Abstract: A method relating to pricing under a contractual service agreement between a customer and a service provider, where the service provider provides maintenance services on a generating unit for a fee. An output of the generating unit is produced by a generator to which the generating unit is operably connected. The method comprising: determining a usage period for the generating unit; monitoring the output of the generating unit during the usage period and, therefrom, designating an output level for the generating unit for the usage period; calculating the fee for the usage period pursuant to a variable pricing plan, the variable pricing plan comprising a price for calculating the fee that varies depending on the designated output level of generating unit for the usage period; and billing the calculated fee to the customer.

Abstract: A method relating to pricing under a contractual service agreement between a customer and a service provider, where the service provider provides maintenance services on a generating unit for a fee. An output of the generating unit is produced by a generator to which the generating unit is operably connected. The method comprising: determining a usage period for the generating unit; monitoring the output of the generating unit during the usage period and, therefrom, designating an output level for the generating unit for the usage period; calculating the fee for the usage period pursuant to a variable pricing plan, the variable pricing plan comprising a price for calculating the fee that varies depending on the designated output level of generating unit for the usage period; and billing the calculated fee to the customer.

Abstract: A power plant control system determines an augmented operating parameter set point responsive to a life cycle cost (LCC) objective function responsive to a LCC model. The augmented operating parameter value may be responsive to an initial set point determined by a controls model and a performance indicator determined by a performance model. The power plant may include a thermal generator, such as a gas turbine or other fuel-burning generator, and the operating parameter may include firing temperature, fuel flow rate, steam pressure/temperature/flow rate, and/or another suitable operating parameter. An offer curve is generated responsive to the augmented operating parameter.

Abstract: A system for augmenting gas turbine power output includes a compressed air supply, and a compressed air storage plenum in fluid communication with the compressed air supply. The compressed air storage plenum is configured to store a compressed air from the compressed air supply for later use. The system further includes an inlet plenum sealingly coupled to an inlet of the gas turbine. The inlet plenum is in fluid communication with the compressed air storage plenum so as to route the compressed air from the compressed air storage plenum into the inlet of the compressor during augmented operation of the gas turbine.

Abstract: A system for augmenting gas turbine power output includes a compressed air supply, and a compressed air storage plenum in fluid communication with the compressed air supply. The compressed air storage plenum is configured to store a compressed air from the compressed air supply for later use. The system further includes an inlet plenum sealingly coupled to an inlet of the gas turbine. The inlet plenum is in fluid communication with the compressed air storage plenum so as to route the compressed air from the compressed air storage plenum into the inlet of the compressor during augmented operation of the gas turbine.

Abstract: A power plant control system determines an augmented operating parameter set point responsive to a life cycle cost (LCC) objective function responsive to a LCC model. The augmented operating parameter value may be responsive to an initial set point determined by a controls model and a performance indicator determined by a performance model. The power plant may include a thermal generator, such as a gas turbine or other fuel-burning generator, and the operating parameter may include firing temperature, fuel flow rate, steam pressure/temperature/flow rate, and/or another suitable operating parameter. An offer curve is generated responsive to the augmented operating parameter.

Abstract: A method of assembling a fluid compression system includes coupling at least one first compression apparatus to a first platform. The method also includes coupling at least one drive apparatus to one of the first platform and a second platform. The method further includes coupling the first platform to the second platform. The at least one second compression apparatus is coupled in series flow communication with the at least one first compression apparatus.

Abstract: A fiber brush seal attached with metallic structure, suitable for use with SiC-SiC ceramic matrix composite (CMC) components. The fibers may be selected from oxides, carbides and nitrides of silicon, tungsten, chromium, iron, titanium, boron, zirconium and aluminum, and may optionally be coated with a boron nitride based coating.

Abstract: A system comprises, a first heat recovery steam generator (HRSG) having an upstream intake duct portion, a first gas turbine engine connected to a first exhaust duct operative to output exhaust from the first gas turbine engine to the upstream intake duct portion of the first HRSG, and a second gas turbine engine connected to a second exhaust duct operative to output exhaust from the second gas turbine engine to the upstream intake duct portion of the first HRSG.

Abstract: A combustor has a flow sleeve and a flow liner defining a generally axial flow direction of compressor discharge air toward combustor burners. A casing is secured to the forward end of the flow sleeve defining an annular plenum along the interior of the flow sleeve. Openings through the flow sleeve supply compressor discharge air into the plenum where the air changes direction for flow through apertures into and generally coaxially with the free air stream. The axial injection minimizes or eliminates energy losses due to cross flow injection within the axial air stream while continuing to cool the liner.

Abstract: A method of assembling a combustion system includes providing a gas turbine engine that includes a gas turbine section coupled downstream from a combustion chamber and coupling a source of oxygen to the gas turbine engine such that a stream of oxygen discharged from the source facilitates displacing nitrogen in the working fluid of the gas turbine engine and facilitates decreasing emissions generated within the gas turbine engine.

Abstract: A gas turbine combustor includes a substantially cylindrical combustor liner located substantially concentrically within a flow sleeve, the combustor liner composed through a ceramic matrix composite material, a forward end of the combustor liner provided with a plurality of circumferentially arranged bolt holes. An inner metal ring is located about an outside surface of the forward end of the combustor liner, the inner metal ring provided with a second plurality of circumferentially spaced bolt holes, with a plurality of bolts extending through the first and second pluralities of bolt holes and secured by self-locking nuts. An outer metal ring is spaced radially outwardly of the inner metal ring, with a plurality of circumferentially spaced struts extending between the inner and outer rings.

Abstract: A method of assembling a fluid compression system includes coupling at least one first compression apparatus to a first platform. The method also includes coupling at least one drive apparatus to one of the first platform and a second platform. The method further includes coupling the first platform to the second platform. The at least one second compression apparatus is coupled in series flow communication with the at least one first compression apparatus.

Abstract: A shroud support method and apparatus for a ceramic component of a gas turbine having: an outer shroud block having a coupling to a casing of the gas turbine; a spring mass damper attached to the outer shroud block and including a spring biased piston extending through said outer shroud block, wherein the spring mass damper applies a load to the ceramic component; and the ceramic component has a forward flange and an aft flange each attachable to the outer shroud block.

Abstract: A shroud support method and apparatus for a ceramic component of a gas turbine having: an outer shroud block having a coupling to a casing of the gas turbine; a spring mass damper attached to the outer shroud block and including a spring biased piston extending through said outer shroud block, wherein the spring mass damper applies a load to the ceramic component; and the ceramic component has a forward flange and an aft flange each attachable to the outer shroud block.

Abstract: A silicon carbide fiber brush seal, suitable for use with SiC—SiC CMC components. The seal may be coated with a boron nitride based coating.

Abstract: A shroud support apparatus for a ceramic component of a gas turbine having: an outer shroud block having a coupling to a casing of the gas turbine; a spring mass damper attached to the outer shroud block and including a spring biased piston extending through said outer shroud block, wherein the spring mass damper applies a load to the ceramic component; and the ceramic component has a forward flange and an aft flange each attachable to the outer shroud block.

Abstract: The damper system includes a ceramic composite shroud in part defining the hot gas path of a turbine and a spring-biased piston and damper block which bears against the backside surface of the shroud to tune the vibratory response of the shroud relative to pressure pulses of the hot gas path in a manner to avoid near or resonant frequency response. The damper block has projections specifically located to bear against the shroud to dampen the frequency response of the shroud and provide a thermal insulating layer between the shroud and the damper block.

Abstract: A method for securing a nozzle for a turbine is provided. The nozzle includes an airfoil having a suction side and a pressure side connected at a leading edge and a trailing edge such that a cooling cavity is defined within the airfoil, the airfoil extending between an inner band and an outer band. The method includes extending at least one member through the airfoil, and at least one of the inner band and the outer band. The method further includes securing the nozzle assembly in position with at least one fastener such that the at least one member is coupled adjacent to at least one of the inner band and the outer band.

Abstract: A method for securing a nozzle for a turbine is provided. The nozzle includes an airfoil having a suction side and a pressure side connected at a leading edge and a trailing edge such that a cooling cavity is defined within the airfoil, the airfoil extending between an inner band and an outer band. The method includes extending at least one member through the airfoil, and at least one of the inner band and the outer band. The method further includes securing the nozzle assembly in position with at least one fastener such that the at least one member is coupled adjacent to at least one of the inner band and the outer band.