Florida Turbine Technologies, Inc.

Siemens Energy, Inc.

Siemens Power Generation, Inc.

United Technologies Corporation

Siemens Westinghouse Power Corporation

United States of America As Represented by the Secretary of the Air Force

Other

Siemens Aktiengesellschaft

Alstom (switzerland) Ltd

Alstom Technology Limited

S&j Design, LLC

George P Liang

Zhihong Gao

Brian J Wessell

John F Soileau

Nan Jiang

Xubin Gu

Joseph B Gilliam

David James Wiebe

Alexander Ralph Beeck

Thomas A Auxier

John Joseph Marra

John E Ryznic

Todd A Ebert

Curtis C Cowan

Gary J Dillard

Hans R Przirembel

Walter Marussich

William J Yeager

Anthony J Malandra

Edward C Hill

George W Beal

Christopher Charles Williams

J Tyson Balkcum, Iii

Ralph Warren Mathews

Timothy J Remley

A cooling system for a turbine airfoil of a gas turbine engine is disclosed, whereby the cooling system includes spanwise extending midflow blockers positioned within one or more cooling channels to maintain an internal through flow channel Mach number. One or more cooling channels may have a larger cross-sectional area proximate to an outer end of the airfoil than at an inner end. One or more cooling channels include midflow blockers extending into the cooling channel. In at least one embodiment, the midflow blocker may extend radially inward from the outer end of the airfoil. The midflow blocker may limit movement of cooling fluid from the pressure side to the suction side or vice versa. The midflow blocker may increase in size moving radially outward as the cross-sectional area of the cooling channel increases as well. Such configuration keeps the internal through flow channel Mach number within design limits.

Turbine airfoil cooling system with spanwise extending fins

A cooling system () for a turbine airfoil () of a gas turbine engine, wherein the airfoil () has a bowed configuration is disclosed. The airfoil () may be configured such that the leading edge () or trailing edge (), or both, may have midsections that are positioned further upstream than outer ends of the leading and trailing edges (). One or more cooling channels () of the cooling system () may have a larger cross-sectional area proximate to an end of the airfoil () than at a midspan location. One or more cooling channels () may have one or more corner blockers () that extend chordwise in the cooling channel () and extend from a corner () toward a centerline axis (), thereby reducing a cross-sectional area of the cooling channel (). The corner blockers () may be positioned within the cooling system () to maintain the flow of cooling fluids through the airfoil () within desired design parameters.

Turbine airfoil cooling system for bow vane

A turbine rotor blade with a main serpentine flow cooling circuit extending from a leading edge region to a trailing edge region, and a mini serpentine flow cooling circuit in the blade tip region connected between the first and second legs of the main serpentine flow circuit. Exit slots in the trailing edge region are connected to the last leg of the main serpentine flow circuit and to the mini serpentine flow circuit to provide cooling for the trailing edge region.

Turbine rotor blade with tip cooling

A trip strip having a saw-tooth configuration that has application for cooling flow channels in a blade of a gas turbine engine. The saw-tooth configuration is defined by trip strip sections positioned end-to-end, where a leading edge of a trip strip section has a lower height than a trailing end of the trip strip section, and where the next trip strip section having the lower height leading edge disrupts the vortex created by the preceding trip strip section so that its size is reduced.

Saw teeth turbulator for turbine airfoil cooling passage

An air cooled turbine blade with a trailing edge cooling circuit that is formed by casting the airfoil with a pressure side trailing edge lip being oversized, and then machining away material from the pressure side wall to leave a pressure side bleed slot with a smaller (t/s) ratio than can be formed by casting alone. In another embodiment, the airfoil is cast with a trailing edge exit hole, and then the material on the pressure side wall in the trailing edge region is machined away to leave a pressure side bleed slot instead of an exit hole.

Turbine airfoil with pressure side trailing edge cooling slots

A micro-circuit cooling module for providing endwall cooling for a vane assembly in a gas turbine engine. The micro-circuit cooling module includes an outer perimeter rail, an upper plate and a lower plate defining a mixing chamber therein. A first plurality of spaced apart strip elements extend along a first direction in an upper channel of the mixing chamber, and a second plurality of strip elements extend along a second direction opposite to the first direction in a lower channel of the mixing chamber so that the first plurality of strip elements and the second plurality of strip elements form a criss-cross configuration. Air enters the module through metering holes in the lower plate and flows through the mixing chamber across the criss-cross elements in a turbulent manner and exits the module through slots in the upper plate.

Turbine endwall with micro-circuit cooling

A turbine blade with a plurality of rows of micro sized near wall cooling channels formed within an outer side of the airfoil wall to produce near wall cooling of the hot surface of the airfoil. The near wall cooling channels extend around the entire airfoil surface from the trailing edge to the leading edge regions and are formed using a metal printing process. Each row of near wall cooling channels discharges into a trench that opens onto the blade tip to provide a seal against hot gas leakage across the blade tips.

Turbine blade with micro sized near wall cooling channels

A film cooling hole for an air cooled turbine airfoil, where the film cooling hole includes a first expansion section with expansion only on the downstream wall and a second expansion section with expansion on the downstream wall and the two side walls. No expansion is formed on the upstream walls on the first and second expansion sections.

Turbine airfoil with film cooling hole

A large span industrial engine turbine rotor blade with a radial extending cooling air passage having a series of turbulence air mixers along the passage, where the turbulence mixers each have an inlet end and a curved and tapered surface such that cooling air is drawn into the inlet end of the mixer and then discharged from the curved and tapered surface into a middle of the passage. The cooling air flows through the passage along a series of these turbulence mixers from one mixer to another mixer along the spanwise length of the passage.

Turbine blade with radial cooling passage having continuous discrete turbulence air mixers

An industrial engine turbine stator vane with a three-pass aft flowing serpentine cooling circuit and turn channels formed outside of the endwalls that connect adjacent legs of the serpentine flow circuit. A ceramic core used to cast the vane includes dual print-outs extending from the turn channel forming pieces that provide a more rigid core structure to prevent core shift or movement during casting. The dual core print-outs form purge air holes for the rim cavity that is then covered with cover plates if purge air holes are not required.

Industrial turbine stator vane

A turbine rotor blade with a serpentine flow cooling circuit, especially a blade with a wide open tip turn, where the tip turn includes a main rib separating the two legs that are connected to the tip turn and include a bleed cooling air hole with a mini rib formed along side the main rib in the downstream leg from the tip turn in which bleed cooling air from the upstream leg flows through the hole and is impinged onto the mini rib. The bleed cooling air not only provides additional cooling for the tip turn region of the blade but eliminates the separation and recirculation issues creates in tip turns of the prior art. The bleed cooling air hole and mini rib can also be used in the root turn.

Turbine blade with serpentine flow cooling

An air cooled turbine rotor blade with a leading edge region cooling circuit having pressure and suction side feed channels separated by a rib, where the feed channels are connected to metering and diffusion cooling channels formed in the pressure and suction side walls and the middle rib that discharge into three rows of exit slots on the leading edge of the blade. The trailing edge region cooling circuit includes rows of serpentine flow circuits each having an impingement channel along a suction side and a return channel in a middle that opens into metering and diffusion channels on the pressure side that discharges into exit slots on the pressure side of the trailing edge region. The middle of the blade is cooled with a multiple pass aft flowing serpentine flow circuit with metering and diffusion film cooling slots.

Turbine rotor blade with super cooling

An turbine stator vane for an industrial engine, the vane having a serpentine flow cooling circuit with a first leg located along a leading edge of the vane airfoil and a partition rib separating the first leg from a second leg. A root turn channel connects the first leg to the second leg. A lower end of the partition rib includes a guide vane that directs cooling air from an aft section of the first leg toward a bleed hole for purging an ISSH. A plurality of turning guide ribs located in the aft section of the first leg also directs the cooling air toward the bleed hole.

Turbine stator vane with root turn purge air hole

An air cooled turbine blade with a leading edge region cooling circuit that includes a row of vortex chambers connected to a cooling air supply cavity, with each vortex chamber connected to a showerhead arrangement of metering and curved diffusion holes that meter and diffuse cooling air prior to discharge onto the blade surface. Thin metering slots supply cooling air to the vortex chambers to promote a vortex flow. The vortex chambers and metering and curved diffusion holes are formed from a metal printing process that cannot be formed using a ceramic core with an investment casting process.

Turbine airfoil with leading edge cooling

A turbine blade with a leading edge region of the airfoil having rows of film cooling slots each connected by one or more metering holes to a cooling air impingement cavity, where the film slots have both a convergent and a divergent shape. The side walls converge while the top and bottom walls diverge within each slot and form a very narrow but tall slot opening on the leading edge surface of the blade.

Growing community of inventors

Palm City, FL, United States of America

George P Liang