Angled turbulence promoter

• US 4,514,144 A
• Filed: 11/07/1983
• Issued: 04/30/1985
• Est. Priority Date: 06/20/1983
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Lee, Ching-Pang
• Primary Examiner(s): Yuen, Henry C.
• Assistant Examiner(s): Kwon, John
• Application Number:
  US06/549,219
• Time in Patent Office: 540 Days
• Field of Search: 416/95, 416/96 A, 416/96 R, 416/97 A, 416/97 R, 415/115, 165/179, 138/38
• US Class Current: 416/96.00R
• CPC Class Codes: B22C 9/04 Use of lost patterns
• CPC Class Codes: B22C 9/103 Multipart cores
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2260/2212 by creating turbulence

Abstract

A turbomachinery airfoil with at least one internal cooling passage is disclosed. The passage has a pair of opposite walls with turbulence promoters, such as ribs or pin arrays, integral therewith. The ribs/pin arrays are angled with respect to the center line of their respective wall and ribs/pin arrays on opposite walls are angled with respect to each other. At least one gap is provided in each rib to provide a flow path for dust which might otherwise collect behind each rib.

Claims

1. A turbine blade with at least one internal cooling passage, said passage including first and second opposite walls, and a plurality of first and second turbulence promoting ribs, wherein:

said first ribs are integral with said first wall of said passge and disposed at a first angle with respect to the center line of said first wall;

said second ribs are integral with said second wall of said passage and disposed at a second angle with respect to the center line of said second wall; and

each of said first and second ribs comprises two rib members separated by a turbulence promoting gap.

2. The blade, as recited in claim 1, wherein said first angle is between 40°

and 90° and

said second angle is between 90° and

140°

.

3. The blade, as recited in claim 2, wherein said first angle is approximately 60°

, said second angle is approximately 120°

, and said gaps of adjacent ribs on each wall are disposed on alternate sides of the center line of said wall.

4. A gas turbine blade with at least one internal cooling passage, said passage being defined by four walls including first and second opposite walls connected by third and fourth walls, and a plurality of first and second turbulence promoting ribs integral with said walls wherein said first ribs extend from the center line of said third wall and perpendicular thereto, across said first wall at a first angle to the center line of said first wall, to the center line of said fourth wall, and perpendicular thereto, wherein:

said second ribs extend from the center line of said third wall and perpendicular thereto, across said second wall at a second angle to the center line of said second wall, to the center line of said fourth wall and perpendicular thereto;

each said first rib comprises two rib members separated by a gap located on said first wall; and

each said second rib comprises two rib members separated by a gap located on said second wall.

5. A blade, as recited in claim 4, wherein said first angle is between 40°

and 90° and

said second angle is between 90° and

140°

.

6. A blade, as recited in claim 5, wherein said first angle is approximately 60°

and said second angle is approximately 120° and

said gaps of adjacent ribs are disposed on alternate sides of the center line of said first and second walls respectively.

7. A turbine blade with at least one internal cooling passage, said passage including first and second opposite walls and a plurality of first and second turbulence promoting ribs, wherein:

said first ribs are integral with said first wall of said passage and disposed at a first angle with respect to the center line of said first wall;

said second ribs are integral with said second wall of said passage and disposed at a second angle with respect to the center line of said second wall; and

each of said first and second ribs comprises a plurality of rib members separated by turbulence promoting gaps.

8. A turbine blade with at least one internal cooling passage, said passage including first and second opposite walls and a plurality of first and second turbulence promoting pin arrays, wherein:

each of said first and second pin arrays comprises a plurality of non-abutting aligned pins;

said first arrays are integral with said first wall of said passage, each array being positioned at a first angle with respect to the center line of said first wall; and

said second arrays are integral with said second wall of said passage, each array being positioned at a second angle with respect to the center line of said second wall.