METHOD AND DEVICE FOR REDUCING TURBINE BLADE PRESSURE LOSS

Japanese Patent JP3218385

B2

PROBLEM TO BE SOLVED: To reduce pressure loss of a transonic turbine vane by which the velocity of flow of main flow gas at a cascade outlet is increased to a transonic speed or a supersonic speed, without the increase of weight.
SOLUTION: Gas for injection is fed to the internal part of a turbine blade 10 and a main flow gas flows from the pressure surface of the rear edge par 20 of a turbine blade along the pressure surface 14 of a turbine blade of which a cascade consists. Injection in the main flow gas is effected at F in a flow velocity ratio of a mass between injection gas and main flow gas, which is determined by density and a speed and reduced to 1 or less. The generation of a shock wave from the pressure surface of a rear edge part is reduced. Incidence of a developing shock wave to a boundary layer to the negative surface of a turbine blade adjoining a turbine blade to generate a shock wave is prevented from occurring and thickening of the boundary layer due to disturbance of an incident shock wave is suppressed to reduce incurring of a pressure loss. This constitution employs a device for a gas turbine for an aircraft, reduces the pressure loss of the turbine blade, and improves the thermal efficiency of a turbine.

Yukio Kawachi
Katsuyuki Shimauchi
Kunihiro Shimizu
Ryoma Nogami

JP22671496A

October 15, 2001

August 28, 1996

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Advanced Material Utilization Gas Generator Research Institute Co., Ltd.

F01D5/12; F01D5/14; F01D5/18; F01D9/02; (IPC1-7): F01D5/14; F01D5/18; F01D9/02

JP5918202A
JP611804A

Akasaka Saka (1 person outside)

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