Method for forming turbine blade with angled internal ribs

• US 7,871,245 B2
• Filed: 06/24/2009
• Issued: 01/18/2011
• Est. Priority Date: 06/23/2005
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Downs, James P., Singer, Irwin D., Pietraszkiewicz, Edward
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US12/490,705
• Publication Number:
  US 20090269210A1
• Time in Patent Office: 573 Days
• Field of Search: 415/115, 415/116, 416/96.R, 416/96.A, 416/97.R, 416/233
• US Class Current: 416/96.00R
• CPC Class Codes: B22C 7/06 Core boxes
• CPC Class Codes: B22C 9/10 Cores; Manufacture or installation of cores breaker cores B22C9/084
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2230/21 by casting
• CPC Class Codes: F05D 2230/50 Building or constructing in particular ways

Abstract

Two pairs of ribs define three intermediate cooling chambers. Each rib in each pair extends parallel to the other rib in the pair. The ribs in a first pair are non-parallel to the ribs in a second pair. A first rib from the first pair is positioned spaced toward the leading edge. A first rib of the second pair is then serially positioned spaced toward the trailing edge. A second rib of the first pair is then positioned toward the trailing edge relative to the first rib in the second pair. A second rib in the second pair is then positioned toward the trailing edge relative to the second rib in the first pair.

Claims

1. A turbine blade comprising:

an airfoil body having a leading edge and a trailing edge, with a plurality of cooling channels being formed within said body;

said cooling channels being separated from adjacent cooling channels by ribs, and a plurality of said cooling channels communicating with each to form a serpentine flow path for cooling fluid; and

two pairs of said ribs defining three intermediate cooling channels with each rib in each of said pairs of ribs extending parallel to the other rib in said pair, and the ribs in the first of said two pair of ribs being non-parallel to the ribs in the second of said two pair, with a first rib from said first pair being positioned spaced toward one of said leading and trailing edges, and with a first rib of said second pair then serially being positioned spaced toward the other of said leading and trailing edges, with a second rib of said first pair then being positioned toward said other of said leading and trailing edges relative to the first rib in said second pair, and a second rib in said second pair then being positioned toward said other of said leading and trailing edges relative to the second rib in said first pair, and such that said two pairs of ribs define said three intermediate cooling channels, with said three intermediate cooling channels having a generally triangular shape.

2. The turbine blade as set forth in claim 1, wherein said one of said leading and trailing edges is said trailing edge.