Airfoil assembly with tensioned blade segments

Patent metadata

Field	Value
Publication number	US-12018586-B2
Application number	US-202218081151-A
Country	US
Kind code	B2
Filing date	Dec 14, 2022
Priority date	Sep 6, 2022
Publication date	Jun 25, 2024
Grant date	Jun 25, 2024

Abstract

An airfoil assembly extends along a radial direction between a root and a tip, the airfoil assembly comprising: a first blade segment positioned proximate the root of the airfoil assembly; a second blade segment positioned adjacent the first blade segment along the radial direction; and a tensioning assembly comprising a plurality of tensioning strings that extend between and mechanically couple the first blade segment and the second blade segment.

First claim

We claim:

1. An airfoil assembly extending along a radial direction between a root and a tip, the airfoil assembly comprising:
a first blade segment positioned proximate the root of the airfoil assembly;
a second blade segment positioned adjacent the first blade segment along the radial direction; and
a tensioning assembly comprising a plurality of tensioning strings that extend between and mechanically couple the first blade segment and the second blade segment,
wherein the plurality of tensioning strings comprises an outer string and a core string, wherein the outer string is formed from a different material than the core string.

2. The airfoil assembly of claim 1 , wherein the plurality of tensioning strings is spaced apart along a camber line of the airfoil assembly.

3. The airfoil assembly of claim 1 , wherein the plurality of tensioning strings comprises twisted or braided strands.

4. The airfoil assembly of claim 1 , wherein the plurality of tensioning strings further comprises:
one or more outer strings positioned proximate at least one of a leading edge or a trailing edge of the airfoil assembly, the outer string being one of the one or more outer strings; and
one or more core strings positioned interior to the one or more outer strings within the airfoil assembly, the core string being one of the one or more core strings, wherein the one or more outer strings are formed from a different material, have a different construction than the one or more core strings, or both.

5. The airfoil assembly of claim 1 , wherein at least one of the plurality of tensioning strings extends at an angle relative to the radial direction.

6. The airfoil assembly of claim 1 , wherein the tensioning assembly further comprises:
an inner tensioning retainer positioned proximate the root of the airfoil assembly such that the first blade segment is positioned between the inner tensioning retainer and the second blade segment along the radial direction, wherein the plurality of tensioning strings is anchored to the inner tensioning retainer.

7. The airfoil assembly of claim 1 , wherein the tensioning assembly further comprises:
an outer tensioning retainer embedded within the second blade segment proximate the tip of the airfoil assembly, wherein the plurality of tensioning strings is anchored to the outer tensioning retainer.

8. The airfoil assembly of claim 1 , wherein the tensioning assembly further comprises:
an intermediate tensioning retainer positioned within the first blade segment or the second blade segment.

9. The airfoil assembly of claim 1 , wherein the tensioning assembly further comprises:
one or more side strings that extend between a leading edge and a trailing edge of the airfoil assembly.

10. The airfoil assembly of claim 9 , wherein the one or more side strings are attached to the plurality of tensioning strings or are embedded in at least one of the first blade segment or the second blade segment.

11. The airfoil assembly of claim 9 , wherein at least one of the one or more side strings has a first end positioned within the first blade segment and a second end positioned within the second blade segment.

12. The airfoil assembly of claim 1 , further comprising:
a third blade segment positioned between the first blade segment and the second blade segment along the radial direction, wherein the tensioning assembly passes through the third blade segment.

13. The airfoil assembly of claim 1 , wherein an outer radial end of the first blade segment defines a locking protrusion and an inner radial end of the second blade segment defines a complementary recess for receiving the locking protrusion of the first blade segment.

14. The airfoil assembly of claim 1 , further comprising:
a frangible blade tip positioned at the tip of the airfoil assembly, wherein the tensioning assembly is connected to the frangible blade tip.

15. The airfoil assembly of claim 14 , wherein the frangible blade tip comprises a plurality of adjacently positioned tip segments.

16. The airfoil assembly of claim 15 , wherein each of the plurality of tip segments define an aperture, and wherein a dowel passes through the aperture of each of the plurality of tip segments to join the plurality of tip segments.

17. The airfoil assembly of claim 1 , further comprising:
a blade skin positioned around the first blade segment, the second blade segment, and the tensioning assembly.

18. A method of manufacturing an airfoil assembly, the method comprising:
positioning a first blade segment of the airfoil assembly adjacent to a second blade segment of the airfoil assembly along a radial direction; and
joining the first blade segment and the second blade segment using a tensioning assembly, the tensioning assembly comprising a plurality of tensioning strings that extend along the radial direction between the first blade segment and the second blade segment,
wherein the plurality of tensioning strings comprises an outer string and a core string, wherein the outer string is formed from a different material than the core string.

19. The method of claim 18 , further comprising:
positioning the first blade segment against an inner tensioning retainer; and
anchoring the plurality of tensioning strings to the inner tensioning retainer such that the first blade segment is positioned between the inner tensioning retainer and the second blade segment along the radial direction.

20. The method of claim 18 , further comprising:
positioning a blade skin around the first blade segment, the second blade segment, and the tensioning assembly.

Assignees

• Gen Electric

Inventors

• Yamarthi David Raju
• Ganiger Ravindra Shankar
• Balaramudu Vasanth Kumar
• Tatiparthi Vishnu Vardhan Venkata
• Jain Nitesh
• Buravalla Vidyashankar Ramasastry

Classifications

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F04D29/388

  characterised by construction · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F01D5/24

  using wire or the like · CPC title

• F01D5/22

  Blade-to-blade connections, {e.g. for damping vibrations} · CPC title