General Electric Company

Robert Jamiolkowski

Robert Jacek Zreda

Daniel Tomasz Ożga

Eric Yves Bracquemart

Deepesh Dinesh Nanda

Rohit Pruthi

Srinivas Rao Pakkala

Przemyslaw Michal Jakubczak

Tomasz Jendrzejewski

Karol Leszczynski

Adam Wisniewski

Przemyslow Michal Jakubczak

Jakub Putowski

Wojciech Drozdzik

The present application provides an exhaust diffuser. The exhaust diffuser may include an outer diffuser section with a forward portion. An outer forward seal system may be positioned on the forward portion. The outer forward seal system may include a seal base removably positioned in a seal pocket.

Turbine exhaust diffuser

A turbine or turbine system includes a compressor, a combustor, a turbine section, a diffuser with a parting line between two components, and a seal along the parting line. The seal includes a protrusion, a recess, and a flexible portion between the protrusion and the recess. The flexible portion has a bent cross-section perpendicular to the parting line. An outer surface of the bent cross-section contacts an inner surface of the recess. An inner surface of the bent cross-section contacts an outer surface of the protrusion. Sealing a parting line between two parts of a diffuser in a gas turbine system includes disposing a flexible portion between a protrusion and a recess of the two parts, contacting an outer surface of the bent cross-section with an inner surface of the recess, contacting an inner surface of the bent cross-section with an outer surface of the protrusion, and pressurizing the diffuser.

Apparatus and method for sealing turbine assembly

A system includes a diffuser section comprising an outer barrel, an outer aft plate, an inner barrel, an inner aft plate, and a plurality of poles, where the outer aft plate is disposed at a downstream end of the outer barrel, the inner aft plate is disposed at a downstream end of the inner barrel, the outer barrel and the inner barrel are disposed about a turbine axis, the diffuser section receives an exhaust gas from a gas turbine, the plurality of poles is circumferentially spaced about the turbine axis, and each pole of the plurality of poles couples a downstream end of the outer aft plate to a downstream end of the inner aft plate.

System of supporting turbine diffuser

A system includes a circumferential lap joint between a downstream end of an outer wall of a turbine outlet and an upstream end of an outer barrel of a diffuser section, where the circumferential lap joint facilitates axial movement of the outer barrel relative to the outer wall, an upstream lip of the outer barrel is disposed radially within a downstream lip of the outer wall, and both the turbine outlet and the diffuser section are configured to receive an exhaust gas.

A method includes inserting axially a radially interior surface of an aft plate assembly into a circumferential groove of an inner barrel of a diffuser section of a gas turbine, where the aft plate assembly is inserted into a first circumferential orientation relative to the circumferential groove, and the circumferential groove is disposed on a radially exterior surface of the inner barrel. The method includes rotating the aft plate assembly circumferentially within the circumferential groove from the first circumferential orientation to a second circumferential orientation, where the inner barrel is configured to axially retain the aft plate assembly when the aft plate assembly is disposed in the second circumferential orientation.

System and method for diffuser AFT plate assembly

A system includes a diffuser section comprising an outer barrel, an inner barrel, a seal interface, and an aft plate, where the outer barrel and the inner barrel are disposed about a turbine axis, and the diffuser section is configured to receive an exhaust gas from a gas turbine. The seal interface is disposed at a downstream end of the inner barrel between the inner barrel and the aft plate. The seal interface includes a first circumferential groove configured to receive the aft plate, where the first circumferential groove opens in a first direction away from the turbine axis.

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Ząbki, Poland

Robert Jamiolkowski