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Title: Compressive stress system for a gas turbine engine

Abstract

The present application provides a compressive stress system for a gas turbine engine. The compressive stress system may include a first bucket attached to a rotor, a second bucket attached to the rotor, the first and the second buckets defining a shank pocket therebetween, and a compressive stress spring positioned within the shank pocket.

Inventors:
Issue Date:
Research Org.:
General Electric Co., Schenectady, NY (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1174213
Patent Number(s):
8985956
Application Number:
13/235,566
Assignee:
General Electric Company (Schenectady, NY)
Patent Classifications (CPCs):
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F - MECHANICAL ENGINEERING F05 - INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04 F05D - INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
DOE Contract Number:  
FC26-05NT42643
Resource Type:
Patent
Resource Relation:
Patent File Date: 2011 Sep 19
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Hogberg, Nicholas Alvin. Compressive stress system for a gas turbine engine. United States: N. p., 2015. Web.
Hogberg, Nicholas Alvin. Compressive stress system for a gas turbine engine. United States.
Hogberg, Nicholas Alvin. Tue . "Compressive stress system for a gas turbine engine". United States. https://www.osti.gov/servlets/purl/1174213.
@article{osti_1174213,
title = {Compressive stress system for a gas turbine engine},
author = {Hogberg, Nicholas Alvin},
abstractNote = {The present application provides a compressive stress system for a gas turbine engine. The compressive stress system may include a first bucket attached to a rotor, a second bucket attached to the rotor, the first and the second buckets defining a shank pocket therebetween, and a compressive stress spring positioned within the shank pocket.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Mar 24 00:00:00 EDT 2015},
month = {Tue Mar 24 00:00:00 EDT 2015}
}

Works referenced in this record:

Resonator device for damping the vibrations of a rotor of a rotary-wing aircraft
patent, August 1981


Rotors for gas turbine engines
patent, April 1987


Turbofan with dynamic vibration damping
patent, September 1992


Rotor blade with platform support and damper positioning means
patent, February 1994


Composite fan platform
patent, April 2001


Turbine blade arrangement
patent, May 2008


Composite blading member and method for making
patent, March 2009


Bi-layer tip cap
patent, July 2009