... of film hole spacing, hole size, and TBC on surface heat transfer. Calculated capture efficiencies compare well with experimental results. 21 10 2010 03 12 2010 25 07 2011 25 07 2011 blades boundary layer turbulence coating techniques computational fluid dynamics cooling...

...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...

... design. The results indicate that the reduction in size was feasible without compromising the efficiency and operation range of the stage. 18 10 2010 24 01 2011 25 07 2011 25 07 2011 blades compressors computational fluid dynamics design of experiments impellers...

... ( Shibata et al., “Performance Improvement of a Centrifugal Compressor Stage by Increasing Degree of Reaction Optimizing Blade Loading of a 3D-Impeller,” ASME Paper No. GT2009-59588 ). In spite of such a high relative velocity diffusion ratio, the same surge margin as with a conventional design was able...

...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. Papa; V. Srinivasan; R. J. Goldstein Mass transfer measurements on the endwall and blade suction surfaces are performed in a five-blade linear cascade with a high-performance rotor blade profile. The effects of purge flow from the wheelspace cavity entering the hot gas path are simulated...

...M. Lorenz; A. Schulz; H.-J. Bauer The present experimental study is part of a comprehensive analysis accounting for heat transfer and aerodynamic losses on a highly loaded low pressure turbine blade with varying surface roughness. Whereas Part I focuses on heat transfer measurements at airfoil...

... thermodynamic loss increase of about 0.7% at low coolant injection rates. Increasing the blowing rates, the additional loss vanishes. 20 09 2010 17 10 2010 20 07 2011 20 07 2011 blades coolants cooling film flow nozzles pressure thermodynamics turbulence In advanced...

...Y.-J. Chan; D. J. Ewins Integral bladed disks (also known as blisks) are more widely used in modern aeroengine compressor designs because of the potential weight savings, but there are challenges in controlling the extreme vibration response levels in mistuned blisks, which are blisks with blades...

...Yasharth Bhartiya; Alok Sinha An algorithm to generate a reduced order model of a multistage rotor in which each stage has a different number of blades has been developed. It is shown that a reduced order model can be developed on the basis of tuned modes of certain bladed disks which can be easily...

...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...

... investigated the combined influence of all cooling circuits. Heat-flux measurements for the airfoil, platform, tip, and root of the turbine blade, as well as the shroud and the vane side of the purge cavity, are used to track the influence of cooling flow. By independently varying the coolant flow rate through...

... at the proper design corrected conditions. Part I of this paper describes the overall experimental matrix, the influence of the cooling mass flows, and temperature profiles from an aerodynamic perspective. The measurements include internal and external pressures for the blade airfoil. Part II of this paper...

..., drives the ingestion of hot gas through the rim seals. Externally induced (EI) ingress is caused by the circumferential distribution of pressure created by the blades and vanes in the turbine annulus: Ingress occurs in those regions where the external pressure is higher than that in the wheel-space...

...Marco Raciti Castelli; Ernesto Benini This paper presents a model for the evaluation of energy performance and aerodynamic forces acting on a small helical Darrieus vertical axis wind turbine depending on blade inclination angle. It consists of an analytical code coupled to a solid modeling...

... blade cooling configuration. A transient liquid crystal technique was used to take spatially resolved surface heat transfer measurements for the ground area between the ribs. A comparison with the smooth baseline configuration reveals local differences and a generally reduced heat transfer for the rib...

... the flat test-surface. The three-dimensional pressure distribution that is established on the test-surface approximates the pressure distributions encountered on swept blades. This type of pressure field produces crossflows in the laminar boundary layer upstream of the separation and within the separation...

... and stabilized near the leading surface, resulting in increased heat transfer on the trailing surface with attenuation at the leading surface ( 4 5 6 7 8 9 ). In addition, the blade orientation was reported to affect the heat augmentation levels in the channel where the 45 deg (or 135 deg) orientation...

...Jeffrey P. Bons; Jon Pluim; Kyle Gompertz; Matthew Bloxham; John P. Clark The synchronous application of flow control in the presence of unsteady wakes was studied on a highly loaded low pressure turbine blade. At low Reynolds numbers, the blade exhibits a nonreattaching separation bubble under...

... be reduced. The proposed combustor and first vane integration does not detrimentally affect the aerodynamics of the combustor and vane system. The concept also simplifies the design and should lower the manufacturing costs. 28 06 2010 29 06 2010 14 07 2011 14 07 2011 blades gas...