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Title: Turbine blade tip flow discouragers

Abstract

A turbine assembly comprises a plurality of rotating blade portions in a spaced relation with a stationery shroud. The rotating blade portions comprise a root section, a tip portion and an airfoil. The tip portion has a pressure side wall and a suction side wall. A number of flow discouragers are disposed on the blade tip portion. In one embodiment, the flow discouragers extend circumferentially from the pressure side wall to the suction side wall so as to be aligned generally parallel to the direction of rotation. In an alternative embodiment, the flow discouragers extend circumferentially from the pressure side wall to the suction side wall so as to be aligned at an angle in the range between about 0.degree. to about 60.degree. with respect to a reference axis aligned generally parallel to the direction of rotation. The flow discouragers increase the flow resistance and thus reduce 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
Publication Date:
Research Org.:
General Electric Co., Schenectady, NY (United States)
OSTI Identifier:
872862
Patent Number(s):
US 6027306
Assignee:
General Electric Company (Schenectady, NY)
DOE Contract Number:  
FC21-95MC31176
Resource Type:
Patent
Country of Publication:
United States
Language:
English
Subject:
turbine; blade; tip; flow; discouragers; assembly; comprises; plurality; rotating; portions; spaced; relation; stationery; shroud; comprise; root; section; portion; airfoil; pressure; wall; suction; disposed; embodiment; extend; circumferentially; aligned; parallel; direction; rotation; alternative; angle; range; degree; 60; respect; reference; axis; increase; resistance; reduce; hot; gas; leakage; differential; improve; overall; efficiency; rotating blade; turbine assembly; reference axis; spaced relation; assembly comprises; tip portion; turbine blade; gas flow; pressure differential; hot gas; alternative embodiment; blade tip; turbine efficiency; blade portions; extend circumferentially; root section; flow resistance; /415/416/

Citation Formats

Bunker, Ronald Scott. Turbine blade tip flow discouragers. United States: N. p., 2000. Web.
Bunker, Ronald Scott. Turbine blade tip flow discouragers. United States.
Bunker, Ronald Scott. 2000. "Turbine blade tip flow discouragers". United States. https://www.osti.gov/servlets/purl/872862.
@article{osti_872862,
title = {Turbine blade tip flow discouragers},
author = {Bunker, Ronald Scott},
abstractNote = {A turbine assembly comprises a plurality of rotating blade portions in a spaced relation with a stationery shroud. The rotating blade portions comprise a root section, a tip portion and an airfoil. The tip portion has a pressure side wall and a suction side wall. A number of flow discouragers are disposed on the blade tip portion. In one embodiment, the flow discouragers extend circumferentially from the pressure side wall to the suction side wall so as to be aligned generally parallel to the direction of rotation. In an alternative embodiment, the flow discouragers extend circumferentially from the pressure side wall to the suction side wall so as to be aligned at an angle in the range between about 0.degree. to about 60.degree. with respect to a reference axis aligned generally parallel to the direction of rotation. The flow discouragers increase the flow resistance and thus reduce 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 = {},
url = {https://www.osti.gov/biblio/872862}, journal = {},
number = ,
volume = ,
place = {United States},
year = {Sat Jan 01 00:00:00 EST 2000},
month = {Sat Jan 01 00:00:00 EST 2000}
}

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