Gas turbine engine combustor
AssigneeROLLS-ROYCE plc
InventorDavid J Sherwood
Life of this patent
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Abstract
A combustor for a gas turbine engine comprising at least one combustor air intake chute wherein at least one of the air intake chutes is configured to enhance the heat transfer relationship between the chute material and the air flowing over it. The air intake chutes have at least one raised feature formed on their inner surface which extends into the airflow passing through the chute. The raised features may take the form of a circumferential rib, an axial rib or a pedestal, or any combination of the same.
Claims15
A combustor for a gas turbine engine, comprising a combustion chamber wall having formed therein at least one hole for admitting air into the combustion chamber and at least one air intake chute disposed coaxially with said hole,
- wherein said chute is configured such that, during engine operation, air admitted through the air intake chute is directed at an angle to a bulk flow of combusting gas and penetrates sufficiently far into the combustor to dilute the combusting gas,
- and wherein at least one third of an inside surface of said chute is provided with raised features and each of said raised features extends radially, such that during engine operation heat is transferred between the chute material and the air flowing through the chute.
Dependencies are inferred from the claim text.