Variable pitch fan blade system

Patent metadata

Field	Value
Publication number	US-10415405-B2
Application number	US-201715494271-A
Country	US
Kind code	B2
Filing date	Apr 21, 2017
Priority date	Apr 21, 2017
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

A gas turbine engine may have a blade receiver for holding a fan blade, wherein the blade receiver is rotatable about a radial axis of the gas turbine engine. The gas turbine engine may also include a variable pitch mechanism comprising an actuation arm. The gas turbine engine may also include a splined index ring disposed between the actuation arm of the variable pitch mechanism and the blade receiver. The splined index ring may include an outer spline and an inner spline.

First claim

What is claimed is:

1. A variable pitch fan blade system comprising:
a blade receiver for holding a fan blade, wherein the blade receiver is rotatable about a radial axis of the gas turbine engine;
a variable pitch mechanism comprising an actuation arm; and
a splined index ring disposed between the actuation arm of the variable pitch mechanism and the blade receiver.

2. The variable pitch fan blade system of claim 1 , wherein the splined index ring comprises an outer spline and an inner spline.

3. The variable pitch fan blade system of claim 2 , wherein outer grooves of the outer spline extend parallel to inner grooves of the inner spline.

4. The variable pitch fan blade system of claim 3 , wherein the outer grooves and the inner grooves extend parallel to the radial axis.

5. The variable pitch fan blade system of claim 2 , wherein the outer spline is concentric with the inner spline.

6. The variable pitch fan blade system of claim 2 , wherein the blade receiver comprises a first ring spline engaging one of the outer spline and the inner spline and the actuation arm comprises a second ring spline engaging the other of the outer spline and the inner spline.

7. The variable pitch fan blade system of claim 6 , wherein the first ring spline of the blade receiver engages the inner spline of the splined index ring and the outer spline of the splined index ring engages the second ring spline of the actuation arm.

8. The variable pitch fan blade system of claim 7 , wherein the outer spline comprises X circumferentially distributed outer teeth, each outer tooth of the outer teeth having an outer angular dimension that is

360
X

degrees and the inner spline comprises Y circumferentially distributed inner teeth, each inner tooth of the inner teeth having an inner angular dimension that is

360
Y

degrees, wherein a non-negative integer multiple of the lesser of the outer angular dimension and the inner angular dimension is equal to the higher of the outer angular dimension and the inner angular dimension plus or minus a predetermined incremental adjustment angle, wherein the predetermined incremental adjustment angle is less than both the outer angular dimension and the inner angular dimension.

9. The variable pitch fan blade system of claim 8 , wherein the predetermined incremental adjustment angle is about 0.25 degrees.

10. The variable pitch fan blade system of claim 9 , wherein the non-negative integer multiple is 2.

11. The variable pitch fan blade system of claim 10 , wherein X is 72 and Y is 137, wherein the outer angular dimension of each outer tooth is 5 degrees and the inner angular dimension of each inner tooth is 2.63 degrees.

12. The variable pitch fan blade system of claim 1 , further comprising:
a fan hub rotatable about an engine central longitudinal axis of a gas turbine engine;
a spring element disposed between the fan hub and the blade receiver, the spring element being biased to exert a radially outward force against the blade receiver; and
an annular retaining ring disposed around the radial axis and disposed between the fan hub and the blade receiver, the annular retaining ring configured to limit radially outward movement of the blade receiver.

13. The variable pitch fan blade system of claim 12 , wherein the annular retaining ring is circumferentially segmented.

14. The variable pitch fan blade system of claim 13 , wherein the annular retaining ring comprises a plurality of circumferential segments that are detachable from each other.

15. A gas turbine engine comprising:
a fan hub rotatable about an engine central longitudinal axis of the gas turbine engine;
a blade receiver for holding a fan blade, the blade receiver rotatably coupled to the fan hub and rotatable about a radial axis of the gas turbine engine;
a spring element disposed between the fan hub and the blade receiver, the spring element being biased to exert a radially outward force against the blade receiver;
a segmented annular retaining ring in direct engagement with the blade receiver, disposed around the radial axis, and disposed between the fan hub and the blade receiver, the segmented annular retaining ring configured to limit radially outward movement of the blade receiver to prevent the blade receiver from decoupling and disengaging from the fan hub, wherein the segmented annular retaining ring comprises a plurality of circumferential segments;
a variable pitch mechanism comprising an actuation arm, wherein the segmented annular retaining ring is in direct engagement with the actuation arm of the variable pitch mechanism; and
a splined index ring directly coupled between the actuation arm of the variable pitch mechanism and the blade receiver, wherein the splined index ring comprises an outer spline and an inner spline, wherein the blade receiver comprises a first ring spline engaging one of the outer spline and the inner spline and the actuation arm comprises a second ring spline engaging the other of the outer spline and the inner spline.

16. A method for adjusting an incidence angle of a fan blade, the fan blade being held by a blade receiver and the blade receiver being rotatable about a radial axis of a gas turbine engine, wherein a splined index ring is disposed between the blade receiver and an actuation arm of a variable pitch mechanism, the method comprising:
disengaging the blade receiver from the splined index ring;
after disengaging the blade receiver from the splined index ring, rotating the blade receiver relative to the splined index ring about the radial axis in a first direction;
after rotating the blade receiver, re-engaging the blade receiver to the splined index ring;
disengaging the splined index ring from the actuation arm of the variable pitch mechanism;
after disengaging the splined index ring from the actuation arm, rotating the splined index ring relative to the actuation arm about the radial axis in a second direction opposite the first direction; and
after rotating the splined index ring, re-engaging the splined index ring with the actuation arm.

17. The method of claim 16 , wherein:
rotating the blade receiver relative to the splined index ring comprises rotating the blade receiver relative to a first number of teeth of one of an outer spline and an inner spline of the splined index ring; and
rotating the splined index ring relative to the actuation arm produces a relative rotation of the actuation arm relative to a second number of teeth of the other of the outer spline and the inner spline of the splined index ring.

18. The method of claim 17 , wherein the outer spline comprises X circumferentially distributed outer teeth, each outer tooth of the outer teeth having an outer angular dimension that is

360
X

degrees and the inner spline comprises Y circumferentially distributed inner teeth, each inner tooth of the inner teeth having an inner angular dimension that is

360
Y

degrees, wherein a non-negative integer multiple of the lesser of the outer angular dimension and the inner angular dimension is equal to the higher of the outer a

Assignees

• United Technologies Corp

Inventors

• Kurz Leslie Charles

Classifications

• B64C11/065

  variable only when stationary · CPC title

• F01D17/162

  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

• B64C11/32

  mechanical · CPC title

• F01D5/3023

  of radial insertion type, e.g. in individual recesses · CPC title

• F05D2260/74

  by turning around an axis perpendicular the rotor centre line · CPC title