressure region from a low-pressure region and has an assembly sleeve made of a rubber elastic material and at least one pressure-activatable rotary seal element with a seal edge. When a specified differential pressure value is exceeded, the seal edge of the rotary seal element rests sealingly against the seal surface of a machine part, thereby directly displacing a support element elastically supported on the rubber elastic assembly sleeve. When the specified differential pressure value is undershot, the support element is moved rearwards axially in the direction of the high-pressure region such that the seal edge of the rotary seal element is moved backwards into the seal edge rest position in which the rotary seal element lies against the seal surface without contact surface pressure or substantially without contact surface pressure or is arranged at a distance from the seal surface.

A cylinder head gasket with a carrier layer and at least one inserted sealing element, wherein the inserted sealing element has a passage opening for combustion gas, the inserted sealing element is fastened on the carrier layer on an outer side which is spaced apart from the passage opening, and the inserted sealing element has at least a first layer and at least one further layer. An engine component comprising the cylinder head gasket is disclosed, the engine component having an engine block unit, a cylinder sleeve unit which delimits the engine block unit at least in regions from a combustion chamber, and a cylinder head unit, wherein the cylinder head gasket is arranged between the cylinder head unit on one hand and the engine block unit and the cylinder sleeve unit on the other hand.

A cylinder head gasket with a carrier layer and at least one inserted sealing element, wherein the inserted sealing element has a passage opening for combustion gas, the inserted sealing element is fastened on the carrier layer on an outer side which is spaced apart from the passage opening, and the inserted sealing element has at least a first layer and at least one further layer. An engine component comprising the cylinder head gasket is disclosed, the engine component having an engine block unit, a cylinder sleeve unit which delimits the engine block unit at least in regions from a combustion chamber, and a cylinder head unit, wherein the cylinder head gasket is arranged between the cylinder head unit on one hand and the engine block unit and the cylinder sleeve unit on the other hand.

The invention relates to a shaft seal (1) which is configured to seal a shaft (2) between a coolant side (8) and a dry side (9) in a water pump. The shaft seal (1) is particularly characterized in that a compressible volume compensator (7) for compensating a temperature-dependent volume fluctuation is provided, which is vertically disposed and interacting with the volume of a barrier fluid (6).

A valve includes at least one valve stem seal, such as a packing seal, that is included in a removable seal cartridge. The valve stem is connected to the actuator via a linkage, which can be removed to provide a linkage gap between the actuator and the valve stem. The seal cartridge can then be slid along the valve stem into the linkage gap and laterally removed from the valve, whereupon the seals within the seal cartridge can be refurbished. The valve can be a rotary or linear valve. In embodiments, the linkage gap can be increased by linear displacement of the actuator away from the valve stem. The seal cartridge can be re-installed in the valve after refurbishment, or a substantially identical replacement seal cartridge can be provided, and can be installed in the valve in replacement of the removed seal cartridge, thereby minimizing downtime of the valve.

In accordance with at least one aspect of this disclosure, a fuel seal for an aircraft fuel system includes a seal ring of a metallic material configured to retain a shape of the seal ring under compression, and a coating of elastomeric material, over molded onto the seal ring and configured to conform to a shape of a sealing surface. In embodiments, the seal ring and coating can be configured to provide drop-tight sealing at a temperature of at least 400 degrees F. In certain embodiments, the seal ring and coating can be configured to seal one or more fuel system components of an aircraft fuel system.

A determination system includes an imaging unit that captures an image of a gasket already used for flange fastening and an analyzing unit that analyzes, based on the image captured, a contact mark formed on the gasket as a result of contact between the gasket and a pair of flanges when the flanges are fastened through the gasket. The analyzing unit includes a detection unit that detects, in the captured image, a contact mark region indicative of the contact mark and enclosed with a first line and a second line, a distance calculation unit that calculates a distance between the first line and the second line, and a state determination unit that determines, based on at least the distance, whether the flanges are properly fastened through the gasket.

The present invention provides a method of replacing a failed pump seal of a pump having a pump housing and a rotating pump shaft. As part of the method, there is provided a specially configured rescue seal. The rescue seal is placed on the pump shaft above the failed seal so that the pump shaft extends through both the failed seal and the rescue seal. In order to affix the rescue seal to the pump shaft and above the failed seal, a plurality of studs are first attached to the pump housing after removing some of the bolts that fasten the failed seal to the pump housing. The failed seal is then secured to the studs with nuts. Nuts are then placed on the studs to secure the rescue seal to the studs above the failed seal.

A mechanical seal assembly adapted for arrangement around a rotating shaft of a pump has first and second seals. Both include primary and mating rings, biasing mechanisms and annular flexible sealing membranes. The two seals can have different seal balances or different biasing forces (or both) to allow the second seal to run dry for extended periods.

A gas turbine engine defining a longitudinal direction and a radial direction is provided. The gas turbine engine includes a turbine section comprising a stationary outer portion, a first rotating component, and a second rotating component, wherein the first rotating component includes an aft airfoil defining a hollow passageway and coupled to a radially extended first rotor portion, wherein the hollow passageway is in fluid communication with the stationary outer portion, wherein the second rotating component is coupled to a radially extended second rotor portion; and a seal assembly between a portion of the first rotating component and the second rotating component, the seal assembly defining a balance piston cavity therebetween, wherein the balance piston cavity is in fluid communication with the hollow passageway, wherein a flow of air is routed through the stationary outer portion and the hollow passageway to the balance piston cavity, and wherein a pressure of the flow of air within the balance piston cavity is controlled to provide an axial thrust that counteracts a thrust load on the second rotor portion.