Thermal barrier washer
AssigneeRaytheon Technologies Corporation
InventorsMathieu Strait, Mainul M. Islam
Life of this patent
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Abstract
An attachment mechanism for a gas turbine engine component includes an elongated body having at least first and second ends. A first attachment feature is formed at the first end. A second attachment feature is formed at the second end. The first and second attachment features define attachment points configured to attach a first gas turbine engine component to a second gas turbine engine component. A fan section for a gas turbine engine and a gas turbine engine are also disclosed.
Claims20
An attachment mechanism for a gas turbine engine component comprising:
- an elongated body having at least first and second ends, wherein the elongated body comprises a rigid, straight and flat bar that extends between the first and second ends and two straight parallel sides connecting the first and second ends;
- a first attachment feature formed at the first end;
- and
- a second attachment feature formed at the second end, wherein the elongated body is solid between the first and second attachment features and the two straight parallel sides, and wherein the first and second attachment features define attachment points configured to attach a first gas turbine engine component to a second gas turbine engine component.
A fan section for a gas turbine engine comprising:
- a fan case configured to surround a fan, wherein the fan case includes at least one mount interface;
- a component configured to be attached to the mount interface;
- and
- an attachment mechanism to attach the component to the fan via the mount interface, the attachment mechanism comprising an elongated body having at least first and second ends and two straight parallel sides connecting the first and second ends, a first attachment feature formed at the first end, and a second attachment feature formed at the second end, wherein the elongated body comprises a rigid, straight and flat bar that is solid between the first and second attachment features and the two straight parallel sides, and wherein the first and second attachment features comprise ring-shaped bodies that are integrally formed with the elongated body as a single-piece structure.
A gas turbine engine comprising:
- a fan section that drives air along a bypass flow path via a bypass duct defined within a fan case;
- a compressor section that drives air along a core flow path for compression and communication into a combustor section and subsequent expansion through a turbine section;
- and
- a component attached to the fan case via an attachment mechanism that comprises an elongated body comprising a rigid, straight and flat bar that extends between first and second ends and two straight parallel sides connecting the first and second ends, and including a first washer formed at the first end and a second washer formed at the second end, wherein the elongated body is solid between the first and second washers and the two straight parallel sides, and wherein the first and second washers are integrally formed with the elongated body as a single-piece structure.
Dependencies are inferred from the claim text.