Cooled turbine blade

• US 5,271,715 A
• Filed: 12/21/1992
• Issued: 12/21/1993
• Est. Priority Date: 12/21/1992
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Miller, Samuel R. Jr., Plank, William L., Zelesky, Mark F., Auxier, Thomas A.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): LARSON, JAMES
• Application Number:
  US07/993,584
• Time in Patent Office: 365 Days
• Field of Search: 416/95, 416/96 R, 416/96 A, 416/97 R, 416/97 A, 415/115
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2260/2212 by creating turbulence vortex generators, turbulators or the like for mixing F05D2240/127

Abstract

An air cooled gas engine turbine blade that includes a plurality of longitudinally spaced cavities adjacent the leading edge of the blade is designed to include angularly disposed impingement passages flowing cooling air into each of the cavities in a direction extending from the root to the tip of the blade and including an annular projection upstream of the impingement passage but adjacent thereto for directing air into the respective cavities with total instead of static pressure. The impingement holes are oriented to align with the film cool holes in the blade surface at the leading edge. Ribs formed between cavities are also oriented to be parallel to the impingement holes.

Claims

1. A turbine blade for a gas turbine engine including a leading edge, a trailing edge a root section and a tip section and including internal air cooling passageways and a plurality of longitudinally extending wall adjacent to the leading edge, a longitudinally extending wall adjacent to the leading edge defining said cavities, the improvement comprising angular, longitudinally spaced impingement holes leading cooling air into said cavities a feed passageway extending from the root section to the tip section of the blade for flowing cooling air internally in said blade, and a projection parallel to and adjacent to said impingement hole extending into said feed passageway and said feed passageway being located closer to said leading edge than said trailing edge of said blade whereby the pressure of said cooling air admitted into said cavities from said impingement holes is total pressure.

2. A turbine blade as claimed in claim 1 wherein said impingement holes are aligned with film cooling holes formed in said leading edge.

3. A turbine blade as claimed in claim 2 including transverse ribs between adjacent cavities being angularly disposed parallel to said impingement holes.