US 2003/0194324 A1 · Turbine blade assembly with pin dampers

Abstract

A turbine blade assembly for a turbine assembly includes a turbine blade having a turbine blade damper cavity formed therein and a plurality of pins positioned within the turbine blade damper cavity. The pins are maintained in the damper cavity during operation of the turbine blade assembly. They reduce vibration of the turbine blade assembly during operation by dissipating energy by friction between adjacent pins and between the pins and the internal surface of the blade that defines the damper cavity.

Drawings

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Drawings

Claims39

Dependent claims

A turbine blade assembly for a turbine assembly, said turbine assembly being rotatable about a central axis, said turbine blade assembly, comprising:

a) a turbine blade, having an internal surface defining a turbine blade damper cavity formed therein;
and
b) a plurality of pins positioned within said turbine blade damper cavity, said pins being contained within each turbine blade damper cavity during operation of the turbine blade assembly,
wherein said plurality of pins reduce vibration of the turbine blade assembly during operation by dissipating energy by friction between adjacent of said pins and between said pins and said internal surface.

1 more element

Dependencies are inferred from the claim text.

Description2,247 words

Summary1,415 words

#1. Field of the Invention

#The present invention relates to turbines and, more particularly, to the vibration damping of turbine blades thereof.

#2. Description of the Related Art

Brief description of the drawings4 figures

#FIG. 1 is an end view of a preferred embodiment of the turbine blade assembly of the present invention.

#FIG. 2 is a cross-sectional view of the embodiment of FIG. 1, shown along Line 2-2 of FIG. 1.

#FIG. 3 is an end view of another embodiment of the turbine blade assembly of the present invention.

Detailed description757 words

#The same parts or elements throughout the drawings are designated by the same reference characters.

#Referring now to the drawings in the character's reference marked thereon, FIGS. 1 and 2 illustrate a preferred embodiment of the turbine blade assembly of the present invention, designated generally as 10. The turbine blade assembly 10 includes a turbine disk 12 that supports a turbine blade 14. The turbine blade 14 has an internal surface 16 defining a turbine blade damper cavity. The turbine blade damper cavity 16 extends from an opening in the distal end, i.e. tip 18, of the turbine blade 14 opposite the turbine disk 12. Damper cavity 16 may, for example, be cylindrical and extend into the turbine blade 14 substantially parallel to or along a longitudinal axis 20 of the turbine blade 14. The turbine blade longitudinal axis 20 extends substantially radially outward, i.e. radial outward or near radial outward, from the central axis of the turbine. Thus, the turbine blade longitudinal axis 20 extends in a range of about 0°-10° from the radially outward direction from the central axis. The turbine blade damper cavity 16 extends in a range of about 0°-45° from the turbine blade longitudinal axis 20.

#Pins 22 are positioned within the turbine blade damper cavity 16. The pins may have circular cross-sections but are not restricted to be of circular cross-section. They can be square, hexagonal or any other suitable shape that dissipates energy by friction within the pin bundle as well as between the walls of the cavity 16 and the outer pins in the pin bundle.

Facts

Application

10/120,584Filed 11 Apr 2002

Published

16 Oct 2003

Term ends

Not estimatedThe source records don’t support an estimate.

Classification4 codes

F01D 5/26
Blades: antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
Y10S 416/50
Fluid reaction surfaces, i.e. impellers: vibration damping features
F01D
Non-positive displacement machines or engines
Y10S
Technical subjects covered by former uspc cross-reference art collections [xracs] and digests

Timeline

10 Apr 2002Assigned to Boeing Company, theassignment of assignor's interest
11 Apr 2002Application filedUS 10/120,584
16 Oct 2003Published
27 Mar 2006Assigned to United Technologies Corporationassignment of assignor's interest
16 May 2006Assigned to United Technologies Corporationassignment of assignor's interest
12 Jun 2013Assigned to Ruby Acquisition Enterprises Co.corrective assignment to correct the assignee's name on original cover sheet previously recorded on reel 017882 frame 0126. assignor(s) hereby confirms the assignee was incorrectly recorded as "united technologies corporation". assignee should be "ruby acquisition enterprises co.".
12 Jun 2013Assigned to Pratt & Whitney Rocketdyne, Inc.change of name
17 Jun 2013Assigned to Wells Fargo Bank, National Associationsecurity agreement
21 Jun 2013Assigned to U.S. Bank National Associationsecurity agreement
8 May 2014Assigned to Aerojet Rocketdyne of De, Inc.change of name
20 Jun 2016Assigned to Bank of America, N.A., AS the Successor Agentnotice of succession of agency (intellectual property)
5 Aug 2016Assigned to Aerojet Rocketdyne of De, Inc. (F/K/A Pratt & Whitney Rocketdyne, Inc.)release of security interest
28 Jul 2023Assigned to Aerojet Rocketdyne of De, Inc. (F/K/A Pratt & Whitney Rocketdyne, Inc.)termination and release of security interest in patents

Turbine blade assembly with pin dampers

Life of this patent

Turbine blade assembly with pin dampers

Life of this patent

Life of this patent

Abstract

Drawings

Drawings

Claims39

Description2,247 words

Drawings

Description2,247 words

Classification4 codes

Life of this patent