General Electric Company

Malath Ibrahim Arar

Jonathon Michael Hadley

David Anthony DeAngelis

Robert Russell Priestley

George Raymond Hubschmitt

Timothy Robert Kemp

James Giles Eignor

Anna Valeria Anllo

Robert Russell Priestly

A method to provide clearance control for a gas turbine having a multi-stage compressor and a turbine having turbine buckets rotating within a turbine shell, the method includes: selecting a first compressor stage from which to extract compressed air; ducting the compressed air from the first compressor stage to the turbine shell; passing the compressed air from the first compressor stage to thermally contract the turbine shell; selecting a second compressor stage from which to extract compressed air and deselecting the first compressor stage; ducting the compressed air from the second compressor stage to the turbine shell, and passing the compressed air from the second compressor stage to thermal expand the turbine shell.

Active clearance control system and method for gas turbine

A gas turbine inlet heating system is disclosed. In one embodiment, the system includes: a compressor having: an inlet bellmouth adjacent to a set of inlet guide vanes (IGVs); and an outlet fluidly connected to the inlet bellmouth; and a conduit coupled to an outlet of the compressor, the conduit including a control valve, the conduit for diverting a first portion of compressed air from the outlet of the compressor to the inlet bellmouth.

Gas turbine inlet heating system

A system for determining a shaft misalignment in a turbomachinary train having a plurality of components with serially coupled rotating shafts. A disclosed system includes a sensor affixed to a component of the turbomachinary train proximate a rotating shaft, wherein the sensor collects vibration data along an axial direction of the rotating shaft. Also provided is a frequency analyzer for generating frequency domain data from the vibration data and an analysis system for analyzing a frequency component of the frequency domain data at one times a rotational frequency of the rotating shaft to identify a misalignment between the rotating shaft and an adjacently coupled rotating shaft.

Axial vibration monitoring for detecting shaft misalignments in turbomachinary trains

A method for controlling a combustor of an engine, the combustor having a fuel to oxidant ratio, the fuel to oxidant ratio being defined as a ratio of an amount of fuel supplied to the combustor divided by an amount of oxygen in an oxidant stream supplied to the combustor includes controlling the fuel to oxidant ratio of the combustor as a function of the amount of oxygen in the oxidant stream.

Method and apparatus for gas turbine dry low NOx combustor corrected parameter control

A nitrogen compressor in an IGCC (integrated gasification, combined cycle) system provides gaseous nitrogen to be directly injected into the combustor of a gas turbine in the IGCC. The nitrogen is injected at substantially the same pressure as the output pressure from the nitrogen compressor. The compressor is controlled to adjust the output pressure of the nitrogen to match a nitrogen injection pressure for the combustor. By controlling the flow (pressure) of the nitrogen injected to a combustor of a gas turbine at the nitrogen compressor, the compressor is relieved of having to overcome the pressure loss through the nitrogen injection valves (which valves are run at or near full open throughout the operation of the nitrogen injection process), and does not need to provide nitrogen at a pressure substantially greater than the nitrogen pressure injected into the combustor.

Method for controlling nitrogen injection into gas turbine

Apparatus for controlling nitrogen injection into gas turbine

The high pressure inlet bleed heat system includes a plurality of tubes which receive heated compressed air from the compressor extraction discharge manifold. The tubes extend into the inlet duct of the compressor, are uniformly spaced one from the other and have a uniform distribution of laterally opening apertures along their lengths in registration with the apertures of next laterally adjacent tubes. The tubes are located downstream of the silencer baffles. By providing choked flow through the apertures and lateral registration of the apertures of adjacent tubes, complete mixing of the heated air with the inlet air vortices behind the silencer baffles is achieved, affording a uniform temperature distribution across the inlet duct with minimum pressure loss. The tubes are constructed to accommodate thermal expansion of the manifold receiving compressor discharge air, the manifold also being supported to accommodate thermal expansion and contraction.

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Clifton Park, NY, United States of America

Malath Ibrahim Arar