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Title: Turbine and method for reducing shock losses in a turbine

Abstract

A turbine includes a rotor and a casing that circumferentially surrounds at least a portion of the rotor. The rotor and the casing at least partially define a gas path through the turbine. A last stage of rotating blades is circumferentially arranged around the rotor and includes a downstream swept portion radially outward from the rotor. A method for reducing shock losses in a turbine includes removing a last stage of rotating blades circumferentially arranged around a rotor and replacing the last stage of rotating blades with rotating blades having a downstream swept portion radially outward from the rotor.

Inventors:
Issue Date:
Research Org.:
General Electric Co., Schenectady, NY (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1344792
Patent Number(s):
9121285
Application Number:
13/479,935
Assignee:
GENERAL ELECTRIC COMPANY (Schenectady, NY)
Patent Classifications (CPCs):
Y - NEW / CROSS SECTIONAL TECHNOLOGIES Y10 - TECHNICAL SUBJECTS COVERED BY FORMER USPC Y10T - TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
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: 2012 May 24
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Ristau, Neil. Turbine and method for reducing shock losses in a turbine. United States: N. p., 2015. Web.
Ristau, Neil. Turbine and method for reducing shock losses in a turbine. United States.
Ristau, Neil. Tue . "Turbine and method for reducing shock losses in a turbine". United States. https://www.osti.gov/servlets/purl/1344792.
@article{osti_1344792,
title = {Turbine and method for reducing shock losses in a turbine},
author = {Ristau, Neil},
abstractNote = {A turbine includes a rotor and a casing that circumferentially surrounds at least a portion of the rotor. The rotor and the casing at least partially define a gas path through the turbine. A last stage of rotating blades is circumferentially arranged around the rotor and includes a downstream swept portion radially outward from the rotor. A method for reducing shock losses in a turbine includes removing a last stage of rotating blades circumferentially arranged around a rotor and replacing the last stage of rotating blades with rotating blades having a downstream swept portion radially outward from the rotor.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2015},
month = {9}
}

Works referenced in this record:

Reduced loss swept supersonic fan blade
patent, February 1988


Method of forming F.O.D.-resistant blade
patent, July 1991


Forward swept rotor blade
patent, December 1992


Rotor airfoils to control tip leakage flows
patent, June 1996


Swept turbomachinery blade
patent, July 1997


Cycle for steam cooled gas turbines
patent, November 1998


Leaned and swept fan outlet guide vanes
patent, March 2001


Convex compressor casing
patent, January 2002


Transonic airfoil and axial flow rotary machine
patent, March 2012