Stator performance and unsteady loading in transonic compressor stages
- Massachusetts Inst. of Tech., Cambridge, MA (United States)
The structure and behavior of wakes from a transonic compressor rotor and their effect on the loading and performance of the downstream stator have been investigated experimentally. The rotor was 23.25 inches in diameter with a measured tip Mach number of 1.23 and a pressure ratio of 1.66. Time and space-resolved measurements have been completed of the rotor and stator outflow, as well of the pressure distribution on the surface of the stator blades. It was found that the wakes from this rotor have large flow angle and flow Mach number variations from the mean flow, significant pressure fluctuations, and a large degree of variation from hub to tip. There was a significant total pressure defect and practically no static pressure variation associated with the stator wakes. Wakes from the rotor exist nearly undiminished in the exit flow of the stator and decay in the annular duct behind the stator. The pressure at all points along the chord over each of the stator blades` surfaces fluctuated nearly in phase in response to the rotor wakes, that is the unsteady chordwise pressure distribution is determined mainly by the change in angle of incidence to the blade and not by the local velocity fluctuations within the passage. The unsteady forces on the stator blades, induced by the rotor wakes, were as high as 25% of the steady forces, and lagged the incidence of the wakes on the leading edge by approximately 180 deg at most radii.
- Sponsoring Organization:
- USDOE
- OSTI ID:
- 290013
- Journal Information:
- Journal of Turbomachinery, Vol. 120, Issue 2; Other Information: PBD: Apr 1998
- Country of Publication:
- United States
- Language:
- English
Similar Records
Predictions of three-dimensional steady and unsteady inviscid transonic stator/rotor interaction with inlet radial temperature nonuniformity
Effects of inlet distortion on the flow field in a transonic compressor rotor