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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:
 [1]
  1. Niskayuna, NY
Issue Date:
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
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.
Bunker, Ronald Scott. Turbine blade tip with offset squealer. United States.
Bunker, Ronald Scott. Mon . "Turbine blade tip with offset squealer". United States. https://www.osti.gov/servlets/purl/873516.
@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