United Technologies Corporation

Pratt-whitney Canada Corp

Pratt & Whintey Canada

William Abdel-Messeh

Frank J Cunha

Justin D Piggush

Ian Tibbott

Michael Papple

Bryan P Dube

Ricardo Trindade

Eleanor D Kaufman

Jesse R Christophel

Raymond C Surace

Anthony P Cherolis

Jeffrey R Levine

Francisco J Cunha

Richard H Page

Daniel Herrera

Brandon W Spangler

Michael D Greenberg

Atul Kohli

Sri Sreekanth

Michael F Blair

Andrew D Milliken

Jose A Lopes

Douglas E Duke

Eric Herbst

Andrew J Lutz

Aaron T Frost

Kevin J Pallos

Kenneth J Sawyer

Jeffrey William Quick

Subhash Arora

Jeffrey W Quick

Eleanor Kaufman

A turbine airfoil comprises a wall portion, a cooling channel, a plurality of trip strips and a plurality of pedestals. The wall portion comprises a leading edge, a trailing edge, a pressure side and a suction side. The cooling channel is for receiving cooling air and extends radially through an interior of the wall portion between the pressure side and the suction side. The plurality of trip strips line the wall portion inside the cooling channel along the pressure side and the suction side. Each of the pedestals is an elongate, tapered pedestal having a curved leading edge. The plurality of pedestals is interposed within the trip strips and connects the pressure side with the suction side.

Cooling system for turbine airfoil including ice-cream-cone-shaped pedestals

A turbine engine component has an airfoil portion having a leading edge, a suction side, and a pressure side and a radial flow leading edge cavity through which a cooling fluid flows for cooling the leading edge. The turbine engine component further has a first set of trip strips and a second set of trip strips which meet at the leading edge nose portion of the leading edge cavity to form a plurality of chevron shaped trip strips and for generating a vortex in the leading edge cavity which impinges on the nose portion of the leading edge cavity and enhances convective heat transfer.

Leading edge cooling using chevron trip strips

An airfoil suitable for use in a gas turbine engine having at least one feed passage at least in part defined along a feed axis which is at least perpendicular to a cavity axis to reduce dirt ingestion into a trailing edge passage.

Coolable airfoil trailing edge passage

A turbine engine airfoil includes an airfoil structure having an exterior surface providing a leading edge. A radially extending first cooling passage is arranged near the leading edge and includes first and second portions. The first portion extends to the exterior surface and forms a radially extending trench in the leading edge. The second portion is in fluid communication with a second cooling passage. In one example, the second cooling passage extends radially, and the first cooling passage wraps around a portion of the second cooling passage from a pressure side to a suction side between the second cooling passage and the exterior surface. In the example, the first portion is arranged between the pressure and suction sides. In one example, the first cooling passage is formed by arranging a core in an airfoil mold. The trench is formed by the core in one example.

Airfoil with wrapped leading edge cooling passage

A turbine component has an airfoil portion with at least one central core element, a pressure side wall, and a suction side wall. The airfoil portion also has a serpentine cooling passageway in at least one of the walls. In a preferred embodiment, the airfoil portion has a serpentine cooling passageway in both of the pressure and suction side walls. A refractory metal core for forming the serpentine cooling passageway(s) is also described.

Peripheral microcircuit serpentine cooling for turbine airfoils

A passageway is provided through which a cooling fluid flows in a first direction. The passageway has a plurality of trip strips positioned within the passageway. Adjacent one of the trip strips are oriented to converge towards each other at a first end to form an apex portion and to form a region in which turbulence is created. The apex portion is oriented at an angle with respect to the first direction.

Advanced turbulator arrangements for microcircuits

A turbine engine component having improved cooling is provided. The turbine engine component includes an airfoil portion having a leading edge, a trailing edge, a pressure side, a suction side, a root, and a tip, and at least one cooling circuit in a wall of the airfoil portion. The at least one cooling circuit has at least one passageway extending between the root and the tip. The at least one passageway has an aspect ratio of no greater than 2:1, and preferably substantially unity.

Microcircuit cooling with an aspect ratio of unity

A turbine engine airfoil includes an airfoil structure having an exterior surface and an end portion. A cooling passage extends a length radially within the structure in a direction toward the end portion. The cooling passage provides a convection surface along the length adjacent to the exterior surface. The convection surface includes a generally uniform width along the length. The cooling passage has generally decreasing cross-sectional areas along the length in the direction.

Airfoil with tapered radial cooling passage

Cooled airfoils and gas turbine engine systems involving such airfoils are provided. In this regard, a representative cooled airfoil includes: an exterior surface defining a leading edge, a trailing edge, a suction side and a pressure side; an interior surface defining an interior cavity; trenches in the exterior surface oriented spanwise along the leading edge; and cooling holes communicating between the interior cavity and the trenches such that cooling air provided to the interior cavity flows from the interior cavity though the cooling holes into the trenches, the cooling holes having exterior apertures located in the trenches and interior apertures located at the interior surface.

Cooled airfoils and gas turbine engine systems involving such airfoils

A turbine component includes an aft cooling circuit that extends between a turbine midsection and a turbine trailing end. The aft cooling circuit includes a trailing end section proximate the trailing end, a first interior section proximate the turbine midsection, and a first intermediate section fluidly connected between the trailing end section and the first interior section. A forward cooling circuit of the turbine component extends between the turbine midsection and a turbine leading end. The forward cooling circuit includes a leading end section proximate the leading end, a second interior section proximate the turbine midsection, and a plurality of second intermediate sections fluidly connected between the leading end section and the second interior section. The leading end section, the second intermediate section, the first intermediate section, and the trailing end section each include a plurality of coolant discharge openings for facilitating cooling of the turbine component.

Cooling arrangement for turbine components

Systems and methods for cooling vane platforms are provided. In this regard, a representative method for cooling a vane platform includes: providing a cooling channel on a platform from which a vane airfoil extends, the cooling channel being defined by a cooling surface and a channel cover, the channel wall being spaced from the cooling surface and located such that the cooling surface is positioned between a gas flow path of the vane and the channel cover; and directing a flow of cooling air through the cooling channel such that heat is extracted from the cooling surface of the platform by the flow of cooling air.

Systems and methods for providing vane platform cooling

A turbine engine component for use in a small engine application has an airfoil portion having a root portion, a tip portion, a suction side wall, and a pressure side wall. The suction side wall and the pressure side wall have the same thickness. Still further, the turbine engine component has a platform with an internal cooling circuit.

Microcircuits for small engines

The ends of cooling air passages in turbine blades and/or vanes of a gas turbine engine are provided with turbulation promoters to enhance the cooling of such structures as inner and outer shrouds and the like to accommodate thermal loads thereon.

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Middletown, CT, United States of America

William Abdel-Messeh