Circumferential seal with seal dampening elements
AssigneeUnited Technologies Corporation
InventorsRoss Wilson, Michael G. McCaffrey
Life of this patent
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Abstract
The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a circumferential seal for a gas turbine engine includes a first beam, a second beam, a seal shoe and at least one feature between the first beam and second beam configured to retain a beam spacer, wherein the at least one feature is configured to dampen at least one of beam and shoe vibration of the circumferential seal. Another embodiment is directed to a circumferential seal including a beam spacer.
Claims20
A circumferential seal for a gas turbine engine, the circumferential seal comprising:
- a first beam;
- a second beam;
- a seal shoe;
- and
- at least one feature between the first beam and second beam configured to retain a beam spacer, wherein the at least one feature is configured to dampen at least one of beam and shoe vibration of the circumferential seal.
A circumferential seal for a gas turbine engine, the circumferential seal comprising:
- a first beam;
- a second beam;
- a seal shoe;
- a beam spacer between the first beam and second beam;
- and
- at least one feature between the first beam and second beam configured to retain the beam spacer, wherein the at least one feature is configured to dampen at least one of beam and shoe vibration of the circumferential seal.
Dependencies are inferred from the claim text.