United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Gina Cavallo

Brandon W Spangler

Ky H Vu

Ryan Alan Waite

Jeffrey J DeGray

Thomas P Dziuba

Jeffrey J Degray

A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a wall that extends about a cooling cavity. The cooling cavity is a dual-fed cavity that is fed from at least two different locations. A rib separates the cooling cavity into a first portion and a second portion that is fluidly isolated from the first portion. The component is an airfoil. The first portion is fed with a first cooling fluid from a first coolant source, and the second portion is fed with a second, different cooling fluid from a second coolant source. The first and second coolant sources are separate and distinct from the component.

Gas turbine engine component with flow separating rib

An airfoil includes an airfoil body extending from an inner diameter platform to an opposed outer diameter platform along a longitudinal axis. The airfoil body defines a leading edge and a trailing edge and has a cavity defined between the leading edge, the trailing edge, the inner diameter platform and the outer diameter platform. The cavity includes an airfoil protrusion extending inward from an inner surface of the airfoil body. The airfoil includes a baffle body within the cavity extending along a baffle body axis. The baffle body has a baffle protrusion extending along a central protrusion axis at an angle with respect to the baffle body axis. The end of the baffle protrusion abuts an end of the airfoil protrusion. A flow path is defined between the inner surface of the airfoil body and the outer surface of the baffle body.

Baffle inserts

A surface structure having a filmhole pattern is disclosed. The filmhole pattern may be an offset herringbone pattern. For instance, the surface structure may have rows of filmholes arranged in filmrows, each filmrow divided into groups of filmholes. A first group may be oriented to direct cooling air generally outward over a surface of the surface structure and a second group may be oriented to direct cooling air generally inward over a surface of the surface structure. Between the first group and the second group of filmholes in each filmrow, a transition region exists. The adjacent filmrows are arranged to enhance the effectiveness of the convective cooling proximate to the transition regions by causing each filmrow to direct cooling air over the transition region of an adjacent filmrow.

Cooling hole patterned surfaces

A component according to an exemplary aspect of the present disclosure includes, among other things, a platform and a feed cavity that feeds a cooling fluid inside of the platform. The feed cavity includes a leg portion and a main body portion that extends from the leg portion inside of the platform. A cooling cavity is inside the platform and in fluid communication with the feed cavity.

Gas turbine engine component with platform cooling circuit

A turbine engine component includes an internal baffle spaced between first and second walls. Each wall may have a plurality of cooling holes in fluid communication with respective upstream and downstream cooling paths defined between the baffle and the respective walls. Cooling air first flows through an upstream end portion of the upstream cooling path, then through a downstream end portion where the air enters a bleed aperture in the baffle. From the bleed aperture, a portion of or all of the cooling air may enter an internal cavity defined by the baffle and, from there, flows through at least one hole that may be a plurality of impingement holes in the baffle, and into the downstream cooling passage where the portion or all of the remaining cooling air may exit the component through the cooling holes in the second wall.

Enclosed baffle for a turbine engine component

A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.

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Watertown, CT, United States of America

Gina Cavallo