A power generation system includes a gas turbine system. The turbine system includes a combustion chamber configured to combust a fuel stream a compressor configured to receive a feed oxidant stream and supply a compressed oxidant to the combustion chamber and an expander configured to receive a discharge from the combustion chamber and generate an exhaust comprising carbon dioxide and electrical energy. The system further includes a retrofittable exhaust gas recirculation system including a splitter configured to split the exhaust into a first split stream and a second split stream, a heat recovery steam generator configured to receive the first split stream and generate a cooled first split stream and a purification system configured to receive the first cooled split stream and the second split stream and generate a recycle stream, wherein the recycle stream is mixed with the fresh oxidant to generate the feed oxidant stream.

Systems and methods for power generation with exhaust gas recirculation

A solar power forecasting system can provide forecasts of solar power output by photovoltaic plants over multiple time frames A first time frame may be several hours from the time of the forecast, which can allow utility personnel sufficient time to make decisions to counteract a forecasted shortfall in solar power output For example, the utility personnel can decide to increase power production and/or to purchase additional power to make up for any forecasted shortfall in solar power output A second time frame can be several minutes from the time of the forecast, which can allow for operations to mitigate effects of a forecasted shortfall in solar power output Such mitigation operations can include directing an energy management system to shed noncritical loads and/or ramping down the power produced by the photovoltaic plants at a rate that is acceptable to the utility to which the photovoltaic plants provide power

Systems and methods for forecasting solar power

A promoted activated carbon sorbent is described that is highly effective for the removal of mercury from flue gas streams. The sorbent comprises a new modified carbon form containing reactive forms of halogen and halides. Optional components may be added to increase reactivity and mercury capacity. These may be added directly with the sorbent, or to the flue gas to enhance sorbent performance and/or mercury capture. Mercury removal efficiencies obtained exceed conventional methods. The sorbent can be regenerated and reused. Sorbent treatment and preparation methods are also described. New methods for in-flight preparation, introduction, and control of the active sorbent into the mercury contaminated gas stream are described.

Sorbents for the oxidation and removal of mercury

A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member (14); (b) a turbine shroud (12) disposed in the support member (14), the shroud (12) being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring (32) mounted between the support member (14) and the shroud (12) and arranged to resiliently urge the shroud (12) to a concentric position within the support member (14).

Mounting apparatus for low-ductility turbine shroud

A ceramic seal segment (30) for a shroud ring (21) of a rotor (15) of a gas turbine engine (10), the ceramic seal segment (30) positioned radially adjacent the rotor (15) and characterised by being a hollow section that defines an inlet (44) and an outlet (64, 66) for the passage of coolant therethrough.

Rotor seal segment

An attachment method and flange for connecting a ceramic matrix composite (CMC) component, such as a gas turbine shroud ring ( 36, 68 ), to a metal support structure. A CMC flange ( 20 A) may be formed by attaching a wedge-shaped block ( 26 ) of a ceramic material to a CMC wall structure ( 22 ), and wrapping CMC layers ( 24 ) of the wall structure ( 22 ) at least partly around the block ( 26 ), forming the flange ( 20 A) with an inner oblique face ( 34 ) and an outer face ( 35 ) normal to the wall structure. An adjacent support structure, such as a metal support ring ( 40 A), may abut the outer face ( 35 ) of the CMC flange ( 20 A) and be clamped or bolted to the CMC flange ( 20 A).

Ceramic matrix composite attachment apparatus and method

A gas turbine includes a compressor, a combustor, a turbine, and a flow path diverting an excess portion of the compressed air produced by the compressor around the turbine The flow path conducts the excess portion into a turbine exhaust gas flow producing a cooled exhaust gas A method of operating the gas turbine includes opening an inlet guide vane of the compressor to allow the compressor to produce an increased volume of compressed air The increased volume exceeds a volume of compressed air needed to support combustion An excess portion of the compressed air is directed into the exhaust gas to produce a cooled exhaust In a combined cycle power plant, the cooled exhaust from the gas turbine may be used to warm a steam turbine portion to a desired temperature while allowing operation of the gas turbine at a power level that produces exhaust gas at a temperature higher than the desired temperature

Method for operating a gas turbine

Aspects of the invention relate to a ring seal for a turbine engine. The ring seal can be made up of a plurality of circumferentially abutted ring seal segments. Each ring seal segment can comprise a plurality of individual channels. The channels can be generally U-shaped in cross-section with a forward span, and aft span and an extension connecting therebetween. The channels can be positioned such that the aft span of one channel can substantially abut the forward span of another channel. The plurality of separate channels can be detachably coupled to each other by, for example, a plurality of pins. The ring seal segment according to aspects of the invention can facilitate numerous advantageous characteristics including greater material selection, selective cooling, improved serviceability, and reduced blade tip leakage. Moreover, the configuration is well suited to handle the operational loads of the turbine.

Turbine engine ring seal

Aspects of the invention are directed to systems for reducing the cooling requirements of a ring seal in a turbine engine. In one embodiment, the ring seal (54) can be made of a ceramic material, such as a ceramic matrix composite. The ceramic ring seal (54) can be connected to metal isolation rings (40, 42) by a plurality of pins (76, 78). The hot gas face (72) of the ring seal (54) can be coated with a thermal insulating material (74). In another embodiment, a ring seal (120) can be made of metal, but it can be operatively associated with a ceramic heat shield (122). The metal ring seal (120) can carry the mechanical loads imposed during engine operation, and the heat shield (122) can carry the thermal loads. By minimizing the amount of ring seal cooling, the ring seal systems according to aspects of the invention can result in improved engine performance and emissions

Ring seal system with reduced cooling requirements

A stacked ceramic matrix composite lamellate assembly (10) including shear force bearing structures (48) for resisting relative sliding movement between adjacent lamellae. The shear force bearing structures may take the form of a cross-lamellar stitch (50), a shear pin (62), a warp (90) in the lamellae, a tongue (104) and groove (98) structure, or an inter-lamellar sealing member (112), in various embodiments. Each shear force bearing structure secures a subset of the lamellae, with at least one lamella being common between adjacent subsets in order to secure the entire assembly.

Douglas A. Keller

Papers

Ceramic matrix composite attachment apparatus and method

Method for operating a gas turbine

Turbine engine ring seal

Ring seal system with reduced cooling requirements

Stacked lamellate assembly