United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

United Technology Corporation

Brandon W Spangler

Dominic J Mongillo, Jr

David R Pack

Atul Kohli

Russell J Bergman

Steven Bruce Gautschi

Edwin Otero

Gina Cavallo

Tracy A Propheter-Hinckley

Ricardo Trindade

Lea Kennard Castle

Ky H Vu

John McBrien

Mark F Zelesky

James Thompson Beals

JinQuan Xu

Adam P Generale

Ryan Alan Waite

Corey D Anderson

Stephen Douglas Murray

Samuel D Draper

Jose A Lopes

Jaime G Ghigliotty Rosado

Edward F Pietraszkiewicz

Matthew A Devore

Benjamin F Hagan

Corneil S Paauwe

Benjamin Bellows

Michael G McCaffrey

Bryan P Dube

Carey J Clum

James B Hoke

Dennis M Moura

Jose R Paulino

Jeffrey S Beattie

Dustin Wayne Davis

Lane Mikal Thornton

Daniel A Snyder

Michael F Blair

Keith A Santeler

Jacob A Snyder

David J Candelori

Michael K Turkington

David J Hyland

Leonard A Bach

Scott D Hjelm

Di Wu

San Quach

Raymond C Surace

Stephen Karl Kramer

Scott D Lewis

William Abdel-Messeh

Allan N Arisi

Bret M Teller

Jeffrey J DeGray

William P Stillman

Sam David Draper

Dave J Hyland

Daniel P Preuss

Craig R McGarrah

Timothy Charles Nash

Joseph W Bridges, Jr

Anita L Tracy

Richard N Allen

John D Wiedemer

Lea Dynnette Castle

Scott W Gayman

Amanda Jean Learned

Trevor Rudy

Edward R Bareiss

Gary A Zess

Lawrence J Willey

Jaimie Schweitzer

David E Gambardella

Jaimie Taraskevich

Christopher J Lehane

Griffin D Lavine

Thomas P Dziuba

Stephen J Yea

Stephen J Yee

Kevin D Tracy

Benjamin B Simpson

Dominic Mongillo

Laurie L Burstynski

Jr Dominic J Mongillo

Benjamin D Bellows

Tracy A Propheter-Hinkley

Dominic J Mongillo Jr

Lea K Castle

Jeffrey J Degray

Jinquan Xu

Sam Draper

Stephen D Murray

Jacob B Snyder

A turbine vane includes a vane body, a baffle, and a plurality of axial divider ribs. The vane body includes a first side wall, a second side wall, and a trailing edge rib forming a cooling passage. The baffle includes a baffle body disposed within the cooling passage. The baffle body includes a first baffle side and a second baffle side. The baffle body forms an internal baffle cavity. The baffle body further forms a plurality of baffle apertures. Each axial divider rib extends between and to the second side wall and the second baffle side. The vane body, the baffle body, and the axial divider ribs form a feed cavity and one or more axial flow channels. The feed cavity is disposed between the vane body and the baffle body at least between the first side wall and the first baffle side. The axial flow channels are formed by the axial divider ribs. Each axial flow channel o is connected in fluid communication with the internal baffle cavity by one or more of the baffle apertures.

Turbine vane for a gas turbine engine

A turbine engine rotor blade is provided that has an airfoil that includes a side wall with exterior and interior wall surfaces. The airfoil includes a first wall channel that is defined by a base surface that is a portion of the side wall interior surface and first and second interior wall surfaces. A first interface surface extends between the base surface and the first interior wall surface. A second interface surface extends between the base surface and the second interior wall surface. A third interface surface extends between the first interior wall surface and the second interior wall surface. The base surface includes base surface first and second segments, and a peak interface surface extending between the base surface first and second segments. The first interface surface is disposed closer to the side wall exterior surface than both the second interface surface and the peak interface surface.

Turbine blade with cooling channels

A method for firing a ceramic core includes: placing the core in a setter, the setter having a plurality of protruding setter posts between second legs of the core and with distal ends supporting first legs of the core; and firing the core in the setter to harden the core. During the firing, the setter posts maintain a predetermined minimum separation between the first legs and the second legs.

Core firing setter

A turbine engine airfoil element has: an airfoil having: an exterior surface including a pressure side and a suction side; and a plurality of spanwise passageways including: a plurality of main body passageways along a camber line; and a plurality of skin passageways between the main body passageways and the exterior surface, wherein; the skin passageways have: a downstream direction from one or more inlets; a skin side; first and second lateral rounded transitions from the skin side; a parting line; and a longitudinally spaced plurality of protrusions from the skin side; and the protrusions have a height profile having: first and second tapering portions tapering from a maximum height, the first and second portions extending downstream; and first and second inwardly concave transitions to the skin passageway lateral rounded transitions.

Skin passageway trip strips

A turbine component includes a body having a pair of spaced walls, with at least one of the walls for facing a fluid flow when mounted in a gas turbine engine. There are a plurality of wall cooling passages having a generally boomerang shape such that a peak apex is spaced from the wall and an indent apex is adjacent to the wall, with the plurality of wall cooling passages having interior sides extending from the peak apex toward the wall to define a corner. Outer sides extend from the corners with a component away from the wall and to the indent apex. A gas turbine engine is also disclosed.

Turbine blade with boomerang shaped wall cooling passages

A turbine blade for a gas turbine engine, including: an airfoil, the having a leading edge, a pressure side, a suction side and a trailing edge; a plurality of internal cooling cavities including a leading edge cavity, a leading edge feed passage, pressure side cooling passages, suction side cooling passages and main body cavities; the leading edge cavity extending towards the suction side; a first crossover row of cooling passages providing fluid communication between the leading edge cavity and the leading edge feed passage; and a second crossover row of cooling passages providing fluid communication between the leading edge cavity and the leading edge feed passage, a centerline of the first crossover row of cooling passages is located closer to the pressure side than a centerline of the second crossover row of cooling passages and the centerline of the second crossover row of cooling passages is located closer to the suction side than the centerline of the first crossover row of cooling passages, and wherein the second crossover row of cooling passages are radially staggered relative to the first crossover row of cooling passages.

Air foil with staggered cooling hole configuration

A turbine blade includes a platform, a root section, and an airfoil section extending from the platform to a tip. The airfoil section includes a leading edge and a trailing edge extending from the platform to the tip. A tip wall is at the tip and extends from the leading edge to the trailing edge. A first core passage extends from the root section to the tip wall between the leading edge and the trailing edge. A first tip flag passage extends adjacent to the tip wall from the first core passage to a first flag outlet on the trailing edge. A second tip flag passage extends toward the leading edge from a second flag outlet on the trailing edge and is between the first tip flag passage and the root section. A second core passage extends from the root section to the second tip flag passage.

Dual tip flag

A turbine engine airfoil element has a plurality of main body passageways along a camber line and having two or more chordwise distributed protuberant portions with necks between the protuberant portions. A plurality of skin passageways include: at least one first skin passageway each nested between a first of the pressure side and the suction side and two adjacent main body passageways; and a plurality of second skin passageways each nested between first of the pressure side and the suction side and two said protuberant portions of a corresponding main body passageway.

Airfoils with lobed cooling cavities

A turbine engine airfoil element has: a plurality of spanwise main body passageways along a camber line; and a plurality of spanwise skin passageways along the pressure side. The spanwise skin passageways include: first skin passageways each having a plurality of film cooling outlets to the pressure side; and second skin passageways each lacking film cooling outlets to the pressure side. Linking passageways extend between the first skin passageways and the second skin passageways. The first skin passageways and second skin passageways are directly fed from one or more inlets of the airfoil element.

Airfoils with mixed skin passageway cooling

An airfoil includes an airfoil wall that defines a leading end, a trailing end, a pressure side, a suction side, and a mean line. First and second ribs each connect the pressure side and the suction side. Each of the first and second ribs define a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the pressure side and the suction side. The first rib, the second rib, and the airfoil wall bound a continuous cooling channel there between. The continuous cooling channel has a pressure side portion to the pressure side of the mean line and a suction side portion to the suction side of the mean line. The pressure side portion and the suction side portion each have a cross-sectioned shape selected from an L-shape, a T-shape, and an l-shape.

Airfoil with ribs defining shaped cooling channel

A core structure for a providing a cooling passage in a gas turbine engine includes a core body that has a first cooling passage core. The first cooling passage core has a first width in a chord-wise direction near a first wall. A second width in the chord-wise direction near a second wall. A third width in the chord-wise direction between the first and second walls. The third width being smaller than the first and second widths to form an hourglass shape.

Hourglass airfoil cooling configuration

An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib connects the first and second sides of the airfoil wall. The rib defines a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall.

Airfoil with rib having connector arms

An airfoil include an airfoil wall that defines a leading end, a trailing end, a first side wall, and a second side wall. A rib connects the first and second side walls of the airfoil wall. The rib includes a first arm by which the rib is solely connected to the first side wall, and second and third arms by which the rib is solely connected to the second side wall.

Airfoil with connecting rib

Airfoils and core assemblies for such airfoils are described. The airfoils include a leading edge cavity defined, in part, by a leading edge interior rib and a trailing edge cavity defined, in part, by a trailing edge interior rib. A plurality of pressure side cavities are defined by pressure side skin cavity walls with at least one pressure side skin cavity wall not extending to the suction side wall. A plurality of suction side cavities are defined by suction side skin cavity walls with at least one suction side skin cavity wall not extending to the pressure side wall. A main body cavity extends between the leading edge interior rib and the trailing edge interior rib and the plurality of side cavities are arranged in a staggered pattern to define the bounds of the main body cavity.

Cooling schemes for airfoils for gas turbine engines

An airfoil element has first and second ribs each connecting the pressure side and the suction side. Each of the first and second ribs define: a tube portion circumscribing a rib passage; and first and second connector arms joining the tube portion to, respectively, the pressure side and the suction side. The first rib, the second rib, and the airfoil wall bound a continuous cooling channel having a pressure side portion to the pressure side of the mean line and a suction side portion to the suction side of the mean line. At least one of the pressure side portion and the suction side portion includes a skin passageway between at least one of the respective tube portions of the first rib and second rib and an adjacent portion of an interior surface of the airfoil wall. The skin passageway has an outer surface formed by the adjacent portion and an inner surface formed by said at least one of the respective tube portions. At least one of the outer surface and the inner surface has a plurality of protrusions into the skin passageway.

Airfoil skin passageway cooling enhancement

Growing community of inventors

Vernon, CT, United States of America

Brandon W Spangler