Blade and airfoil damping configurations

Patent metadata

Field	Value
Publication number	US-11339665-B2
Application number	US-202016816568-A
Country	US
Kind code	B2
Filing date	Mar 12, 2020
Priority date	Mar 12, 2020
Publication date	May 24, 2022
Grant date	May 24, 2022

Abstract

The present embodiments set forth a blade including an airfoil, the airfoil including a tip cap, a pressure sidewall and a suction sidewall extending axially between corresponding leading and trailing edges and radially between the base and the tip cap. The blade, including the airfoil and base, being formed in at least two airfoil parts, each of the two airfoil parts including contacting edges engaging each other respective contacting edges, the contacting edges defining a joint for preloading each of the at least two parts with each other and with the base. The at least two airfoil parts forming the airfoil being retained to each other by an interference fit at the joint. The interference fit providing frictional damping of vibrations in the blade during blade operation.

First claim

What is claimed is:

1. A blade, the blade comprising:
a base;
an airfoil, the airfoil including a tip cap, a pressure sidewall and a suction sidewall extending axially between corresponding leading and trailing edges and radially between the base and the tip cap,
the blade, including the airfoil and the base, being formed in at least two airfoil parts, each of the at least two airfoil parts including contacting edges engaging other respective contacting edges, the contacting edges defining a joint for preloading each of the at least two parts with each other and with the base, the at least two airfoil parts each including a projection, each projection of the at least two airfoil parts including an extending lip aligned with each other and each projection of the at least two airfoil parts abutting at a contact face; and
wherein the at least two airfoil parts forming the airfoil are retained to each other by an interference fit at the joint, the interference fit providing frictional damping of vibrations in the blade during blade operation; wherein the interference fit includes a first bulbous male portion on one part of the at least two parts and a first female part in another part of the at least two parts, and the first male portion and the first female portion fit closely together in the interference fit.

2. A blade according to claim 1 , wherein the blade further includes at least one cooling passage exiting the blade at the tip cap at a cooling hole.

3. A blade according to claim 2 , wherein the first male portion and the first female portion are each positioned on the cooling hole.

4. A blade according to claim 3 , wherein the interference fit further includes a second bulbous male portion in the another part of the at least two parts and a second female part in the one part of the at least two parts, wherein the second male portion and the second female portion are each positioned on the cooling hole opposite the first male portion and the first female portion, and the second male portion and the second female portion fit closely together in the interference fit.

5. A blade according to claim 4 , wherein the airfoil includes two cooling holes at the tip cap, the interference fit further including projections including mating lips, the projections and the mating lips disposed between the two cooling holes at the tip cap, the interference fit including a male portion on one part of the at least two parts and a female part in another part of the at least two parts, wherein the male portion and the female portion are each positioned between the cooling holes, and the male portion and the female portion fit closely together in the interference fit.

6. A blade according to claim 3 , wherein the interference fit includes the first bulbous male portion on one part of the at least two parts and the first female part in another part of the at least two parts, and the first male portion and the first female portion fit closely together in the interference fit.

7. A blade according to claim 1 , wherein the blade includes two airfoil parts.

8. A blade according to claim 7 , wherein a first part of the two parts forms the leading edge, and a second part of the two parts forms the trailing edge.

9. A blade according to claim 7 , wherein one part of the two parts forms both the leading edge and the trailing edge.

10. A blade according to claim 7 , wherein a portion of each of the first part and the second part of the two parts form a portion of the leading edge and form a portion of the trailing edge.

11. A blade according to claim 10 , wherein the first part forming the leading edge and the trailing edge defines a slot on one of the pressure sidewall and suction sidewall, the second part of the airfoil disposed in the slot in the interference fit at the joint, the interference fit being capable of frictional damping of vibrations in the blade during blade operation.

12. A blade according to claim 1 , wherein the base of the blade is formed in at least two base parts, each of the at least two base parts being formed together with a corresponding part of the at least two airfoil parts.

13. A blade according to claim 12 , wherein the blade includes two airfoil parts connected to two base parts.

14. A blade according to claim 12 , wherein the blade includes four airfoil parts connected to four base parts, each of the four parts forming the blade and including contacting edges defining the joint with the interference fit at respective joints.

15. A blade according to claim 14 , wherein a first part of the four parts includes the leading edge of the airfoil, and a fourth part of the airfoil includes the trailing edge of the airfoil.

16. A blade according to claim 14 , wherein each of the four parts form the tip cap of the airfoil.

17. A turbine engine, the turbine engine comprising:
a blade including:
a base;
an airfoil, the airfoil including a tip cap, a pressure sidewall and a suction sidewall extending axially between corresponding leading and trailing edges and radially between the base and the tip cap,
the blade, including the airfoil and base, being formed in at least two airfoil parts, each of the two airfoil parts including contacting edges engaging each other respective contacting edges, the contacting edges defining a joint for preloading each of the at least two parts with each other and with the base, the at least two airfoil parts each including a projection, each projection of the at least two airfoil parts including an extending lip aligned with each other and each projection of the at least two airfoil parts abutting at a contact face; and
wherein the at least two airfoil parts forming the airfoil being retained to each other by an interference fit at the joint, the interference fit providing frictional damping of vibrations in the blade during turbine engine operation; wherein the interference fit includes a first bulbous male portion on one part of the at least two parts and a first female part in another part of the at least two parts, and the first male portion and the first female portion fit closely together in the interference fit.

18. A turbine engine according to claim 17 , wherein the base of the blade includes at least two base parts, each of the at least two base parts being formed together with a corresponding part of the at least two airfoil parts.

Assignees

• Gen Electric

Inventors

• Hart Andrew Clifford
• Li Jing
• Chakrabarti Suryarghya
• Balkcum Iii James Tyson
• Feigl Markus

Classifications

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title

• F01D5/22

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

• F01D5/225

  by shrouding · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F05D2260/221

  Improvement of heat transfer · CPC title