Siemens Energy Global Gmbh & Co. Kg

Siemens Energy, Inc.

Siemens Aktiengesellschaft

Ali Akturk

Jose L Rodriguez

Krishan Mohan

David Monk

John A Orosa

Matthew D Montgomery

David L Wasdell

Marco Claudio Pio Brunelli

Andrew Miller

Taylor Hynds

Fuad Ismayilov

Ardit Bitincka

A waste heat recovery systemis provided to (i) capture waste heat, such as from or within an exhaust pipeof a tractor-trailer, (ii) extract a thermal heat value from the waste heat, (iii) convert the thermal heat value into electricity, and (iv) route the electricity to an electricity sink, such as a tractor-trailerTransport Refrigeration Unit (TRU).

Waste heat recovery system

A turbine blade tip includes a tip cap disposed over a blade airfoil and having a pressure side edge and a suction side edge. A notch is formed by a radially inward step adjacent to the suction side edge of the tip cap. The notch is defined by a radially extending step wall and a radially outward facing land. The step wall extends radially inward from the suction side edge of the tip cap to the land, whereby the land is positioned radially inward in relation to a radially outer surface of the tip cap. The notch extends along at least a portion of the suction sidewall in a direction from the leading edge to the trailing edge. In a further aspect, a method is provided for servicing a blade that includes machining a suction side notch as described above.

Turbine blade and corresponding servicing method

A turbine blade includes a tip cap disposed over an outer wall of a blade airfoil. A trench is defined on a radially outer side of the tip cap facing a hot gas path fluid. The trench is formed by a trench floor flanked on laterally opposite sides by first and second trench side faces such that the trench floor is located radially inwardly in relation to a radially outer surface of the tip cap. The trench extends from a trench inlet located at or proximal to an airfoil leading edge to a trench outlet located at or proximal to an airfoil trailing edge. The trench is configured to entrain a tip leakage flow from the trench inlet to the trench outlet.

Turbine blade with tip trench

An impingement cooling system for a gas turbine engine includes an initial impingement surface () with a centrally located opening (). A plurality of channels () and plurality of sub-channels () extends radially outward from the opening () and are formed by a plurality of fixtures () and plurality of sub-fixtures () that each separates each adjacent channel () and sub-channel () respectively. The plurality of fixtures () and plurality of sub-fixtures () each have a rounded upstream end () in a plane parallel relative to the initial impingement surface (). The plurality of fixtures () and the plurality of sub-fixtures () each have a concave shape along a middle portion () of the fixture () and sub-fixture () along an axis perpendicular to the initial impingement surface (). The plurality of channels () is divided into the plurality of sub-channels () extending radially outward of an inlet of each channel () from a stagnation point () created in the channel at an upstream end () of the sub-fixture ().

Impingement cooling features for gas turbines

An arrangement to minimize vibrations in a gas turbine exhaust diffuser is provided. The arrangement includes a projection coupled to an inner cylindrical surface or the outer cylindrical surface of a fluid flow path of the gas turbine exhaust diffuser. The projection minimizes pressure oscillations in the gas turbine exhaust diffuser such that an unsteadiness of the fluid flow surrounding the second tangential strut is reduced. A method to minimize pressure oscillations in a gas turbine diffuser is also provided.

Gas turbine diffuser outer diameter and inner diameter wall strips for turbine exhaust manifold pressure oscillation reduction

An arrangement to control vibrations in a gas turbine exhaust diffuser is provided. The arrangement includes a protrusion coupled to a turbine exhaust cylinder strut for controlling shock induced oscillations in a gas turbine diffuser. The controlled shock induced oscillations minimize pressure fluctuations in the gas turbine exhaust diffuser such that an unsteadiness of the fluid flow surrounding the turbine exhaust cylinder strut is reduced. A method to fluid flow induced vibrations in a gas turbine diffuser is also provided.

Growing community of inventors

Oviedo, FL, United States of America

Ali Akturk