General Electric Company

Sal Albert Leone

Hua Zhang

Sacheverel Quentin Eldrid

Susan Marie Hyde

Ming Zhou

Thomas Francis Taylor

Christopher R Banares

Matthew David Book

Harry Kirk Mathews, Jr

Canan Uslu Hardwicke

Ravi Rajamani

Bruce Wayne Miller

Jonathan Carl Thatcher

Bruce Gordon Norman

Gene David Palmer

John Harry Down

Douglas Arthur Lupe

Edward Eugene Gibler

James Lee Burns

Ampili Kishore Kumar

Gary Joseph Drlik

Anju Narendra

Peter A Stinnett

Chad Ernest Findlay

A turbine system may include several air lines that extend from a compressor to a turbine, and the air lines may have valves. Additionally, the turbine system may also include several sensors that are coupled to the valves, several actuators that are coupled to the valves, and a controller that can send a command to set a valve position of one of the valves based at least partially on a valve position of another valve.

Systems and methods for reducing airflow imbalances in turbines

A combined cycle power plant includes at least one gas turbine, at least one steam turbine and a heat recovery boiler in combination to produce electricity and/or process steam. The heat recovery boiler has a duct for receiving and confining gas turbine exhaust gas from the gas turbine. Heat transfer tubes for heating water and steam for use in the bottoming steam cycle (steam turbine and/or process steam) are disposed within the heat recovery boiler and have exterior surfaces in fluid communication with the gas turbine exhaust gas and interior surfaces in circulatory fluid communication with water and/or steam. A cellular material is attached to the exterior surfaces of the heat transfer tubes and operates to enhance heat transfer from the gas turbine exhaust gas to the water and/or steam.

Combined cycle power plant

A combined cycle power plant includes a first generator driven by a gas turbine for generating electricity. The combined cycle power plant further includes a heat recovery steam generator disposed to receive exhaust gas from the gas turbine. The heat recovery steam generator includes an evaporator having tubes receptive to water flow therethrough. The tubes are disposed to be exposed to the exhaust gas, such that a flow of the exhaust gas passes around the tubes transfers heat from the exhaust gas to the tubes and thereby the water flowing through the tubes sufficient for the water to evaporate into steam. The tubes each having an outer surface with a plurality of deformations formed therein sufficient to introduce turbulence in the flow of the exhaust gas for enhancing heat transfer from the exhaust gas to the tubes.

Heat transfer tubes having dimples arranged between adjacent fins

A fault detection and isolation system for detecting leaks and blockages in a fluid handling system having at least one component through which fluid flows includes sensors for measuring fluid conditions upstream and downstream of the component. The sensors generate signals that are representative of the upstream and downstream fluid conditions and are fed to a control algorithm. The control algorithm uses the measured fluid conditions to generate estimates of an inlet state for the component and an outlet state for the component. The control algorithm also calculates innovation sequences for the estimated inlet and outlet states, and then compares the innovation sequences to predetermined thresholds to detect leaks and blockages.

Model-based detection of leaks and blockages in fluid handling systems

The invention provides a brush seal assembly, and method of using, for reducing adverse fluid flow effects to a brush seal,.the brush seal assembly comprising a support housing having a passage; a rotating shaft disposed in the passage of the support housing, the rotating shaft including a shaft body having a periphery and an annular tooth extending around the periphery of the shaft body; and an annular brush seal including a plurality of bristles extending around the shaft body, each of the plurality of bristles attached to and extending from the support housing in the passage towards the rotating shaft. The brush seal assembly further includes an annular abradable material portion being constructed of an abradable material, the abradable material portion having a groove extending around an inner periphery thereof, the abradable material portion disposed in the passage around, and proximate to, the tooth of the rotating shaft such that the tooth of the rotating shaft is disposed in the groove of the abradable material portion.

Brush seal assembly and method of using brush seal assembly

In a multi-stage turbine wherein at least one turbine wheel supports a row of buckets for rotation, and wherein the turbine wheel is located axially between first and second annular fixed arrays of nozzles, a cooling air circuit for purging a wheelspace between the turbine wheel and the second fixed annular array of nozzles comprising a flowpath through a shank portion of one or more buckets connecting a wheelspace between the turbine wheel and the first fixed annular array of nozzles with the wheelspace between the turbine wheel and the second fixed annular array of nozzles.

Stage 3 bucket shank bypass holes and related method

The invention provides a brush seal, and a method of using a brush seal, for providing a seal between a support housing and a rotating shaft. The brush seal comprises a support portion; a back plate connected to and extending from the support portion on a back side of the support portion. The brush seal further includes a set of bristles attached to the support portion, the back plate disposed on a back side of the set of bristles and supporting the set of bristles. The brush seal further includes at least one fitting portion connected to and extending from the support portion, each of the at least one fitting portions configured to mate with a corresponding slot in the support housing so as to prevent mis-fit of the brush seal in the support housing.

Brush seal and method of using brush seal

In a land based gas turbine including a compressor, a combustor and turbine section including at least three stages, an improvement comprising an inlet into a third stage nozzle from the compressor for feeding cooling air from the compressor to the third stage nozzle; at least one passageway running substantially radially through each airfoil of the third stage nozzle and an associated diaphragm, into an annular space between the rotor and the diaphragm; and passageways communicating between the annular space and individual buckets of the third stage.

Cooling supply system for stage 3 bucket of a gas turbine

A system and method are provided for controlling cooling air flow for pressure modulation of turbine components, such as the turbine outer sidewall cavities. The pressure at which cooling and purge air is supplied to the turbine outer side wall cavities is modulated, based on compressor discharge pressure (Pcd), thereby to generally maintain the back flow margin (BFM) so as to minimize excessive leakage and the consequent performance deterioration. In an exemplary embodiment, the air pressure within the third stage outer side wall cavity and the air pressure within the fourth stage outer side wall cavity are each controlled to a respective value that is a respective prescribed percentage of the concurrent compressor discharge pressure. The prescribed percentage may be determined from a ratio of the respective outer side wall pressure to compressor discharge pressure at Cold Day Turn Down (CDTD) required to provide a prescribed back flow margin.

System for pressure modulation of turbine sidewall cavities

A method is provided for controlling cooling air flow for pressure modulation of turbine components, such as the turbine outer sidewall cavities. The pressure at which cooling and purge air is supplied to the turbine outer side wall cavities is modulated, based on compressor discharge pressure (Pcd), thereby to generally maintain the back flow margin (BFM) so as to minimize excessive leakage and the consequent performance deterioration. In an exemplary embodiment, the air pressure within the third stage outer side wall cavity and the air pressure within the fourth stage outer side wall cavity are each controlled to a respective value that is a respective prescribed percentage of the concurrent compressor discharge pressure. The prescribed percentage may be determined from a ratio of the respective outer side wall pressure to compressor discharge pressure at Cold Day Turn Down (CDTD) required to provide a prescribed back flow margin.

Growing community of inventors

Scotia, NY, United States of America

Sal Albert Leone