Divided baffle for components of gas turbine engines
AssigneeUnited Technologies Corporation
InventorsDominic J. Mongillo, Jr., Ricardo Trindade, Nicholas M. LoRicco
Life of this patent
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Abstract
Divided baffles for a gas turbine engines are provided. The divided baffles include a baffle body having a first end and a second end, at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities, at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities, and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.
Claims20
A divided baffle for a gas turbine engine, the divided baffle comprising:
- a baffle body having a first end and a second end;
- at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities;
- at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities;
- and
- at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.
A component for a gas turbine engine, the component comprising:
- an airfoil having a leading edge, a trailing edge, a suction side, and a pressure side, wherein an airfoil cavity is formed within the airfoil, wherein the airfoil extends from an inner diameter to an outer diameter;
- and
- a divided baffle installed within the airfoil cavity, the divided baffle comprising:
- a baffle body having a first end and a second end, wherein the first end is located proximate the inner diameter and the second end is located proximate the outer diameter;
- at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities;
- at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities;
- and
- at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.
A gas turbine engine comprising:
- an airfoil having a leading edge, a trailing edge, a suction side, and a pressure side, wherein an airfoil cavity is formed within the airfoil, wherein the airfoil extends from an inner diameter to an outer diameter;
- and
- a divided baffle installed within the airfoil cavity, the divided baffle comprising:
- a baffle body having a first end and a second end, wherein the first end is located proximate the inner diameter and the second end is located proximate the outer diameter;
- at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities;
- at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities;
- and
- at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.
Dependencies are inferred from the claim text.