Back to results
US 2021/0348516 A1Published application
Hybrid vane segment with ceramic matrix composite airfoils
AssigneesRolls-Royce North American Technologies Inc., ROLLS-ROYCE plc
InventorsTed J. Freeman, Jay E. Lane, Michael J. Whittle, Anthony Razzell
Life of this patent
Estimating the term…
Abstract
A vane assembly for use with a gas turbine engine includes an outer wall, an inner wall, and a plurality of airfoils. The outer wall and the inner wall extend at least partway about an axis. At least one of the airfoils is coupled with the outer end wall and the inner end wall to transmit force loads through the vane assembly.
Claims20
A vane assembly adapted for use with a gas turbine engine, the vane assembly comprising
- an inner end wall comprising metallic materials, the inner end wall arranged circumferentially partway about a central axis and defining a first portion of a flow path of the vane assembly,
- an outer end wall comprising metallic materials, the outer end wall arranged circumferentially partway about the central axis and located radially outward of the inner end wall, the outer end wall defining a second portion of the flow path of the vane assembly,
- a first airfoil comprising metallic materials, the first airfoil extends radially between the inner end wall and the outer end wall and defines a third portion of the flow path of the vane assembly, and
- a second airfoil comprising entirely ceramic matrix composite materials, the second airfoil extends radially between the inner end wall and the outer end wall and defines a fourth portion of the flow path of the vane assembly, the second airfoil being spaced apart circumferentially from the first airfoil,
- wherein the first airfoil is mechanically fixed with the inner end wall and the outer end wall to transmit force loads acting axially on the inner end wall to the outer end wall during use of the vane assembly and the second airfoil is coupled with the outer end wall for movement therewith and extends radially into a pocket formed in the inner end wall so as to minimize transmission of the force loads acting axially on the inner end wall through the second airfoil.
2 more elements
A vane assembly adapted for use with a gas turbine engine, the vane assembly comprising
- a first end wall arranged circumferentially at least partway about a central axis,
- a second end wall arranged circumferentially at least partway about the central axis and spaced apart radially from the first end wall,
- a first airfoil that extends radially between the first end wall and the second end wall, the first airfoil fixed to the first end wall and the second end wall for movement with the first end wall and the second end wall, and
- a second airfoil that extends radially between the first end wall and the second end wall, the second airfoil being spaced apart circumferentially from the first airfoil, and the second airfoil coupled with the second end wall for movement therewith and extends radially into a pocket formed in the first end wall.
1 more element
A method comprising
- providing an outer end wall, an inner end wall, and a first airfoil integrated as a single component, the outer end wall includes an airfoil passage that extends through the outer end wall, and the inner end wall includes a pocket,
- inserting a second airfoil through the airfoil passage in the outer end wall and into the pocket in the inner end wall, and
- coupling a rim of the second airfoil to an outward facing support wall of the outer end wall and securing the rim with a retention plate so that the rim is radially located between the support wall and the retention plate, and the retention plate blocks movement of the second airfoil.
Dependencies are inferred from the claim text.