A three-dimensional turbine engine analysis compressor code (TEACC) for steady-state inlet distortion
- Sverdrup Technology, Inc., Arnold AFB, TN (United States)
- Virginia Polytechnic Inst. and State Univ., Blacksburg, VA (United States). Mechanical Engineering Dept.
The direct approach of modeling the flow between all blade passages for each blade row in the compressor is too computationally intensive for practical design and analysis investigations with inlet distortion. Therefore a new simulation tool called the Turbine Engine Analysis Compressor Code (TEACC) has been developed. TEACC solves the compressible, time-dependent, three-dimensional Euler equations modified to include turbomachinery source terms, which represent the effect of the blades. The source terms are calculated for each blade row by the application of a streamline curvature code. TEACC was validated against experimental data from the transonic NASA rotor, Rotor 1B, for a clean inlet and for an inlet distortion produced by a 90-deg, one-per-revolution distortion screen. TEACC revealed that strong swirl produced by the rotor caused the compressor to increase in loading in the direction of rotor rotation through the distorted region and decrease in loading circumferentially away from the distorted region.
- Sponsoring Organization:
- USDOE
- OSTI ID:
- 290050
- Report Number(s):
- CONF-970604--
- Journal Information:
- Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 3 Vol. 120; ISSN JOTUEI; ISSN 0889-504X
- Country of Publication:
- United States
- Language:
- English
Similar Records
Rotating stall control in a high-speed stage with inlet distortion. Part 1: Radial distortion
Inlet distortion generated forced response of a low-aspect-ratio transonic fan