One-piece combustor cowl

• US 5,924,288 A
• Filed: 03/06/1997
• Issued: 07/20/1999
• Est. Priority Date: 12/22/1994
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Duke, Richard A., Fortuna, Douglas M., Napoli, Phillip D.
• Primary Examiner(s): KOCZO JR, MICHAEL
• Application Number:
  US08/811,754
• Time in Patent Office: 866 Days
• Field of Search: 60/39.36, 60/752, 60/755, 60/756
• US Class Current: 60/752
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence

Abstract

A one-piece cowl is provided for use in assembled relationship with a combustor of a gas turbine engine. The cowl is of a generally annular configuration which defines a central cowl axis, and is axially elongated and aerodynamically contoured relative to the central cowl axis. In order to provide a vibratory damping function for the cowl, a solid lip of increased thickness is formed at a leading edge of the cowl.

Claims

1. A one-piece, integrally formed cowl for use in assembled relationship with a combustor of a gas turbine engine, said cowl being of a generally annular configuration defining a central cowl axis and being axially elongated and aerodynamically contoured relative to said central cowl axis, wherein said cowl is located radially adjacent to only one side of a plurality of circumferentially spaced mixers of said combustor, said cowl comprising:

(a) an aft section connected to a liner of said combustor;

(b) a middle section located upstream of said aft section; and

(c) a fore section located upstream of said middle section and being oriented substantially perpendicular to said central cowl axis, said fore section increasing in thickness from an initial thickness adjacent said middle section to a maximum thickness in order to form a solid lip at a leading edge of said cowl.

2. The one-piece cowl of claim 1, said aft section being oriented substantially parallel to said central cowl axis.

3. The one-piece cowl of claim 1, said middle section being substantially arcuate.

5. The one-piece cowl of claim 1, wherein said middle section is oriented at an angle to said aft section in a range of 125 to 150°

.

6. The one-piece cowl of claim 1, wherein said middle section is oriented at an angle to said fore section in a range of 145°

to 155°

.

7. The one-piece cowl of claim 1, wherein said solid lip is substantially teardrop-shaped.

8. The one-piece cowl of claim 1, wherein said maximum thickness of said fore section is greater than said middle section thickness by 4 to 5 times.

9. The one-piece cowl of claim 1, wherein said fore section and said middle section are substantially arcuate and said fore section has a radius less than a radius of said middle section.

4. The one-piece cowl of cliam 1, wherein said cowl is located radially to the outside of side spaceed mixers.

10. A one-piece, integrally formed cowl for use in assembled relationship with a combustor of a gas turbine engine, said cowl being of a generally annular configuration defining a central cowl axis and being axially elongated and aerodynamically contoured relative to said central cowl axis, wherein said cowl is located radially adjacent to only one side of a plurality of circumferentially spaced mixers of said combustor, said cowl comprising:

(a) an aft section connected to a liner of said combustor;

(b) a middle section located upstream of said aft section; and

(c a fore section located upstream of said middle section, said fore section increasing in thickness form an initial thickness adjacent said middle section to a maximum thickness in order to form a solid lip at a leading edge of said cowl;

wherein said leading edge of said cowl is a surface whose plane intersects said central cowl axis at an angle in a range of 40 to 50°

.

11. A one-piece, integrally formed cowl for use in assembled relationship with a combustor of a gas turbine engine, said cowl being of a generally annular configuration defining a central cowl axis and being axially elongated and aerodynamically contoured relative to said central cowl axis, wherein said cowl is located radially adjacent to only one side of a plurality of circumferentially spaced mixers of said combustor, said cowl comprising:

(a) an aft section connected to a liner of said combustor;

(b) a middle section located upstream of said aft section, wherein said middle section and said aft section are substantially arcuate and said middle section has a radius less than a radius of said aft section; and

(c) a fore section located upstream of said middle section, said fore section increasing in thickness from an initial thickness adjacent said middle section to a maximum thickness in order to form a solid lip at a leading edge of said cowl.