HALO seal build clearance methods

1. A seal for use in a gas turbine engine between a static structure and a rotating member, comprising:

a support ring for attachment to the static structure;

a shoe coupled to the support ring via an arm, and for facing the rotating member; and

an adhesive disposed between the shoe and the support ring,

wherein the adhesive secures the shoe with respect to the support ring against an inboard spring force provided by the arm, and

wherein the adhesive is configured to burn off at an elevated temperature to allow the shoe to move towards an inboard position.

2. The seal of claim 1 , wherein the adhesive is disposed between the arm and the support ring.

3. The seal of claim 1 , further comprising a stop extending from the support ring, wherein the adhesive is disposed between the shoe and the stop.

4. The seal of claim 1 , further comprising a shoe tab extending from the shoe, wherein the adhesive is disposed between the shoe tab and the support ring.

5. The seal of claim 1 , wherein the adhesive is a cyanoacrolate adhesive.

6. A seal arrangement of a gas turbine engine, comprising:

a static structure;

a rotating member;

a carrier ring attached to the static structure;

a seal coupled to the carrier ring, the seal comprising a support ring and a shoe coupled to the support ring via an arm, the shoe facing the rotating member;

a seal ring coupled to the carrier ring and axially adjacent the seal; and

an adhesive disposed between the support ring and the shoe,

wherein the adhesive secures the shoe with respect to the support ring against an inboard spring force provided by the arm, and

wherein the adhesive is configured to burn off at an elevated temperature to allow the shoe to move towards an inboard position.

7. The seal arrangement of claim 6 , wherein the adhesive is disposed between the arm and the support ring.

8. The seal arrangement of claim 6 , further comprising a stop extending from the support ring, wherein the adhesive is disposed between the shoe and the stop.

9. The seal arrangement of claim 6 , further comprising a shoe tab extending from the shoe, wherein the adhesive is disposed between the shoe tab and the support ring.

10. The seal arrangement of claim 6 , wherein the adhesive is a cyanoacrolate adhesive.

11. A method for assembling a seal arrangement in a gas turbine engine having a static structure and a rotating member, the method comprising:

applying an adhesive to a seal; and

applying a force to a shoe of the seal

wherein the seal comprises:

a support ring attached to the static structure;

the shoe coupled to the support ring via an arm, the shoe facing the rotating member; and

the adhesive disposed between the shoe and the support ring,

wherein the adhesive secures the shoe with respect to the support ring against an inboard spring force provided by the arm, and

wherein the adhesive is configured to burn off at an elevated temperature to allow the shoe to move towards an inboard position.

12. The method of claim 11 , further comprising removing the force from the shoe, wherein the adhesive secures the shoe with respect to the static structure in response to the force being removed.

13. The method of claim 11 , wherein the seal comprises a stop extending from the support ring, and wherein the adhesive is applied between the shoe and the stop.

14. The method of claim 11 , wherein the adhesive is applied between the arm and the support ring.

15. The method of claim 11 , wherein the adhesive is applied between the shoe and the support ring.

16. The method of claim 11 , further comprising: applying heat to at least one of a carrier ring and a static support piece; and disposing the seal arrangement into the at least one of the carrier ring and the static support piece, wherein the heat is applied to at least one of the carrier ring and the static support piece prior to applying the adhesive to the seal.

17. The method of claim 11 , further comprising disposing the rotating member adjacent the seal.