Morphing structures for fan inlet variable vanes

Patent metadata

Field	Value
Publication number	US-11655778-B2
Application number	US-202117396050-A
Country	US
Kind code	B2
Filing date	Aug 6, 2021
Priority date	Aug 6, 2021
Publication date	May 23, 2023
Grant date	May 23, 2023

Abstract

A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.

First claim

What is claimed is:

1. A vane system for a gas turbine engine comprising:
a plurality of vane assemblies spaced circumferentially about an engine axis, the vane assemblies each including:
an airfoil extending between a leading edge and a trailing edge, the trailing edge comprising a plurality of radial segments interspaced by deformable supports, and
a control rod extending through the airfoil and driving the plurality of radial segments to change the shape of the trailing edge; and

wherein one of the control rod and the radial segments include a plurality of protrusions and the other includes angled slots receiving the protrusions.

2. A gas turbine engine comprising:
a fan section, a compressor section, and a turbine section;
a plurality of vane assemblies spaced circumferentially about an engine axis, the vane assemblies each including:
an airfoil extending between a leading edge and a trailing edge, wherein the trailing edge comprises a plurality of radial segments interspaced by deformable supports, and
a control rod extending through the airfoil and driving the radial segments to change the shape of the trailing edge; and

wherein the radial segments are one of metal, carbon fiber, and ceramic, and the deformable supports are formed of an elastomeric material comprising at least one of polyurethane, isoprene, silicone, and fluroelastomer.

3. The gas turbine engine of claim 2 , wherein the control rod drives the plurality of radial segments to pivot from an initial position to a morphed position in which the radial segments each have a different angle relative to the leading edge.

4. The gas turbine engine of claim 3 , wherein one of the control rod and the radial segments includes a plurality of protrusions and the other includes angled slots receiving the protrusions.

5. The gas turbine engine of claim 4 , wherein the control rod includes the plurality of protrusions and each radial segment includes an angled slot receiving a protrusion.

6. The gas turbine engine of claim 4 , wherein the control rod translates radially within the airfoil such that the protrusions slide within the angled slots driving the radial segments to pivot into the morphed position.

7. The gas turbine engine of claim 2 , wherein the airfoil includes a pressure side and a suction side, and a flexible skin surrounds the pressure side and suction side.

8. The gas turbine engine of claim 7 , wherein the flexible skin is comprised of one of ethylene propylene diene monomer, synthetic rubber, and thermoplastic polyurethane.

9. The gas turbine engine of claim 7 , wherein the flexible skin on the pressure side slides relative to the flexible skin on the suction side when the airfoil changes shape.

10. The gas turbine engine of claim 2 , further including a single synchronization ring that drives the control rod of each vane assembly to change the shape of each airfoil simultaneously.

11. The gas turbine engine of claim 2 , further comprising a first and second synchronization ring driving control rods of a first and second subset of the plurality of vane assemblies respectively, wherein the first and second synchronization rings drive the control rods to change the shape of the airfoils in the first and second subset independently.

12. The gas turbine engine of claim 2 , wherein the control rod of each of the plurality of vane assemblies is driven by a separate actuator to change the shape of each airfoil independently.

13. The gas turbine engine of claim 2 , further comprising a controller controlling actuation of the control rods, the controller actuating the control rods to change the shape of the airfoils in response to a change in operating conditions.

14. The gas turbine engine of claim 13 , wherein the controller controls actuation of at least one synchronization ring, the at least one synchronization ring driving the control rod of each of the vane assemblies and driving a flap portion of each airfoil to pivot about an airfoil axis.

15. The gas turbine engine of claim 13 , wherein the controller drives the plurality of vane assemblies into a non-axisymmetric configuration in response to non-axisymmetric fan inlet conditions.

16. The gas turbine engine of claim 2 , wherein the vane assemblies further include a bell-crank mechanism driving a flap portion of the airfoil to pivot about an airfoil axis and driving the control rod to change the shape of the trailing edge.

17. The gas turbine engine of claim 2 , wherein the plurality of vane assemblies are located in the fan section.

18. The gas turbine engine of claim 2 , wherein the plurality of vane assemblies are located in the compressor section.

19. A vane system for a gas turbine engine comprising:
a plurality of vane assemblies spaced circumferentially about an engine axis, the vane assemblies each including:
an airfoil extending between a leading edge and a trailing edge, the trailing edge comprising a plurality of radial segments interspaced by deformable supports, and
a control rod extending through the airfoil and driving the plurality of radial segments to pivot from an initial position to a morphed position in which the radial segments each have a different angle relative to the leading edge; and

wherein the radial segments are one of metal, carbon fiber, and ceramic, and the deformable supports are formed of an elastomeric material comprising at least one of polyurethane, isoprene, silicone, and fluroelastomer.

20. The vane system of claim 19 , wherein one of the control rod and the radial segments includes a plurality of protrusions and the other includes angled slots receiving the protrusions, and the control rod translates radially within the airfoil such that the protrusions slide within the angled slots driving the radial segments into the morphed position.

Assignees

• Raytheon Tech Corp

Inventors

• Joly Michael M
• Chaudhry Zaffir A
• Kuczek Andrzej Ernest
• Sharma Om P
• Kalitzin Georgi
• Evans Simon W

Classifications

• F02C9/58

  with control of a variable-pitch propeller · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F02K3/06 Primary

  with front fan · CPC title

• F02C9/20

  by throttling; by adjusting vanes · CPC title

• 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