Siemens Energy, Inc.

Other

Siemens Aktiengesellschaft

Siemens Power Generation, Inc.

Adam Matthew Foust

Nitin Chhabra

David Allen Little

Raymond Scott Nordlund

Gerard McQuiggan

Damien G Teehan

Gary V Hildebrandt

David J Gloekler

Shervin Rodd

Hubert Edward Paprotna

Raymond S Nordlund

An abdominal exercise assembly includes a bracket that is longitudinally elongated to extend substantially across a door frame. The bracket has a pair of foot recesses each integrated into the bracket to have a respective one of a user's feet positioned in the foot recesses. A plurality of foot pads is each positioned on the bracket and each of the foot pads extends along a respective one of the foot recesses to cushion a respective one of the user's feet when the user's feet are extended into the foot recesses. A pair of clamps is each movably integrated into the bracket. Each of the clamps is movable toward or away from the bracket to engage opposite sides of the door frame for retaining the bracket in the door frame.

Abdominal exercise assembly

An interface () is provided between a combustor basket () and a transition () of a gas turbine engine (). The interface () includes a tongue () formed in one of the combustor basket () and the transition (), and a groove () formed in another of the combustor basket () and the transition (). The tongue () is received within the groove () to define the interface (). A sealing arrangement is also provided and includes an annular combustion outlet () and an annular transition inlet (), with a labyrinth seal () positioned between an end () of the annular combustion outlet and an end () of the annular transition inlet to form a labyrinth path () there between. An inner diameter () of the annular combustion outlet () is axially aligned with an inner diameter () of the annular transition outlet ().

Interface between a combustor basket and a transition of a gas turbine engine

A starting process for a gas turbine () that holds the turbine speed of rotation at an ignition speed setting during an ignition window (), with the ignition speed setting being based on ambient air conditions to achieve a specified combustor air mass flow rate (). A fuel flow rate may be set based on the fuel type and temperature to achieve a particular air/fuel ratio in a combustor. The fuel flow rate may be adjusted during the ignition window and thereafter based on a combustor inlet air temperature (). Completion of ignition may be determined by a reduction () in a blade path temperature spread (). After ignition, fuel flow is increased to accelerate the turbine to full speed. At any point, the fuel flow may be reduced, or its increase may be slowed, to avoid exceeding a temperature limit in the turbine.

Gas turbine starting process

A turbine engine assembly for a generator including a turbine engine having a compressor section, a combustor section and a turbine section. An air bleed line is in communication with the combustor section for receiving combustor shell air from the combustor section and conveying the combustor shell air as bleed air to a plurality of stages of the turbine section. Bleed air is controlled to flow through the air bleed line when an operating load of the turbine engine assembly is less than a base load of the engine to bypass air exiting the compressor section around a combustor in the combustor section and effect a flow of high pressure combustor shell air to the stages of the turbine section.

Cooling of turbine components using combustor shell air

A gas turbine combustion system for a turbine engine is disclosed. The gas turbine combustion system may include a plurality of combustor baskets positioned circumferentially about a longitudinal axis of the turbine engine, at least one firing nozzle extending into each of the plurality of combustor baskets and a fuel delivery system in communication with each of the at least one firing nozzles and in communication with at least one fuel source. Each combustor basket may include a fuel flow control device of the fuel delivery system inline with each of the at least one firing nozzles in that combustor basket such that fuel flow to some of the combustor baskets can be shut off while fuel flow to firing nozzles in other combustor baskets remains unobstructed, thereby permitting some combustor baskets to remain non-fired while other combustor baskets are firing to reduce CO emissions.

Sequential combustion firing system for a fuel system of a gas turbine engine

Aspects of the invention relate to a system and method for actively managing blade tip clearances in a turbine engine, particularly under start up and steady state operating conditions. During start up, the rotor can be cooled while the blade ring can be heated. During steady state operation, the rotor may be heated while the blade ring may be cooled. The sources of the heating fluid and cooling fluid can be compressor delivery air, boiler steam and ambient air. The fluids can be compressed to maintain efficiency.

Tip clearance control

Aspects of the invention relate to a system and method for actively controlling compressor clearances in a turbine engine by passing a thermal fluid in heat exchanging relation through a compressor vane carrier. During some operational conditions, such as hot restart or spin cool, it may be desirable to heat the vane carrier to enlarge or at least prevent a decrease in compressor clearances. In such cases, a heated thermal fluid can be provided by reclaiming residual exhaust energy from a heat recovery steam generator. At any condition where improved performance is desired, such as at base load operation, the vane carrier can be cooled to minimize compressor clearances. A cooled thermal fluid can be bleed air from an upstream portion of the compressor, water-cooled high pressure bleed air from a downstream portion of the compressor, or feed water from the bottoming cycle in a combined cycle engine.

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Orlando, FL, United States of America

Adam Matthew Foust