Turbine blade tip with offset squealer

Bunker, Ronald Scott

Title: Turbine blade tip with offset squealer

Abstract

An industrial turbine assembly comprises a plurality of rotating blade portions in a spaced relation with a stationary shroud. The rotating blade includes a root section, an airfoil having a pressure sidewall and a suction sidewall defining an outer periphery and a tip portion having a tip cap. An offset squealer is disposed on the tip cap. The offset squealer is positioned inward from the outer periphery of the rotating blade. The offset squealer increases the flow resistance and reduces the flow of hot gas flow leakage for a given pressure differential across the blade tip portion so as to improve overall turbine efficiency.

Inventors:

Bunker, Ronald Scott ^[1]

Niskayuna, NY

Issue Date:: 2001-01-01

Research Org.:: General Electric Co., Schenectady, NY (United States)

OSTI Identifier:: 873516

Patent Number(s):: 6179556

Assignee:: General Electric Company (Schenectady, NY)

Patent Classifications (CPCs):: Y - NEW / CROSS SECTIONAL TECHNOLOGIES Y02 - TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE Y02T - CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

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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Y - NEW / CROSS SECTIONAL TECHNOLOGIES Y02 - TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE Y02T - CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
Y02T50/60 - Efficient propulsion technologies

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
F05D2260/231 - Preventing heat transfer

F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D5/20 - Specially-shaped blade tips to seal space between tips and stator {
F01D5/187 - {Convection cooling}

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DOE Contract Number:: FC21-95MC31176

Resource Type:: Patent

Country of Publication:: United States

Language:: English

Subject:: turbine; blade; tip; offset; squealer; industrial; assembly; comprises; plurality; rotating; portions; spaced; relation; stationary; shroud; root; section; airfoil; pressure; sidewall; suction; defining; outer; periphery; portion; cap; disposed; positioned; inward; increases; flow; resistance; reduces; hot; gas; leakage; differential; improve; overall; efficiency; rotating blade; turbine assembly; spaced relation; assembly comprises; outer periphery; tip portion; turbine blade; gas flow; pressure differential; hot gas; blade tip; turbine efficiency; wall defining; blade portions; root section; flow resistance; /415/416/

Citation Formats


                    Bunker, Ronald Scott. Turbine blade tip with offset squealer.  United States: N. p., 2001. 
        Web.

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                    Bunker, Ronald Scott. Turbine blade tip with offset squealer.  United States.

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                    Bunker, Ronald Scott. Mon .  
        "Turbine blade tip with offset squealer".  United States.  https://www.osti.gov/servlets/purl/873516.

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@article{osti_873516,

  title        = {Turbine blade tip with offset squealer},

  author       = {Bunker, Ronald Scott},

  abstractNote = {An industrial turbine assembly comprises a plurality of rotating blade portions in a spaced relation with a stationary shroud. The rotating blade includes a root section, an airfoil having a pressure sidewall and a suction sidewall defining an outer periphery and a tip portion having a tip cap. An offset squealer is disposed on the tip cap. The offset squealer is positioned inward from the outer periphery of the rotating blade. The offset squealer increases the flow resistance and reduces the flow of hot gas flow leakage for a given pressure differential across the blade tip portion so as to improve overall turbine efficiency.},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {2001},

  month        = {1}

}

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Works referenced in this record:

A Summary of the Cooled Turbine Blade Tip Heat Transfer and Film Effectiveness Investigations Performed by Dr. D. E. Metzger
conference, February 2015

Kim, Y. W.; Abdel-Messeh, W.; Downs, J. P.
ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition, Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
https://doi.org/10.1115/94-GT-167

Cavity Heat Transfer on a Transverse Grooved Wall in a Narrow Flow Channel
journal, February 1989

Metzger, D. E.; Bunker, R. S.; Chyu, M. K.
Journal of Heat Transfer, Vol. 111, Issue 1, p. 73-79
https://doi.org/10.1115/1.3250661

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Title: Turbine blade tip with offset squealer

Abstract

Citation Formats

A Summary of the Cooled Turbine Blade Tip Heat Transfer and Film Effectiveness Investigations Performed by Dr. D. E. Metzger conference, February 2015

Cavity Heat Transfer on a Transverse Grooved Wall in a Narrow Flow Channel journal, February 1989

A Summary of the Cooled Turbine Blade Tip Heat Transfer and Film Effectiveness Investigations Performed by Dr. D. E. Metzger
conference, February 2015

Cavity Heat Transfer on a Transverse Grooved Wall in a Narrow Flow Channel
journal, February 1989