Sealing device for a gas turbine combustor
AssigneesJeremy Metternich, Stephen W. Jorgensen, David Giel, Ramesh Keshava-Bhattu
InventorsJEREMY METTERNICH, Stephen W. Jorgensen, David Giel, Ramesh Keshava-Bhattu
Life of this patent
Estimating the term…
Abstract
The present invention discloses a novel apparatus and way for sealing a portion of a gas turbine combustor in order to regulate the flow of compressed air into an annular passage adjacent to a combustion liner. A compressible seal is utilized having a first annular portion, a second annular portion, and a transition portion, the compressible seal regulates airflow passing through the compressible seal via a plurality of openings and/or axially extending slots.
Claims31
A sealing system for a gas turbine combustor comprising:
- a combustion liner positioned along an axis of the gas turbine combustor;
- a flow sleeve positioned radially outward of the combustion liner and forming an annular passage between the combustion liner and the flow sleeve;
- a compressible seal having a first annular portion, a second annular portion, and a transition portion, where the compressible seal is positioned between the combustion liner and the flow sleeve, the compressible seal regulates airflow passing through the compressible seal and into the annular passage.
A seal for a gas turbine combustor comprising:
- a first annular portion having a first diameter;
- a second annular portion having a second diameter, the second annular portion radially outward of the first annular portion;
- and,
- a transition portion extending between the first annular portion and the second annular portion, the transition portion having a plurality of openings for regulating flow of a cooling fluid and a plurality of axial slots.
A method of regulating cooling fluid flow to a gas turbine combustor comprising:
- providing a seal extending between a combustion liner and a flow sleeve, the seal having a plurality of slots proximate the flow sleeve and a plurality of openings in the seal;
- directing a cooling fluid across the seal;
- and,
- permitting a portion of the cooling fluid to flow between the seal and the combustion liner to cool a liner aft end.
A sealing system for a gas turbine combustor comprising:
- a combustion liner positioned along an axis of the gas turbine combustor;
- a flow sleeve positioned radially outward of the combustion liner and forming an annular passage between the combustion liner and the flow sleeve;
- a transition duct having a first wall and a second wall, where the second wall is located radially outward of the first wall, the first wall engaged with the combustion liner;
- and,
- a compressible seal having a first annular portion secured to the flow sleeve and a second annular portion in contact with the second wall of the transition duct.
A sealing system for a gas turbine combustor comprising:
- a combustion liner positioned along an axis of the gas turbine combustor;
- a flow sleeve positioned radially outward of the combustion liner and forming an annular passage between the combustion liner and the flow sleeve;
- a transition duct having a first wall and a second wall, where the second wall is located radially outward of the first wall, the first wall engaged with the combustion liner;
- and,
- a compressible seal having a first annular portion secured to the second wall of the transition duct and a second annular portion in contact with the flow sleeve.
Dependencies are inferred from the claim text.