Method and apparatus for turbine interstage seal ring
AssigneeGeneral Electric Company
InventorsChristopher Sean Bowes, Ian David Wilson
Life of this patent
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Abstract
A seal assembly for a gas turbine engine including a seal member and an interstage seal ring including an axially forward member coupled to a first radially inward surface of a first disk and an axially aft member coupled to a second radially inward surface of a second disk, wherein the seal ring is configured to move in an axial direction while the upstream and downstream arms are coupled to the first and second disk respectively.
Claims18
A seal assembly for a gas turbine engine including a first disk and a second disk, said seal assembly comprising:
- a seal member;
- and
- an interstage seal ring comprising an axially forward member coupled to a first radially inward surface of the first disk and an axially aft member coupled to a second radially inward surface of the second disk, said seal ring configured to move in an axial direction while said upstream and downstream arms are coupled to the first and second disks respectively.
A method for assembling a seal assembly for a gas turbine engine rotor assembly, said method comprising:
- coupling a seal ring to a first disk such that an upstream arm of the seal ring engages a first radially inward surface of the first disk;
- and
- coupling the seal ring to a second disk such that a downstream arm of the seal ring engages a second radially inward surface of the second disk, wherein the seal ring is configured to move in an axial direction while the upstream and downstream arms are coupled to the first and second disk respectively.
A gas turbine engine comprising:
- a fan and combustor coupled in serial flow communication;
- and
- a rotor assembly comprising:
- a first disk;
- a second disk;
- and
- a seal assembly extending between the first disk and the second disk, said seal assembly comprising:
- an interstage seal ring, said interstage seal ring comprising:
- a forward member coupled to a radially inward surface of said first disk and an aft member coupled to a radially inward surface of said second disk, said seal ring is configured to move in an axial direction while said upstream and downstream arms remain coupled to said first and second disks respectively.
Dependencies are inferred from the claim text.