Title:
TURBINE ROTOR BLADE FOR SYMMETRIC BLADE TYPE TURBINE
Document Type and Number:
Japanese Patent JP2630701
Kind Code:
B2
Abstract:
PURPOSE: To obtain high operating characteristics in a symmetric blade type (wells) turbine rotor blade by deviating a zero lift angle to a negative (minus) value, and preventing a lift drag ratio, a tangential force coefficient, and efficiency from lowering at a small attack angle for reduced drag.
CONSTITUTION: In a blade body 11, an air introduction scoop 15 is installed at its front edge 14, jet deflection holding type amplifiers (repeater) 16, 23 are mounted inside a blade, control nozzles 17, 18 are positioned at airfoil lines 12, 13 on both the sides of it, and jet flap injection nozzles 28, 29 are installed at its rear edge in order. By forming a jet flap mechanism of simple fluid element control, the flow around the blade can be controlled with fluid energy from the jet flap injection nozzle, and high lift drag ratio and large tangential force can be obtained. It is possible for the symmetric blade to prevent efficiency from lowering at a small attack angle and obtain high efficiency from a stable high rotational speed, thus obtaining the blade of a low pressure and high speed turbine rotor with further increased load burden characteristics and operating characteristics.
Inventors:
NOZU RIKURO
Application Number:
JP33638691A
Publication Date:
July 16, 1997
Filing Date:
October 21, 1991
Export Citation:
Assignee:
NOZU RIKURO
International Classes:
F01D1/24; B64C21/04; F01D1/30; F01D5/18; F01D19/00; F03B13/14; (IPC1-7): F01D5/18
Attorney, Agent or Firm:
Suzuki Masaaki