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Title: 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:
 [1]
  1. 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 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
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
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 = {2011},
month = {3}
}

Patent:

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