Development of a transonic front stage of an axial flow compressor for industrial gas turbines

Journal Article · Sat Oct 01 04:00:00 EDT 1994 · Journal of Turbomachinery; (United States)

DOI:https://doi.org/10.1115/1.2929450· OSTI ID:6692229

Katoh, Y; Ishii, H; Tsuda, Y; Yanagida, M ^[1]; Kashiwabara, Y ^[2]

---

1. Hitachi, Ltd., Ibaraki (Japan). Mechanical Engineering Research Lab.
2. Kanagawa Inst. of Tech., (Japan). Dept. of Mechanical Systems Engineering

This paper describes the aerodynamic blade design of a highly loaded three-stage compressor, which is a model compressor for the front stage of an industrial gas turbine. Test results are presented that confirm design performance. Some surge and rotating stall measurement results are also discussed. The first stator blade in this test compressor operates in the high subsonic range at the inlet. To reduce the pressure loss due to blade surface shock waves, a shock-free airfoil is designed to replace the first stator blade in an NACA-65 airfoil in a three-stage compressor. Comparison of the performance of both blades shows that the shock-free airfoil blade reduces pressure loss. This paper also presents some experimental results for MCA (multicircular arc) airfoils, which are used for first rotor blades.

• OSTI ID: 6692229
• Journal Information: Journal of Turbomachinery; (United States), Journal Name: Journal of Turbomachinery; (United States) Vol. 116:4; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

20 FOSSIL-FUELED POWER PLANTS
200104* -- Fossil-Fueled Power Plants-- Components
COMPRESSOR BLADES
COMPRESSORS
EFFICIENCY
ENGINES
EQUIPMENT
GAS COMPRESSORS
GAS TURBINE ENGINES
GAS TURBINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MACHINERY
THERMAL EFFICIENCY
TURBINES
TURBOMACHINERY