Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Siemens Power Generation, Inc.

Siemens Aktiengesellschaft

Clifford E Johnson

Samer P Wasif

Robert James Bland

Domenico Gambacorta

David Allen Little

Werner Krebs

Matthias Hase

Weidong Cai

Michael Huth

Rajesh Rajaram

Wojciech Dyszkiewicz

Krishna C Miduturi

Daniel Cassar

Joachim Lepers

Mark Seifarth

Thomas Primke

Yohannes Ghermay

Ben Karanja

Sachin S Terdalkar Terdalkar

Domenlco Gambacorta

A system effective for dual utilization of cooling fluid in a gas turbine engine is provided. A cooling annulus is subject to a hot-temperature combustion flow received from a combustor basket and includes a liner including a feed channel to receive cooling fluid. A feed manifold is in fluid communication with feed channel to feed cooling fluid to a plurality of conduits in fluid communication with a plurality of exit orifices that is in fluid communication with a plurality of resonators. A distributor manifold includes a plurality of manifold sectors in fluid communication with a plurality of conduits arranged to convey cooling fluid. Some of the plurality of resonators operates with different amounts of cooling fluid. A group of the plurality of exit orifices is configured to supply an amount of cooling fluid appropriate for a resonator in fluid communication with the group of the plurality of exit orifices.

System with conduit arrangement for dual utilization of cooling fluid in a combustor section of a gas turbine engine

A method, including: operating an industrial gas turbine engine having a plurality of combustor cans arranged in an annular array, each can having burner stages and a pilot burner arrangement having a premix pilot burner and a diffusion pilot burner; operating in asymmetric combustion, wherein at least one can is a warm can where respective burners stages are off and remaining cans operate as hot cans where respective burner stages are on; and while maintaining a constant rate of fuel flow to the pilot burner arrangement of the warm can, changing fuel fractions within the pilot burner arrangement of the warm can.

Method of selective combustor control for reduced emissions

A cooling arrangement (), including: a substrate having a pocket () defined by a rib side surface () and a bottom surface (); a feature () formed in the rib side surface; and an impingement plate (). In an installed configuration () a resilience of the impingement plate enables an interference between the impingement plate and the feature that locks the impingement plate in an installed position (). An elastic compression of the impingement plate from the installed configuration eliminates the interference.

Impingement cooling arrangement having a snap-in plate

A method of transitioning from a first operating mode to a second operating in a gas turbine engine. An amount of fuel provided to a primary fuel injection system of the combustor apparatus is reduced. An amount of fuel provided to a secondary fuel/air injection system of the combustor apparatus is reduced, wherein the secondary fuel/air injection system provides fuel to a secondary combustion zone downstream from a main combustion zone. A total amount of air provided to the combustor apparatus is reduced, wherein portions of the air are provided to each of the injection systems. Upon reaching operating parameters corresponding to the second operating mode, the amount of fuel provided to the primary fuel injection system is increased, the amount of fuel provided to the secondary fuel/air injection system is reduced, and the total amount of air provided to the combustor apparatus is increased.

Operation of a combustor apparatus in a gas turbine engine

A gas turbine combustor having a Helmholtz resonator in a post-swirler homogenization zone upstream of the combustor zone. Embodiments of the present invention provide Helmholtz resonators that include cavities that occupy a remainder of a post-swirler homogenization zone, which also includes at least one flow-directing structure that passes a fuel/oxidizer mixture from a main swirler assembly into a combustion zone of a combustor. Thus, an open annular region of the combustor is converted into a multi-purpose zone that includes at least one Helmholtz resonator.

Forward-section resonator for high frequency dynamic damping

A resonator system for a turbine engine can improve acoustic performance and cooling effectiveness. During engine operation, a combustor liner exhibits alternating hot and cold regions in the circumferential direction corresponding to the non-uniform temperature distribution of the combustion flame. Accordingly, high flow resonators are formed with the liner in substantial alignment with the hot regions of the fluid flow within the liner, and low flow resonators are formed with the liner in substantial alignment with cold regions of the fluid flow within the liner. As a result, appropriate amounts of cooling can be provided to the liner so that cooling air usage is optimized. Alternatively or in addition, the liner can include two or more rows of resonators, which can provide an enhanced acoustic damping response. The resonators in the first row can be aligned with or offset from the resonators in the second row.

Flow control through a resonator system of gas turbine combustor

Embodiments of the present invention provide resonators () that have lateral walls () disposed at non-square angles relative to the liner's longitudinal (and flow-based) axis () such that a film cooling of substantial portions of an intervening strip () is provided from apertures (A,B,) in a resonator box () adjacent and upstream from the intervening strip (). This film cooling also cools weld seams () along the lateral walls () of the resonator boxes (). In various embodiments the lateral wall angles are such that film cooling may be provided to include the most of the downstream portions of the intervening strips (). These downstream portions are closer to the combustion heat source and therefore expected to be in greater need of cooling.

Non-rectangular resonator devices providing enhanced liner cooling for combustion chamber

A combustor assembly is provided comprising a combustor casing; a liner coupled to the combustor casing; a burner assembly coupled to the combustor casing; and at least one resonator assembly. The resonator assembly comprises a resonator outer plate having at least one opening, a resonator side wall coupled to the resonator outer plate, and a resonator inner plate defined by a portion of the liner. The resonator inner plate is coupled to the resonator side wall and has at least one slot formed therein having an aspect ratio of at least 4:1.

Combustor assembly including one or more resonator assemblies and process for forming same

One or more Helmholtz-type resonators () is/are provided at the junction () of a combustor () and a combustion chamber () of a gas turbine engine (). In one embodiment, adjacent Helmholtz-type resonators (), which may be separated by respective baffles (), have different volumes that help provide for damping different undesired combustion-generated acoustic pressure waves. In some embodiments, a structural member () may be provided between adjacent Helmholtz-type resonators () at the junction. At least one of the plurality of Helmholtz-type resonators comprises one or more inlet openings (), and one or more exit openings (). Embodiments (-) are described in which Helmholtz-type resonators provided at the junction are enlarged in size using various approaches. The positioning at the junction, upstream of the space () in which combustion occurs, and providing a plurality of differently sized resonators, provides for improved flexibility and resonator damping efficiencies.

Resonator device at junction of combustor and combustion chamber

A method and system () for monitoring a health of a combustion dynamics sensing system () includes monitoring respective dynamic conditions of at least two combustor cans () of a can annular combustor () of a gas turbine engine with respective dynamic condition sensors () associated with each of the cans. The method also includes establishing a baseline relationship between the respective dynamic conditions and then identifying a variance from the baseline relationship indicative of a degraded signal quality provided by a dynamic condition sensor associated with at least one of the cans.

Monitoring health of a combustion dynamics sensing system

A method for monitoring combustion dynamics of a can annular combustor () of a gas turbine engine includes monitoring respective dynamic operating conditions of cans () of the can annular combustor with respective dynamic operating condition sensors () associated with each of the cans. The method also includes grouping the cans into two or more groups according to their respective dynamic operating conditions and identifying a sensor providing an anomalous dynamic operating condition reading for at least one of the cans. The method further includes determining a need to service the identified sensor according to the associated can's group membership.

Combustion dynamics monitoring

Aspects of the invention are directed to an acoustic resonator with improved impingement cooling effectiveness. The resonator includes a plate with an inside face and an outside face. A plurality of passages extend through the plate. The resonator includes a side wall that extends from and about the plate. A plurality of cooling tubes are attached to the resonator plate such that an inner passage of each cooling tube is in fluid communication with a respective passage in the resonator plate. The resonator can be secured to a surface of a turbine engine combustor component to define a closed cavity. The ends of the cooling tubes are spaced from the surface. Thus, a coolant can enter the passages in the plate and can be directed to the surface so as to impingement cool the surface. The cooling tubes can minimize coolant loss by dispersion in the cavity.

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Orlando, FL, United States of America

Clifford E Johnson