Abstract: A rotor journal support system (10) configured to allow for a bearing shoe (16) to properly align to the rotor (14) while keeping the bearing shoe (16) constrained during handling, installation, and operation limit is disclosed. The rotor journal support system (10) may be configured to enable limited movement of a bearing shoe (16) such that when the rotor journal (14) is installed, the bearing shoe (16) is properly aligned with the rotor journal (14), thereby requiring less torque to turn the rotor journal (14) from a stop than when the bearing shoe (16) is misaligned. The rotor journal support system (10) may include bearing shoe supports (88) extending radially outward from the bearing shoe (16). The bearing shoe support (88) may include an outer bearing surface (100) having at least a partial spherical shape configured to bear against the aligning ring (24).

Abstract: A thermocouple probe assembly for monitoring the temperature of an exhaust gas flow at an output of a gas turbine engine. The probe assembly includes a plenum pipe positioned within an opening extending through an outer casing wall and a plenum plate of the engine, where an air gap is provided between the casing wall and the plate. The plenum pipe is rigidly secured to the plenum plate and resiliently mounted to the casing wall so that the plenum pipe is operable to slide relative to the wall. The probe assembly further includes a diffuser liner boss rigidly secured to an outer liner of an exhaust gas diffuser in the gas turbine engine, where the liner boss includes a central bore, and where the shaft of the thermocouple probe extends through the central bore in the liner boss so that the sensor is positioned within the exhaust gas diffuser.

Abstract: A sealing system (20) for an optical sensor of a turbine engine that diverts and exhaust seal leakage away from the seal (22, 24) to prevent ingestion of humid air through the seal (22, 24) is disclosed. The sealing system (20) may include inner and outer optical housings (26, 28) with first and second seals (22, 24) positioned there between separating inner and outer optical housings (26, 28) radially. The sealing system (20) may include one or more leakage manifolds (30) positioned between the first and second seals (22, 24) and containing one or more manifold rings (32). The manifold ring (32) may be positioned between and in contact with the first and second seals (22, 24) enabling the first and second seals (22, 24) to form a double seal. The manifold ring (32) may also be configured to capture leakage air that has seeped past the first seal (22) and exhaust that leakage air through one or more exhaust vents (34) in the outer optical housing (28) before leaking through the sealing system (20).

Abstract: A rotor journal support system (10) configured to allow for a bearing shoe (16) to properly align to the rotor (14) while keeping the bearing shoe (16) constrained during handling, installation, and operation limit is disclosed. The rotor journal support system (10) may be configured to enable limited movement of a bearing shoe (16) such that when the rotor journal (14) is installed, the bearing shoe (16) is properly aligned with the rotor journal (14), thereby requiring less torque to turn the rotor journal (14) from a stop than when the bearing shoe (16) is misaligned. The rotor journal support system (10) may include bearing shoe supports (88) extending radially outward from the bearing shoe (16). The bearing shoe support (88) may include an outer bearing surface (100) having at least a partial spherical shape configured to bear against the aligning ring (24).

Abstract: A sealing system (20) for an optical sensor of a turbine engine that diverts and exhaust seal leakage away from the seal (22, 24) to prevent ingestion of humid air through the seal (22, 24) is disclosed. The sealing system (20) may include inner and outer optical housings (26, 28) with first and second seals (22, 24) positioned there between separating inner and outer optical housings (26, 28) radially. The sealing system (20) may include one or more leakage manifolds (30) positioned between the first and second seals (22, 24) and containing one or more manifold rings (32). The manifold ring (32) may be positioned between and in contact with the first and second seals (22, 24) enabling the first and second seals (22, 24) to form a double seal. The manifold ring (32) may also be configured to capture leakage air that has seeped past the first seal (22) and exhaust that leakage air through one or more exhaust vents (34) in the outer optical housing (28) before leaking through the sealing system (20).

Abstract: A thermocouple probe assembly for monitoring the temperature of an exhaust gas flow at an output of a gas turbine engine. The probe assembly includes a plenum pipe positioned within an opening extending through an outer casing wall and a plenum plate of the engine, where an air gap is provided between the casing wall and the plate. The plenum pipe is rigidly secured to the plenum plate and resiliently mounted to the casing wall so that the plenum pipe is operable to slide relative to the wall. The probe assembly further includes a diffuser liner boss rigidly secured to an outer liner of an exhaust gas diffuser in the gas turbine engine, where the liner boss includes a central bore, and where the shaft of the thermocouple probe extends through the central bore in the liner boss so that the sensor is positioned within the exhaust gas diffuser.

Abstract: A can annular industrial gas turbine engine, including: a single-piece rotor shaft spanning a compressor section (82), a combustion section (84), a turbine section (86); and a combustion section casing (10) having a section (28) configured as a full hoop. When the combustion section casing is detached from the engine and moved to a maintenance position to allow access to an interior of the engine, a positioning jig (98) is used to support the compressor section casing (83) and turbine section casing (87).

Abstract: A cooling system for turbine engines for controlling cooling of rotor cooling air and heating of fuel gas is disclosed. The cooling system may be formed from a housing formed from a main plenum, a rotor air cooler positioned at least partially in the main plenum and a fuel gas heater positioned at least partially in the main plenum downstream from rotor air cooler. The cooling system may include a by-pass plenum for returning used cooling air back to a region upstream of the rotor air cooler. An exhaust fluid control device may control fluid flow out of the first exhaust opening at the second end of the main plenum, and a by-pass fluid control device may control fluid flow into the by-pass inlet opening of the by-pass plenum. The control devices and a fan may control circulation of cooling fluids through the main plenum.

Abstract: A can annular industrial gas turbine engine, including: a single-piece rotor shaft spanning a compressor section (82), a combustion section (84), a turbine section (86); and a combustion section casing (10) having a section (28) configured as a full hoop. When the combustion section casing is detached from the engine and moved to a maintenance position to allow access to an interior of the engine, a positioning jig (98) is used to support the compressor section casing (83) and turbine section casing (87).

Abstract: A cooling system for turbine engines for controlling cooling of rotor cooling air and heating of fuel gas is disclosed. The cooling system may be formed from a housing formed from a main plenum, a rotor air cooler positioned at least partially in the main plenum and a fuel gas heater positioned at least partially in the main plenum downstream from rotor air cooler. The cooling system may include a by-pass plenum for returning used cooling air back to a region upstream of the rotor air cooler. An exhaust fluid control device may control fluid flow out of the first exhaust opening at the second end of the main plenum, and a by-pass fluid control device may control fluid flow into the by-pass inlet opening of the by-pass plenum. The control devices and a fan may control circulation of cooling fluids through the main plenum.

Abstract: Aspects of the invention relate to a system and method for operating a turbine engine assembly. The turbine engine assembly has a turbine engine having a compressor section, a combustor section and a turbine section. The combustor section has a lower T_PZ limit and the turbine engine has a design load. The assembly further includes at least one air bleed line from the compressor and at least one valve for controlling air flow through the bleed line. Control structure is provided for opening the valve to allow bleed air to flow through the bleed line when an operating load is less than the design load. The flow rate through the bleed line is increased as the operating load is decreased, reducing the power delivered by the turbine assembly while maintaining the T_PZ above a lower T_PZ limit. A method for operating a turbine engine assembly is also disclosed.

Abstract: Aspects of the invention relate to a system and method for operating a turbine engine assembly. The turbine engine assembly has a turbine engine having a compressor section, a combustor section and a turbine section. The combustor section has a lower T_PZ limit and the turbine engine has a design load. The assembly further includes at least one air bleed line from the compressor and at least one valve for controlling air flow through the bleed line. Control structure is provided for opening the valve to allow bleed air to flow through the bleed line when an operating load is less than the design load. The flow rate through the bleed line is increased as the operating load is decreased, reducing the power delivered by the turbine assembly while maintaining the T_PZ above a lower T_PZ limit. A method for operating a turbine engine assembly is also disclosed.

Abstract: The exhaust gas of a turbine engine can include water vapor. Aspects of the invention relate to various systems for recovering water from the exhaust gas of a gas turbine engine. In one system, a portion of the exhaust gas can be routed to an absorption chiller. In another system, a portion of the exhaust gas can be routed to a direct contact heat exchanger. In a third system, a portion of the exhaust gas can be routed to a fin-fan cooler. In each of these systems, the portion of gas can be cooled below its dew point temperature to release a portion of its humidity as liquid water. Aspects of the invention can be used with the turbine exhaust of simple and combined cycle power plants. A water recovery system according to aspects of the invention can minimize or eliminate a power plant's dependence on local water sources.

Abstract: The exhaust gas of a turbine engine can include water vapor. Aspects of the invention relate to various systems for recovering water from the exhaust gas of a gas turbine engine. In one system, a portion of the exhaust gas can be routed to an absorption chiller. In another system, a portion of the exhaust gas can be routed to a direct contact heat exchanger. In a third system, a portion of the exhaust gas can be routed to a fin-fan cooler. In each of these systems, the portion of gas can be cooled below its dew point temperature to release a portion of its humidity as liquid water. Aspects of the invention can be used with the turbine exhaust of simple and combined cycle power plants. A water recovery system according to aspects of the invention can minimize or eliminate a power plant's dependence on local water sources.

Abstract: An apparatus and method are disclosed for removably attaching an ISO corner fitting to a composite material shipping container. The apparatus and method of the invention comprises a post that is anchored in the composite material frame of the container. The ISO corner fitting is then attached to the post using a connector assembly that may be engaged and disengaged as needed to attach and detach the ISO corner fitting from the post. The post has a plurality of grooves formed thereon that help hold the post in the composite material of the shipping container. The grooves transfer any tension or compression loads that are applied to the ISO corner fitting directly to the shipping container.

Abstract: A method for rotatably balancing a driveshaft includes the initial step of using a conventional balancing apparatus is used to determined the size and location of the balance weights needed to properly balance the driveshaft. Next, an adhesive material is applied to either or both of the driveshaft and the balance weight. The balance weight is preferably formed having an inner surface that is curved to conform with the curvature of the outer surface of the driveshaft. The preferred balance weight is further formed having a relatively thin outer peripheral rim portion having a plurality of radially outwardly extending teeth formed thereon. The overall size of the balance weight may be varied to provide differing amounts of weight for facilitating the balancing process.

Abstract: An improved combined cycle power plant (10) having a plurality of kettle boilers (30,31,32) used in sequence for cooling the compressed air being directed via line (29) to cool portions of the gas turbine (20). The kettle boilers remove heat from the compressed air and produce a plurality of steam flows in lines (70,71,73) at pressures in parallel with the heat recovery steam generator (41,42,43) steam flows. Steam in line (72) for cooling other portions of the gas turbine is maintained at a very high level of purity by providing a high rate of blowdown through line (65) from the steam drum (45) providing the steam. Heat from the blowdown flow is directed to heat exchanger (66) to heat incoming fuel gas from source (26), or alternatively to heat the condensate via line (74) during periods of fuel oil operation.

Abstract: An improved system for recovering waste heat from a combustion turbine in a combined cycle power plant of the type that includes at least one combustion turbine and at least one steam turbine includes a first heat recovery system for heating condensate in the steam turbine cycle with heat from the hot exhaust gases from the combustion-type turbine, and a second heat recovery system for heating the fuel that is used in the combustion turbine with heat from the exhaust gases. The second system permits recovery of heat energy that is not recovered by the first system, thereby improving plant efficiency.

Abstract: The efficiency of a combined cycle power plant is improved by preheating fuel supplied to a combustion turbine. The flow rate of feed water through an economizer section of a heat recovery steam generator is increased, and the excess flow, over that required to sustain saturated steam production in an evaporator section, is flowed through a heat exchanger to preheat the fuel.

Abstract: A deaerating subsystem in a combined cycle power plant includes a deaerator and a storage tank coupled to the deaerator, the deaerating subsystem being adapted for isolation of the deaerator when it is defective even while the overall combined cycle power plant is operating. Blind flanges are provided in a downcomer and in vapor risers between the deaerator and the storage tank for such isolation. Also provided is a condensate bypass for preventing the reception of the condensate by the deaerator, and for enabling the storage tank to receive the condensate directly. Thermal energy is input into the storage tank such that controlled amounts of heated condensate from the steam generator, and controlled amounts of dry steam can be input to the storage tank while the deaerator is isolated for repairs.