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Keywords: gas turbines
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Journal Articles
Article Type: Research Papers
J. Turbomach. July 2012, 134(4): 041018.
Published Online: July 25, 2011
... compared with a uniform one can lead to better diffuser performance and that a moderate residual swirl can improve the performance as well. In the second part of this paper, the minimization of exhaust losses in heavy-duty gas turbines is discussed and illustrated by two practical examples. 17 10...
Journal Articles
Article Type: Research Papers
J. Turbomach. July 2012, 134(4): 041020.
Published Online: July 25, 2011
...Weiguo Ai; Thomas H. Fletcher Numerical computations were conducted to simulate flash deposition experiments on gas turbine disk samples with internal impingement and film cooling using a computational fluid dynamics (CFD) code ( FLUENT ). The standard k- ω turbulence model and Reynolds-averaged...
Journal Articles
Article Type: Research Papers
J. Turbomach. July 2012, 134(4): 041021.
Published Online: July 25, 2011
... density Subscripts ∞ freestream condition c coolant s surface Wright , I. G. , Leyens , C. , and Pint , B. A. , 2000 , “ An Analysis of the Potential for Deposition, Erosion, or Corrosion in Gas Turbine Fueled by the Products of Biomass Gasification...
Journal Articles
Article Type: Research Papers
J. Turbomach. July 2012, 134(4): 041013.
Published Online: July 21, 2011
... of the holes due to the distributed coolant film. Close cylindrical hole spacing of 2.25d displayed similar behavior to the shaped-hole configuration. 12 10 2010 30 11 2010 21 07 2011 21 07 2011 coal ash combustion equipment coolants cooling gas turbines natural gas technology...
Journal Articles
Article Type: Research Papers
J. Turbomach. July 2012, 134(4): 041007.
Published Online: July 20, 2011
... the transition onset upstream. However, in some cases, at low Reynolds numbers and freestream turbulence, surface roughness suppresses boundary layer separation and decreases the trailing edge boundary layer thickness by up to 30%. aerodynamics blades boundary layer turbulence gas turbines heat transfer...
Journal Articles
Article Type: Research Papers
J. Turbomach. July 2012, 134(4): 041008.
Published Online: July 20, 2011
...Yogi Sheoran; Bruce Bouldin; P. Murali Krishnan Inlet swirl distortion has become a major area of concern in the gas turbine engine community. Gas turbine engines are increasingly installed with more complicated and tortuous inlet systems such as those found on embedded installations on unmanned...
Journal Articles
Article Type: Research Papers
J. Turbomach. July 2012, 134(4): 041003.
Published Online: July 19, 2011
...Valerio Lallini; Jan Janikovic; Pericles Pilidis; Riti Singh; Panagiotis Laskaridis A tool to evaluate the turbine cooling air schedule during the flight path is presented. The method is suitable for complex gas turbine engine models where accurate calculation of thermodynamic parameters...
Journal Articles
Article Type: Research Papers
J. Turbomach. May 2012, 134(3): 031012.
Published Online: July 15, 2011
...J. Michael Owen; Kunyuan Zhou; Oliver Pountney; Mike Wilson; Gary Lock Rotationally induced (RI) ingress is caused by the negative pressure (relative to the external air) inside the wheel-space of a gas turbine; this negative pressure, which is created by the rotating flow in the wheel-space...
Journal Articles
Article Type: Research Papers
J. Turbomach. May 2012, 134(3): 031022.
Published Online: July 15, 2011
... jets, each impinging on a different adjacent wall. The ribs are aligned with the inclined jet axes, have the same pitch, and are staggered to the impinging jets. The flow exhausts through two staggered rows of holes opposing the impingement wall. The passage geometry is related to a modern gas turbine...
Journal Articles
Article Type: Research Papers
J. Turbomach. May 2012, 134(3): 031009.
Published Online: July 14, 2011
... was key to producing the most effective separation control. Evidence suggests that flow control using vortex generator jets (VGJs) will be effective in the highly unsteady low pressure turbine environment of an operating gas turbine, provided the VGJ location and amplitude are adapted for the specific...
Journal Articles
Article Type: Research Papers
J. Turbomach. May 2012, 134(3): 031005.
Published Online: July 14, 2011
...Budimir Rosic; John D. Denton; John H. Horlock; Sumiu Uchida This paper numerically investigates the interaction between multiple can combustors and the first vane in an industrial gas turbine with 16 can combustors and 32 vanes in order to find ways of reducing the overall cooling requirements...
Journal Articles
Article Type: Research Papers
J. Turbomach. May 2012, 134(3): 031008.
Published Online: July 14, 2011
... of CFD Analysis for Film Cooling on Gas Turbine Blade-Analysis of Cooling Performance on a Blade Leading Edge ,” CRIEPI Report No. M08017 (in Japanese). Sakai , E. , Takahashi , T. , Funazaki , K. , and Salleh , H. B. , 2009 , “ Evaluation of CFD Analysis for Film Cooling on Gas...
Journal Articles
Article Type: Research Papers
J. Turbomach. March 2012, 134(2): 021021.
Published Online: June 30, 2011
... 30 06 2011 aerospace engines computational fluid dynamics Coriolis force finite volume methods flow simulation gas turbines heat transfer Navier-Stokes equations vortices Gas turbines are widely used for power generation as well as aircraft propulsion. The continuous demand...
Journal Articles
Article Type: Research Papers
J. Turbomach. March 2012, 134(2): 021017.
Published Online: June 29, 2011
...A. Hirschmann; S. Volkmer; M. Schatz; C. Finzel; M. Casey; M. Montgomery Large industrial gas turbines for combined heat and power generation normally have axial diffusers leading to the heat recovery steam generator. The diffusers operate with high inlet axial Mach number (0.6...
Journal Articles
Article Type: Research Papers
J. Turbomach. March 2012, 134(2): 021018.
Published Online: June 29, 2011
...L. He Gas turbine performance improvement requires efficient and accurate prediction tools for film-cooling of high pressure turbine blades. Use of computational fluid dynamics in the cooling design faces a challenge due to a wide range of length scales to be resolved. The difficulty is also...
Journal Articles
Article Type: Research Papers
J. Turbomach. March 2012, 134(2): 021016.
Published Online: June 28, 2011
...Ting Wang; T. S. Dhanasekaran Internal mist/steam blade cooling technology is proposed for advanced gas turbine systems that use the closed-loop steam cooling scheme. Previous experiments on mist/steam heat transfer with a 2D slot jet impingement onto a concave surface showed cooling enhancement...
Journal Articles
Article Type: Research Papers
J. Turbomach. March 2012, 134(2): 021014.
Published Online: June 28, 2011
... 06 2011 28 06 2011 aerodynamics blades boundary layers computational fluid dynamics engines gas turbines nozzles transonic flow wakes The performance of the turbine section in a gas turbine engine plays a major role in the overall efficiency of the engine. They depend...
Journal Articles
Article Type: Research Papers
J. Turbomach. March 2012, 134(2): 021012.
Published Online: June 27, 2011
...Arne Vorreiter; Susanne Fischer; Horst Saathoff; Rolf Radespiel; Joerg R. Seume Airfoil active flow control has been attempted in the past in order to increase the permissible loading of boundary layers in gas turbine components. The present paper presents a stator with active flow control...
Journal Articles
Article Type: Research Papers
J. Turbomach. March 2012, 134(2): 021001.
Published Online: June 21, 2011
...Md. Hamidur Rahman; Sung In Kim; Ibrahim Hassan High thermal load appears at the blade tip and casing of a gas turbine engine. It becomes a significant design challenge to protect the turbine materials from this severe situation. As a result of geometric complexity and experimental limitations...
Journal Articles
Article Type: Research Papers
J. Turbomach. January 2012, 134(1): 011021.
Published Online: June 1, 2011
... / q 0 , which mean the direction of heat transfer changes from film to wall to wall to film, appear in the upstream region of the holes shown in Fig. 16 . The reason for the negative value is that the used value of φ is too small in the upstream region. In the real gas turbine situations...