Airfoil with cavity damping

Patent metadata

Field	Value
Publication number	US-11339666-B2
Application number	US-202016851629-A
Country	US
Kind code	B2
Filing date	Apr 17, 2020
Priority date	Apr 17, 2020
Publication date	May 24, 2022
Grant date	May 24, 2022

Abstract

An article, such as a turbine blade, includes an airfoil. The airfoil includes a body, the body having an elongated internal cavity extending from a tip of the body. The cavity is defined an internal wall within the body. At least one elongated damping element is disposed in the elongated internal cavity and frictionally engages the internal wall. Thus, the least one elongated damping element is capable of damping vibrations in the article.

First claim

What is claimed is:

1. An article, the article comprising:
an airfoil, including:
a body, the body having an elongated internal cavity extending from a tip of the body, the cavity defined by an internal wall within the body;
at least one elongated damping element, the at least one elongated damping element disposed in the elongated internal cavity and frictionally engaging the internal wall, thus being capable of damping vibrations,
wherein the at least one elongated damping element includes at least one retention structural member, and the at least one elongated damping element being frictionally positioned in the elongated internal cavity by a friction fit of the at least one retention structural member against the internal wall of the cavity, and
the at least one elongated damping element disposed in the elongated internal cavity includes an impingement sleeve, and
wherein at least one retention member of the impingement sleeve includes at least one contact point protrusion on the impingement sleeve, the at least one contact point protrusion including a circular dimple, and each at least one contact point protrusion including the at least one retention structural member frictionally engaging the internal wall of the cavity.

2. The article of claim 1 , wherein the at least one contact point protrusion on the impingement sleeve further comprises a plurality of contact point protrusions on the impingement sleeve.

3. The article of claim 1 , wherein the airfoil includes a tip, a base, and a root, the base and root being at an opposite end of the airfoil from the tip, the cavity extends from the tip of the airfoil towards the base and the root, the at least one elongated damping element extends longitudinally from the tip toward the base and the root.

4. The article of claim 3 , wherein the at least one elongated damping element extends longitudinally from the tip and ends at or below the base.

5. The article of claim 3 , wherein the at least one elongated damping element extends longitudinally from the tip and extends into the root.

6. The article of claim 1 , where each of the at least one elongated damping element permits cooling fluid flow in the cavity and around each of the at least one elongated damping element, whereby amounts of cooling fluid flow in the cavity of airfoil are reduced by the at least one damping element positioned in the cavity.

7. The article of claim 1 , wherein the article includes a turbine blade in a turbine.

8. An article, the article comprising:
an airfoil, including:
a body, the body having an elongated internal cavity extending from a tip of the body, the cavity defined by an internal wall within the body;
at least one elongated damping element, the at least one elongated damping element disposed in the elongated internal cavity and frictionally engaging the internal wall, thus being capable of damping vibrations,
wherein the at least one elongated damping element includes at least one retention structural member, and the at least one elongated damping element being frictionally positioned in the elongated internal cavity by a friction fit of the at least one retention structural member against the internal wall of the cavity, and
wherein the airfoil comprises a tip and a base, the base being at an opposite end of the airfoil from the tip, the cavity extending from the tip of the airfoil towards the base,
wherein the airfoil further comprises at least one part-span shroud on the body, the at least one part-span shroud positioned between the tip and the base of the airfoil, the at least one elongated damping element extending from the tip of the airfoil and ending in the cavity at the part-span shroud.

9. The article of claim 8 , wherein the at least one part-span shroud further comprises at least one retention pin aperture, an impingement sleeve comprising at least one impingement sleeve through hole aligned with the at least one retention pin aperture, and
wherein the article further comprises a retention pin configured for extending through the at least one retention pin aperture in the at least one part-span shroud and the at least one impingement sleeve through hole of the impingement sleeve for securing the at least one impingement sleeve to the part-span shroud of the airfoil.

10. The article of claim 8 , wherein the at least one elongated damping element disposed in the elongated internal cavity includes an impingement sleeve.

11. The article of claim 10 wherein at least one retention member of the impingement sleeve includes at least one contact point protrusion on the impingement sleeve, each at least one contact point protrusion including the at least one retention structural member frictionally engaging the internal wall of the cavity.

12. The article of claim 11 , wherein the at least one contact point protrusion on the impingement sleeve further comprises a plurality of contact point protrusions on the impingement sleeve.

13. The article of claim 8 , wherein the airfoil includes a root, the base and root being at an opposite end of the airfoil from the tip, the cavity extends from the tip of the airfoil towards the base and the root, the at least one elongated damping element extends longitudinally from the tip toward the base and the root.

14. The article of claim 13 , wherein the at least one elongated damping element extends longitudinally from the tip and ends at or below the base.

15. The article of claim 13 , wherein the at least one elongated damping element extends longitudinally from the tip and extends into the root.

16. A turbine blade, the blade comprising:
an airfoil, including:
a body, the body having an elongated internal cavity extending from a tip of the body, the cavity defined by an internal wall within the body;
at least one elongated damping element, the at least one elongated damping element disposed in the elongated internal cavity and frictionally engaging the internal wall,
wherein the at least one elongated damping element disposed in the elongated internal cavity includes an impingement sleeve, and wherein at least one retention member of the impingement sleeve includes at least one contact point protrusion on the impingement sleeve, the at least one contact point protrusion including a circular dimple, and each at least one contact point frictionally engaging an internal wall of the cavity,
wherein the at least one elongated damping element includes at least one retention structural member, and the at least one elongated damping element being frictionally positioned in the elongated internal cavity by a friction fit of the at least one retention structural member against the internal wall of the cavity, and
the at least one elongated damping element in the elongated internal cavity includes an impingement sleeve, and
wherein at least one retention member of the impingement sleeve includes at least one contact point protrusion on the impingement sleeve, each at least one contact point protrusion including the at least one retention structural member frictionally engaging the internal wall of the cavity.

17. The turbine blade of claim 16 , wherein the airfoil includes a tip and a base, the base being at an opposite end of the airfoil from the tip, the cavity extending from the tip of the airfoil towards the base, and
wherein the airfoil further includes at least one part-span shroud on the body, the at least one part-span shroud positioned between the tip and the base of the airfoil, the at least one elongated damping element extending from the tip of the airfoil and ending in the cavity at t

Assignees

• Gen Electric

Inventors

• Hart Andrew Clifford
• Delvaux John Mcconnell
• Weber Joseph Anthony
• Zhang James
• De Diego Peter

Classifications

• F05D2250/185

  serpentine-like · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2260/202

  by film cooling · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F01D5/16 Primary

  for counteracting blade vibration · CPC title