Turbine blade with showerhead film cooling slots

• US 8,851,848 B1
• Filed: 02/20/2012
• Issued: 10/07/2014
• Est. Priority Date: 02/20/2012
• Status: Expired due to Fees

• Current Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Original Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Inventors: Liang, George
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): Christensen, Danielle M
• Application Number:
  US13/400,404
• Time in Patent Office: 960 Days
• Field of Search: 415/115, 416/95, 416/96.R, 416/97.R, 416/232
• US Class Current: 416/97.R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F05D 2240/303 related to the leading edge of a rotor blade
• CPC Class Codes: F05D 2250/323 convergent
• CPC Class Codes: F05D 2250/324 divergent
• CPC Class Codes: F05D 2260/201 by impingement of a fluid

Abstract

A turbine blade with a leading edge region of the airfoil having rows of film cooling slots each connected by one or more metering holes to a cooling air impingement cavity, where the film slots have both a convergent and a divergent shape. The side walls converge while the top and bottom walls diverge within each slot and form a very narrow but tall slot opening on the leading edge surface of the blade.

Claims

1. An air cooled turbine rotor blade comprising:

an airfoil with a leading edge region;

a leading edge impingement cavity located in the leading edge region;

a row of film cooling slots in the leading edge region extending along a spanwise direction of the airfoil;

a metering hole connected each of the film cooling slots to the leading edge impingement cavity;

each of the film cooling slots having two side walls that form a divergent cooling air flow; and

,

each of the film cooling slots having a top and bottom wall that form a convergent cooling air flow.

2. The air cooled turbine rotor blade of claim 1, and further comprising:

each of the film cooling slots is connected to a plurality of metering holes.

3. The air cooled turbine rotor blade of claim 1, and further comprising:

the airfoil includes three rows of film cooling slots with a middle row along a stagnation line of the airfoil and one row of each of the two sides of the middle row.

4. The air cooled turbine rotor blade of claim 1, and further comprising:

the film cooling slots have a downstream cross section flow area that is from two to five times a cross section flow area of the metering holes.

5. The air cooled turbine rotor blade of claim 1, and further comprising:

the film cooling slots are angled in a radial upward direction toward a blade tip.

6. The air cooled turbine rotor blade of claim 1, and further comprising:

the film cooling slots have openings on the airfoil surface with a thin width and a tall spanwise height.

7. The air cooled turbine rotor blade of claim 1, and further comprising:

the film cooling slots have a downstream cross section flow area that is greater than an upstream cross section flow area formed within the slot.