Current Research at the Gas Turbine Laboratory

Current Research at the Gas Turbine Laboratory - LeoNg...

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Current Research at the Gas Turbine Laboratory  Design and Assessment of a Low-Noise Hybrid Wing Body Aircraft Leo Ng Advisor: Prof. Spakovszky Reducing the environmental impact of air travel is a major  focus in aeronautical research today. The hybrid wing body aircraft, in which the fuselage and the  wings are blended together, has the potential to be more fuel efficient, produces fewer emissions, and  generates less noise. This project aims to develop a set of advanced predictive methods that will  enable the design of a hybrid wing body aircraft to meet NASA’s N+2 objectives: (i) 25% less fuel  burn, (ii) 80% less emissions, and (iii) 52 dB less noise compared to current aircrafts in service. This research is performed in collaboration with industry and  builds upon the work done on the SAX-40 prototype from the Silent Aircraft Initiative. The existing  tools for analyzing aircraft performance and predicting airframe noise will be further refined. The goal  is to design and optimize a hybrid wing body aircraft that will meet industry requirements. A wind  tunnel experiment is planned for the final phase of this project to validate the design and predictive  methodologies used throughout the development process. (Images: The Silent Aircraft Experimental (SAX-40) prototype.)      Effects of Impeller-Diffuser Interaction on Aerodynamic Performance  of Centrifugal Compressors David Tarr Advisors: Dr. Tan, Prof. Greitzer
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CC3 compressor; photo courtesy of NASA Glenn  Research Center This work is aimed at a key problem of modern centrifugal compressor stages: the impact of unsteady  interaction between the rotating impeller blades and stationary diffuser vanes on performance and  aeromechanics. Three important technical issues are of engineering interest:  1. The effect of these unsteady interactions on the time-averaged performance of a modern  centrifugal compressor stage;  2. Initiation and development of aerodynamic instabilities in a centrifugal compressor; and  3. Use of (1) to propose design guidelines and potential innovative designs for achieving  incremental improvements in performance.  The current focus is on technical issues (1) and (3), however future project phases will use the initial  results to infer their potential impact on issue (2). In addition to addressing the technical aerodynamic  issues, assessment and validation of new analytical approaches and computational tools for use in  centrifugal compressor stage design and analysis will be carried out during the course of the research  program.
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This note was uploaded on 12/24/2009 for the course AEROSPACE engine taught by Professor Prof during the Spring '09 term at École Normale Supérieure.

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Current Research at the Gas Turbine Laboratory - LeoNg...

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