Burner seal of a gas turbine and method for manufacturing the same
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorCarsten Clemen
Life of this patent
Estimating the term…
Abstract
A burner seal of a gas turbine with a substantially tubular base body, which has a ring-shaped inlet lip on the inflow side and a funnel at its outflow side, wherein an inner diameter of the inflow side is embodied to be larger than an inner diameter of a sealing surface that is arranged axially in front of the funnel, wherein cooling channels are formed in the base body distributed about the circumference, wherein the cooling channels are formed respectively in the base body in the area of the sealing surface and of the funnel, and respectively open into an end area of the funnel in an exit hole.
Claims13
A burner seal of a gas turbine comprising:
- a tubular base body including an inflow side and an outflow side;
- a ring-shaped inlet lip on the inflow side;
- a funnel on the outflow side;
- a sealing surface arranged axially upstream of the funnel, wherein an inner diameter of the inflow side is larger than an inner diameter of the sealing surface;
- an entry hole located in an inner surface of the burner seal;
- an exit hole positioned in the funnel;
- and
- a cooling channel formed in the base body and extending from the entry hole to the exit hole.
A method for manufacturing a burner seal, comprising:
- providing:
- a tubular base body including an inflow side and an outflow side;
- a ring-shaped inlet lip on the inflow side;
- a funnel on the outflow side;
- a sealing surface arranged axially upstream of the funnel, wherein an inner diameter of the inflow side is larger than an inner diameter of the sealing surface;
- an entry hole located in an inner surface of the burner seal;
- an exit hole positioned in the funnel;
- and
- a cooling channel formed in the base body and extending from the entry hole to the exit hole;
- manufacturing the burner seal using an additive process.
Dependencies are inferred from the claim text.