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:
-
- 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):
-
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:
- 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 = {Mon Jan 01 00:00:00 EST 2001},
month = {Mon Jan 01 00:00:00 EST 2001}
}
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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
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