Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Anthony Waywood

Ching-Pang Lee

Jae Y Um

Steven Koester

Eric Joseph Schroeder

Zhengxiang Pu

Sin Chien Siw

Erik Johnson

Wayne J McDonald

Harry Holloman

Gerald L Hillier

Mohamed Abdullah

A turbine airfoil includes a trailing edge coolant cavity between a pressure sidewall and a suction sidewall. The trailing edge coolant cavity is positioned adjacent to and extending out to a trailing edge of the turbine airfoil. The interior includes an internal arrangement comprising an array of discrete fins formed aft of the trailing edge coolant cavity along the trailing edge.

Turbine airfoil with trailing edge features and casting core

An integrated airfoil and platform cooling system () for a turbine rotor blade () includes an inlet () located at the root () for receiving a supply of a coolant (K), and at least one cooling leg () fluidly connected to the inlet () and configured for conducting the coolant (K) in a radially outboard direction. The cooling leg () is defined at least partially by a span-wise extending internal cavity () within a blade airfoil (). An entrance of the cooling leg () comprises a flow passage () that extends radially outboard and laterally into a blade platform (), so as to direct a radially outboard flowing coolant (K) to impinge on an inner side () of a radially outer surface () of the blade platform (), before leading the coolant (K) into the cooling leg ().

Turbine rotor blade with airfoil cooling integrated with impingement platform cooling

A core structure () includes a first core element () including a leading edge section (), a tip section (), and a turn section () joining the leading edge and tip sections (). The first core element () is adapted to be used to form a leading edge cooling circuit () in a gas turbine engine airfoil (). The leading edge cooling circuit () includes a cooling fluid passage () having a leading edge portion () formed by the first core element leading edge section (), a tip portion () formed by the first core element tip section (), and a turn portion () formed by the first core element turn section (). Each of the leading edge portion (), the tip portion (), and the turn portion () of the cooling fluid passage () are formed concurrently in the airfoil () by the first core element ().

Gas turbine airfoil including integrated leading edge and tip cooling fluid passage and core structure used for forming such an airfoil

An airfoil () for a gas turbine engine in which the airfoil () includes an internal cooling system () with one or more internal cavities having an insert () contained within an aft cooling cavity () to form nearwall cooling channels having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels may be controlled via a plurality of cooling fluid flow controllers () extending from the outer wall () forming the generally hollow elongated airfoil (). The cooling fluid flow controllers () may be collected into spanwise extending rows. In at least one embodiment, the cooling fluid flow controllers () may be positioned within a pressure side nearwall cooling channel () and a suction side nearwall cooling channel () that are both in fluid communication with a trailing edge channel (). The trailing edge channel () may also include cooling fluid flow controllers () extending between the outer walls () forming the pressure and suction sides.

Internal cooling system with insert forming nearwall cooling channels in an aft cooling cavity of an airfoil usable in a gas turbine engine

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Cincinnati, OH, United States of America

Anthony Waywood