Experimental and Numerical Study of Gust and Gust Response in a Rotor/Stator Axial Compressor

Abstract

This paper addresses the gust response on the stator of a rotor/stator axial compressor, by decomposing the response into vortical and potential contributions. Experiments were conducted in a large-scale, low-speed compressor rig, with two axial gap cases — 10% and 30% chord — and at two time-mean loadings. To determine the gust response due to potential contribution, a two-step approach was taken. First, a panel code was used to determine the gust in the mid-gap plane for the rotor/stator configuration. Then, this calculated gust served as an inlet boundary of a Reynolds-averaged Navier-Stokes code for the stator cascade configuration. The vortical contributed gust response was found by subtracting the potential contributed response from the measured response. Results show that the vortical contributed response is largest near the instant when the rotor wake impinges at the stator leading edge. The potential contributed response reaches a maximum when the rotor trailing edge is axially upstream of the stator leading edge. The vortical contributed response dominates for all cases studied.

Reduction of Unsteady Blade Loading by Beneficial Use of Vortical and Potential Disturbances in an Axial Compressor With Rotor Clocking

“…Moreover, phase-locked averaging technique was also used to filter non-blade-to-blade periodic signals (240 typical ensembles were used). Hsu et al (1996) provides details on gust measurement using the slanted hot-wire technique, with an accuracy from calibration of ± 1 percent in magnitude and ± 1.5 deg in flow angles. Pressure Surf.…”

“…Figure 7 presents the transverse vortical and potential gusts decomposed from slanted hot-wire data using the procedure described in Hsu et al (1996) (also see Chung and Wo (1997), which used Navier-Stokes results where Hsu et al used experimental data). The hot-wire was located axially upstream of the stator leading edge at the midgap position for both 10 and 30 percent chord gap cases.…”

Reduction of Unsteady Blade Loading by Beneficial Use of Vortical and Potential Disturbances in an Axial Compressor With Rotor Clocking

“…Moreover, phase-locked averaging technique was also used to filter non-blade-to-blade periodic signals (240 typical ensembles were used). Hsu et al (1996) provides details on gust measurement using the slanted hot-wire technique, with an accuracy from calibration of +/-I% in magnitude and +/-1.5 degree in flow angles.…”

Influence of Position of Intake Struts on Unsteady Load and Vibration of First-Stage Rotor

“…Meanwhile, the influence of blade vibration on the surface excitation force can be ignored, and the excitation force and the aerodynamic damping can be solved separately [30,31]. The decoupling method is suitable for calculating the vibration of turbomachinery blades, and the calculation cost is obviously lower than that of the coupling method, which is widely used in the calculation of the force vibration of compressor blades [32]. In this paper, the decoupling method is used to calculate the blade vibration.…”