Siemens Aktiengesellschaft

Other

Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Matthew J Golsen

Gary Brian Merrill

Jose L Rodriguez

Jan H Marsh

Daniel M Joo

Wayne J McDonald

Denis Torres Gonzalez

Stephen Wright

John T Harrington

A turbine airfoil includes an airfoil body and a generally hollow flow displacement element positioned in an interior portion of the airfoil body and extending along a span-wise extent thereof. The flow displacement element defines an inactive cavity therewithin. The flow displacement element is spaced from a pressure side wall and a suction side wall of the airfoil body to respectively define a first near-wall cooling flow channel and a second near-wall cooling flow channel. The flow displacement element includes an outer surface facing the near-wall cooling flow channels and an inner surface facing the inactive cavity. The inner surface facing the inactive cavity includes features configured to influence a mass and/or stiffness of the turbine airfoil, to thereby produce a predetermined modal frequency response of the turbine airfoil.

Turbine airfoil incorporating modal frequency response tuning

An airfoil for a turbine engine includes an array of features positioned in an interior portion of the airfoil. Each feature extends from a pressure side to a suction side. The array includes multiple radial rows (A-N) of features with the features in each row (A-N) being interspaced radially to define coolant passages therebetween. The radial rows (A-N) are spaced along a forward-to-aft direction toward an airfoil trailing edge. The coolant passages of the array are fluidically interconnected to lead a pressurized coolant toward the trailing edge via a serial impingement on to the rows of features. The coolant passages are geometrically configured to bias a coolant flow therethrough toward a first side in relation to a second side of the outer wall to effect a greater cooling of the first side than the second side.

Turbine airfoil with biased trailing edge cooling arrangement

The present disclosure provides a core structure comprising a trailing edge section including a plurality of rib-forming apertures () defined by a plurality of radially-extending channel elements () and axially-extending passage elements () and a radially outer low flow framing channel element () located adjacent to a radially outer edge (). The core structure may be used for casting a gas turbine engine airfoil (). The radially outer framing channel element () comprises a plurality of notches () extending radially inwardly from the radially outer edge (). A distal portion () of the notches () overlaps in an axial direction with the rib-forming apertures () of a first axially-aligned outer row (). A radial height of at least one of a first and a second axially-extending passage element () is greater than a prevalent radial height of other axially-extending passage elements () in the core structure.

Turbine blade trailing edge with low flow framing channel

A combustor assembly () including guide vanes () located between an inner cylinder () and a flow sleeve (). Each guide vane () includes a circumferentially angled flow directing portion () adjacent to a leading edge (). The leading edge () of at least one guide vane () can be located radially inward along the longitudinal axis () relative to the leading edge () of at least one other of the guide vanes (). The length of the guide vanes () may vary, and the circumferential spacing between a first pair of the guide vanes () can be different from a spacing between a second pair of the guide vanes ().

Combustor arrangement including flow control vanes

A turbine airfoil usable in a turbine engine and having at least one cooling system with an efficient trip strip is disclosed At least a portion of the cooling system may include one or more cooling channels having one or more trip strips protruding from an inner surface forming the cooling channel. The trip strip may have improved operating characteristics including enhanced heat transfer capabilities and a substantial reduction in pressure drop typically associated with conventional trip strips In at least one embodiment, the trip strip may have a cross-sectional area with a first section of an upstream surface of the trip strip being positioned nonparallel and nonorthogonal to a surface forming the cooling system channel extending upstream from the at least one trip strip and a concave shaped downstream surface of the at least one trip strip that enables separated flow to reattach to the cooling fluid flow.

Growing community of inventors

Deltona, FL, United States of America

Matthew J Golsen