US 2026/0309033 A1Published application

Internal baffle for a gas turbine engine vane

AssigneeRtx Corporation

InventorsBrendan Harders, Dawit Dereje, Shawn M. McMahon

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Abstract

A turbine vane includes a vane body and a baffle. The vane body includes an inner side forming an internal cavity. The vane body further forms at least one retention feature recess on the inner side. The baffle is disposed within the internal cavity. The baffle includes a tubular body. The tubular body subdivides the internal cavity into an outer cavity portion and an inner cavity portion. The outer cavity portion is formed between the inner side and the baffle tubular body. The inner cavity portion is circumscribed by the tubular body. The tubular body includes at least one protruding retention feature. The at least one protruding retention feature is disposed within the at least one retention feature recess. The at least one protruding retention feature disposed within the at least one retention feature recess obstructs radial movement of the baffle relative to the vane body.

Claims21

Dependent claims

A turbine vane of a gas turbine engine for an aircraft propulsion system, the turbine vane comprising:

a vane body extending between and to an outer radial vane end and an inner radial vane end, the vane body including an inner side forming an internal cavity extending through the vane body between the outer radial vane end and the inner radial vane end, the vane body further forming at least one retention feature recess on the inner side;
and
a baffle disposed within the internal cavity, the baffle extending between and to an outer radial baffle end and an inner radial baffle end, the baffle including a tubular baffle body extending between and to the outer radial baffle end and the inner radial baffle end, the tubular baffle body subdividing the internal cavity into an outer cavity portion and an inner cavity portion, the outer cavity portion formed between the inner side and the baffle tubular baffle body, the inner cavity portion circumscribed by the tubular baffle body, the tubular baffle body including at least one protruding retention feature, the at least one protruding retention feature disposed within the at least one retention feature recess, the at least one protruding retention feature disposed within the at least one retention feature recess obstructing radial movement of the baffle relative to the vane body;
wherein the at least one retention feature recess is recessed from surrounding portions of the inner side, the vane body includes a rim forming an outer radial recess end of the at least one retention feature recess, and the at least one protruding retention feature projects outward from surrounding portions of the tubular baffle body into the at least one retention feature recess at the rim.

1 more element

A gas turbine engine for an aircraft propulsion system, the gas turbine engine comprising:

a bladed turbine rotor rotatable about a rotational axis of the gas turbine engine, the bladed turbine rotor including an upstream rotor stage and a downstream rotor stage;
and
a turbine vane stage disposed axially between the upstream rotor stage and the downstream rotor stage, the turbine vane stage including a plurality of turbine vanes, at least one of the plurality of turbine vanes including a vane body and a baffle, the vane body extending between and to an outer radial vane end and an inner radial vane end, the vane body including an inner side forming an internal cavity extending through the vane body between the outer radial vane end and the inner radial vane end, the vane body further forming at least one retention feature recess on the inner side at the outer radial vane end;
and
a baffle disposed within the internal cavity, the baffle including at least one protruding retention feature, the at least one protruding retention feature disposed within the at least one retention feature recess, the at least one protruding retention feature disposed within the at least one retention feature recess obstructing radial movement of the baffle relative to the vane body.

2 more elements

Dependencies are inferred from the claim text.