Compressor variable vane spindle mount with floating seal
An actuation structure changes the orientation of a vane airfoil. A spindle is fixed to the airfoil such that when the arm turns the spindle, the spindle turns the airfoil, the spindle extends through a bore in the housing. A mount is between the spindle and the housing at the bore, with a metal wear sleeve pressed into the housing at the bore, such that it is part of the housing. A bushing is secured to an outer periphery of the spindle such that a bearing surface during rotation of the spindle is provided by an outer periphery of the bushing and an inner periphery of the metal wear sleeve. A seal is radially outward of the bushing with the seal providing an air seal between the spindle and the bore. A gas turbine engine is also disclosed.
1. A compressor section for a gas turbine engine comprising:
a compressor rotor and at least one row of blades configured to rotate during operation of an associated engine;
at least one row of vanes positioned to be adjacent the at least one row of blades;
the at least one row of vanes having airfoils which are variable such that an orientation of a respective airfoil relative to an axial direction through the compressor section may change;
an actuation structure for changing the orientation of the airfoil, the actuation structure including an arm for being selectively moved to rotate a spindle, the spindle being fixed to the airfoil such that when the arm turns the spindle, the spindle turns the airfoil, the spindle extending through a bore in a housing;
a mount between the spindle and the housing at the bore, with a metal wear sleeve pressed into the housing at the bore, such that the metal wear sleeve is part of the housing;
a bushing secured to an outer periphery of the spindle such that a bearing surface during rotation of the spindle is provided by an outer periphery of the bushing and an inner periphery of the metal wear sleeve; and
a seal radially outward of the bushing with the seal providing an air seal between the spindle and the bore.
2. The compressor section as set forth in claim 1 , wherein the seal floats radially on the spindle.
3. The compressor section as set forth in claim 1 , wherein the bore in the housing is provided in part by an inwardly turned end of the metal wear sleeve.
4. The compressor section as set forth in claim 3 , wherein the spindle extends beyond an upper end of the bushing.
5. The compressor section as set forth in claim 4 , wherein a chamber is defined by the inwardly turned end of the metal wear sleeve and an upper end of the bushing and the seal is received in the chamber.
6. The compressor section as set forth in claim 1 , wherein the bushing is formed of a carbon composite material.
7. The compressor section as set forth in claim 1 , wherein the seal is formed of one of a composite material, a metal, a rubber material or polyamide.
8. The compressor section as set forth in claim 1 , wherein the metal wear sleeve is formed of a steel or nickel.
9. The compressor section as set forth in claim 1 , wherein the spindle extends beyond an upper end of the bushing.
10. The compressor section as set forth in claim 9 , wherein a chamber is defined by the housing and the upper end of the bushing, and the seal is received in the chamber.
11. The compressor section as set forth in claim 1 , wherein the bushing is formed of two parts, with a chamber defined intermediate the two parts and between an outer surface of the spindle and an inner surface of the metal wear sleeve, and the seal is received within that intermediate chamber.
12. The compressor section as set forth in claim 1 , wherein a chamber is defined between an end of the bushing and the vane airfoil, and the seal is received in the chamber.
13. A gas turbine engine comprising:
a compressor section, a combustor, and a turbine section;
the compressor section having a compressor rotor and at least one row of blades configured to rotate during operation of the engine;
at least one row of vanes positioned to be adjacent the at least one row of blades;
the at least one row of vanes having airfoils which are variable such that an orientation of a respective airfoil relative to an axial direction through the compressor section may change;
an actuation structure for changing the orientation of the airfoil, the actuation structure including an arm for being selectively moved to rotate a spindle, the spindle being fixed to the airfoil such that when the arm turns the spindle, the spindle turns the airfoil, the spindle extending through a bore in a housing;
a mount between the spindle and the housing at the bore, with a metal wear sleeve pressed into the housing at the bore, such that the metal wear sleeve is part of the housing;
a bushing secured to an outer periphery of the spindle such that a bearing surface during rotation of the spindle is provided by an outer periphery of the bushing and an inner periphery of the metal wear sleeve; and
a seal radially outward of the bushing with the seal providing an air seal between the spindle and the bore.
14. The gas turbine engine as set forth in claim 13 , wherein the seal floats radially on the spindle.
15. The gas turbine engine as set forth in claim 13 , wherein the bore in the housing is provided in part by an inwardly turned end of the metal wear sleeve.
16. The gas turbine engine as set forth in claim 13 , wherein the spindle extends beyond an upper end of the bushing.
17. The gas turbine engine as set forth in claim 16 , wherein a chamber is defined by the inwardly turned end of the metal wear sleeve and an upper end of the bushing, and the seal is received in the chamber.
18. The gas turbine engine as set forth in claim 13 , wherein the spindle extends beyond an upper end of the bushing, and a chamber is defined by the housing and the upper end of the bushing and the seal is received in the chamber.
19. The gas turbine engine as set forth in claim 13 , wherein the bushing is formed of two parts, with a chamber defined intermediate the two parts and between an outer surface of the spindle and an inner surface of the metal wear sleeve, and the seal is received within that intermediate chamber.
20. The gas turbine engine as set forth in claim 13 , wherein a chamber is defined between an end of the bushing and the vane airfoil, and the seal is received in the chamber.