Lightweight tierod
The present disclosure provides an assembly for a gas turbine engine. The assembly may comprise a tierod, a bearing mounting ring, and a joint coupling the tierod to the bearing mounting ring. The joint may be configured to increase a volume of a bearing compartment on an inner surface of the bearing mounting ring. A coefficient of thermal expansion of the bearing mounting ring may be substantially the same as the coefficient of thermal expansion of the tierod.
1. An assembly for a gas turbine engine, comprising:
a tierod;
a bearing mounting ring defining a bearing compartment; and
a brazed joint located between mating surfaces of the tierod and the bearing mounting ring, wherein the mating surfaces of the tierod and the bearing mounting ring face one another;
wherein the tierod extends through the bearing mounting ring and comprises a flange within the bearing compartment, wherein the brazed joint is between the flange and an inner surface of the bearing mounting ring that defines a boundary of the bearing compartment.
2. The assembly of claim 1 , wherein the tierod comprises a base comprising the flange, a rod extending from the base, and a head opposite the base and extending from the rod.
3. The assembly of claim 2 , wherein the brazed joint is disposed between and couples an outer surface of the flange to the inner surface of the bearing mounting ring.
4. The assembly of claim 3 , wherein the brazed joint is configured to decrease a thickness of the flange.
5. The assembly of claim 2 , wherein the rod extends through an aerodynamic fairing, wherein there is a space between an outer surface of the bearing mounting ring and the aerodynamic fairing, and wherein the rod extends through the outer surface of the bearing mounting ring and through the bearing mounting ring to dispose the flange within the bearing compartment.
6. The assembly of claim 2 , wherein the head is configured to be mechanically coupled to an annular outer structure.
7. The assembly of claim 1 , wherein the bearing mounting ring comprises at least one aperture for receiving the tierod.
8. The assembly of claim 1 , wherein the brazed joint is configured to increase a volume of the bearing compartment on the inner surface of the bearing mounting ring.
9. The assembly of claim 1 , wherein a coefficient of thermal expansion of the bearing mounting ring is substantially the same as a coefficient of thermal expansion of the tierod.
10. The assembly of claim 1 , wherein the tierod comprises a cast nickel alloy.
11. A gas turbine engine, comprising:
an annular outer structure;
a fairing structure comprising a plurality of aerodynamic fairings;
an assembly comprising a tierod and a bearing mounting ring defining a bearing compartment, wherein the tierod extends through the bearing mounting ring and comprises a flange; and
a brazed joint between the flange and an inner surface of the bearing mounting ring that defines a boundary of the bearing compartment, wherein the brazed joint is between the inner surface of the bearing mounting ring and a surface of the flange that faces the inner surface of the bearing mounting ring.
12. The gas turbine engine of claim 11 , wherein there is a space between an outer surface of the bearing mounting ring and the fairing structure.
13. The gas turbine engine of claim 11 , wherein the tierod further comprises a rod extending from a base, and a head opposite the base and extending from the rod, wherein the base comprises the flange.
14. The gas turbine engine of claim 13 , wherein the head of the tierod is configured to be mechanically coupled to the annular outer structure.
15. The gas turbine engine of claim 11 , wherein the tierod extends radially from the bearing mounting ring, through the fairing structure, to the annular outer structure.
16. The gas turbine engine of claim 11 , wherein a coefficient of thermal expansion of the tierod is the same as a coefficient of thermal expansion of the bearing mounting ring.
17. The gas turbine engine of claim 11 , wherein the brazed joint is configured to increase a volume of the bearing compartment.
18. A method of assembling an assembly of a gas turbine engine, comprising:
positioning a fairing structure within an annular outer structure;
inserting a tierod through a bearing mounting ring, the tierod comprising a flange comprising an outer surface and the bearing mounting ring comprising an inner surface defining a bearing compartment, wherein the flange is disposed in the bearing compartment;
inserting the tierod through the fairing structure;
coupling the tierod to the annular outer structure; and
coupling the outer surface of the flange of the tierod to the inner surface of the bearing mounting ring via a brazed joint this is located between the outer surface of the flange and the inner surface of the bearing mounting ring.
19. An assembly for a gas turbine engine, comprising:
a tierod, wherein the tierod comprises a base comprising a flange, a rod extending from the base, and a head opposite the base and extending from the rod;
a bearing mounting ring defining a bearing compartment; and
a brazed joint located between mating surfaces of the tierod and the bearing mounting ring, wherein the mating surfaces of the tierod and the bearing mounting ring face one another, wherein the brazed joint is disposed between and couples an outer surface of the flange to an inner surface of the bearing mounting ring.
20. An assembly for a gas turbine engine, comprising:
a tierod, wherein the tierod comprises a base comprising a flange, a rod extending from the base, and a head opposite the base and extending from the rod;
a bearing mounting ring defining a bearing compartment; and
a brazed joint located between mating surfaces of the tierod and the bearing mounting ring, wherein the mating surfaces of the tierod and the bearing mounting ring face one another;
wherein the rod extends through an aerodynamic fairing, wherein there is a space between an outer surface of the bearing mounting ring and the aerodynamic fairing, wherein the rod extends through the outer surface of the bearing mounting ring and through the bearing mounting ring to dispose the flange within the bearing compartment, and wherein the brazed joint is between the flange and an inner surface of the bearing mounting ring that defines a boundary of the bearing compartment.