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US 8,006,477 B2Granted
Re-heat combustor for a gas turbine engine
AssigneeGeneral Electric Company
InventorConstantin Dinu
Life of this patent
Estimating the term…
Abstract
A turbine engine includes a turbine section having a first turbine portion and a second turbine portion arranged along a central axis. A re-heat combustor is arranged between the first and second turbine portions. The re-heat combustor includes a combustion duct having a curvilinear flow portion. The curvilinear flow portion provides an increased residence time of combustion products passing through the re-heat combustor.
Claims13
A turbine engine comprising:
- a turbine section including a first turbine portion and a second turbine portion arranged along a central axis;
- and
- a re-heat combustor arranged between the first and second turbine portions, the re-heat combustor including a combustion duct having a combustion flow inlet and a bypass flow inlet adjacent to the combustion flow inlet, the combustion flow inlet extends to a combustion flow outlet through a curvilinear flow portion having a vertex, the curvilinear flow portion extending from the combustion flow inlet to the vertex radially outwardly from the central axis, the curvilinear flow portion providing increased residence time of combustion products passing through the re-heat combustor.
Dependencies are inferred from the claim text.