Airfoil trailing edge cooling configuration

• US 5,102,299 A
• Filed: 11/10/1986
• Issued: 04/07/1992
• Est. Priority Date: 11/10/1986
• Status: Expired due to Fees

• Current Assignee: United States Of America As Represented By The Secretary Of The Air Force
• Original Assignee: United States Of America As Represented By The Secretary Of The Air Force
• Inventors: Frederick, Robert
• Primary Examiner(s): Powell, Jr., Everette A.
• Application Number:
  US07/928,348
• Time in Patent Office: 1,975 Days
• Field of Search: 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

Abstract

An airfoil includes a plurality of interior cooling air paths arranged so as to provide crossover metering and pressure side bleed of cooling air at the trailing edge region of the airfoil.

Claims

1. An airfoil having a pressure side wall and a suction side wall defining a forward region and a trailing edge region of said airfoil;

said pressure side wall abutting said suction side wall in said trailing edge region of said airfoil;

a cavity for receiving cooling air formed between the inner surfaces of said pressure side wall and said suction side wall in said forward region of said airfoil;

a plurality of cooling air discharge slots formed in said pressure side wall in said trailing edge region of said airfoil; and

air flow metering and crossover means in said trailing edge region of said airfoil for passing cooling air from said cavity to said cooling air discharge slots;

said air flow metering and crossover means comprising a plurality of cooling air input channels each formed in the inner surface of said suction side wall and entering said cavity, a plurality of cooling air output channels each formed in the inner surface of said pressure side wall and coupled to one of said plurality of cooling air discharge slots, and a plurality of air passageways each formed in the inner surface of said suction side of said airfoil and coupling one of said plurality of cooling air input channels to a corresponding one of said plurality of cooling air output channels.

2. An airfoil as defined in claim 1 wherein each of said plurality of cooling air input channels and each of said plurality of cooling air output channels are of substantially the same width.

3. An airfoil as defined in claim 2 wherein each of said plurality of air passageways has a width of less than one half the width of one of said plurality of cooling air input channels.

4. An airfoil as defined in claim 3 wherein each of said plurality of cooling air input channels, air passageways and cooling air output channels are of substantially rectangular cross section.

5. An airfoil as defined in claim 4 wherein each of said plurality of air passageways symmetrically overlies the width of the corresponding one of said plurality of cooling air output channels.

6. An airfoil as defined in claim 5 wherein said pressure side wall and said suction side wall are separate pieces, said inner surface of said pressure side wall and said inner surface of said suction side wall being bonded together at said trailing edge region.