Isolation seals for gas turbine engines

1. An isolation seal for a gas turbine engine, the isolation seal comprising:

an elastomer body configured to be attached to a first case structure at a first end and a second case structure at a second end; and

a seal shield configured to be attached to the first case structure, the seal shield having a shielding member configured to define a protected space between the shielding member and the elastomer body,

wherein the shielding member comprises a hollow body having a cooling manifold and cooling channels extending a length of the shielding member along the protected space with a plurality of cooling apertures configured to direct a cooling flow from the cooling channels out through the cooling apertures into the protected space and direct said cooling flow at the elastomer body.

2. The isolation seal of claim 1 , further comprising a reinforcement band configured to support and retain the elastomer body.

3. The isolation seal of claim 1 , wherein the shielding member has a flow director portion on an end thereof.

4. The isolation seal of claim 1 , wherein the elastomer body is formed from at least one of room-temperature-vulcanizing silicone, silicone-based material, multi-directional fiber layer reinforced structure, or rubber impregnated fabric.

5. The isolation seal of claim 1 , wherein the shielding member is formed from at least one of titanium alloy, nickel alloy, cobalt alloy, or stainless steel.

6. A gas turbine engine comprising:

a first case structure;

a second case structure;

an elastomer isolation seal arranged between the first case structure and the second case structure and provide sealing engagement therebetween, the elastomer isolation seal having an elastomer body; and

a seal shield attached to the first case structure, the seal shield having a shielding member configured to define a protected space between the shielding member and the elastomer body,

wherein the shielding member comprises a hollow body having a cooling manifold and cooling channels extending a length of the shielding member along the protected space with a plurality of cooling apertures configured to direct a cooling flow from the cooling channels out through the cooling apertures into the protected space and direct said cooling flow at the elastomer body.

7. The gas turbine engine of claim 6 , further comprising a reinforcement band configured to support and retain the elastomer body.

8. The gas turbine engine of claim 6 , wherein the shielding member has a flow director portion on an end thereof.

9. The gas turbine engine of claim 6 , further comprising:

a cooling source; and

a cooling supply aperture formed in the first case structure, wherein the cooling supply aperture defines a fluid connection between the cooling source and the protected space.

10. The gas turbine engine of claim 9 , wherein the cooling source is a bypass duct of the gas turbine engine at a location upstream of a combustor section.

11. The gas turbine engine of claim 6 , wherein the shielding member extends from the first case structure to the second case structure.

12. The gas turbine engine of claim 11 , further comprising a secondary seal arranged between the shielding member and the second case structure.

13. The gas turbine engine of claim 12 , wherein the secondary seal is a perforated finger seal.

14. The gas turbine engine of claim 6 , wherein the elastomer isolation seal is connected to the first case structure at a first attachment structure and to the second case structure at a second attachment structure.

15. The gas turbine engine of claim 14 , wherein the seal shield is attached to the first case structure at the first attachment structure.

16. The gas turbine engine of claim 6 , wherein the first case structure is an engine case and the second case structure is an exhaust nozzle.