Turbine and method for reducing shock losses in a turbine

Ristau, Neil

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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:: Ristau, Neil

Issue Date:: 2015-09-01

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):: 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

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F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D5/141 - {Shape, i.e. outer, aerodynamic form
F01D5/145 - {Means for influencing boundary layers or secondary circulations

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
F05D2240/302 - characteristics related to shock waves, transonic or supersonic flow
F05D2240/307 - related to the tip of a rotor blade

Y - NEW / CROSS SECTIONAL TECHNOLOGIES Y10 - TECHNICAL SUBJECTS COVERED BY FORMER USPC Y10T - TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
Y10T29/49238 - Repairing, converting, servicing or salvaging

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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.

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                    Ristau, Neil. Turbine and method for reducing shock losses in a turbine.  United States.

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                    Ristau, Neil. Tue .  
        "Turbine and method for reducing shock losses in a turbine".  United States.  https://www.osti.gov/servlets/purl/1344792.

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@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}

}

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Works referenced in this record:

Method of and apparatus for preventing leading edge shocks and shock-related noise in transonic and supersonic rotor blades and the like
patent, November 1976

Bliss, Donald B.
US Patent Document 3,989,406
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/3989406

Reduced loss swept supersonic fan blade
patent, February 1988

Weingold, Harris D.; Harvey, Walter B.
US Patent Document 4,726,737
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/4726737

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

Blair, Lawrence W.; Schaefer, Robert A.
US Patent Document 5,031,313
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/5031313

Forward swept rotor blade
patent, December 1992

Wadia, Aspi Rustom; Szucs, Peter; Niskode, Padmakar M.
US Patent Document 5,167,489
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/5167489

Rotor airfoils to control tip leakage flows
patent, June 1996

Sharma, Om P.; Staubach, Joseph B.; Stetson, Gary M.
US Patent Document 5,525,038
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/5525038

Swept turbomachinery blade
patent, July 1997

Spear, David A.; Biederman, Bruce P.; Orosa, John A.
US Patent Document 5,642,985
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/5642985

Cycle for steam cooled gas turbines
patent, November 1998

Schonewald, Roger W.; Ramachandran, Jairaj; Scheper, Jr., George W.
US Patent Document 5,839,267
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/5839267

Leaned and swept fan outlet guide vanes
patent, March 2001

Wadia, Aspi Rustom; Szucs, Peter; Hemmelgarn, Bruce A.
US Patent Document 6,195,983
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/6195983

Convex compressor casing
patent, January 2002

Decker, John J.; Breeze-Stringfellow, Andrew
US Patent Document 6,338,609
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/6338609

Transonic airfoil and axial flow rotary machine
patent, March 2012

Nagai, Naonori; Iwatani, Junji
US Patent Document 8,133,012
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/8133012

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Similar Records

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

Abstract

Citation Formats

Method of and apparatus for preventing leading edge shocks and shock-related noise in transonic and supersonic rotor blades and the like patent, November 1976

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

Method of and apparatus for preventing leading edge shocks and shock-related noise in transonic and supersonic rotor blades and the like
patent, November 1976

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