Patent application number | Description | Published |
20120167545 | PURGE SYSTEM, SYSTEM INCLUDING A PURGE SYSTEM, AND PURGE METHOD - A purge system and liquid fuel atomizing system, a system including a purge system and liquid fuel atomizing system, and a method of purging and atomizing are disclosed. The purging involves a first nozzle, a second nozzle, a third nozzle, and a staged compression system having a first stage and a second stage. The first stage is configured to selectively direct a first pressurized fluid stream to the first nozzle and the second nozzle. The second stage is configured to selectively direct a second pressurized fluid stream to the third nozzle. | 07-05-2012 |
20120167577 | GAS TURBINE SYSTEM AND PROCESS - A gas turbine system and process include a compressor component configured to compress fluid to form a compressed fluid stream, a combustor configured to receive at least a first portion of the compressed fluid stream and at least partially combust a syngas to form a combustor discharge stream, and a turbine component positioned to receive the combustor discharge stream and to form a turbine component stream. In the system and process, a cool stream directed from a second system cools the turbine component stream. | 07-05-2012 |
20130343868 | Systems and Methods to Control Flow in a Rotor Wheel - Embodiments of the present application include a gas turbine system. The system may include a rotor wheel and one or more impeller vanes radially disposed on the rotor wheel. The system may also include one or more fluid passages defined by adjacent impeller vanes. The one or more fluid passages may be radially disposed across the rotor wheel. Moreover, the system may include one or more shape memory alloy valves disposed within each of the fluid passages. The one or more shape memory alloy valves may be configured to change shape to control a flow of fluid through the fluid passages. | 12-26-2013 |
20140109580 | PART LOAD PERFORMANCE IMPROVEMENT USING DEFORMABLE BORE PLUGS - A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel for air flow from a compressor, a first cooling channel and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel, the restrictor device responding to regulate the flow of air based on that temperature. The restrictor device may be a two-way shape memory alloy. | 04-24-2014 |
20140110092 | ATOMIZING AIR HEAT FOR ATTEMPERATION - An attemperation system and an atomizing air system are integrated for a combined cycle turbine including a gas turbine and a steam turbine. The atomizing air system receives compressor discharge air for fuel atomization. The atomizing air system includes an atomizing air cooler that serves to cool the compressor discharge air. A heat recovery steam generator receives exhaust from the gas turbine and generates steam for input to the steam turbine via an attemperation system. A feed water circuit draws feed water from the heat recovery steam generator and communicates in a heat exchange relationship with the atomizing air cooler to heat the feed water. The feed water circuit communicates the heated feed water to the attemperation system of the heat recovery steam generator. | 04-24-2014 |
20140123623 | GAS TURBOMACHINE SYSTEM INCLUDING AN INLET CHILLER CONDENSATE RECOVERY SYSTEM - A gas turbomachine system includes a compressor portion including an inlet portion, a turbine portion fluidically connected to, and mechanically linked with, the compressor portion, and a combustor assembly including at least one combustor fluidically connected to the turbine portion. An inlet system is fluidically connected to the inlet portion of the compressor portion. The inlet system includes an inlet chiller. An inlet chiller condensate recovery system is fluidically connected to the inlet system. The inlet chiller condensate recovery system includes an inlet fluidically connected to the inlet chiller and an outlet fluidically connected to one of the compressor portion and the combustor assembly. | 05-08-2014 |
20140130478 | GAS TURBOMACHINE INCLUDING A FUEL PRE-HEAT SYSTEM - A gas turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, a combustor assembly including at least one combustor fluidically connected to the turbine portion, and an accessory mechanically linked with and driven by the turbine portion. The gas turbomachine also includes a fuel pre-heat system including a fuel pre-heat element having a fuel circuit fluidically connected to the at least one combustor arranged in a heat exchange relationship with a heating medium circuit fluidically connected to at least one of the compressor portion, the turbine portion, and the accessory. | 05-15-2014 |
20140140806 | ENTHALPY DETERMINING APPARATUS, SYSTEM AND METHOD - Various embodiments include apparatuses and related methods for determining the enthalpy of steam. In some embodiments, an apparatus includes: an extraction conduit fluidly connected with a steam turbine section, the extraction conduit for obtaining wet steam from the steam turbine section; a mixing chamber fluidly connected with the extraction conduit; an injector fluidly connected with the mixing chamber, the injector for providing dry steam to the mixing chamber for mixing with the wet steam from the steam turbine section to produce a sample mixture; and an enthalpy detection system fluidly connected with the mixing chamber, the enthalpy detection system configured to determine an enthalpy of the sample mixture. | 05-22-2014 |