Sealing configuration to reduce air leakage

1. A seal assembly for a fluid transfer tube that extends through a casing in a gas turbine engine, the fluid transfer tube defining a longitudinal vector (L) extending through an axis of the fluid transfer tube proximate the casing and positioned at a non-zero angle (A) with respect to a normal vector (N) representing a surface normal to an outer surface of the casing, comprising:

a base member having a first side configured to mate with the outer surface of the casing and a second side opposite the first side;

an annular ring configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, the annular ring having a first interior surface and a second interior surface that are shaped to have the same angle (A) that the longitudinal vector (L) makes with the normal vector (N);

a first O-ring disposed between the annular ring and the fluid transfer tube, the annular ring including a first groove configured for seating the first O-ring;

a second O-ring disposed between the base member and the annular ring, the annular ring including a second groove configured for seating the second O-ring; and

an attachment ring configured to secure the annular ring and the base member to the casing.

2. The seal assembly of claim 1 , wherein the base member is constructed of a metallic material.

3. The seal assembly of claim 2 , wherein the attachment ring is constructed of a metallic material.

4. The seal assembly of claim 3 , wherein the annular ring is constructed of at least one of an aluminum alloy or a titanium alloy.

5. The seal assembly of claim 1 , wherein the annular ring comprises a first split ring and a second split ring.

6. The seal assembly of claim 5 , wherein both the base member and the attachment ring include a plurality of holes extending therethrough and configured for attaching the base member and the attachment ring to the casing via a plurality of bolts.

7. The seal assembly of claim 5 , further comprising a wear sleeve configured to surround the portion of the fluid transfer tube.

8. The seal assembly of claim 7 , wherein the wear sleeve is configured to surround a thermal insulation sleeve disposed between the portion of the fluid transfer tube and the wear sleeve.

9. A transfer tube assembly for a gas turbine engine, comprising:

a fluid transfer tube configured to extend through a casing, the fluid transfer tube defining a longitudinal vector (L) extending through an axis of the fluid transfer tube proximate the casing and positioned at a non-zero angle (A) with respect to a normal vector (N) representing a surface normal to an outer surface of the casing;

a base member having a first side configured to mate with the outer surface of the casing and a second side opposite the first side;

an annular ring configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, the annular ring having a first interior surface and a second interior surface that are shaped to have the same angle (A) that the longitudinal vector (L) makes with the normal vector (N);

a first O-ring disposed between the annular ring and the fluid transfer tube, the annular ring including a first groove configured for seating the first O-ring;

a second O-ring disposed between the base member and the annular ring, the annular ring including a second groove configured for seating the second O-ring; and

an attachment ring configured to secure the annular ring and the base member to the casing.

10. The transfer tube assembly of claim 9 , further comprising a thermal insulation sleeve positioned between the fluid transfer tube and the annular ring.

11. The transfer tube assembly of claim 10 , further comprising a wear sleeve positioned between the thermal insulation sleeve and the annular ring.

12. The transfer tube assembly of claim 11 , wherein the annular ring comprises a first split ring and a second split ring.

13. A bleed air assembly for a gas turbine engine, comprising:

a fluid transfer tube configured to provide compressed air from a compressor to a component external to the compressor, the fluid transfer tube defining a longitudinal vector (L) extending through an axis of the fluid transfer tube proximate the casing and positioned at a non-zero angle (A) with respect to a normal vector (N) representing a surface normal to an outer surface of the casing;

a base member having a first side configured to mate with the outer surface of the casing and a second side opposite the first side;

an annular ring configured to mate with the second side of the base member and to surround an exterior surface of the fluid transfer tube, the annular ring having a first interior surface and a second interior surface that are shaped to have the same angle (A) that the longitudinal vector (L) makes with the normal vector (N);

a first O-ring disposed between the annular ring and the fluid transfer tube, the annular ring including a first groove configured for seating the first O-ring;

a second O-ring disposed between the base member and the annular ring, the annular ring including a second groove configured for seating the second O-ring; and

an attachment ring configured to secure the annular ring and the base member to the casing.

14. The bleed air assembly of claim 13 , wherein the first O-ring and the second O-ring are configured to enable movement of the fluid transfer tube with respect to the casing.

15. The bleed air assembly of claim 14 , further comprising a thermal insulation sleeve positioned between the fluid transfer tube and the annular ring.

16. The bleed air assembly of claim 14 , further comprising a wear sleeve positioned between the fluid transfer tube and the annular ring.

17. The bleed air assembly of claim 14 , wherein the annular ring comprises a first split ring and a second split ring.