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Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Turbomach. May 2012, 134(3): 031020.
Published Online: July 15, 2011
...-mounted on the upper surface of the aircraft (Fig. 3 ), the boundary layer ingested into the inlet will be closely affected by its bottom wall but not the top wall. This assertion is supported by the results to be shown later, as the boundary layer on the top wall, which begins at the inlet highlight...
Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Turbomach. January 2012, 134(1): 011002.
Published Online: May 24, 2011
... and performance assessment methodology for advanced propfan powered aircraft configurations. The approach is based on first principles and combines a coupled aircraft and propulsion system mission and performance analysis tool with 3D unsteady, full-wheel CRP computational fluid dynamics computations...
Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Turbomach. April 2011, 133(2): 021021.
Published Online: October 26, 2010
...N. D. Cardwell; P. P. Vlachos; K. A. Thole Gas turbines for aircraft are designed for operation with a clean inlet air flow. This ideal operational condition is often violated during take-off and landing, where the probability of particle ingestion is high, with sand and dirt being the most...
Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Turbomach. October 2010, 132(4): 041018.
Published Online: May 11, 2010
.... , 1987 , “ Secondary Flow, Turbulent Diffusion and Mixing in Axial-Flow Compressors ,” J. Turbomach. 0889-504X , 109 , pp. 455 – 482 . 10.1115/1.3262127 Wisler , D. C. , 1988 , Advanced Compressor and Fan Systems, GE Aircraft Engines, Copyright. Wadia , A. R. , and Beacher...
Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Turbomach. October 2010, 132(4): 041013.
Published Online: May 5, 2010
... injected into industrial compressors for purposes of power augmentation. For that matter, They were mainly interested in the effects of aircraft compressors on runway approach during heavy rainstorms. Hence, it is reasonable to assume that at much lower levels of injection typical of application...
Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Turbomach. October 2010, 132(4): 041002.
Published Online: April 26, 2010
...P. N. Shah; D. D. Mobed; Z. S. Spakovszky A novel air-brake concept for next-generation, low-noise civil aircraft is introduced. Deployment of such devices in clean airframe configuration can potentially reduce aircraft source noise and noise propagation to the ground. The generation of swirling...
Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Turbomach. October 2010, 132(4): 041003.
Published Online: April 26, 2010
...George Kopasakis; Joseph W. Connolly; Daniel E. Paxson; Peter Ma Under the NASA Fundamental Aeronautics Program, the Supersonics Project is working to overcome the obstacles to supersonic commercial flight. The proposed vehicles are long, slim body aircrafts with pronounced aeroservoelastic modes...
Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Turbomach. July 2010, 132(3): 031019.
Published Online: April 7, 2010
... loss, and to obtain data of Nusselt number and pressure loss coefficient for the design of turbine nozzles in the future by applying this new cooling structure to next-generation small-class aircraft engines. Additionally a preliminary analysis of airfoil cooling was performed to evaluate both cooling...
Topics: Cooling
Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Turbomach. July 2010, 132(3): 031018.
Published Online: April 5, 2010
..., new aircraft engines tend to have low pressure turbines with blades that have a reduced chord. This adds to the significance of the separation bubble in terms of the profile loss and the problems of controlling this with wakes alone. At the same time there is a growing interest in high altitude...
Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Turbomach. July 2010, 132(3): 031017.
Published Online: April 5, 2010
.... , 1969 , “ Discharge Coefficients for Thick Plate Orifices With Approach Flow Perpendicular and Inclined to the Orifice Axis ,” NASA Technical Report No. TN D-5467. 26 08 2008 01 03 2009 05 04 2010 05 04 2010 aerospace components aircraft design engineering durability...
Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Turbomach. July 2010, 132(3): 031011.
Published Online: March 25, 2010
... conditions, and particles present in clouds, during in-flight conditions, are the primary sources of particle ingestion for aircraft turbine engines. Blockages from these particles in these cooling passages reduce the effectiveness of cooling by decreasing the coolant flow rate, and subsequently part life...
Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Turbomach. January 2010, 132(1): 011008.
Published Online: September 16, 2009
...Michael Flouros Advanced aircraft engine development dictates high standards of reliability for the lubrication systems, not only in terms of the proper lubrication of the bearings and the gears, but also in terms of the removal of the large amounts of the generated heat. Heat is introduced both...
Journal Articles
Publisher: ASME
Article Type: Igti Scholar Lecture
J. Turbomach. July 2009, 131(3): 031101.
Published Online: April 20, 2009
... to in the research community. The case histories of two projects are given to illustrate the point: the development of the concept of “smart jet engines” and the Silent Aircraft Initiative. In addition to providing a capability to attack multidisciplinary problems, the way in which collaboration can enhance...
Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Turbomach. July 2009, 131(3): 031011.
Published Online: April 9, 2009
... , “ Compressor Stability and Control: Review and Practical Implications ,” Proceedings of the RTO AVT Symposium 51 on Active Control Technology for Enhanced Performance Operational Capabilities of Military Aircraft, Land Vehicles and Sea Vehicles , Braunschweig, Germany. Kefalakis , M. , and Papailiou...
Journal Articles
Publisher: ASME
Article Type: Technical Papers
J. Turbomach. July 2007, 129(3): 479–487.
Published Online: July 23, 2006
...Cesare A. Hall; Daniel Crichton The Silent Aircraft Initiative is a research project funded by the Cambridge-MIT Institute aimed at reducing aircraft noise to the point where it is imperceptible in the urban environments around airports. The propulsion system being developed for this project has...
Journal Articles
Publisher: ASME
Article Type: Technical Papers
J. Turbomach. January 2007, 129(1): 184–191.
Published Online: February 1, 2006
...Daniel Crichton; Liping Xu; Cesare A. Hall Preliminary fan design for a functionally silent aircraft has been performed with noise reduction as the primary goal. For such an aircraft the fan design must, in addition to delivering low cruise fuel burn, enable low jet and fan source noise during...
Journal Articles
Publisher: ASME
Article Type: Technology Review
J. Turbomach. January 2005, 127(1): 2–4.
Published Online: February 9, 2005
... February 2004 09 02 2005 jet engines aerospace propulsion turbines aircraft I was pleased and honored to be invited to make the opening presentation of the International Gas Turbine Institute Budugur “Bud” Lakshminarayana Memorial Session. It has been a privilege to know and work...
Journal Articles
Publisher: ASME
Article Type: Technical Papers
J. Turbomach. April 2006, 128(2): 332–339.
Published Online: March 1, 2004
... condition. In a cruise condition, the aircraft is moving through stagnant air, creating a constant angle of flight relative to the incoming flow direction. In order to simulate angle of attack, additional boundary layer growth was required and an additional constant area section was installed ahead...
Journal Articles
Publisher: ASME
Article Type: Technical Papers
J. Turbomach. July 2003, 125(3): 497–504.
Published Online: August 27, 2003
... aircraft boundary layer turbulence pressure control vortices rotors Few successful attempts have been made to reduce secondary loss through application of end-wall profiling to a blade row. One successful application of profiling has been demonstrated in the Linear Cascade at Durham University...
Journal Articles