General Electric Company

Ge Infrastructure Technology, LLC

Nicholas Magina

Fei Han

Kwanwoo Kim

Owen Graham

Sharath Nagaraja

Michael John Hughes

Andrew Joseph Wickersham

Timothy Healy

Ramal Janith Samarasinghe

Arin Cross

A gas turbine engine includes a compressor section for compressing air flowing therethrough to provide a compressed air flow, a combustor including a combustion chamber, the combustion chamber configured to combust a mixture of a fuel flow and the compressed air flow to generate combustion products, and a turbine section having at least one turbine driven by the combustion products. The gas turbine engine includes a multicavity damper in fluid communication with the combustion chamber to dampen an instability generated in the combustion chamber by the combustion products. The multicavity damper has a plurality of cavity volumes and the length of each cavity volume is different.

Turbine engine having a multicavity damper

A method for detecting flameholding in at least one combustor of a turbine engine includes measuring dynamic pressure data of the at least one combustor of the turbine engine; converting the dynamic pressure data to frequency-domain spectral energy amplitudes for the dynamic pressure data; and comparing the spectral energy amplitudes against a dynamic amplitude threshold value to determine whether the amplitudes exceed the threshold minimum amplitude value, wherein exceeding the dynamic amplitude threshold indicates a flameholding occurrence.

Methods and systems to detect flameholding in turbine assemblies

The systems and methods described herein relate to a dome of a gas turbine assembly configured to suppress pressure pulsations. The systems and methods provide a dome having an aperture configured to surround an injector assembly of a combustor. The dome having a front panel extending radially from the aperture. The systems and methods couple a first cavity to the front panel. The first cavity includes a series of ducts. A first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.

Gas turbine assemblies and methods

An inline fluid damper device comprises a flow-through conduit configured to be placed inside a larger exterior conduit through which a fluid flows. The flow-through conduit is elongated and extending around a center axis. The damper device also comprising an indirect flow conduit coupled with the flow-through conduit. The indirect flow conduit is also configured to be placed inside the larger exterior conduit. The flow-through conduit and the indirect flow conduit are configured to dampen one or more flow fluctuations or pressure fluctuations in the fluid flowing in the larger exterior conduit by dividing the fluid into a first portion that flows along the center axis through the flow-through conduit and a second portion that concurrently flows outside of the flow-through conduit along the center axis and along a different direction.

Inline fluid damper device

Growing community of inventors

Niskayuna, NY, United States of America

Nicholas Magina