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Study on restriction method for end-wall boundary layer thickness in axial helium gas compressor for gas turbine high temperature gas cooled reactor

Takada, Shoji; Takizuka, Takakazu; Yan, X.; Kunitomi, Kazuhiko ; Inagaki, Yoshiyuki

Aerodynamic performance test was carried out using a 1/3 scale, 4-stage model of helium gas compressor to investigate an effect of end-wall over-camber to prevent decrease of axial velocity in end-wall boundary layer. The model compressor consists of a rotor, 500 mm in diameter, which is driven at a rotational speed of 10800 rpm. The rotor blade span of the first stage is 34 mm. The test was carried out under the condition that the helium gas pressure 0.88 MPa, temperature 30 $$^{circ}$$C, and mass flow rate 12.47 kg/s at the inlet. A 3-dimensional aerodynamic code, which was verified using the test data, showed that axial velocity was lowered by using a blade which increased the inlet blade angle around the end-wall region of the casing side in comparison with that using the original design blade, because the inlet flow angle mismatched with the inlet blade angle of the rotor blade. The overall adiabatic efficiency of the full scale 20-stage compressor was predicted 89.7% from the test data.

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