General Electric Company

Deepesh Dinesh Nanda

Rohit Chouhan

Daniel Tomasz Ożga

Robert Jacek Zreda

Santhosh Kumar Vijayan

Rohit Pruthi

Eric Yves Bracquemart

Craig Allen Bielek

Gunnar Leif Siden

Joseph Anthony Cotroneo

Robert Jamiolkowski

Manjunath Bangalore Chengappa

Tomasz Jendrzejewski

Chengappa Manjunath

Robert Jamiołkowski

Soumyik Kumar Bhaumik

Adam Wisniewski

An exhaust device for a combined cycle power plant, includes a diffuser and a plenum. The diffuser includes a first wall, a second wall, a diffuser inlet, a diffuser outlet, and a diffuser flow path. The first and second walls extend circumferentially about a centerline axis of the exhaust device. The second wall is spaced from the first wall. The diffuser flow path is defined between the first and second walls, and extends from the diffuser inlet to outlet. The plenum includes an inlet wall portion and a non-circular plenum outlet, where the inlet wall portion is coupled to the diffuser outlet. The non-circular plenum outlet is spaced from the diffuser outlet along an axial direction of the exhaust device.

Exhaust device and an associated method thereof

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

The present disclosure provides an exhaust diffuser for a gas turbine engine. The exhaust diffuser may include a hub, a casing, and a strut extending between the hub and the casing. The hub may include an angled configuration about the strut and a substantially flat configuration downstream of the angled configuration.

Exhaust diffuser

An exhaust gas diffuser () including: a radially-outer peripheral casing (); a hub () located within said radially-outer peripheral casing and coaxial with a center axis () of the casing; main struts () located at circumferentially-spaced locations about the hub and extending radially-outwardly to the radially outer peripheral casing; and small struts () located at circumferentially-spaced locations between the main struts; wherein the main struts and small struts have substantially parallel longitudinal chord lines and each of the small struts have a cross-sectional area smaller than a cross-sectional area of the main struts. An exhaust gas diffuser including: a radially-outer peripheral casing; a hub located within said radially-outer peripheral casing and coaxial with a center axis of the casing; main struts located at circumferentially-spaced locations about the hub and extending radially-outwardly to the radially outer peripheral casing; and small struts located at circumferentially-spaced locations between the main struts; wherein the main struts and small struts have substantially parallel longitudinal chord lines and each of the small struts have a cross-sectional area smaller than a cross-sectional area of the main struts.

Exhaust gas diffuser with main struts and small struts

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 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

Methods, systems, and apparatuses for high efficiency exhaust duct flow path. In an embodiment, an exhaust duct flow path may be created by calculating the efficiency of an exhaust duct flow path with an initial measurement. The initial measurement may be changed and the efficiency analyzed. Then the efficiency of the exhaust duct flow path with the changed measurement may be compared to the efficiency of the exhaust duct flow path with the initial measurement.

Method, process, and system for high efficiency gas turbine exhaust duct flow-path

A system and method for integrating sections of a turbine are provided. In one system, a turbine includes a last stage bucket section with a first annular outer wall that is angled with respect to a centerline of the turbine at a first angle average. The turbine also includes a diffuser section having a second annular outer wall that is angled with respect to the centerline of the turbine at a second angle average for improving radial swirl. The first angle average is greater than the second angle average.

System and method for integrating sections of a turbine

A diffuser assembly is provided herein. In certain embodiments, the diffuser assembly may include an outer boundary member and an inner boundary member, with the inner boundary member being positioned radially inward of the outer boundary member. The diffuser assembly also may include an exhaust flow path defined between the outer boundary member and the inner boundary member. Further, the diffuser assembly may include at least one flow deflecting member operatively attached to the outer boundary member. The flow deflecting member may be adjustable about the outer boundary member to produce a substantially uniform velocity distribution within the exhaust flow path.

Diffuser assemblies having at least one adjustable flow deflecting member

A system includes multiple blades coupled to a rotor, a stationary shroud disposed about the multiple blades, and a clearance between the stationary shroud and each blade end of the multiple blades, wherein the clearance is configured to enable over tip leakage flow. The system also includes a diffuser section that includes an outer wall defining an expanding flow path downstream from the multiple blades. The outer wall includes a first wall portion having a first angle relative to a rotational axis of the multiple blades, and the clearance is configured to enable an increase in the first angle by maintaining the boundary layer along the outer wall with the over tip leakage flow.

Turbine exhaust diffusion system and method

In accordance with one embodiment, a system includes a turbine engine including an axial-radial diffuser section disposed about a first longitudinal axis downstream in an exhaust flow path from a turbine section. The system also includes an exhaust plenum including a first plenum portion disposed about the axial-radial diffuser section, wherein the first plenum portion includes a curved wall portion that diverges away from a circumference of the axial-radial diffuser section. The exhaust plenum also includes a second plenum portion extending away from the first plenum portion downstream along a second longitudinal axis of the exhaust plenum approximately crosswise to the first longitudinal axis.

Turbine exhaust plenum

An apparatus is provided and includes a plenum into which a fluid is exhausted, the plenum including a wall toward which the exhausted fluid is directed, the wall including first sections, second sections interposed between the first sections and a flow splitter interposed between the second sections, and a plane of the second sections being recessed from a plane of the first sections and the flow splitter protruding from the plane of the second sections.

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Bengaluru, India

Deepesh Dinesh Nanda