Combustion chamber of gas turbine with starter film cooling
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorsMiklos Gerendas, Michael Ebel
Life of this patent
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Abstract
A combustion chamber of a gas turbine includes starter film cooling of a combustion chamber wall 4 and several circularly arranged burners 7 with local maxima and minima in the intensity of the starter film 3 being provided around the circumference of the combustion chamber wall 4.
Claims27
A gas turbine combustion chamber including starter film cooling of a combustion chamber wall and several circularly arranged burners, wherein, the starter film cooling is provided by starter film holes positioned in a head of the combustion chamber upstream of any film cooling holes provided on a wall of the combustion chamber, the starter film holes being grouped into at least a first set of groups and a second set of groups, the first set of groups providing local starter film maxima with a greatest starter film air flow in certain sectors around a circumference of the combustion chamber where a thermal load is greater as compared to the second set of groups providing local starter film minima with a least starter film air flow in other sectors around the circumference of the combustion chamber where a thermal load is lesser to decrease a temperature gradient of the combustion chamber wall in a circumferential direction.
A gas turbine combustion chamber, comprising:
- a plurality of burners positioned around a circumference of the combustion chamber;
- a plurality of starter film holes positioned around the circumference of a head of the combustion chamber upstream of any film cooling holes provided on a wall of the combustion chamber to provide starter film cooling of the combustion chamber, the starter film holes being arranged in at least a first set of groups to provide local starter film maxima with a greatest starter film air flow in certain sectors around a circumference of the combustion chamber where a thermal load is greater and a second set of groups to provide local starter film minima with a least starter film air flow in other sectors around the circumference of the combustion chamber where a thermal load is lesser to decrease a temperature gradient of the combustion chamber wall in a circumferential direction.
Dependencies are inferred from the claim text.