Blade platform with damper restraint

Patent metadata

Field	Value
Publication number	US-10677073-B2
Application number	US-201715397519-A
Country	US
Kind code	B2
Filing date	Jan 3, 2017
Priority date	Jan 3, 2017
Publication date	Jun 9, 2020
Grant date	Jun 9, 2020

Abstract

A blade for a gas turbine engine is disclosed herein. The blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; a damper restraint located at a peripheral edge of the platform, wherein the damper restraint is a raised feature extending along at least a portion of the peripheral edge of the platform.

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 of the blade, wherein the platform defines a cavity;
a damper seal located in the cavity;
a damper restraint located at a peripheral edge of the platform, wherein the damper restraint comprises at least one raised feature extending along at least a portion of the peripheral edge of the platform, and the at least one raised feature has an uninterrupted profile that extends along an entire length of a top surface portion of the damper seal, the top surface portion extending past opposite sides of the at least one raised feature.

2. The blade as in claim 1 , wherein the at least one raised feature is a pair of raised features extending along at least a portion of opposing peripheral edges of the platform.

3. The blade as in claim 1 , wherein the damper restraint extends along a suction side of the platform.

4. The blade as in claim 1 , wherein the damper restraint extends along a pressure side of the platform.

5. The blade as in claim 1 , wherein the blade is a turbine blade.

6. The blade as in claim 1 , wherein the blade is a compressor blade.

7. A gas turbine engine, comprising:
a disk;
a plurality of blades secured to the disk, each of the plurality of blades having a root, and a platform located between the root and an airfoil of the blade, wherein a seam is defined by adjoining platforms of each of the plurality of blades when they are secured to the disk, the platform of each of the plurality of blades defining a cavity and having a damper restraint retaining movement of a damper seal received in the cavity, the damper seal covering the seam and a top surface portion of the damper seal engages the damper restraint, wherein the top surface portion of the damper seal extends past opposite sides of the damper restraint and the damper restraint is located at a peripheral edge of the platform of each of the plurality of blades, wherein the damper restraint comprises at least one raised feature extending along at least a portion of the peripheral edge of the platform, and the at least one raised feature has an uninterrupted profile that extends along an entire length of the top surface portion of the damper seal.

8. The gas turbine engine as in claim 7 , wherein the damper restraint of each of the plurality of blades extends along a suction side of the platform of each of the plurality of blades.

9. The gas turbine engine as in claim 7 , wherein the damper restraint of each of the plurality of blades extends along a pressure side of the platform of each of the plurality of blades.

10. The gas turbine engine as in claim 7 , wherein each of the plurality of blades are a turbine blade.

11. The gas turbine engine as in claim 7 , wherein each of the plurality of blades are a compressor blade.

12. The gas turbine engine as in claim 7 , wherein the damper seal of each of the plurality of blades is formed from stamped sheet metal and a top surface portion of the damper seal contacts the damper restraint of each of the plurality of blades.

13. The gas turbine engine as in claim 7 , wherein the damper restraint extends along a suction side of the platform and a pressure side of the platform.

14. A method of damping vibrations between adjoining blades of a gas turbine engine, comprising:
sealing a seam defined by adjoining platforms of the adjoining blades of the gas turbine engine by locating a damper seal over the seam wherein portions of a top surface portion of the damper seal extend past the seam and along underside surfaces of the adjoining 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 the damper seal with at least one protrusion extending along a peripheral edge of at least one of the adjoining platforms, wherein the at least one protrusion has an uninterrupted profile and extends along an entire length of the top surface portion of the damper seal.

15. The method as in claim 14 , wherein the damper seal is formed from stamped sheet metal and the adjoining blades are either compressor blades or turbine blades.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Thistle Charles
• Hassan Mohamed

Classifications

• F01D5/22 Primary

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

• F01D5/26 Primary

  Antivibration means not restricted to blade form or construction or to blade-to-blade connections {or to the use of particular materials} · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F01D11/006

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