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Keywords: turbines
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Journal Articles
Article Type: Research-Article
J. Turbomach. November 2016, 138(11): 111007.
Paper No: TURBO-16-1051
Published Online: May 17, 2016
...Matthew Collins; Kam Chana; Thomas Povey The high pressure (HP) rotor tip and over-tip casing are often life-limiting features in the turbine stages of current gas turbine engines. This is due to the high thermal load and high temperature cycling at both low and high frequencies. In the last few...
Journal Articles
Article Type: Research Papers
J. Turbomach. July 2012, 134(4): 041022.
Published Online: July 25, 2011
...Vikram Shyam; Ali Ameri; Jen-Ping Chen In a previous study, vane-rotor shock interactions and heat transfer on the rotor blade of a highly loaded transonic turbine stage were simulated. The geometry consists of a high pressure turbine vane and a downstream rotor blade. This study focuses...
Journal Articles
Article Type: Research Papers
J. Turbomach. July 2012, 134(4): 041017.
Published Online: July 21, 2011
... is given. stators turbines The theoretical analysis leads to consider that the value of S 3 ∗ is most important in the variable geometry process. In that line, three statements follow. 1 If the reduced section variation is the dominant effect, then both of the classical...
Journal Articles
Article Type: Research Papers
J. Turbomach. July 2012, 134(4): 041013.
Published Online: July 21, 2011
...Weiguo Ai; Nathan Murray; Thomas H. Fletcher; Spencer Harding; Scott Lewis; Jeffrey P. Bons Deposition on film-cooled turbine components was studied in an accelerated test facility. The accelerated deposition facility seeds a natural-gas burning combustor with finely ground coal ash particulate...
Journal Articles
Article Type: Research Papers
J. Turbomach. July 2012, 134(4): 041016.
Published Online: July 21, 2011
...Filippo Coletti; Manfredi Scialanga; Tony Arts The present contribution is devoted to the experimental study of the conjugate heat transfer in a turbine blade cooling cavity located near the trailing edge. The cooling scheme is characterized by a trapezoidal cross-section, one rib-roughened wall...
Journal Articles
Article Type: Research Papers
J. Turbomach. July 2012, 134(4): 041006.
Published Online: July 20, 2011
...M. Lorenz; A. Schulz; H.-J. Bauer The present experimental study is part of a comprehensive heat transfer analysis on a highly loaded low pressure turbine blade and endwall with varying surface roughness. Whereas a former paper ( Lorenz et al., 2009, “An Experimental Study of Airfoil and Endwall...
Journal Articles
Article Type: Research Papers
J. Turbomach. July 2012, 134(4): 041004.
Published Online: July 19, 2011
...S. Naik; C. Georgakis; T. Hofer; D. Lengani This paper investigates the flow, heat transfer, and film cooling effectiveness of advanced high pressure turbine blade tips and endwalls. Two blade tip configurations have been studied, including a full rim squealer and a partial squealer with leading...
Journal Articles
Article Type: Research Papers
J. Turbomach. May 2012, 134(3): 031014.
Published Online: July 15, 2011
...R. M. Mathison; C. W. Haldeman; M. G. Dunn Heat-flux measurements are presented for a one-and-one-half stage high-pressure turbine operating at design-corrected conditions with modulated cooling flows in the presence of different inlet temperature profiles. Coolant is supplied from a heavily film...
Journal Articles
Article Type: Research Papers
J. Turbomach. May 2012, 134(3): 031011.
Published Online: July 15, 2011
...C. W. Haldeman; M. G. Dunn; R. M. Mathison A fully cooled transonic high-pressure turbine stage is utilized to investigate the combined effects of turbine stage cooling variation and vane inlet temperature profile on heat transfer to the blades with the stage operating at the proper design...
Journal Articles
Article Type: Research Papers
J. Turbomach. May 2012, 134(3): 031015.
Published Online: July 15, 2011
...R. M. Mathison; C. W. Haldeman; M. G. Dunn The independent influences of vane trailing edge and purge cooling are studied in detail for a one-and-one-half stage transonic high-pressure turbine operating at design-corrected conditions. This paper builds on the conclusions of Part I, which...
Journal Articles
Article Type: Research Papers
J. Turbomach. May 2012, 134(3): 031013.
Published Online: July 15, 2011
... turbines The orifice equations for swirling flow developed by Owen ( 1 2 ) were applied to the case of externally induced (EI) ingress in Part I ( 3 ) of this two-part paper. The EI case applies when the ingress is dominated by the flow in the external annulus of a gas turbine, or, more accurately...
Journal Articles
Article Type: Research Papers
J. Turbomach. May 2012, 134(3): 031006.
Published Online: July 14, 2011
...Diganta P. Narzary; Kuo-Chun Liu; Akhilesh P. Rallabandi; Je-Chin Han Adiabatic film-cooling effectiveness is examined on a high-pressure turbine blade by varying three critical engine parameters, viz., coolant blowing ratio, coolant-to-mainstream density ratio, and freestream turbulence intensity...
Journal Articles
Article Type: Technical Briefs
J. Turbomach. May 2012, 134(3): 034501.
Published Online: July 14, 2011
...Ambady Suresh; Douglas C. Hofer; Venkat E. Tangirala The definition of turbine efficiency for a machine subjected to unsteady periodic inflows is studied. Since mass and energy are conserved quantities over a period, there is no ambiguity in calculating the actual work output of the turbine over...
Journal Articles
Article Type: Research Papers
J. Turbomach. May 2012, 134(3): 031007.
Published Online: July 14, 2011
... , 46 , pp. 653 – 669 . 10.1016/S0017-9310(02)00325-3 Sewall , E. A. , and Tafti , D. K. , 2008 , “ Large Eddy Simulation of Flow and Heat Transfer in the Developing Flow Region of a Rotating Gas Turbine Blade Internal Cooling Duct With Coriolis and Buoyancy Forces ,” ASME J...
Journal Articles
Article Type: Research Papers
J. Turbomach. May 2012, 134(3): 031003.
Published Online: July 14, 2011
...Budimir Rosic; Liping Xu Blade lean, i.e., nonradial blade stacking, has been intensively used over the past in the design process of low aspect ratio gas and steam turbines. Although its influence on turbine efficiency is not completely understood, it has been proved as an effective way...
Journal Articles
Article Type: Research Papers
J. Turbomach. March 2012, 134(2): 021025.
Published Online: July 7, 2011
... 07 07 2011 07 07 2011 boundary layer turbulence cooling flow simulation jets turbines Although the advance in metallurgy clearly increased the potential temperature of the turbine component material, the cooling methods are the essential technology that allows higher turbine...
Journal Articles
Article Type: Research Papers
J. Turbomach. March 2012, 134(2): 021024.
Published Online: July 7, 2011
... is used to predict turbine and compressor end wall flows, flow around a fan blade section, jet flows, and a cutback trailing edge. Also, application of NLES to the flow in an idealized high pressure compressor drum cavity is considered. Generally, encouraging results are found. However, challenges remain...
Journal Articles
Article Type: Research Papers
J. Turbomach. March 2012, 134(2): 021020.
Published Online: June 30, 2011
...P. Palafox; M. L. G. Oldfield; P. T. Ireland; T. V. Jones; J. E. LaGraff High resolution Nusselt number distributions were measured on the blade tip surface of a large, 1.0 m chord, low-speed cascade representative of a high-pressure turbine. Data were obtained at a Reynolds number of 4.0 × 10 5...
Journal Articles
Article Type: Research Papers
J. Turbomach. March 2012, 134(2): 021015.
Published Online: June 28, 2011
...Richard J. Fawcett; Andrew P. S. Wheeler; Li He; Rupert Taylor The benefits of different film cooling geometries are typically assessed in terms of their time-averaged performance. It is known that the mixing between the coolant film and the main turbine passage flow is an unsteady process...
Journal Articles
Article Type: Research Papers
J. Turbomach. March 2012, 134(2): 021011.
Published Online: June 27, 2011
...Chia Hui Lim; Graham Pullan; John Northall A methodology is presented to allow designers to estimate the penalty for turbine efficiency associated with film cooling. The approach is based on the control volume analysis of Hartsel and the entropy-based formulations of Young and Wilcock. The present...