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US 2002/0162331 A1Published application
Gas turbine combustor, particularly for an aircraft engine
AssigneeFiatavio S.p.A.
InventorDaniele Coutandin
Life of this patent
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Abstract
A gas turbine combustor, in particular for an aircraft engine, has at least one chamber, through which combustion gas flows in use, and which is defined by a lateral wall with channeling for feeding cooling air into the chamber and cooling the lateral wall; part of the channeling is defined by at least one double wall for guiding a relative stream of cooling air into the chamber in a tangential direction with respect to the lateral wall.
Claims14
1) A gas turbine combustor (5), in particular for an aircraft engine (1);
- the combustor comprising at least one chamber (14), through which combustion gas flows in use;
- at least one lateral wall (15) defining said chamber (14);
- and channeling means (60) associated with said lateral wall (15) to permit the passage of a cooling fluid for cooling the lateral wall (15);
- and being characterized by also comprising guide means (31, 32, 36) at least partly defining said channeling means (60) to feed at least one stream (F1, F2) of said cooling fluid into said chamber (14) in a tangential direction with respect to said lateral wall (15).
1 more element
Dependencies are inferred from the claim text.