Search
Now showing items 1-10 of 23
A numerical analysis of 3-D inviscid stator/rotor interactions using non-reflecting boundary conditions
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1992], 1992)
This dissertation presents a method for the computation of three-dimensional inviscid, transonic steady and unsteady flows, primarily in axial flow turbines. The work is divided into two major contributions. The first is ...
Active stabilization of rotating stall and surge in a transonic single stage axial compressor
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 1997, 1997)
Rotating stall and surge have been stabilized in a transonic single-stage axial compressor using active feedback control. The control strategy is to sense upstream wall static pressure patterns and feed back the measured ...
The effect of upstream rotor vortical disturbances on the time-average performance of axial compressor stators
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 1997, 1997)
Time-accurate Reynolds-averaged Navier-Stokes simulations have been carried out to investigate the impact of upstream rotor wakes and tip leakage vortices on the loss of a compressor stator. The objective is to (1) identify ...
Measurements of rotor stalling in a matched and a mismatched multistage compressor
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1995], 1995)
This paper presents the results from a set of experiments on stall inception in multistage axial flow compressors. The experiments were tailored to investigate phenomena having a wide range of time and length scales. This ...
A computational model for rotating stall and inlet distortions in multistage compressors
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1999], 1999)
This thesis presents the conceptualization and development of a computational model for describing three-dimensional non-linear disturbances associated with instability and inlet distortion in multistage compressors. ...
UNSFLO : a numerical method for the calculation of unsteady flow in turbomachinery
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1991], 1991)
Introduction: There are four principal sources of unsteadiness in a single stage of a turbomachine in which there is one row of stationary blades (stators) and one row of moving blades (rotors). As shown in Fig. 1.1, ...
Aerodynamics of aircraft engines : stride and stumbles
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 1992, 1992)
Summary: Attempts to understand and predict the aerodynamic behaviour of compressors and turbines in aircraft gas turbines have been encouraged by the intense competitive pressure which exists. Many of the apparently most ...
Control of the unsteady flow in a stator blade row interacting with upstream moving wakes
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1993], 1993)
A computational study of the unsteady flow in a 2-D stator blade row interacting with upstream rotor wakes has been carried out. A direct spectral-element Navier-Stokes solver has been used for the laminar flow regime ...
Active control of rotating stall in axial compressors
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1992], 1992)
An active control system has been implemented on a low-speed single-stage axial compressor. This control system stabilizes the perturbations which normally lead to rotating stall, thus extending the range of operation of ...
Role of flow alignment and inlet blockage on vaned diffuser performance
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 1997, 1997)
A computational investigation of the effects of inlet conditions on straight-channel diffuser performance is undertaken. The steady, three-dimensional, Navier-Stokes solver used for the investigation is found to adequately ...