Heat transferring cooling features for an airfoil

• US 7,819,169 B2
• Filed: 05/14/2007
• Issued: 10/26/2010
• Est. Priority Date: 11/09/2004
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Coons, Todd, Botnick, Christina, Pietraszkiewicz, Edward F.
• Primary Examiner(s): Kerns; Kevin P
• Application Number:
  US11/748,070
• Publication Number:
  US 20080044282A1
• Time in Patent Office: 1,261 Days
• Field of Search: 164/369, 164/28, 164/132, 164/137
• US Class Current: 164/132
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2230/21 by casting
• CPC Class Codes: F05D 2250/185 serpentine-like
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/22141 using fins or ribs
• CPC Class Codes: F28F 3/12 Elements constructed in the shape of a hollow panel, e.g. with channels F28D1/02, F28D1/03 take precedence
• CPC Class Codes: Y10T 29/49339 Hollow blade
• CPC Class Codes: Y10T 29/49341 with cooling passage

Abstract

A turbine blade airfoil assembly includes a cooling air passage. The cooling air passage includes a plurality of impingement openings that are isolated from at least one adjacent impingement opening. The cooling air passage is formed and cast within a turbine blade assembly through the use of a single core. The single core forms the features required to fabricate the various separate and isolated impingement openings. The isolation and combination of impingement openings provide for the augmentation of convection and film cooling and provide the flexibility to tailor airflow on an airfoil to optimize thermal performance of an airfoil.

Claims

1. A method of forming cooling passages for an airfoil assembly comprising the steps of:

(a) forming a first core including impingement structures for forming impingement openings and separation structures for forming channels isolating each of the impingement openings from any other impingement openings;

(b) casting the airfoil assembly with the first core of step (a) disposed within a mold; and

(c) removing the first core from the cast airfoil assembly, wherein the cooling passages include channels isolating adjacent airflow communicated through adjacent impingement openings.

2. The method as recited in claim 1, wherein said step (a) includes forming a plurality of film hole structures for forming a corresponding plurality of film holes in the airfoil assembly.

3. The method as recited in claim 1, wherein said step (a) includes forming the separation structures for forming the channels such that a portion of each channel interfits within another of the channels.

4. The method as recited in claim 1, including the step of forming a main core for forming a main cavity within the airfoil assembly for receiving and communicating cooling air to the cooling passages formed by the first core.

5. The method as recited in claim 1, wherein said step (a) includes forming a plurality of turbulation structures for forming a corresponding plurality of turbulation features within the cooling passage of the airfoil assembly.

6. A method of forming an airfoil assembly comprising:

forming a first core including structures for forming impingement openings for communicating air from a main cavity against an interior surface of an outer wall of the airfoil assembly, and at least one structure for forming a divider that isolates adjacent impingement openings;

supporting the first core within a mold;

casting the airfoil assembly with the first core to form a first cavity including impingement openings in communication with a main cavity and the divider isolating adjacent impingement openings; and

removing the first core from the cast airfoil assembly.

7. The method as recited in claim 6, including forming the structure for forming the divider to include structures that form a wall extending between a top surface and a bottom surface of the first cavity.

8. The method as recited in claim 6, including forming the structure for forming the divider to include structures that form a wall that separates each of the impingement openings from each adjacent impingement opening.

9. The method as recited in claim 8, including forming the first core with structures for forming the first cavity to include a first expansion chamber and a second expansion chamber in the cast airfoil assembly separated by the divider.

10. The method as recited in claim 9, wherein the each adjacent impingement opening formed by the first core communicates cooling air flow to a different one of the first and second expansion chambers.