Near wall cooling for a highly tapered turbine blade
Abstract
A turbine blade having a pressure sidewall and a suction sidewall connected at chordally spaced leading and trailing edges to define a cooling cavity. Pressure and suction side inner walls extend radially within the cooling cavity and define pressure and suction side near wall chambers. A plurality of mid-chord channels extend radially from a radially intermediate location on the blade to a tip passage at the blade tip for connecting the pressure side and suction side near wall chambers in fluid communication with the tip passage. In addition, radially extending leading edge and trailing edge flow channels are located adjacent to the leading and trailing edges, respectively, and cooling fluid flows in a triple-pass serpentine path as it flows through the leading edge flow channel, the near wall chambers and the trailing edge flow channel.
- Inventors:
-
- Palm City, FL
- Issue Date:
- Research Org.:
- Siemens Energy, Inc. (Orlando, FL)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1016549
- Patent Number(s):
- 7901182
- Application Number:
- US Patent Application 11/804,434
- Assignee:
- Siemens Energy, Inc. (Orlando, FL)
- 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:
- FC26-05NT42644
- Resource Type:
- Patent
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING
Citation Formats
Liang, George. Near wall cooling for a highly tapered turbine blade. United States: N. p., 2011.
Web.
Liang, George. Near wall cooling for a highly tapered turbine blade. United States.
Liang, George. Tue .
"Near wall cooling for a highly tapered turbine blade". United States. https://www.osti.gov/servlets/purl/1016549.
@article{osti_1016549,
title = {Near wall cooling for a highly tapered turbine blade},
author = {Liang, George},
abstractNote = {A turbine blade having a pressure sidewall and a suction sidewall connected at chordally spaced leading and trailing edges to define a cooling cavity. Pressure and suction side inner walls extend radially within the cooling cavity and define pressure and suction side near wall chambers. A plurality of mid-chord channels extend radially from a radially intermediate location on the blade to a tip passage at the blade tip for connecting the pressure side and suction side near wall chambers in fluid communication with the tip passage. In addition, radially extending leading edge and trailing edge flow channels are located adjacent to the leading and trailing edges, respectively, and cooling fluid flows in a triple-pass serpentine path as it flows through the leading edge flow channel, the near wall chambers and the trailing edge flow channel.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Mar 08 00:00:00 EST 2011},
month = {Tue Mar 08 00:00:00 EST 2011}
}