Raytheon Technologies Corporation

Rtx Corporation

United Technologies Corporation

David R Pack

Brandon W Spangler

James D Hill

Gabriel L Suciu

Julian Partyka

Pitchaiah Vijay Chakka

Brian D Merry

JinQuan Xu

Edwin Otero

William P Stillman

Gregory M Dolansky

Jaime G Ghigliotty Rosado

Griffin D Lavine

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 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 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

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

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

Airfoil for gas turbine engines are described. The airfoils have internal walls and internal cavities. A leading edge cavity is defined within the airfoil body along a leading edge and a leading edge feed cavity is arranged aft of the leading edge cavity. A bent leading edge rib is arranged between the leading edge cavity and the leading edge feed cavity. A main body cavity is arranged aft of the leading edge feed cavity and defined at least in part by two interior ribs that define a part of the leading edge feed cavity. The main body cavity is fluidly connected to the leading edge feed cavity by an interior fluid connection through the intersection of the two interior ribs. A shield cavity is arranged to thermally shield the leading edge feed cavity from heat pickup along the suction side of the airfoil body.

An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides joining the leading end and the trailing end. First and second ribs each connect the first and second sides of the airfoil wall. Each of the first and second ribs define a tube portion that circumscribes a rib passage and includes cooling apertures, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall. The airfoil wall and the first and second ribs bound a cooling channel there between. The cooling apertures of the first and second ribs open at the cooling channel such that there is a cooling circuit in which the rib passages of the first and second ribs are fluidly connected through the cooling apertures and the cooling channel.

Airfoil with ribs having connector arms and apertures defining a cooling circuit

A modified shaped heat exchanger hot air inlet and hot air outlet comprising a first heat exchanger manifold surrounding said hot air inlet and a second heat exchanger manifold surrounding said hot air outlet; an array of shaped inlets and shaped outlets, each of said shaped inlets and shaped outlets being configured to align vertices with thermal load directions responsive to a thermal expansion mismatch between the hot air inlet and hot air outlet and respective first heat exchanger manifold and second heat exchanger manifold.

Modified shaped heat exchanger inlets/outlets

A blade for use with a gas turbine engine includes an attachment and an airfoil. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of intersecting ribs transitioning from an airfoil cross sectional geometry to an attachment cross section geometry.

Blade neck transition

A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil has a leading edge and a trailing edge that define the true chord length. The airfoil includes a first portion near the airfoil base with a first density and a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction. The second portion is in the range of 90% span to 100% span.

Gas turbine engine blade with variable density and wide chord tip

An airfoil for use with a gas turbine engine includes a pressure side wall and a suction side wall. The suction side wall is configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of ribs forming a plurality of trapezoidal shaped cavities to receive a cooling airflow. The plurality of ribs being shaped in a way to allow for thermal growth of the airfoil, while minimizing stress in the airfoil.

Blade/vane cooling passages

A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly.

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Ellington, CT, United States of America

David R Pack