Spar with embedded plenum passage
AssigneeRaytheon Technologies Corporation
InventorsJon E. Sobanski, Howard J. Liles
Life of this patent
Estimating the term…
Abstract
A spar for a vane arc segment of a gas turbine engine includes an elongated spar leg that has a spar wall that circumscribes a core passage. There is a plenum passage embedded in the spar wall between inner and outer portions of the spar wall. The inner portion of the spar wall is fully solid such that the plenum passage is fluidly isolated from the core passage. The outer portion of the spar wall has a plurality of cooling through-holes for emitting cooling air from the plenum passage.
Claims23
A spar for a vane arc segment of a gas turbine engine, comprising:
- an elongated spar leg having a spar wall that circumscribes a core passage;
- and
- a plenum passage embedded in the spar wall between inner and outer portions of the spar wall relative to the core passage, the outer portion of the spar wall having a plurality of cooling through-holes for emitting cooling air from the plenum passage.
A vane arc segment for a gas turbine engine, comprising:
- an airfoil section having an airfoil wall defining a leading edge, a trailing edge, a pressure side, and a suction side, the airfoil section having an internal cavity;
- a spar extending through the internal cavity for supporting the airfoil section, the spar being spaced from the airfoil wall, the spar having
- an elongated spar leg including a spar wall that circumscribes a core passage, and
- a plenum passage embedded in the spar wall between inner and outer portions of the spar wall relative to the core passage, the outer portion of the spar wall having a plurality of cooling through-holes for emitting cooling air from the plenum passage toward the airfoil wall.
A gas turbine engine comprising:
- a compressor section;
- a combustor in fluid communication with the compressor section;
- and
- a turbine section in fluid communication with the combustor, the turbine section having vane arc segments disposed about a central axis of the gas turbine engine, each of the vane arc segments includes:
- an airfoil section having an airfoil wall defining a leading edge, a trailing edge, a pressure side, and a suction side, the airfoil section having an internal cavity, and
- a spar extending through the internal cavity for supporting the airfoil section, the spar being spaced from the airfoil wall, the spar having
- an elongated spar leg including a spar wall that circumscribes a core passage, and
- a plenum passage embedded in the spar wall between inner and outer portions of the spar wall relative to the core passage, the outer portion of the spar wall having a plurality of cooling through-holes for emitting cooling air from the plenum passage toward the airfoil wall.
Dependencies are inferred from the claim text.