4 edition of Experimental and numerical investigation of losses in low-pressure turbine blade rows found in the catalog.
Experimental and numerical investigation of losses in low-pressure turbine blade rows
by National Aeronautics and Space Administration, Glenn Research Center, National Technical Information Service, distributor in [Cleveland, Ohio], [Springfield, Va
Written in English
|Statement||Daniel J. Dorney ... [et al.].|
|Series||[NASA technical memorandum] -- NASA/TM-2000-209910., NASA technical memorandum -- 209910.|
|Contributions||Dorney, Daniel J., NASA Glenn Research Center.|
|The Physical Object|
A detailed experimental investigation was conducted into the interaction of a convected wake and a separation bubble on the rear suction surface of a highly loaded low-pressure (LP) turbine blade. MHPS’s low-pressure (LP) steam turbine are considered. The geometrical model was created with a modified blade count for L-0 stators to allow the simulation of only a sector of the full annular domain and it includes full span shrouds and tip-cavity paths and seals for both rotor blade rows.
In particular, the effects produced by mutually shifting (clocking) the airfoils in the stationary blade rows has been investigated. The experimental data and computational results indicate that airfoil clocking can be used to increase the efficiency and reduce the unsteady rotor loadings in axial compressors. This decreases the overall work output and also changes the flow incidence onto the downstream blade rows. Using a series of high-fidelity eddy resolving simulations, the current study attempts to provide an improved understanding for the complex flow physics over the endwalls of a high-lift Low Pressure Turbine (LPT) blade.
Figure shows a first-stage turbine blade with a shower headtype cooling at the leading edge of the blade, cooling holes in rows throughout the blade span airfoil section, and also cooling holes along the trailing edge. The advanced technology turbine blades have a thermal barrier coating (TBC) to further protect the blade. "Numerical Investigation of the Effect of Roughness and Passing Wakes on LP Turbine Blades Performance." Proceedings of the ASME Turbo Expo Power for Land, Sea, and Air. Volume 6: Turbomachinery, Parts A and B.
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Experimental and Numerical Investigation of Losses in Low-Pressure Turbine Blade Rows Daniel J. Dorney, James P. Lake, Paul I. King, and David E. Ashpis Unclassified -Unlimited Subject Categories.
Experimental and numerical investigation of losses in low-pressure turbine blade rows (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors / Contributors: Daniel J Dorney; NASA Glenn Research Center.
Experimental and Numerical Investigation of Losses in Low-Pressure Turbine Blade Rows. Experimental and numerical investigation of losses in low-pressure turbine blade rows (OCoLC) Material Type: Document, Government publication, National government publication, Internet resource: Document Type: Internet Resource, Computer File: All Authors / Contributors: Daniel J Dorney; NASA Glenn Research Center.
Experimental and numerical investigation of losses in low-pressure turbine blade rows. Study of low Reynolds number effects on the losses in low-pressure turbine blade rows.
Experimental investigation of separation on low pressure turbine blades. Experimental and numerical investigation of losses in low-pressure turbine blade rows.
Daniel Dorney. The paper presents the total pressure experimental measurements carried out at the Romanian Research and Development Institute for Gas Turbines COMOTI in order to determine the total pressure losses in the Inter - Turbine Duct of a two spools gas turbine, as a function of the gas turbine operating regime (mass flow rate) and rotational speed.
Experimental and numerical results from a study dealing with the effect of loading level and chord-wise loading distribution on low-pressure turbine (LPT) blade performance are presented. Only a single blade row is considered here, and the study is conducted in a stationary linear cascade that simulates the aero characteristics.
Predicting Separation and Transitional Flow in Turbine Blades at Low Reynolds Numbers—Part II: The Application to a Highly Separated Turbine Blade Cascade Geometry J. Turbomach (July, ) Comparison of Semi-Empirical Correlations and a Navier-Stokes Method for the Overall Performance Assessment of Turbine Cascades.
The results of the numerical survey demonstrated substantial benefits of relatively small bleed rates to the local flow field and to the performance of the two blade rows. On the rotor, boundary layer fluid was removed from the main flow path through an axisymmetric slot in the casing over the rotor tip.
Experimental and numerical investigation of losses in low-pressure turbine blade rows. Daniel Dorney. reached. The modified loss correlation was implemented in a turbine design tool.
Hence it is tested for usability in design calculations. The presented paper will describe the experimental and numerical setup, the relevant loss correlations from open literature and the modifications of the correlations to extend their validity range.
Experimental and Numerical Investigation of Losses in Low-Pressure Turbine Blade Rows NASA/TM— January AIAA–– The NASA STI Program Office in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science.
The NASA Scientific and Technical. The present study analyzes the secondary flow field of the front-loaded low-pressure turbine blade designated L2F with and without blade profile contouring at the junction of the blade and endwall.
Experimental Investigation of the Clocking Effect in a Stage Axial Turbine—Part II: Unsteady Results and Boundary Layer Behavior J.
Turbomach (April, ) Effects of Multiblocking and Axial Gap Distance on Performance of Partial Admission Turbines: A Numerical Analysis.
Aerodynamic measurements were acquired on a modern single-stage, transonic, high-pressure turbine with the adjacent low-pressure turbine vane row (a typical civilian one and one-half stage turbine rig) to observe the effects of low-pressure turbine vane clocking on overall turbine performance.
The experimental results constituted in this systematic investigation are available for download and should serve as a basic data set for future calculations with different turbulence and transition models, thereby shedding some light on the complexity and modeling required for a suitable numerical treatment of the wake-induced transition process.
Experimental and Numerical Investigation of Losses in Low-Pressure Turbine Blade Rows Experimental and Numerical Investigation of Losses in Low-Pressure Turbine Blade Rows Dorney, Daniel J.; Lake, James P.; King, Paul I.; Ashpis, David E.
E x p e r i m e n t a l d a t a and n u m e r i c a l s i m u l a t i o n s o f l o w - p r e s s u r e t u r b i n e s h a v. Experimental and Numerical Investigation of Losses in Low-Pressure Turbine Blade Rows.
Article. Several recent studies have revealed that the performance of low-pressure turbine blades is a. Experimental data and numerical simulations of low-pressure turbines have shown that unsteady blade row interactions and separation can have a significant impact on the turbine efficiency.
Measured turbine efficiencies at takeoff can be as much as two points higher than those at cruise conditions. Secondary flow and loss development in the TDiv-EIZ low-pressure turbine cascade are investigated utilizing (U)RANS simulations in cases with and without periodically incoming wakes at M a 2 t h = 0.
59 and R e 2 t h = 2 × 10 5. The predictions are compared to experimental data presented by Kirik and Niehuis (). The axial mid-span and overall loss development in the TDiv-EIZ and. Comprehensive experimental investigations were conducted to get deeper insight into the physics of stator clocking in turbomachines.
Different measurement techniques were used to investigate the influence of varying clocking positions on the highly unsteady flow field in a stage axial low-pressure (LP) turbine.EXPERIMENTAL AND NUMERICAL INVESTIGATION OF LOSSES IN LOW-PRESSURE TURBINE BLADE ROWS Daniel J.
Dorney x Virginia ('omn_onwealth!-niversity Richmond. VA James P. Lake _' AFRL/PRRS Edwards AFB, CA Paul I. King b Air Force Institute of Technology Wright-Patterson AFB, OH David E. Ashpis c NASA Glenn Research Center Cleveland, OH ABSTRACT.