Abstract: The power plant comprises an integrally geared vapor compressor arrangement, comprised of a bull gear and a compressor shaft with a pinion meshing with the bull gear. The plant further comprises a vapor source, fluidly connectable with an inlet of the integrally geared vapor compressor arrangement. A vapor turbine arrangement is fluidly connectable with an outlet of the integrally geared vapor compressor arrangement for receiving a stream of compressed and superheated vapor from the integrally geared vapor compressor arrangement. An electric generator driven by the vapor turbine arrangement converts mechanical power produced by the vapor turbine arrangement into electric power.

Abstract: The concentrated solar power (CSP) plant comprises a solar field and a vapor turbine system. The vapor turbine system includes a vapor turbine arrangement. The vapor turbine arrangement receives super-heated vapor generated by heating a working fluid circulating in the vapor turbine system. The plant further comprises a thermal transfer system configured for transferring solar thermal energy from the solar field to the vapor turbine system. Moreover, a supplemental-energy delivery device is provided, which is configured for superheating the vapor, when the solar thermal energy from the solar field is insufficient to generate superheated vapor.

Abstract: A power plant includes a first turbine having a plurality of turbine stages. The first turbine discharges a first fluid flow. A second turbine is operatively coupled to the first turbine. The second turbine receives the first fluid flow from the first turbine and a second fluid flow. An interface member is mounted between the first and second turbines. The interface member includes a main body portion having an inner surface, an inlet portion and an outlet portion that combine to form a fluid flow path that extends between the first and second turbines. The interface member further includes an input member having an input passage that leads the second fluid into the fluid flow path. The interface member also includes a baffle plate that extends toward the fluid flow path. The baffle plate establishes a flow gap between the input passage and the inlet and outlet portions.

Abstract: A composite material for use in turbine support structures. The composite material may include a first material having a positive coefficient of thermal expansion and a second material having a negative coefficient of thermal expansion, a negative Poisson ratio, or both a negative coefficient of thermal expansion and a negative Poisson ratio.

Abstract: A method of fabricating an exhaust hood is provided for use with a turbine engine. The method includes providing an upper shell casing wherein the upper shell casing is fabricated from a composite material, and coupling the upper shell casing to a lower shell casing such that a turbine is housed within the exhaust hood, the shell casing is fabricated from a composite material. A turbine assembly is also provided.

Abstract: A power plant includes a first turbine having a plurality of turbine stages. The first turbine discharges a first fluid flow. A second turbine is operatively coupled to the first turbine. The second turbine receives the first fluid flow from the first turbine and a second fluid flow. An interface member is mounted between the first and second turbines. The interface member includes a main body portion having an inner surface, an inlet portion and an outlet portion that combine to form a fluid flow path that extends between the first and second turbines. The interface member further includes an input member having an input passage that leads the second fluid into the fluid flow path. The interface member also includes a baffle plate that extends toward the fluid flow path. The baffle plate establishes a flow gap between the input passage and the inlet and outlet portions.

Abstract: A method of fabricating an exhaust hood is provided for use with a turbine engine. The method includes providing an upper shell casing wherein the upper shell casing is fabricated from a composite material, and coupling the upper shell casing to a lower shell casing such that a turbine is housed within the exhaust hood, the shell casing is fabricated from a composite material. A turbine assembly is also provided.

Abstract: A composite material for use in turbine support structures. The composite material may include a first material having a positive coefficient of thermal expansion and a second material having a negative coefficient of thermal expansion, a negative Poisson ratio, or both a negative coefficient of thermal expansion and a negative Poisson ratio.

Abstract: A method of monitoring radial clearances in a steam turbine during operation of the turbine is provided. The method, in an exemplary embodiment, includes measuring a temperature of the rotor shaft at a time1 and at a time2, measuring a temperature of the rotor blade at time1 and at time2, measuring a temperature of the shell at time1 and at time2, calculating a shaft radial growth between time1 and time2, calculating a blade growth between time1 and time2, calculating a shell radial growth between time1 and time2, and determining a change in a radial gap between the shell and a distal end of the rotor blade from time1 to time2 using the following equation: change in radial gap=shell radial growth?shaft radial growth?blade growth.

Abstract: A method of monitoring radial clearances in a steam turbine during operation of the turbine is provided. The method, in an exemplary embodiment, includes measuring a temperature of the rotor shaft at a time1 and at a time2, measuring a temperature of the rotor blade at time1 and at time2, measuring a temperature of the shell at time1 and at time2, calculating a shaft radial growth between time1 and time2, calculating a blade growth between time1 and time2, calculating a shell radial growth between time1 and time2, and determining a change in a radial gap between the shell and a distal end of the rotor blade from time1 to time2 using the following equation: change in radial gap=shell radial growth−shaft radial growth−blade growth.