Siemens Energy, Inc.

Acudyne Incorporated

Jody W Wilson

Richard Colin Charron

Raymond Scott Nordlund

Adam J Weaver

Jay Alan Morrison

David Allen Little

Matthew D Montgomery

Hubertus Edward Paprotna

Daniel J Pierce

Eduardo E Bancalari

Ernie B Campbell

Darren T Engle

Joseph Fadok

Adam Weaver

Raymond S Nordlund

Eduardo Bancalari

A compressor-less micro gas turbine has a compressed working medium container for maintaining a gas turbine under pressure. A combustion chamber is in fluid communication with the compressed gas container for receiving a gas from the gas container and heating the gas within the combustion chamber to create an expanded gas. A heater heats the combustion chamber to expand the working gas therein. A turbine in fluid communication with the combustion chamber for receiving the expanded gas. The expanded gas drives the turbine. A generator is operatively coupled to the turbine. The turbine provides a mechanical input to the generator causing the generator to produce electricity.

Compressor-less micro gas turbine power generating system

An arrangement () for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement () including a plurality of interconnected integrated exit piece (IEP) sections () defining an annular chamber () oriented concentric to a gas turbine engine longitudinal axis () upstream of the turbine first stage blade section. Each respective IEP () includes a first flow path section () receiving and fully bounding a first flow from a respective can annular combustor along a respective common axis () there between, and delivering a partially bounded first flow to a downstream adjacent IEP section (). Each respective IEP further includes a second flow path section () receiving a partially bounded second flow from an upstream adjacent IEP () and delivering at least part of the second flow to the turbine first stage blade section.

Assembly for directing combustion gas

An arrangement for delivering gasses from can combustors of a can annular gas turbine combustion engine to a turbine first stage section including a first row of turbine blades, the arrangement including a flow-directing structure for each combustor, wherein each flow-directing structure includes a straight path and an annular chamber end, wherein the annular chamber ends together define an annular chamber for delivering the gas flow to the turbine first stage section, wherein gasses flow from respective combustors, through respective straight paths, and into the annular chamber as respective straight gas flows, and wherein the annular chamber is configured to unite the respective straight gas flows along respective shear planes to form a singular annular gas flow, and wherein the annular chamber is configured to impart circumferential motion to the singular annular gas flow before the singular annular gas flow exits the annular chamber to the first row of blades.

Modular transvane assembly

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 cover assembly disposed about a rotor in a gas turbine engine. The cover assembly comprises a first cover, a second cover, and securing structure. The first cover is disposed about the rotor and comprises a forward end and an opposed aft end. The first cover is associated with a case mounting structure that is fixed to an engine casing. The second cover is disposed about the rotor and comprises a forward end and an opposed aft end. At least a portion of the first cover is disposed radially outwardly from the second cover. The securing structure couples the first cover to the second cover and permits relative radial movement between the first and second covers.

Cover assembly for gas turbine engine rotor

A transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine has an internal passage from an inlet to an outlet that is offset from the inlet in the longitudinal, radial and tangential directions. The offset outlet and the curved internal passage discharge the gas flow toward the first stage blade array at an angle in the tangential direction relative to the longitudinal direction. This angled discharge can be presented directly to the blades, thus avoiding the need for first stage vanes and the associated costs and complexity.

Combustion transition duct providing stage 1 tangential turning for turbine engines

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.

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Winter Springs, FL, United States of America

Jody W Wilson