Combustion liner for a gas turbine engine

• US 4,622,821 A
• Filed: 01/07/1985
• Issued: 11/18/1986
• Est. Priority Date: 01/07/1985
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Madden, Thomas J.
• Primary Examiner(s): Casaregola, Louis J.
• Assistant Examiner(s): Thorpe, Timothy S.
• Application Number:
  US06/689,253
• Time in Patent Office: 680 Days
• Field of Search: 60/752, 60/755, 60/757, 60/759, 60/756, 60/758, 60/760, 431/351, 431/352
• US Class Current: 60/757
• CPC Class Codes: F05B 2260/202 by film cooling
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

The liner of a combustor for a gas turbine engine is constructed to include a refilmer at the combustion/dilution air holes so as to form a film of cool air along the inner surface of the liner in the combustion, that would otherwise be destroyed by the combustion/dilution air.

Claims

1. For a gas turbine power plant, a combustor having a plurality of panels generally circular in shape and extending axially arranged end to end to define an annular combustion chamber, each of said panels having an inner surface subjected to combustion gases and an outer surface subjected to power plant cooler air, means on the downstream end to develop a film of a cool air flowing from said outer surface into said combustion chamber adjacent said inner surface, a plurality of openings in said panels for directing from said outer surface said cooler air to be used as combustion/dilution air radially into said combustion chamber passing through a portion of said film of cool air and obstructing the path of said portion, means for redefining the cooling film downstream of said openings relative to the flow of said combustion gases, a grommet supported to one of said panels having a generally circular body extending through each of said openings, a lip extending from the end of said grommet partially circumscribing said circular body on its downstream side relative to the flow of said combustion gases, said lip extending axially in said downstream direction and spaced from said inner surface, means for directly impinging said cool air from said outer surface onto said lip so that the impinged air is directed to flow adjacent said inner surface in said downstream direction, said lip having opposing said edges support means extending from said side edges to said circular body and defining with said lip an open ended channel, said channel being oriented with respect to said panels to orient the flow discharging from said lip in a given downstream direction.

2. For a gas turbine power plant as in claim 1 wherein said grommet includes a plurality of apertures overlying said lip for leading cool air from said outer surface to impinge on said lip.

3. For a gas turbine power plant as in claim 2 wherein said apertures are circular shaped holes.

4. For a gas turbine power plant as in claim 2 wherein said apertures are slots extending from one end of said grommet.

5. For a gas turbine power plant as in claim 1 wherein said means for impinging cool air includes apertures formed in said panels downstream of said grommet.

6. For a gas turbine power plant as in claim 5 where said apertures are circular shaped holes or slots.