Isolation seals for gas turbine engines
Isolation seals for gas turbine engines are described. The isolation seals include a first interface member configured to be fixedly attached to a first case structure, the first interface member being a full-hoop structure, a housing configured to be mounted to a second case structure, a connector pin arranged within the housing and moveable relative to the housing, and a second interface member located on an end of the connector pin, the second interface member being a full-hoop structure. The first interface member and the second interface member are engageable to form a seal therebetween.
1. An isolation seal for a gas turbine engine, the isolation seal comprising:
a first interface member configured to be fixedly attached to a first case structure, the first interface member being a full-hoop structure;
a housing fixedly attached to and mounted to a second case structure by at least one retaining element:
a connector pin arranged within the housing and moveable relative to the housing; and
a second interface member directly connected to an end of the connector pin, the second interface member being a full-hoop structure,
wherein the first interface member and the second interface member are engageable to form a seal therebetween.
2. The isolation seal of claim 1 , further comprising a biasing member arranged within the housing, the biasing member configured to urge the second interface member away from the housing.
3. The isolation seal of claim 1 , further comprising at least one additional retaining element configured to fixedly attach the first interface member to the first case structure.
4. The isolation seal of claim 1 , wherein the first interface member and the second interface member are each formed of metal.
5. A gas turbine engine comprising:
a first case structure;
a second case structure; and
an isolation seal arranged between the first case structure and the second case structure and provide sealing engagement therebetween, the isolation seal comprising:
a first interface member configured to be fixedly attached to the first case structure, the first interface member being a full-hoop structure;
a housing fixedly attached to and mounted to a second case structure by at least one retaining element:
a connector pin arranged within the housing and moveable relative to the housing; and
a second interface member directly connected to an end of the connector pin, the second interface member being a full-hoop structure,
wherein the first interface member and the second interface member are engageable to form a seal therebetween.
6. The gas turbine engine of claim 5 , further comprising a biasing member arranged within the housing, the biasing member configured to urge the second interface member away from the housing.
7. The gas turbine engine of claim 5 , further comprising at least one additional retaining element configured to fixedly attach the first interface member to the first case structure.
8. The gas turbine engine of claim 5 , wherein the first interface member and the second interface member are each formed of metal.
9. The gas turbine engine of claim 5 , wherein the first case structure is an engine case and the second case structure is an exhaust nozzle.
10. The gas turbine engine of claim 5 , further comprising a secondary seal arranged between a portion of the second interface member and the second case structure.
11. The gas turbine engine of claim 5 , further comprising a plurality of additional housings and a plurality of additional connector pins, wherein each of the additional connector pins engages to the second interface member.
12. The gas turbine engine of claim 5 , wherein the first case structure comprises a bypass liner and the second case structure comprises an inner exhaust liner.
13. The gas turbine engine of claim 12 , further comprising a flowpath seal configured to join and seal the bypass liner to the inner exhaust liner.
14. The gas turbine engine of claim 12 , wherein a portion of a bypass duct is defined between the isolation seal and at least one of the bypass liner and the inner exhaust liner.
15. The gas turbine engine of claim 14 , wherein the location of the isolation seal is downstream along the bypass duct from a combustor section of the gas turbine engine.
16. The gas turbine engine of claim 5 , wherein the isolation seal provides sealing engagement between the first interface member and the second interface member when the first case structure and the second case structure during relative movement therebetween.
17. The gas turbine engine of claim 16 , wherein the relative movement is at least one of axial, radial, and angular.
18. The gas turbine engine of claim 16 , wherein the relative movement comprises each of axial relative movement, radial relative movement, and angular relative movement.