초록 ▼

A nozzle assembly (10) for a turbine engine includes an inner band (16) and an outer band (14) spaced apart from each other. An airfoil (12) installed between the bands has a leading edge (18) and a trailing edge (20). The airfoil has cavities formed in it for fluid flow through the nozzle assembly.

A nozzle assembly (10) for a turbine engine includes an inner band (16) and an outer band (14) spaced apart from each other. An airfoil (12) installed between the bands has a leading edge (18) and a trailing edge (20). The airfoil has cavities formed in it for fluid flow through the nozzle assembly. A plurality of film cooling holes (1A-6H) are formed in a sidewall of the airfoil on a concave side of the assembly, and a plurality of film cooling holes (1J-1R) are formed in a sidewall of the nozzle on a convex side thereof. The holes are formed on each side of the airfoil, adjacent the trailing edge of the nozzle, in a plurality of rows of holes including at least a forward row (C, J), an aft row (A, L), and an intermediate row (B, K). The spacing between the intermediate row and aft row is substantially closer than the spacing between the forward row and the intermediate row.

대표청구항 ▼

The invention claimed is: 1. A nozzle assembly for a turbine engine comprising: an inner band and an outer band spaced apart from each other; a nozzle installed between the bands and having an inner segment and a trailing edge, the nozzle having cavities formed therein for fluid flow through the no

The invention claimed is: 1. A nozzle assembly for a turbine engine comprising: an inner band and an outer band spaced apart from each other; a nozzle installed between the bands and having an inner segment and a trailing edge, the nozzle having cavities formed therein for fluid flow through the nozzle assembly; a plurality of film cooling holes formed in a sidewall of the nozzle on a concave side thereof and a plurality of film cooling holes formed in a sidewall of the nozzle on a convex side thereof, the film cooling holes being formed on each side of the nozzle in a plurality of rows of holes including at least a forward row, an aft row, and a row intermediate the forward and aft rows, the spacing between the intermediate row and aft row being substantially closer together than the spacing between the forward row and the intermediate row; and wherein the size and location of each hole are set forth in Table 1. 2. A nozzle assembly for a turbine engine comprising: an inner band and an outer band spaced apart from each other; a nozzle installed between the bands and having an inner segment and a trailing edge, the nozzle having cavities formed therein for fluid flow through the nozzle assembly; a plurality of film cooling holes formed in a sidewall of the nozzle on a concave side thereof and a plurality of film cooling holes formed in a sidewall of the nozzle on a convex side thereof, the film cooling holes being formed on each side of the nozzle in a plurality of rows of holes including at least a forward row, an aft row, and a row intermediate the forward and aft rows, the spacing between the intermediate row and aft row being substantially closer together than the spacing between the forward row and the intermediate row; and wherein the size and location of each hole are set forth in Table 2. 3. In a gas turbine engine, a first stage nozzle assembly comprising: a plurality of circumferentially arranged nozzle segments with the respective segments being connected to one another to form an annular array defining a path for hot gasses passing through the first stage; each segment including an inner band and an outer band spaced apart from each other with an airfoil installed between the bands, the airfoil having an inner segment and a trailing edge, and cavities formed therein for fluid flow through the airfoil; a plurality of film cooling holes formed in respective sidewalls of the airfoil on a concave side and a convex side of the airfoil, the film cooling holes being formed on each side of the airfoil, in a plurality of rows of holes including a forward row, an intermediate row, and an aft row, with the spacing between the intermediate row and the aft row being substantially closer together than the spacing between the forward row and the intermediate row; and wherein the size and location of each hole are set forth in Table 1. 4. In a gas turbine engine, a first stage nozzle assembly comprising: a plurality of circumferentially arranged nozzle segments with the respective segments being connected to one another to form an annular array defining a path for hot gasses passing through the first stage; each segment including an inner band and an outer band spaced apart from each other with an airfoil installed between the bands, the airfoil having an inner segment and a trailing edge, and cavities formed therein for fluid flow through the airfoil; a plurality of film cooling holes formed in respective sidewalls of the airfoil on a concave side and a convex side of the airfoil, the film cooling holes being formed on each side of the airfoil, in a plurality of rows of holes including a forward row, an intermediate row, and an aft row, with the spacing between the intermediate row and the aft row being substantially closer together than the spacing between the forward row and the intermediate row; and wherein the size and location of each hole are set forth in Table 2.