Blade platform with damper restraint

Patent metadata

Field	Value
Publication number	US-10731479-B2
Application number	US-201715397557-A
Country	US
Kind code	B2
Filing date	Jan 3, 2017
Priority date	Jan 3, 2017
Publication date	Aug 4, 2020
Grant date	Aug 4, 2020

Abstract

A blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; a damper restraint retaining a lateral edge of a damper seal received in the cavity, wherein the lateral edge of the damper seal extends between a first end portion and an opposing second end portion of the damper seal, the first end portion and the second end portion extend towards the root when the damper seal is located in the cavity and wherein the damper restraint extends along and adjacent to a portion of the lateral edge of the damper seal.

First claim

What is claimed is:

1. A blade for a gas turbine engine, comprising:
a root;
a platform located between the root and an airfoil, wherein the platform defines a cavity;
a damper seal supported by a first radially inner surface of the platform;
a groove in the first radially inner surface, the groove having a groove bottom radially outward of the first radially inner surface, wherein the groove is positioned such that a lateral edge of the damper seal enters the groove as the damper seal moves circumferentially toward the root.

2. The blade as in claim 1 , wherein the groove extends along an entire length of the lateral edge of the damper seal.

3. The blade as in claim 1 , wherein the groove is located on a suction side of the blade.

4. The blade as in claim 1 , wherein the groove is located on a pressure side of the blade.

5. The blade as in claim 1 , wherein the damper seal is formed from stamped sheet metal and wherein the blade is either a turbine blade or a compressor blade.

6. A disc of a gas turbine engine having a plurality of blades, each of the plurality of blades comprising:
a root;
a platform located between the root and an airfoil, wherein the platforms of adjacent blades of the plurality of blades are located adjacent to each other in order to define a cavity; and
a single damper restraint located on a suction side of the blade, wherein only the single damper restraint retains any lateral edge of a damper seal when the damper seal is received in the cavity and spans across a seam between adjacent platforms such that portions of the damper seal extend past the seam and along an underside of the adjacent platforms, the lateral edge of the damper seal extending between a first end portion and an opposing second end portion of the damper seal, the first end portion and the second end portion extend towards the root when the damper seal is located in the cavity and is covering the seam and wherein the damper restraint extends along and is adjacent to a portion of the lateral edge of the damper seal when the damper seal is covering the seam.

7. The blade disc as in claim 6 , wherein the single damper restraint extends along an entire length of the lateral edge of the damper seal.

8. The blade disc as in claim 6 , wherein the single damper restraint is a protrusion that extends away from an interior surface of the platform.

9. The disc as in claim 6 , wherein the single damper restraint is a rail extending away from an interior surface of the platform that is configured to mirror a contour of the lateral edge of the damper seal.

10. The blade disc as in claim 6 , wherein the single damper restraint is a groove formed in an interior surface of the platform.

11. The blade disc as in claim 6 , wherein the damper seal is formed from stamped sheet metal and wherein the blade is either a turbine blade or a compressor blade.

12. A method of damping vibrations between adjacent blades of a gas turbine engine, comprising:
sealing a seam defined by adjacent platforms of a pair of blades of a disc of the gas turbine engine by locating a damper seal over the seam wherein portions of the damper seal extend past the seam and along underside surfaces of the adjacent platforms when the damper seal is located over the seam; and
restraining movement of the damper seal in a direction away from the seam by retaining only a single lateral edge of the damper seal with a damper restraint formed in the underside surface of one of the adjacent platforms of the pair of blades, wherein the one of the adjacent platforms of the pair of blades extends from a suction side of one of the pair of blades.

13. The method as in claim 12 , wherein the pair of blades are either a pair of turbine blades or a pair of compressor blades.

14. The method as in claim 12 , wherein the damper restraint is a plurality of protrusions that extend away from an interior surface of the platform.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Thistle Charles
• Hassan Mohamed

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F01D11/006

  Sealing the gap between rotor blades or blades and rotor · CPC title

• Y10S416/50

  Vibration damping features · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D5/22 Primary

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