IMPINGEMENT COOLING BAFFLE
First Claim
1. A component for a gas turbine engine, comprising:
- a first component end;
a second component end;
a cavity extending from the first component end to the second component end; and
a baffle assembly located in the cavity including;
a first baffle portion inserted into the cavity; and
a second baffle portion inserted into the cavity;
the first baffle portion overlapping the second baffle portion.
4 Assignments
0 Petitions
Accused Products
Abstract
A component for a gas turbine engine includes a first component end, a second component end and a cavity extending from the first component end to the second component end. A baffle assembly is located in the cavity including a first baffle portion inserted into the cavity and a second baffle portion inserted into the cavity. The first baffle portion overlaps the second baffle portion. A vane for a gas turbine engine includes an outer platform, an inner platform and an airfoil portion extending. A core extends through the airfoil portion. A baffle is positioned in the core and is offset from the core wall. The baffle includes a first baffle portion inserted into the core and a second baffle portion inserted into the core. One of the first baffle portion or the second baffle portion overlaps the other of the first baffle portion or the second baffle portion.
-
Citations
20 Claims
-
1. A component for a gas turbine engine, comprising:
-
a first component end; a second component end; a cavity extending from the first component end to the second component end; and a baffle assembly located in the cavity including; a first baffle portion inserted into the cavity; and a second baffle portion inserted into the cavity; the first baffle portion overlapping the second baffle portion. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
-
-
9. A vane for a gas turbine engine comprising:
-
an outer platform; an inner platform; an airfoil portion extending between the outer platform and the inner platform; a core defined by a core wall extending through the airfoil portion from the outer platform to the inner platform; a baffle disposed in the core and offset from the core wall, the baffle including; a first baffle portion inserted into the core; and a second baffle portion inserted into the core; one of the first baffle portion or the second baffle portion overlaps the other of the first baffle portion or the second baffle portion. - View Dependent Claims (10, 11, 12, 13, 14, 15, 16, 17)
-
-
18. A gas turbine engine, comprising:
-
a compressor section; a combustor section; a turbine section; and a component including; a first component end; a second component end; a cavity extending from the first component end to the second component end; and a baffle assembly located in the cavity including; a first baffle portion inserted into the cavity; and a second baffle portion inserted into the cavity; the first baffle portion overlapping the second baffle portion. - View Dependent Claims (19, 20)
-
Specification