Laser Anemometer Measurements in a Transonic Axial Flow Compressor Rotor

Abstract

A l a s e r anomometer system employing an e f f i c i e n t data acquisition technique has been used to make measurements upstream, within, and downstream of the c o w pressor rotor. A fluorescent dye technique allowed measurements within endwali boundary layers. Adjustable l a s e r beau orientation minimized shadowed regions and enabled r a d i a l velocity measurements outside of the blade row. The flow phenomena investigated include flow variations from passage t o passage, the rotor shocksystem, three-dimensional flows i n t h e blade wake, and the development of the outer endwall beundaty layer. Laser anemometer measurements a r e compared t o a numerical solution of the streamfunction equations and t o measurements made with conventional instmuentation.

Numerical Researches on Aeroelastic Problem of a Rotor due to IGV/Fan Interaction

“…As a classic twodimensional cascade aeroelastic experiment, the STCF4 (Standard Test Configuration 4) [17,18] is first calculated as methodology validation. NASA Rotor 67 [19] , a typical transonic fan case, is chosen to be the research object. A simple straight IGV with NACA0012 airfoil is put in front of the fan.…”

State-of-Art of Transonic Axial Compressors

“…(Burguburu et al, 2004) Fig. 3 is related to a both aerodynamic and structural optimization of the well-known transonic compressor rotor 67 (Strazisar et al, 1989), where the aerodynamic objective aimed at maximizing the total pressure ratio whereas the structural objective was to minimize the blade weight, with the constraint that the new design had comparable mass flow rate as the baseline design (Lian & Liou, 2005). The optimization was carried out at the design operating point.…”

Experimental Investigation of an Aspirated Fan Stage

“…Furthermore, F 23 does not require any iteration because it only depends on quantities measured in the experiment. F 23 has only a small dependence on radial angle and Mach number.…”

“…Equations (C.8) to (C.10) shows the calculation of the static pressure. P* = P 2 -K, 2 (P 2 -Pi + P 3 -Pi) (C.8) P** = P 3 -K, 3 (P 2 -P 1 + P 3 -Pi) (C.9) P = -(Ps* + P**) (C.10) 2 From [17], two nondimensionalized coefficients (F 23 and C, 4 ) can be determined based on the 4 measured pressure for a sample point during the experiment of interest. The same can be done for each data point taken during the calibration.…”

“…The same can be done for each data point taken during the calibration. Because the Mach number, tangential and radial angle are known during the calibration, curves can be generated for F 23 as functions of tangential angle (0) for constant Mach number and radial angle. Similarly, curves of C, 4 , C, 1 , K, 2 , K, 3 and H 2 3 can be generated as a function of radial angle (#) for constant tangential angles and Mach numbers.…”