A compressor rotor for turbomachinery, such as a compressor, is provided. Disclosed embodiments can benefit from seal elements that may be arranged to inhibit passage onto respective hirth couplings of process fluid being processed by the compressor. A seal element may be affixed to adjacent rotor components (e.g., adjacent impeller bodies) by way of a slip or interference fit connection to one of the adjacent components and may be affixed to the other adjacent rotor component by way of a elastically flexible frustoconical inner surface of the seal element that permits the seal element to be placed in a spring-loaded condition, which generates a biasing force to circumferentially clamp onto a frustoconical outer surface of the other adjacent rotor component. This arrangement is conducive to user-friendly assembly/disassembly of the seal elements with respect to the adjacent rotor components.

A radial seal and radial seal assembly (10) are disclosed. An embodiment of seal assembly may include an inner rotating shaft (20) with inner rotating shaft fluid feed holes (22); a primary segmented seal (30); a secondary segmented seal (40); a tertiary seal (50) that may axially seal the primary and secondary segmented seals; and an outer housing (60) including a plurality of outer housing fluid feed holes (62). In embodiments, the assembly is configured so that, as the inner rotating shaft rotates, the inner rotating shaft fluid feed holes periodically come into fluid communication alignment with outer housing fluid feed holes.

A turbine system including a sealing component is presented. The sealing component includes a ceramic material. The ceramic material includes grains having an average grain size of less than 10 microns. A turbine shroud assembly including the sealing component is also presented.

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a first side plate, a second side plate and a backing plate that extend circumferentially about an assembly axis. A first brush seal and a second brush seal are positioned on opposite sides of the backing plate such that the first brush seal is between the first side plate and the backing plate and such that the second brush seal is between the second side plate and the backing plate. The first brush seal is dimensioned to establish a first sealing relationship with a first gas turbine engine component. The second brush seal is dimensioned to establish a second sealing relationship with a second gas turbine engine component. A method of assembly is also disclosed.

A method is provided for testing an annular seal within a gas turbine engine. During this method, a vacuum is applied to a first volume through a conduit. The annular seal is between the first volume and a second volume. A vacuum pressure is measured within the conduit while the vacuum is applied. The measured vacuum pressure is compared to a threshold vacuum pressure. A difference between the measured vacuum pressure and the threshold vacuum pressure is indicative of leakage across the annular seal from the second volume to the first volume.

An impeller shroud assembly for a gas turbine engine includes an annular impeller shroud disposed about an axial centerline. The impeller shroud includes a shroud inducer portion and a shroud exducer portion disposed radially outward of the shroud inducer portion and extending to an outer radial end of the impeller shroud. The shroud inducer portion and the shroud exducer portion defining an impeller-facing surface of the impeller shroud. The impeller shroud has a pivot point defined between the shroud inducer portion and the shroud exducer portion. The impeller shroud assembly further includes a clearance control device connected to the shroud exducer portion of the impeller shroud proximate the outer radial end. The clearance control device is configured to pivot the shroud exducer portion of the impeller shroud about the pivot point between a first axial position and a second axial position.

A seal device includes a first sidewall, a second sidewall and a carbon seal element. The first sidewall is arranged with a first tool die which centers the first sidewall about an axis. The first sidewall axially contacts the first tool die along the axis. The carbon seal element is arranged with a centering element which centers the carbon seal element about the axis. The carbon seal element circumscribes and radially contacts the centering element. The second sidewall is arranged with a second tool die which centers the second sidewall about the axis. The second sidewall axially contacts the second tool die along the axis. The first tool die and the second tool die are moved axially together along the axis to press fit the second sidewall into a bore of the first sidewall and axially capture the carbon seal element between the first sidewall and the second sidewall.

A seal device includes a first sidewall, a second sidewall and a carbon seal element. The first sidewall is arranged with a first tool die which centers the first sidewall about an axis. The first sidewall axially contacts the first tool die along the axis. The carbon seal element is arranged with a centering element which centers the carbon seal element about the axis. The carbon seal element circumscribes and radially contacts the centering element. The second sidewall is arranged with a second tool die which centers the second sidewall about the axis. The second sidewall axially contacts the second tool die along the axis. The first tool die and the second tool die are moved axially together along the axis to press fit the second sidewall into a bore of the first sidewall and axially capture the carbon seal element between the first sidewall and the second sidewall.

A seal land for a gas turbine engine can include a seal body circumferentially extending about a longitudinal centerline axis. The seal body includes at least one sealing surface that extends in a plane that is transverse to the longitudinal centerline axis.

An assembly for a gas turbine engine, comprises a fairing assembly extending generally axially through a portion of the gas turbine engine, a first component disposed radially inward of the fairing assembly, a second component disposed axially adjacent to the first component, a flow diverter, and a finger seal. The flow diverter includes a mounting portion securing the flow diverter to the first component, and an arm extending in an axial direction from the mounting portion toward the second component. The finger seal includes a fixed end secured between the flow diverter mounting portion and the first component.