Doosan Heavy Industries & Construction Co., Ltd

Siemens Energy, Inc.

Siemens Aktiengesellschaft

Kevin J Spence

Charalambos Polyzopoulos

Stephen A Ramier

Juan Enrique Portillo Bilbao

Richard L Thackway

Daniel W Garan

David P Holzapfel

Vladimir Belyaev

Vinayak V Barve

Rajesh Rajaram

Danning You

Esam Abu-Irshaid

Joseph Scott Markovitz

Khalil Farid Abou-Jaoude

Blake R Cotten

Stephan J Storms

Michael Brody

Urmi B Dave

Vaidyanathan Krishnan

Michael C Escandon

A combustor can include: a combustion chamber; a cap covering the combustion chamber; a first swirler inlet cup passing through the cap and having a first length and a first bell mouth; a second swirler inlet cup passing through the cap and having a second length and a second bell mouth; and a third swirler inlet cup passing through the cap and having a third length and a third bell mouth, wherein the first length is different from the third length, and wherein the first bell mouth is different from the third bell mouth. The first, second, and third swirler inlet cups can have different diameters, respectively.

Device to correct flow non-uniformity within a combustion system

A transition piece can include: an inner transition piece providing a gas channel; a plurality of cooling rings disposed on the inner transition piece; a plurality of film holes formed on the inner transition piece; and a plurality of impingement holes formed on the plurality of cooling rings, wherein the plurality of film holes are arranged to correspond to the plurality of cooling rings. Each of the plurality of cooling rings includes a cavity such that the plurality of film holes connect the cavity to the gas channel and the plurality of impingement holes connect the cavity to an outside of the inner transition piece.

Transition piece having cooling rings

An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and NOx emissions, and eliminated impingement of cooling water on walls of the combustor. A new combustor includes a plate-fin design which provides improved cooling, while the combustor also makes more efficient use of available cooling air and has an improved component life. A new transition component has a smoother shape which reduces stagnation of combustion gas flow and impingement of combustion gas on transition component walls, improved materials and localized thickness increases for better durability, and improved cooling features for more efficient usage of cooling air.

W501D5/D5A DF42 combustion system

A flow conditioner in a combustor of a gas turbine comprises a body and a flow conditioning portion configured to be placed in an air path providing air flow to a combustion chamber, the flow conditioning portion including a plurality of holes tuned to a damping frequency to dampen a pressure fluctuation caused by combustion dynamics from the combustion chamber.

Flow conditioner to reduce combustion dynamics in a combustion system

A combustion system can include: a liner defining a combustion chamber; a casing covering the combustion chamber; a first tube disposed in the liner; a machined union disposed inside the casing and connected to the first tube; a second tube passing through the casing and connected to the machined union; a sensor housing disposed outside the casing and connected to the second tube; and an infinite tube connected to the sensor housing.

Impedance tube having a machined union

A cross-flame duct for connecting adjacent combustors together in a gas turbine to guard against flameout conditions within the combustors, whereby the cross-flame duct includes first and second ducts forming a slip joint to prevent stress from developing within the cross-flame duct is disclosed. The cross-flame duct remains flexible during turbine operation due to the slip joint, thereby preventing damaging thermal and mechanical stresses from developing within the cross-flame duct and enhancing the useful life of the cross-flame duct and associated components. The first and second ducts include cooling chambers positioned between outer sleeves and inner housings and maintained with one or more standoffs to reduce thermal stress and gradients or prevent material loss due to overheating or burning. The cooling chambers are supplied with cooling fluids via one or more fluid ports extending through the outer sleeves enabling air to flow through the cooling chambers and into the combustors.

Cross ignition flame duct

A gas turbine engine combustor basket has nested outer and inner liners that are separated by a gap at their respective distal downstream ends for passage of cooling air between the liners. Radially inwardly projecting platefins formed on an inner circumferential surface of the outer liner maintain the cooling air passage gap. In some embodiments effusion cooling through holes are formed in the inner liner outer circumference, oriented in the air passage gap between the fins, so that cooling air passes through the effusion holes into the cooling air passage gap.

Gas turbine engine combustor basket with inverted platefins

Growing community of inventors

Winter Springs, FL, United States of America

Kevin J Spence