Methods and systems for controlling infiltration of ambient air into, and exfiltration of process gas out of, an organic Rankine system. A system comprises a first sealing mechanism configured to seal at least one shaft against exfiltration of a process gas when the turbomachine is operating. The system further comprises a second sealing mechanism configured to seal the at least one shaft against infiltration of ambient air when the system is in a standstill mode. The system further comprises one or more pressure sensors configured to detect a pressure of gas within the system to monitor whether infiltration of ambient air has occurred and a system purge is needed.

A circumferential seal assembly suitable for forming a thin film between a rotatable runner and a sealing ring is presented. The assembly includes an annular seal housing, a rotatable runner, an annular seal ring, and a plurality of groove structures. Each groove structure includes a groove and an optional feed groove. The groove includes at least two adjoining steps defined by base walls arranged to decrease depthwise. Two adjoining base walls are disposed about a base shoulder. Each base shoulder locally redirects a longitudinal flow to form an outward radial flow in the direction of the annular seal ring. The base walls are bounded by and intersect a pair of side walls. A side wall includes side shoulders which narrows the groove widthwise and locally redirects the longitudinal flow to form a lateral flow in the direction of the other side wall. Outward and lateral flows separately or in combination enhance stiffness of a thin-film layer between the annular seal ring and the rotatable runner.

A circumferential seal assembly suitable for forming a thin film between a rotatable runner and a sealing ring is presented. The assembly includes an annular seal housing, a rotatable runner, an annular seal ring, and a plurality of groove structures. Each groove structure includes a groove and an optional feed groove. The groove includes at least two adjoining steps defined by base walls arranged to decrease depthwise. Two adjoining base walls are disposed about a base shoulder. Each base shoulder locally redirects a longitudinal flow to form an outward radial flow in the direction of the annular seal ring. The base walls are bounded by and intersect a pair of side walls. A side wall includes side shoulders which narrows the groove widthwise and locally redirects the longitudinal flow to form a lateral flow in the direction of the other side wall. Outward and lateral flows separately or in combination enhance stiffness of a thin-film layer between the annular seal ring and the rotatable runner.

An effusion cooling element for the surface of a hot gas path (HGP) component is disclosed. The effusion cooling element includes a coolant swirling chamber embedded within the body of the HGP component. A coolant delivery passage is in the body and configured to deliver a coolant to the coolant swirling chamber. The coolant swirling chamber imparts a centrifugal force to the coolant. An effusion opening is in the HGP surface and in fluid communication with the coolant swirling chamber, the effusion opening having a smaller width than the coolant swirling chamber. The coolant exits the effusion opening over substantially all of 360° about the effusion opening, creating a coolant film on the HGP surface.

An aspirating face seal assembly for a turbo-machine including a rotor assembly having a first radially extending portion defining a rotor surface is disclosed. The aspirating face seal assembly includes a seal body including a second radially extending portion defining a bearing surface and having a plurality of return channels. The second radially extending portion is disposed in the turbo-machine such that the bearing surface is disposed facing the rotor surface. The aspirating face seal assembly further includes an annular ring including one or more openings. The annular ring is concentrically disposed on the second radially extending portion and between the rotor surface and the second radially extending portion and configured to rotate in an event of rub between the first radially extending portion and the annular ring. A turbo-machine including the aspirating face seal assembly and a method for operating an aspirating face seal are also disclosed.

A method for shortening the start-up process of a steam turbine is provided which has a turbine housing and turbine components which are provided inside the turbine housing. The turbine components during operation come into contact with hot steam which flows through the turbine housing and include a turbine shaft which passes axially through the turbine housing. Sealing regions, which during operation of the steam turbine are acted upon by seal steam, are formed between the turbine shaft and the turbine housing. Thermal energy is fed to the steam turbine during a shutdown of said steam turbine, wherein seal steam is fed to the interior of the turbine housing during the shutdown of the steam turbine in order to heat and/or to keep warm the turbine components which are provided in the interior of the turbine housing.

A seal for a gas turbine engine includes a plurality of seal arc segments. Each of the seal arc segments includes radially inner and outer sides and sloped first and second circumferential sides. The seal arc segments are circumferentially arranged about an axis such that the sloped first and second circumferential sides define gaps circumferentially between adjacent ones of the seal arc segments. Each of the gaps extends from the radially inner sides along a respective central gap axis that slopes with respect to a radial direction from the axis.

A gas turbine engine having a bearing housing with a housing cavity and a shaft rotating about a rotation axis. One or more bearings support the shaft. A housing supporting the bearing and defining a chamber axially adjacent to the bearing. A seal assembly is in the housing between the chamber and an exterior of the chamber. The seal assembly includes a seal supported by the housing and surrounding the shaft so as to define an annular gap between an inner surface of the seal and an outer surface associated to the shaft, the gap defining a part of a sealing path of the seal assembly for air to flow from said exterior into the chamber. An impeller rotates with the shaft and located radially inward of the gap relative to the rotation axis, the impeller oriented to drive oil toward the bearing.

A turbomachine includes a compressor section, a turbine section, and a rotary component. The rotary component is attached to and rotatable with a portion of at least one of the compressor section and the turbine section. The turbomachine additionally includes a seal having a gas bearing. The gas bearing defines an inner surface along a radial direction of the turbomachine, a high pressure end, and a low pressure end. The gas bearing supports the rotary component and also prevents an airflow from the high pressure end to the low pressure end between the rotary component and the inner surface of the gas bearing.

A turbomachine includes a compressor section, a turbine section, and a rotary component. The rotary component is attached to and rotatable with a portion of at least one of the compressor section and the turbine section. The turbomachine additionally includes a seal having a gas bearing. The gas bearing defines an inner surface along a radial direction of the turbomachine, a high pressure end, and a low pressure end. The gas bearing supports the rotary component and also prevents an airflow from the high pressure end to the low pressure end between the rotary component and the inner surface of the gas bearing.