...Bram Hulhoven; John D. Coull; Dougal Jackson; Nicholas R. Atkins High-pressure turbine blade (HPTB) shrouds suffer manufacturing variations in both platform alignment and inter-platform gap width. Compared to hub endwalls, the aerothermal effects of shroud platform steps and gaps has had little...

..., the methodology is confirmed to avoid both overfitting and underfitting. 1 Corresponding author. Email: arman.mirhashemi@nasa.gov Email: paht.juangphanich@nasa.gov Email: kenji.miki@nasa.gov Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the J ournal...

..., and more efficient low-pressure turbines (LPT). Efficiency gains in LPTs can be achieved by reducing the losses associated with the shroud leakage flows. Flow control studies on the topic have traditionally focused on reducing the mixing loss, which constitutes a considerable proportion of the total loss...

...Sergio Grasa; Guillermo Paniagua Pressure gain combustion is considered a possible path toward improved thermal cycle efficiency and reduced carbon emissions. However, ad hoc turbine designs are required to maximize the thermodynamic potential; the new turbomachinery should be suited...

... initiative to investigate the feasibility of incorporating active flow control technologies in a high lift/high work low-pressure turbine stage. References [ 2 , 4 – 9 ] are quite representative of the available literature on flow control technologies in that although many techniques have shown considerable...

...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...

...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...

... is given. 02 04 2010 07 02 2011 21 07 2011 21 07 2011 stators turbines Basically, the only purpose of a turbine stage is to supply energy to devices such as electric generators or compressor stages. This energy is taken from the total enthalpy of the inlet fluid, which...

...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...

...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...

...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...

...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...

... Φ min from the effectiveness data for RI or EI ingress. engines orifices (mechanical) swirling flow 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...

...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...

...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...

...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...

...% for δ = 0.2 and by 45% for δ = 0.3 on the leading side from that of the stationary case. 08 07 2010 22 07 2010 14 07 2011 14 07 2011 Modern turbine blades are exposed to increasingly hot combustion gas temperatures required to increase the overall thrust of the turbine...

...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...

...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...

...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...