Airfoil tip geometry to reduce blade wear in gas turbine engines

Patent metadata

Field	Value
Publication number	US-10633983-B2
Application number	US-201615063048-A
Country	US
Kind code	B2
Filing date	Mar 7, 2016
Priority date	Mar 7, 2016
Publication date	Apr 28, 2020
Grant date	Apr 28, 2020

Abstract

An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and a trailing edge, the leading edge and the trailing edge define a chord distance. The airfoil includes a tip portion extending between the pressure sidewall and the suction sidewall. The tip portion includes a planar section and a recessed section. The recessed section extends adjacent to the planar section such that a thickness of the planar section is less than a thickness of the airfoil. The recessed section is offset a predetermined distance from the leading edge and the trailing edge along the chord distance.

First claim

What is claimed is:

1. An airfoil for use in a turbomachine, said airfoil comprising:
a pressure sidewall;
a suction sidewall coupled to said pressure sidewall, wherein said suction sidewall and said pressure sidewall define a leading edge and a trailing edge, wherein said leading edge and said trailing edge define a chord distance; and
a tip portion extending between said pressure sidewall and said suction sidewall, said tip portion comprising at least one planar section, said at least one planar section comprising a first section having a first thickness and a second section having a second thickness, wherein the second thickness is substantially equal to a thickness of said airfoil, said second section located at or about a mid-chord distance between and distanced from said leading edge and said trailing edge, said first section defining at least one recessed section, said at least one recessed section extending between said at least one planar section and said suction sidewall such that said pressure sidewall extends to said at least one planar section, said at least one recessed section offset from said leading edge and said trailing edge along the chord distance, wherein the first thickness is less than the second thickness.

2. The airfoil in accordance with claim 1 , wherein a cross-sectional area of said planar section is within a range of between and including approximately 40% and approximately 70% less than a cross-sectional area of said airfoil and configured to reduce a contact area of said tip portion and a surrounding casing to decrease airfoil wear during contact with the surrounding casing.

3. The airfoil in accordance with claim 1 , wherein said at least one recessed section is offset from said leading edge within a range between and including approximately 15% and approximately 30% of the chord distance.

4. The airfoil in accordance with claim 1 , wherein said at least one recessed section is offset from said trailing edge within a range between and including approximately 15% and approximately 30% of said chord distance.

5. The airfoil in accordance with claim 1 , wherein said at least one recessed section is offset from said leading edge within a range between and including approximately 15% and approximately 30% of the chord distance and offset from said trailing edge within a range between and including approximately 15% and approximately 30% of the chord distance.

6. The airfoil in accordance with claim 1 , wherein said at least one recessed section comprises a first recessed section offset from said leading edge, wherein said first section further defines a second recessed section offset from said trailing edge, wherein said first recessed section is separate from said second recessed section.

7. The airfoil in accordance with claim 6 , wherein said second recessed section extends between said at least one planar section and said pressure sidewall.

8. The airfoil in accordance with claim 1 , wherein said at least one planar section comprises a pressure section adjacent said pressure side and a suction section adjacent said suction side, wherein said at least one recessed section is substantially U-shaped extending between said pressure section and said suction section.

9. The airfoil in accordance with claim 1 , wherein said recessed section extends substantially perpendicular from said at least one planar section within a range between and including approximately 0.8 millimeters (mm) and approximately 1 mm.

10. The airfoil in accordance with claim 1 , wherein said at least one planar section has a substantially uniform thickness except for the second thickness of said second section.

11. A turbomachine comprising:
a casing;
a rotor assembly, said casing at least partially extending about said rotor assembly, said rotor assembly comprising:
a rotor shaft; and
a plurality of rotor blades coupled to said rotor shaft, each rotor blade of said plurality of rotor blades comprising an airfoil comprising a pressure sidewall and a suction sidewall coupled to said pressure sidewall, wherein said suction sidewall and said pressure sidewall define a leading edge and a trailing edge, wherein said leading edge and said trailing edge define a chord distance, said airfoil further comprising a tip portion extending between said pressure sidewall and said suction sidewall, said tip portion comprising at least one planar section, said at least one planar section comprising a first section having a first thickness and a second section having a second thickness, wherein the second thickness is substantially equal to a thickness of said airfoil, said second section located at or about a mid-chord distance between and distanced from said leading edge and said trailing edge, said first section defining at least one recessed section, said at least one recessed section extending between said at least one planar section and said suction sidewall such that said pressure sidewall extends to said at least one planar section, said at least one recessed section offset from said leading edge and said trailing edge along the chord distance, wherein the first thickness is less than the second thickness.

12. The turbomachine in accordance with claim 11 , wherein a cross-sectional area of said planar section is within a range between and including approximately 40% and approximately 70% less than a cross-sectional area of said airfoil.

13. A method of assembling a turbomachine, the turbomachine including a casing, a rotor shaft, and a plurality of rotor blades, each rotor blade of the plurality of rotor blades including an airfoil including a pressure sidewall and a suction sidewall coupled to the pressure sidewall, wherein the suction sidewall and the pressure sidewall define a leading edge and a trailing edge, wherein the leading edge and the trailing edge define a chord distance, the airfoil further including a tip portion extending between the pressure sidewall and the suction sidewall, said method comprising:
forming at the tip portion at least one planar section including a first section having a first thickness and a second section having a second thickness, the second thickness substantially equal to a thickness of said airfoil, said second section located at or about a mid-chord distance between and distanced from said leading edge and said trailing edge, said first section defining at least one recessed section adjacent said at least one planar section, wherein said at least one recessed section is offset from said leading edge and said trailing edge along the chord distance, wherein the first thickness is less than the second thickness; and
coupling the rotor blade to the rotor shaft such that during turbomachine operation when the tip portion contacts the casing wear of the rotor blade is reduced,
wherein forming the at least one planar section further comprises removing blade material from the suction sidewall to define the at least one recessed section.

14. An airfoil for use in a turbomachine, said airfoil comprising:
a pressure sidewall;
a suction sidewall coupled to said pressure sidewall, wherein said suction sidewall and said pressure sidewall define a leading edge and a trailing edge, wherein said leading edge and said trailing edge define a chord distance; and
a tip portion extending between said pressure sidewall and said suction sidewall, said tip portion comprising at least one planar section, said at least one planar section comprising a first section having a first thickness and a second section having a second thickness, wherein the second thickness is substantially equal to a thickness of said airfoil, said second section loc

Assignees

• Gen Electric

Inventors

• Barua Ananda
• Sarawate Neelesh Nandkumar
• Lewis Kenneth Martin
• Sun Changjie
• Mukherjee Yu Xie
• Raghavan Sathyanarayanan

Classifications

• F01D5/20 Primary

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

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• F05D2230/10

  by removing material · CPC title

• F01D11/08

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F05D2250/75

  given by its similarity to a letter, e.g. T-shaped · CPC title