Gas turbine engine aft bearing arrangement
An example gas turbine engine includes a turbine and first and second spools coaxial with one another. The first spool is arranged within the second spool and extends between forward and aft ends. The aft end extends axially beyond the second spool and supports the turbine. A housing is arranged downstream from the turbine. First and second bearings are mounted to the aft end of the first spool and supported by the housing portion.
1. A bearing hub for a gas turbine engine comprising:
first and second hub walls integrally formed with one another to provide a unitary structure;
a radial to axial translation flange arm extending outward from an apex of the unitary structure;
a translation flange extending outward from said radial to axial translation flange arm and angled relative to said radial to axial translation flange arm;
a spring arm connected to the apex for connecting the bearing hub to a canted annular flange, the spring arm including at least a first flex point, a second flex point, and a third flex point, and wherein a stiffness of each of said flex points is configured to determine an amount of radial vibrations translated to axial vibrations by said bearing hub; and
wherein each of said first, second, and third flex point is an angled corner of said spring arm.
2. The bearing hub of claim 1 , wherein the translation flange arm extends axially aftward from said apex of said unitary structure.
3. The bearing hub of claim 1 , wherein the first and second hub walls are inclined radially inward from an annular apex, and a first and second bearing are respectively supported by the first and second walls opposite the apex.
4. The bearing hub of claim 3 , wherein a focal node of radial vibrations of the bearing hub is the first bearing.
5. The bearing hub of claim 1 , wherein said spring arm is rigidly connected to said apex.
6. A gas turbine engine comprising:
a fan;
a compressor fluidly connected to the fan, the compressor comprising a first compressor section and a second compressor section;
a combustor fluidly connected to the compressor;
a turbine section fluidly connected to the combustor, the turbine section comprising:
a first turbine section coupled to the first compressor section via a shaft;
a second turbine section;
first and second hub walls integrally formed with one another to provide a unitary structure;
a radial to axial translation flange arm extending outward from an annular apex of the unitary structure;
a translation flange extending outward from said radial to axial translation flange arm and angled relative to said radial to axial translation flange arm;
a turbine exhaust case arranged downstream from the second turbine section and supporting the annular apex;
a spring arm connecting the annular apex to a canted annular flange of the turbine exhaust case, the spring arm including at least a first flex point, a second flex point, and a third flex point, and wherein a stiffness of each of said flex points is configured to determine an amount of radial vibrations translated to axial vibrations by said bearing hub; and
wherein each of said first, second, and third flex point is an angled corner of said spring arm.
7. The gas turbine engine of claim 6 , wherein the translation flange arm extends axially aftward from said apex of said unitary structure.
8. The gas turbine engine of claim 6 , wherein said translation flange is received in an annular cavity and is supported by the canted annular flange.
9. The gas turbine engine of claim 8 , wherein said annular cavity includes an axial vibration damper.
10. A gas turbine engine comprising:
a fan;
a compressor fluidly connected to the fan, the compressor comprising a first compressor section and a second compressor section;
a combustor fluidly connected to the compressor;
a turbine section fluidly connected to the combustor, the turbine section comprising:
a first turbine section coupled to the first compressor section via a shaft;
a second turbine section;
first and second hub walls integrally formed with one another to provide a unitary structure;
a radial to axial translation flange arm extending outward from an annular apex of the unitary structure;
a translation flange extending outward from said radial to axial translation flange arm, said translation flange being received in an annular cavity and being supported by a canted annular flange, wherein said annular cavity includes an axial vibration damper and wherein said axial vibration damper comprises at least a first wire mesh structure disposed between said translation flange and a first wall of said annular cavity;
a turbine exhaust case arranged downstream from the second turbine section and supporting the annular apex; and
a spring arm connecting the annular apex to a canted annular flange of the turbine exhaust case.
11. The gas turbine engine of claim 10 , wherein said axial vibration damper comprises at least a second wire mesh structure disposed between said translation flange and a second wall of said annular cavity.
12. A gas turbine engine comprising:
a fan;
a compressor fluidly connected to the fan, the compressor comprising a first compressor section and a second compressor section;
a combustor fluidly connected to the compressor;
a turbine section fluidly connected to the combustor, the turbine section comprising:
a first turbine section coupled to the first compressor section via a shaft;
a second turbine section;
first and second hub walls integrally formed with one another to provide a unitary structure;
a radial to axial translation flange arm extending outward from an annular apex of the unitary structure;
a translation flange extending outward from said radial to axial translation flange arm, said translation flange being received in an annular cavity and being supported by a canted annular flange, wherein said annular cavity includes an axial vibration damper and wherein said axial vibration damper comprises at least a first seal defining a damping annulus within said annular cavity;
a turbine exhaust case arranged downstream from the second turbine section and supporting the annular apex; and
a spring arm connecting the annular apex to a canted annular flange of the turbine exhaust case.
13. The gas turbine engine of claim 12 , further comprising a damping fluid disposed within said damping annulus.
14. The turbine engine of claim 13 , wherein said damping fluid is damping oil.
15. The turbine engine of claim 12 , wherein said axial vibration damper comprises at least a second seal further defining the damping annulus.
16. The turbine engine of claim 12 , wherein said seal is one of an elastomeric O-ring seal and a piston ring.