General Electric Company

Robert Jacek Zreda

Daniel Tomasz Ożga

Robert Jamiolkowski

Deepesh Dinesh Nanda

Eric Yves Bracquemart

Wiktor Jan Wojciechowski

Robert Jamiołkowski

Tomasz Waldemar Biwanski

Deepesh D Nanda

A diffuser for a turbine engine includes a first wall that extends circumferentially about a centerline axis of the turbine engine. The diffuser also includes a second wall that extends circumferentially about the centerline axis. At least a portion of the second wall is positioned radially outwardly from at least a portion of the first wall. A flow path is defined by the first wall and the second wall. The flow path extends from an inlet configured to receive an axial flow of a fluid, to a circumferentially extending outlet configured to emit the fluid in a substantially radial direction. The outlet extends asymmetrically about the centerline axis.

Diffuser for a turbine engine and method of forming same

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 diffuser configured to receive exhaust gas from a turbine. The diffuser includes an outer barrel, an inner barrel, a seal interface, an outer aft plate, an inner aft plate, and poles. An upstream end of the outer barrel includes an upstream lip interfacing with a downstream lip of an outer wall of the turbine outlet, forming a lap joint. The outer barrel includes a plurality of axial segments disposed between the upstream end of the outer barrel and the outer aft plate, and the axial segments. The inner barrel includes a plurality of axial segments disposed between an upstream end of the inner barrel and the seal interface. The seal interface includes a groove configured to receive the inner aft plate. The poles are spaced about the turbine axis and couple an end of the outer aft plate to an end of the inner aft plate.

System and method for 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.

System of supporting turbine diffuser outlet

A valve system is provided including a valve seat, an outlet passage and a stop valve. The valve seat has a crenulated portion. The crenulated portion has an annular recess and a plurality of teeth that are separated by a plurality of circumferential gaps. At least one of the teeth has an angled surface that borders between one of the plurality of circumferential gaps and the respective one of the plurality of teeth. The angled surface is oriented at an angle with respect to an axis that extends radially outwardly from a central axis of the valve seat. The outlet passage is located downstream of the valve seat for directing flow out of the valve assembly. The stop valve is located within the annular recess of the crenulated portion.

Growing community of inventors

Warsaw, Poland

Robert Jacek Zreda