General Electric Company

Exxonmobil Upstream Research Company

Siemens Energy, Inc.

Siemens Power Generation, Inc.

Christian Michael Hansen

Brian Denver Potter

Richard Alan Huntington

Michael James Healy

Todd Franklin Denman

Franklin F Mittricker

Samuel David Draper

Loren K Starcher

James Anthony West

Sulabh K Dhanuka

Dennis M O'Dea

Moorthi Subramaniyan

Karl Dean Minto

Alfred Paul Matheny

Friedrich T Rogers

Douglas Giles Moody

Dennis M O'DEA

A system includes a gas turbine system having a turbine combustor, a turbine driven by combustion products from the turbine combustor, and an exhaust gas compressor driven by the turbine. The exhaust gas compressor is configured to compress and supply an exhaust gas to the turbine combustor. The gas turbine system also has an exhaust gas recirculation (EGR) system. The EGR system is configured to recirculate the exhaust gas along an exhaust recirculation path from the turbine to the exhaust gas compressor. The system further includes a main oxidant compression system having one or more oxidant compressors. The one or more oxidant compressors are separate from the exhaust gas compressor, and the one or more oxidant compressors are configured to supply all compressed oxidant utilized by the turbine combustor in generating the combustion products.

System and method for oxidant compression in a stoichiometric exhaust gas recirculation gas turbine system

A system includes a gas turbine engine that includes a combustor section having one or more combustors configured to generate combustion products and a turbine section having one or more turbine stages between an upstream end and a downstream end. The one or more turbine stages are driven by the combustion products. The gas turbine engine also includes an exhaust section disposed downstream from the downstream end of the turbine section. The exhaust section has an exhaust passage configured to receive the combustion products as an exhaust gas. The gas turbine engine also includes a mixing device disposed in the exhaust section. The mixing device is configured to divide the exhaust gas into a first exhaust gas and a second exhaust gas, and to combine the first and second exhaust gases in a mixing region to produce a mixed exhaust gas.

System and method for exhausting combustion gases from gas turbine engines

Locking spacer assemblies, rotor assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a first end piece and a second end piece each configured to fit into a space between platforms of adjacent rotor blades, the first end piece and second end piece each comprising an outer surface and an inner surface, the outer surface having a profile adapted to project into an attachment slot, wherein the inner surfaces of the first and second end pieces generally face each other. The locking spacer assembly further includes an actuator movable between the inner surfaces, the actuator comprising a projection, the projection comprising a first surface and a second surface formed on the projection and configured to engage the inner surfaces, the first and second surfaces generally perpendicular to radial.

Locking spacer assembly

A locking spacer assembly for securing adjacent rotor blades includes a first end piece having a platform portion and a root portion that define an angled first inner surface of the first end piece. The root portion defines a first projection adapted to project into a recess portion of the attachment slot. A second end piece fits between the first inner surface and a sidewall portion of the attachment slot and includes a platform portion and a root portion that define a second projection adapted to project into a recess portion of the attachment slot. The platform portion and the root portion define an angled second inner surface and that is configured to mate with the first inner surface. A borehole extends through the platform portion of the first end piece and the root portion of the second end piece and a fastener extends through the borehole.

Locking spacer assembly inserted between rotor blades

Locking spacer assemblies, rotor assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a first end piece and a second end piece each configured to fit into a space between platforms of adjacent rotor blades, the first end piece and second end piece each comprising an outer surface and an inner surface, the outer surface having a profile adapted to project into an attachment slot, wherein the inner surfaces of the first and second end pieces generally face each other. The locking spacer assembly further includes an actuator movable between the inner surfaces, the actuator comprising a projection configured to engage the inner surface, the actuator further comprising a plurality of locating protrusions extending from the projection, the locating protrusions configured to fit within locating channels defined in the first end piece and the second end piece.

A mechanical drive train for testing a full scale compressor rig is disclosed. The drive train can include an electric motor, a gear box, and a gas turbine. The compressor rig is coupled to the drive train between the gear box and gas turbine. The drive train can further include a torque converter for transferring torque from the electric motor to the compressor rig. The drive train is configured to test a full scale compressor rig over the entire speed and load operating range, allowing for full compressor mapping from choke to stall at full load, part load (power turn down) and partial speed conditions. The drive train can also be used to test a compressor rig or gas turbine over the full range of operability for the compressor rig or gas turbine without having to connect the gas turbine to the power grid at the power generation site.

Mechanical drive train for testing full scale compressor rigs and gas turbines

A gas turbine engine is provided comprising an outer casing and a plurality of circumferentially positioned vane segments. The outer casing is provided with a circumferential casing slot. The plurality of circumferentially positioned vane segments are coupled to the outer casing. Each vane segment comprises at least one vane airfoil, a radially inner shroud coupled to a first end of the airfoil, a radially outer shroud coupled to a second end of the airfoil, and a strongback fixedly coupled to axially spaced-apart portions of the outer shroud such that a gap is provided between the strongback and the outer shroud. The strongback may comprise axially spaced-apart first and second end portions received in the casing slot.

Gas turbine engine

A locking spacer assembly for filling a void between adjacent components in a turbine engine. In at least one embodiment, the locking spacer assembly may be configured to be inserted between adjacent turbine blades in a disc groove in a turbine blade stage assembly. The locking spacer assembly may be formed from fore and aft end supports and a locking device having fore and aft angled surfaces for urging the fore and aft end supports into lateral recesses in the disc groove. The locking spacer assembly may also include a mid spacer positioned between the fore and aft end supports. A retainer may be attached to the locking device to draw the fore and aft angled surfaces of the locking device into contact with the fore and aft support surfaces and urge the first and second end supports into lateral recesses in the disc groove.

Growing community of inventors

Simpsonville, SC, United States of America

Christian Michael Hansen