Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Other

Adam J Weaver

Raymond Scott Nordlund

Robert H Bartley

Jody W Wilson

Mahmut Faruk Aksit

David B Allen

Daniel O Davies

Matthias Hase

Miguel Bascones

Wojciech Dyszkiewicz

James Bertoncello

Erdem Gorgun

Ali Ihsan Yurddas

Manish Kumar

Ertugrul Tolga Duran

Sadik Hazer

Joseph L Evins

Kunyuan Zhou

Markus Raben

Lashanda N Williams

Viraj Wadatkar

Khamhou Sayavong

A seal for sealing a gap in a combustion apparatus of a gas turbine between a first side and an opposite second side. The seal includes a steel strap with a flat shape and a first metal web with a flat shape attached to the steel strap on the first side and a second metal web attached to the steel strap on the second side. Thereby the seal has a seal thickness with at least the steel strap plus the first metal web plus the thickness of the second metal web, wherein the seal thickness is at most 0.2-times of width of the seal. The new seal has an Omega shape of the second metal web, which is therefore attached on both sides with a flat shaped portion to the steel strap.

Seal for combustion apparatus

A sealing arrangement in a gas turbine engine to seal a gap between first and second turbine components is provided. The sealing arrangement includes a first arcuate feather seal connected to an anchoring assembly of the sealing arrangement affixed to the first turbine component. A second arcuate feather seal is affixed to the second turbine component. The first arcuate feather seal and the second arcuate feather seal are responsive to a pressure differential that develops across the gap to form a pressure-loaded sealing joint between respective sealing surfaces of the first arcuate feather seal and the second arcuate feather seal. The sealing arrangement provides substantial design flexibility since it can reliably provide appropriate sealing functionality while enabling multiple degrees of freedom, such as to accommodate radial and/or axial displacements that can develop between the first turbine component and the second turbine component.

Sealing arrangement with pressure-loaded feather seals to seal gap between components of gas turbine engine

A transition duct support apparatus and a method to support an exit frame in a transition duct in a gas turbine engine are provided. A stiffener () may be arranged to provide support to an outer edge () of an exit frame () in a transition duct (). Stiffener () may be configured to circumferentially extend between mutually opposed corners () of the exit frame of the transition duct. A brace () may be connected to a centrally-disposed section () and may extend to support respective end portions () of the stiffener. The support apparatus is effective to provide a respective tuned level of stiffness support with respect to one or more axes of the exit frame in the transition duct. The apparatus and method may be effective for distributing mechanical stresses on the exit frame of the transition duct and/or neighboring regions in the transition duct.

Transition duct support and method to provide a tuned level of support stiffness

An adaptor for quickly, easily, and safely attaching and removing compatible tools from the end of a boom of an excavating machine.

Versatile connector for excavator tools

A transition duct () for a gas turbine engine () having improved cooling and reduced stress levels. The transition duct may be formed of two panels (() joined together with welds () disposed remote from the bent corner regions () of the panels. Cooling channels () extending longitudinally in the direction of flow of the hot combustion gas carried by the duct are formed within each panel, including the corner regions. Because the entire annular width (W) of the transition duct is cooled, the gap (G) separating adjacent ducts around the inlet to the turbine () may be reduced when compared to prior art designs. Two-panel construction with welds remote from the corner regions is facilitated by maintaining the minimum bend radius in the corners (R) and in the direction of flow (R) to be greater than in prior art designs.

Cooled transition duct for a gas turbine engine

A transition-to-turbine seal () including an upstream portion () adapted to engage a flange () of a transition (). The upstream portion () may be U-shaped in cross-sectional profile and include a primary wall () that includes a proximal section () and a distal section () relative to a hot gas path (). The proximal section () includes a plurality of recesses () which are spaced apart and separated by intervening wall (). In each recess () is provided one or more outlets () of cooling fluid holes (). The outlets () communicate via the cooling fluid holes () with a supply of compressed cooling fluid, such as compressed air that is provided from the compressor. During operation the outlets () release this fluid into the respective recesses (). The flow of cooling fluid provides for a more uniform cooling effect that includes impingement and convective cooling.

Transition-to-turbine seal apparatus and transition-to-turbine seal junction of a gas turbine engine

One embodiment of a transition-to-turbine seal () comprises a first, flattened section () adapted to be received in a peripheral axial slot () of a transition (), and a second, generally C-shaped section (). The generally C-shaped section () comprises a flattened portion () near the first, flattened section (), and a curved portion () extending to a free edge (). A fiber metal strip component () may be attached to the flattened portion () to define a first engagement surface adapted to engage an upstream side () of an outer vane seal rail (), and a second engagement surface, adjacent the free edge (), provides an opposed wear surface adapted to engage a downstream side () of the outer vane seal rail (). System embodiments also are described, in which such transition-to-turbine seal () is isolated from a hot gas path () by provision of a plurality of cooling apertures () in the transition ().

Slidable spring-loaded transition-to-turbine seal apparatus and heat-shielding system, comprising the seal, at transition/turbine junction of a gas turbine engine

Aspects of the invention relate to a system for supporting the exit end of a transition duct. The system includes a plurality of support ring segments that collectively form an annular support ring assembly. Each support ring segment can have an outer span and an inner span that are joined by a central column. Lateral openings can be defined on each side of the central column. The lateral openings of two adjacent support ring segments can cooperate to form an opening. An outlet region of a transition duct can be inserted into a respective opening and engage seals provided along the opening. The interface of adjacent ring segments occurs along an imaginary line across the outlet of the common transition duct body. Each support ring segment can be attached to the transition duct as well as to a fixed portion of the engine such as the turbine stationary support structure.

Support system for transition ducts

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Oviedo, FL, United States of America

Adam J Weaver