No description available.

Thesis--Auburn University, 2009. / Abstract. Includes bibliographic references (p.90-92).

No description available.

Thesis (PhD)--University of Stellenbosch, 2006. / Bibliography. Also available via the Internet.

Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1993. / Vita. Abstract. Includes bibliographical references (leaves 99-102). Also available via the Internet.

No description available.

Thesis (M. Eng.(Mechanical and Aeronautical Engineering))-Universiteit van Pretoria, 2007. / Abstract in English. Includes bibliographical references.

Thesis (M.S.)--University of Texas at El Paso, 2008. / Title from title screen. Vita. CD-ROM. Includes bibliographical references. Also available online.

During a ten-stage compressor rig test conducted at Wright-Patterson AFB, several instances of compressor surge were observed. While surge is known to occur in high-speed multi-stage compressors, very little transient data pertaining to such events exists in the open literature, exclusive of engine data. In an attempt to make more data of this type available to researchers, surge data from the ten-stage compressor test is presented and analyzed in this thesis. Graphical presentation and data analysis techniques are employed in an effort to characterize the surge behavior of this compressor. Furthermore, the predictions of a computer-based transient compressor model are compared to the data for study. In the course of reviewing the data included in this thesis, certain abnormalities were noted in the overall behavior of this compressor. During testing, several researchers found that the speed boundary between surge and rotating stall occurred between 80% and 81 % corrected design rotor speeds. 1hls boundary did not change when the compressor discharge volume was increased or decreased. This seemed to contradict accepted theory, which predicts a shift in the surge/rotating stall boundary with discharge volume changes. An investigation into the possible causes of this phenomenon was conducted as part of this thesis. Several theories were explored, including the possibility of excess volume communicating with the compressor during instability. Although the excess volume theory could not be proven, it remains the most likely cause of the usual surge/rotating stall boundary behavior. / Master of Science

Dynamic compression system response is a major concern in the operability of aircraft gas turbine engines. Computer models have been developed to predict compressor response to changing operating conditions. These models require a knowledge of the steady state operating characteristics as inputs, which limits the ability to use them as predicting tools. The full range of dynamic axial flow compressor operation spans forward and reversed flow conditions. A model for predicting the wide flow range characteristics of axial flow compressor stages has been developed and a parametric study of the effect of changing design variables on steady state performance has been conducted. This model was applied to a 3-stage, low speed compressor with very favorable results and to a 10-stage, high speed compressor with mixed results. Conclusions were made regarding the inception of stalling and the effects associated with operating a stage in a multistage environment. It was also concluded that there are operating points of an isolated compressor stage that are not attainable when that stage is operated in a multi-stage environment. A stage located in a multi-stage environment can also operate at points which cannot be reached when the stage is operated in isolation. / Master of Science