Compound cooling flow turbulator for turbine component

• US 8,894,367 B2
• Filed: 09/17/2010
• Issued: 11/25/2014
• Est. Priority Date: 08/06/2009
• Status: Active Grant

• Current Assignee: Mikro Systems, Inc., Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Mikro Systems, Inc., Siemens Energy Incorporated (Siemens AG)
• Inventors: Lee, Ching-Pang, Jiang, Nan, Marra, John J., Rudolph, Ronald J.
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US12/884,464
• Publication Number:
  US 20110033312A1
• Time in Patent Office: 1,530 Days
• Field of Search: 415/115, 415/116, 415/175, 415/176, 415/177, 415/178, 416/95, 416/96.R, 416/96.A, 416/97.R, 416/235, 416/236.R, 416/236.A, 416/237, 416/228, 165/109.1, 165/133, 165/183, 165/184
• US Class Current: 416/96.R
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2250/181 ridged
• CPC Class Codes: F05D 2250/60 Structure; Surface texture
• CPC Class Codes: F05D 2250/611 undulated
• CPC Class Codes: F05D 2250/70 Shape
• CPC Class Codes: F05D 2250/711 convex
• CPC Class Codes: F05D 2250/712 concave
• CPC Class Codes: F05D 2260/2212 by creating turbulence vortex generators, turbulators or the like for mixing F05D2240/127
• CPC Class Codes: F05D 2260/22141 using fins or ribs

Abstract

Multi-scale turbulation features, including first turbulators (46, 48) on a cooling surface (44), and smaller turbulators (52, 54, 58, 62) on the first turbulators. The first turbulators may be formed between larger turbulators (50). The first turbulators may be alternating ridges (46) and valleys (48). The smaller turbulators may be concave surface features such as dimples (62) and grooves (54), and/or convex surface features such as bumps (58) and smaller ridges (52). An embodiment with convex turbulators (52, 58) in the valleys (48) and concave turbulators (54, 62) on the ridges (46) increases the cooling surface area, reduces boundary layer separation, avoids coolant shadowing and stagnation, and reduces component mass.

Claims

1. A turbine component with an interior cooling surface comprising:

a plurality of first convex turbulation features separated by first valleys;

a plurality of concave turbulation features smaller than the first convex turbulation features formed on each of said first convex turbulation feature; and

a plurality of second convex turbulation features smaller than the valleys formed on said valleys;

wherein the first convex turbulation features comprise first ridges, and further comprising parallel additional ridges that are larger than the first ridges on the interior cooling surface, wherein the first ridges are formed between and parallel to the additional ridges.

2. The turbine component of claim 1, wherein the concave turbulation features comprises grooves, and the second convex turbulation features comprise second ridges.