Film cooling for the trailing edge of a steam cooled nozzle

• US 7,086,829 B2
• Filed: 02/03/2004
• Issued: 08/08/2006
• Est. Priority Date: 02/03/2004
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Findlay, Matthew, Fuller, Jason, Chiurato, Cathy, Itzel, Gary
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): White, Dwayne J
• Application Number:
  US10/771,195
• Publication Number:
  US 20050169746A1
• Time in Patent Office: 917 Days
• Field of Search: 415/115, 415/116, 415/914, 416/90.R, 416/92, 416/95, 416/96.R, 416/97.R, 416/97.A, 416/96.A
• US Class Current: 415/115
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 9/02 Nozzles; Nozzle boxes; Stator blades; Guide conduits , e.g. individual nozzles nozzle boxes F01D9/047
• CPC Class Codes: F05D 2240/122 related to the trailing edge of a stator vane
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/205 Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
• CPC Class Codes: F05D 2260/2322 steam

Abstract

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.

Claims

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.