Title:
AXIAL-FLOW TURBINE BLADE FOR GAS TURBINE MECHANISM
Document Type and Number:
Japanese Patent JPS58172407
Kind Code:
A
Abstract:
The present axial-flow turbine blade has two cooling channels extending radially through the blade. These radial channels communicate with each other through impingement cooling ducts or holes (3) extending substantially axially through the blade. One channel (1) supplies cooling fluid through the holes (3) into the other channel (2) which is located nearer the leading edge (8) of the blade and extends substantially in parallel to the leading edge (8). The cooling fluid impacts on the wall of the other channel (2) and is laterally blown out at a side wall of the blade. For optimal cooling, especially of the leading edge of the blade, which is subject to severe thermal loads, this edge is penetrated by cooling elements (4) in the form of pins or wires in axial alignment with the impingement cooling holes or ducts (3). These cooling pins or wires (4) reach into the channel (2) nearer the leading edge with their tapered end (5) and are made of a highly thermally conductive material. The second cooling channel (2) nearer the leading edge (8) may have different cross-sectional shapes, for example the shape may be at least partially rounded along circumferential wall sections, or it may be circular, elliptical, elongated or the like for an improved guiding of the cooling fluid such as air.
Inventors:
HERUMUUTO GUREESU
HORUSUTO GUREEMURU
HORUSUTO GUREEMURU
Application Number:
JP4805783A
Publication Date:
October 11, 1983
Filing Date:
March 24, 1983
Export Citation:
Assignee:
MTU MUENCHEN GMBH (DE)
International Classes:
F01D5/18; (IPC1-7): F01D5/18
Attorney, Agent or Firm:
Toshio Yano
Previous Patent: JPS58172406
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