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:
-
- Niskayuna, NY
- Issue Date:
- Research Org.:
- General Electric Co., Schenectady, NY (United States)
- OSTI Identifier:
- 872862
- Patent Number(s):
- 6027306
- 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
- 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. Sat .
"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 = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2000},
month = {1}
}
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