Static wear seals for a combustor transition
A static wear seal for an interface between two components is provided. The static wear seal includes a body portion including a receptacle configured to receive an insert portion. The insert portion is disposed within the receptacle. The receptacle is formed within the body portion at a surface of the body portion known to wear due to contact with a turbine component and includes a locking means such that the insert portion is retained within the receptacle. The insert portion is configured to receive wear due to contact with the turbine component. A transition seal assembly for a gas turbine engine including at least two seals wherein one of the two seals is a static wear seal is provided as well as a method to protect a wear surface of a static wear seal sealing an interface between the turbine components.
1. A static wear seal for an interface between two turbine components, comprising:
a U-shaped body portion including a receptacle configured to receive an insert portion,
the insert portion disposed within the receptacle;
wherein the receptacle is formed within the body portion at a first surface of the body portion capable of wear due to contact with one of the turbine components,
wherein the first surface comprises an interior surface of the U-shaped body portion,
and
wherein the insert portion is configured to receive wear due to the contact with the one of the turbine components,
wherein the first surface includes a stepped profile,
wherein the first surface engages a corresponding second surface of the insert portion, the second surface having a corresponding stepped profile to the stepped profile of the first surface, and
wherein the corresponding stepped profile of the second surface interfits with stepped profile of the first surface to prevent radial and axial movement of the insert portion.
2. The static wear seal as claimed in claim 1 , wherein a material of the insert portion is different than a material of the body portion.
3. The static wear seal as claimed in claim 2 , wherein the material of the insert portion is a cobalt-based material.
4. The static wear seal as claimed in claim 1 , wherein the insert portion is a coating.
5. A transition seal assembly for a gas turbine engine, along which exhaust gas generated in a combustion chamber flows toward a turbine of the gas turbine engine, comprising:
a first seal including a U-shaped body portion with a receptacle formed within the body portion at a first surface;
a second seal including a second surface that contacts the first seal; and
an insert portion disposed within the receptacle,
wherein the first surface comprises an interior surface of the U-shaped body portion,
wherein the insert portion is configured to receive wear due to contact with the surface of the second seal,
wherein the first surface includes a stepped profile,
wherein the second surface includes a corresponding stepped profile that interfits with the stepped profile of the first surface, and
wherein engagement of the first surface with the second surface prevents radial and axial movement of the insert portion.
6. The transition seal assembly as claimed in claim 5 , wherein the body portion comprises an L-shaped body member including one leg member.