Annular combustor with outer transition liner cooling

• US 5,237,813 A
• Filed: 08/21/1992
• Issued: 08/24/1993
• Est. Priority Date: 08/21/1992
• Status: Expired due to Term

• Current Assignee: Alliedsignal Inc., American Hoechst Corporation (Sanofi )
• Original Assignee: Alliedsignal Inc.
• Inventors: Harris, Mark M., Marsh, David N.
• Primary Examiner(s): Bertsch, Richard A.
• Assistant Examiner(s): WICKER, WILLIAM
• Application Number:
  US07/934,053
• Time in Patent Office: 368 Days
• Field of Search: 60/39.36, 60/760, 60/752, 60/754
• US Class Current: 60/804
• CPC Class Codes: F23R 3/02 characterised by the air-flow or gas-flow configuration reverse- flow combustion chambers F23R3/54; cyclone or vortex type combustion chambers F23R3/58
• CPC Class Codes: F23R 3/50 Combustion chambers comprising an annular flame tube within an annular casing toroidal combustion chambers F23R3/52
• CPC Class Codes: F23R 3/54 Reverse-flow combustion chambers

Abstract

A reverse flow annular combustor is provided having downstream wall comprised of a shroud covering the outer surface of the outer transition liner. The shroud abuts the transition liner at a plurality of points to define a plurality of passages between the shroud and the liner. The passages receiving cooling through the shroud at its radial inner end and expel the cooling air through the liner at its outer radial portion and into the hot gas in the combustor. Thus, the air used to cool the liner is also used for dilution mixing with the combustion gas.

Claims

1. A reverse flow annular combustor for a gas turbine engine having an upstream end and a downstream end comprising at least one annular wall, extending radially from an inner end to an outer end which is upstream of said inner end, said wall disposed at said downstream end of said combustor and having an interior surface exposed to the hot gas in said combustor, and an annular shroud disposed about an exterior surface of said angular wall and abutting thereto at a plurality of points thereby defining a plurality of passages between said wall and shroud, said passages receiving air through a plurality of holes through the inner radial end of said shroud and delivering air to a plurality of apertures through the outer radial end of said wall.

2. The combustor of claim 1 wherein said wall and said shroud are concave.

3. The combustor of claim 1 wherein said apertures have a total area at least twice the total area of said holes.

4. The combustor of claim 1 wherein said passages are sized so that the velocity of the air flow therein corresponds to a Mach number range of about 0.15 to about 0.25.

5. The combustor of claim 4 wherein said passages are sized to a width of about 0.030 to about 0.080 inches.

6. The combustor of claim 5 wherein said passages includes an enlarged portion in fluid communication with said apertures for providing static pressure recovery to the air flowing therethrough.

7. The combustor of claim 6 wherein said holes and said apertures are equi-circumferentially spaced.