Multi-hole film cooled combustor liner with rectangular film restarting holes
AssigneeGeneral Electric Company
InventorHoward L. Foltz
Life of this patent
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Abstract
A gas turbine engine combustor liner having conventional dilution holes disposed therethrough and multi-hole film cooling holes to provide a cooling film on the hot side of the liner is provided with generally rectangular film starting apertures disposed downstream, with respect to the predetermined cooling film flow direction, of the dilution holes in predetermined otherwise cooling film dry areas on the hot side of the combustor liner. In one embodiment the multi-hole film cooling holes and the rectangular film starting apertures are angled sharply in the downstream direction and angled in a circumferential direction which generally coincides with a predetermined swirl angle of the flow along the surface of the liner within the combustion zone.
Claims10
An annular gas turbine combustor liner comprising:
- a hot side and cold side and a forward and aft end and said aft end being located downstream of said forward end,
- a plurality of multi-hole film cooling holes to inject cooling air to form a cooling film on the hot side of the combustor liner,
- a plurality of dilution holes disposed in the liner,
- a plurality of generally rectangular film starting apertures disposed in areas immediately downstream of said dilution holes, with respect to a predetermined cooling film flow direction, and
- wherein said multi-hole film cooling holes and said film starting apertures have respective sharply angled downstream slant angles.
A gas turbine combustion section comprising:
- a combustor casing,
- a single wall sheet metal combustor liner disposed inward of said combustor casing,
- said combustor liner comprising:
- a hot side and cold side and a forward and aft end and said aft end being located downstream of said forward end,
- a plurality of multi-hole film cooling holes having sharply downstream angled slant angles to inject cooling air to form a cooling film on the hot side of the combustor liner,
- said plurality of multi-hole film cooling holes forming at least one continuous pattern of small, closely spaced, and sharply downstream angled film cooling holes spaced at least sufficiently close enough together to effect a continuous cooling film on said hot side of said combustor liner during combustion section operation,
- said continuous pattern extending essentially over the entire length of said combustor liner,
- said multi-hole film cooling holes operable to inject all of the cooling air at essentially said slant angle,
- a plurality of dilution holes disposed in the liner, and
- a plurality of generally rectangular film starting apertures disposed in areas immediately downstream of said dilution holes wherein said rectangular film starting apertures are sharply angled downstream, with respect to a predetermined cooling film flow direction.
Dependencies are inferred from the claim text.