Gas turbine rotary blade with tip insert

Patent metadata

Field	Value
Publication number	US-9752441-B2
Application number	US-201213362968-A
Country	US
Kind code	B2
Filing date	Jan 31, 2012
Priority date	Jan 31, 2012
Publication date	Sep 5, 2017
Grant date	Sep 5, 2017

Abstract

A rotary blade is provided that includes a root, an airfoil, and a tip insert. The airfoil is attached to the root, and has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip. The slot extends in a chordwise direction between the leading edge and trailing edge. The tip insert has a base end and a rub end. The base end of the tip insert is disposed within the slot. The rub end of the tip insert extends radially outward from the airfoil tip.

First claim

What is claimed is:

1. A rotary blade, comprising:
a root,
an airfoil attached to the root, wherein the airfoil has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip, and wherein the slot extends in a chordwise direction between the leading edge and trailing edge; and
a tip insert having a base end and a rub end, the tip insert configured as a unitary and uninterrupted body;
wherein the base end of the tip insert is disposed within the slot, and the rub end of the tip insert extends radially outward from the airfoil tip;
wherein the tip insert and the airfoil are discretely formed bodies;
wherein the tip insert comprises metal and/or ceramic; and
wherein the slot is disposed in the tip between the pressure side surface and the suction side surface of the airfoil; and
wherein a portion of the slot extends to the pressure side surface of the rotary blade adjacent to the trailing edge of the blade.

2. The rotary blade of claim 1 , wherein the slot extends all the way between the leading edge and the trailing edge.

3. The rotary blade of claim 1 , further comprising a leading edge insert disposed at the leading edge of the rotary blade.

4. The rotary blade of claim 1 , wherein the airfoil comprises aluminum, and the tip insert comprises anodized aluminum, titanium and/or ceramic.

5. The rotary blade of claim 1 , wherein the slot is substantially rectangular-shaped.

6. The rotary blade of claim 1 , wherein at least a portion of the slot is arcuately shaped.

7. The rotor blade of claim 1 , wherein the tip insert is made of a material with a greater durability than a material from which the airfoil is made.

8. A rotary blade, comprising:
a root,
an airfoil attached to the root, wherein the airfoil has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip, and wherein the slot extends in a chordwise direction between the leading edge and trailing edge;
a tip insert having a base end and a rub end, the tip insert configured as a unitary and uninterrupted body; and
a leading edge insert disposed at the leading edge of the rotary blade;
wherein the base end of the tip insert is disposed within the slot, and the rub end of the tip insert extends radially outward from the airfoil tip;
wherein the tip insert and the airfoil are discretely formed bodies;
wherein the tip insert comprises metal and/or ceramic; and
wherein the leading edge insert extends chordwise along a first portion of the tip for a first distance, the tip insert extends chordwise along a second portion of the tip for a second distance, and a sum of the first distance and the second distance is equal to or greater than a chordlength of the airfoil tip.

9. A rotary blade tip insert for a rotary blade having an airfoil that has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip, wherein the slot extends in a chordwise direction between the leading edge and trailing edge, the tip insert comprising:
a unitary and uninterrupted body having a width extending radially between an inner surface of a base end and an outer surface of a rub end, and a length extending between a forward end and an aft end;
wherein the base end is configured to be received within the slot and the rub end is configured to extend radially outward from the airfoil tip;
wherein the tip insert comprises metal and/or ceramic;
wherein the tip insert is at least one of welded or brazed to the airfoil;
wherein the slot is disposed in the tip between the pressure side surface and the suction side surface; and
wherein a portion of the slot extends to the pressure side surface adjacent to the trailing edge.

10. The rotary blade tip insert of claim 9 , wherein the length of the tip insert is substantially equal to the chordwise distance between the leading edge and the trailing edge of the airfoil.

11. The rotary blade tip insert of claim 9 , wherein the tip insert comprises anodized aluminum, titanium and/or ceramic.

12. The rotary blade tip insert of claim 9 , wherein a widthwise cross-section of the tip insert is substantially rectangular-shaped.

13. The rotary blade tip insert of claim 9 , wherein at least a portion of a width-wise cross-section of the tip insert is arcuately shaped.

14. A rotary blade assembly within a gas turbine engine, the assembly comprising:
a plurality of rotary blades extending radially outwardly from a hub, each of the rotor blades having a tip insert and an airfoil that has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip, wherein the slot extends in a chordwise direction between the leading edge and trailing edge, wherein the tip insert has a base end and a rub end, and wherein the base end of the tip insert is disposed within the slot, and the rub end of the tip insert extends radially outward from the airfoil tip; and
a containment case disposed radially outside of the rotary blades and circumferentially surrounding the plurality of blades, wherein the containment case includes an abradable blade outer air seal;
wherein the tip insert and the airfoil are discretely formed bodies;
wherein the tip insert comprises metal and/or ceramic, and the tip insert is configured as an integrally formed body;
wherein the tip insert is at least one of welded or brazed to the airfoil;
wherein the slot is disposed in the tip between the pressure side surface and the suction side surface; and
wherein a portion of the slot extends to the pressure side surface adjacent to the trailing edge.

15. The rotary blade assembly of claim 14 , wherein the plurality of rotary blades are fan blades.

16. The rotary blade assembly of claim 14 , wherein the airfoil comprises aluminum, and the tip insert comprises anodized aluminum, titanium and/or ceramic.

17. The rotary blade assembly of claim 14 , wherein the slot in each of the plurality of rotary blades is at least partially arcuately shaped.

18. The rotary blade assembly of claim 14 , wherein the plurality of rotary blades are compressor blades.

19. The rotary blade assembly of claim 14 , wherein the plurality of rotary blades are turbine blades.

Assignees

• Hildebrand Gregory C
• Hansen James O
• Parkos Jr Joseph
• Weisse Michael A
• Hertel Christopher J
• Meyer Jesse
• United Technologies Corp

Inventors

• Hildebrand Gregory C
• Hansen James O
• Parkos Jr Joseph
• Weisse Michael A
• Hertel Christopher J
• Meyer Jesse

Classifications

• F01D5/20 Primary

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• F01D11/122

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title