Combustor liner cooling arrangement
This patent describes a gas turbine engine combustor aft of the gas turbine compressor section. It comprises: liner disposed inwardly of a combustor outer wall and in the compressor discharge airflow, wherein the compressor discharge airflow is used for combustor cooling air and the liner is positioned for flow of cooling air past the exterior of the liner; a plurality of small firm cooling holes in the liner, the film cooling holes being inclined toward the aft end of the combustor to direct cooling air along the interior surface of the liner; first means of the liner for blocking direct flow of air to the small film cooling holes and providing a path for reverse flow of air between the first means and the exterior surface of the liner; second means disposed aft of the first means for diverting a portion of the air and providing reverse flow of the diverted air into the path; and a first plurality of larger holes in the liner at the point of reversal of flow of the air for passing dirt particles therethrough.
- Assignee:
- General Electric Co., Cincinnati, OH
- Patent Number(s):
- US 7896510; A
- Application Number:
- PPN: US 7-316560A
- OSTI ID:
- 6911976
- Resource Relation:
- Patent File Date: 27 Feb 1989
- Country of Publication:
- United States
- Language:
- English
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