A method of installing a retaining ring assembly in a turbine case is provided. The method may include installing a blade outer air seal into a case before installation of a retaining ring assembly. The method may further include installing a key system on a retaining ring to create the retaining ring assembly. The method may also include installing the retaining ring assembly in a case. The method may further include rotating the retaining ring assembly in the case until key system is aligned with a case slot. The method may also include tightening the key system to the retaining ring and cause key system to engage the case slot.

A turbine engine comprising a compressor section and a turbine section in serial flow arrangement defining a working air flow path with a heat exchanger in fluid communication the working air flow path, and a nuclear fuel in thermal communication with the heat exchanger and a release valve in fluid communication with the working air flow path.

A flow guiding appliance of a turbomachine, in particular of an aircraft engine, for a partial exit flow of an outlet guide vane of a compressor, wherein, a flow guiding element delimits an annular channel about a shaft of the turbomachine. A frictional engagement connecting surface at the circumference of the flow guiding element connects the flow guiding element to another structural component of the turbomachine. The frictional engagement connecting surface with a closed enveloping surface can be inserted in a deformed state into the structural component with a circular cylindrical sealing surface with at least two opposite points. The at least two points of the closed enveloping surface are arranged in at least two opposite frictionally engaged contact areas of the circular cylindrical sealing surface following deformation. The invention also relates to a method for creating a flow guiding element.

A turbine blade includes an airfoil that includes a root end and a tip end. The tip end is radially spaced from the root end. A tip shroud extends from the tip end. The tip shroud includes a shroud plate. The shroud plate includes a plurality of undulating ridges.

A plant according to an embodiment includes a gas turbine; a heat recovery unit that includes a primary heat recovery steam generator in which a primary heat exchanging unit generates primary steam by exchanging heat that is the thermal energy of the flue gas from the gas turbine, and a secondary heat recovery steam generator that is installed independently from the primary heat exchanging unit, and in which a secondary heat exchanging unit generates secondary steam by exchanging heat that is the thermal energy of the flue gas partly having exchanged heat in the primary heat exchanging unit included in the primary heat recovery steam generator; a primary steam turbine; a CO.sub.2 recovery unit; and a first reboiler heat supply line.

A plant according to an embodiment includes a gas turbine; a heat recovery unit that includes a primary heat recovery steam generator in which a primary heat exchanging unit generates primary steam by exchanging heat that is the thermal energy of the flue gas from the gas turbine, and a secondary heat recovery steam generator that is installed independently from the primary heat exchanging unit, and in which a secondary heat exchanging unit generates secondary steam by exchanging heat that is the thermal energy of the flue gas partly having exchanged heat in the primary heat exchanging unit included in the primary heat recovery steam generator; a primary steam turbine; a CO.sub.2 recovery unit; and a first reboiler heat supply line.

Provided are techniques for proactively operating gas-oil separation plant (GOSP) type process facilities that include determining historical operational characteristics of a GOSP for a past time interval using historical operational data for the GOSP, determining expected operating characteristics of the GOSP for a subsequent time interval using the historical operational characteristics, determining an operating plan for the GOSP using the expected operating characteristics, and operating the GOSP in accordance with the operating plan.

A secondary air system for an aircraft engine comprises an air flow path communicating between a source of pressurized cooling air and an air consuming component. A filter is disposed in the air flow path upstream from the air consuming component. The filter has at least one of: openings of a size selected for capturing suspended particles; and a filter surface material for binding with chemical contaminants.

A secondary air system for an aircraft engine comprises an air flow path communicating between a source of pressurized cooling air and an air consuming component. A filter is disposed in the air flow path upstream from the air consuming component. The filter has at least one of: openings of a size selected for capturing suspended particles; and a filter surface material for binding with chemical contaminants.

A turbine section for a gas turbine engine includes an independently controllable wheel downstream of the first static vane structure and a turbine rotor downstream of the independently controllable wheel. A method of generating thrust for a gas turbine engine, includes rotating a independently controllable wheel located downstream of a combustor and upstream of a turbine rotor to augment a swirl of a core flow combustion gases.