Variable vane for gas turbine engine

Patent metadata

Field	Value
Publication number	US-9309778-B2
Application number	US-201113340983-A
Country	US
Kind code	B2
Filing date	Dec 30, 2011
Priority date	Dec 30, 2010
Publication date	Apr 12, 2016
Grant date	Apr 12, 2016

Abstract

A turbomachine includes a variably positioned vane, an outer spindle integral with a vane outer button, where the vane is coupled to the vane outer button, an annular sleeve defining the spindle, where the annular sleeve contacts the vane outer button at a radially inward extent and contacts a turbine casing at a radially outward extent. The annular sleeve includes a wall portion having an aperture and the spindle extends through the aperture. A nut engages spindle threads, where the nut applies force to the wall portion toward the radially inward extent. An end of the spindle extends through the turbine casing, and a cantilever rotation actuator is coupled to the end of the spindle. A first bearing and second bearing engage the annular sleeve. A vane inner button is coupled to the vane, and a third bearing engages the vane inner button.

First claim

What is claimed is:

1. A turbomachine, comprising:
a variably positioned vane;
a spindle integral with a vane outer button, wherein the vane is coupled to the vane outer button;
an annular sleeve defining the spindle, wherein the annular sleeve contacts the vane outer button at a radially inward extent and contacts a turbine casing at a radially outward extent, wherein the annular sleeve comprises a wall portion positioned perpendicular to the spindle, the wall portion including an aperture and the spindle extending from the vane outer button to and through the aperture, and wherein the spindle includes threads;
a nut engaged with the threads, the nut applying force to the wall portion toward the radially inward extent;
wherein a radially outward end of the spindle extends though the turbine casing,
and wherein a cantilever rotation actuator is coupled to the radially outward end of the spindle;
a first rolling element engaging the annular sleeve substantially near the radially outward extent, wherein the first rolling element is coupled to the turbine casing; and
a second rolling element engaging the annular sleeve substantially near the radially inward extent, wherein the second rolling element is coupled to an outer endwall ring.

2. The turbomachine of claim 1 , further comprising: a vane inner button coupled to the vane at a radially inward portion of the vane, a third rolling element engaging the vane inner button, and wherein the third rolling element rotatably engages the vane inner button.

3. The turbomachine of claim 2 , further comprising an annular sleeve wall aperture and at least one vane outer button aperture, wherein the sleeve wall aperture and the at least one vane outer button aperture are structured to allow cooling air to enter the vane.

4. The turbomachine of claim 1 , wherein the annular sleeve comprises an outer diameter at least two times greater than a diameter of the spindle.

Assignees

• Ress Jr Robert A
• Rolls Royce Nam Tech Inc

Inventors

• Ress Jr Robert A

Classifications

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D17/14

  varying effective cross-sectional area of nozzles or guide conduits · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F04D29/563 Primary

  specially adapted for elastic fluid pumps · CPC title