EBookClubs

Read Books & Download eBooks Full Online

EBookClubs

Read Books & Download eBooks Full Online

Book EXPERIMENTAL INVESTIGATION OF BOUNDARY LAYER BEHAVIOR IN A SIMULATED LOW PRESSURE TURBINE NASA TM 1998 207921 SEP 15 1998

Download or read book EXPERIMENTAL INVESTIGATION OF BOUNDARY LAYER BEHAVIOR IN A SIMULATED LOW PRESSURE TURBINE NASA TM 1998 207921 SEP 15 1998 written by United States. National Aeronautics and Space Administration and published by . This book was released on 1999* with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book EXPERIMENTAL STUDY OF BOUNDARY LAYER BEHAVIOR IN A SIMULATED LOW PRESSURE TURBINE NASA TM 1998 208503 JAN 20 1999

Download or read book EXPERIMENTAL STUDY OF BOUNDARY LAYER BEHAVIOR IN A SIMULATED LOW PRESSURE TURBINE NASA TM 1998 208503 JAN 20 1999 written by United States. National Aeronautics and Space Administration and published by . This book was released on 1999* with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Experimental investigation of boundary layer behavior in a simulated low pressure turbine ASME 98 GT 34

Download or read book Experimental investigation of boundary layer behavior in a simulated low pressure turbine ASME 98 GT 34 written by Ki H. Sohn and published by . This book was released on 1998 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Stockholm, Sweden, June 2 - June 5, 1998.

Book Experimental Study of Transitional Flow Behavior in a Simulated Low Pressure Turbine

Download or read book Experimental Study of Transitional Flow Behavior in a Simulated Low Pressure Turbine written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-24 with total page 216 pages. Available in PDF, EPUB and Kindle. Book excerpt: A detailed investigation of the flow physics occurring on the suction side of a simulated Low Pressure Turbine (LPT) blade was performed. A contoured upper wall was designed to simulate the pressure distribution of an actual LPT airfoil onto a flat lower plate. The experiments were carried out for the Reynolds numbers of 35,000, 70,000, 100,000 and 250,000 with four levels of freestream turbulence ranging from 1% to 4%. For the three lower Reynolds numbers, the boundary layer on the flat plate was separated and formed a bubble. The size of laminar separation bubble was measured to be inversely proportional to the freestream turbulence levels and Reynolds numbers. However, no separation was observed for the Re = 250,000 case. The transition on a separated flow was found to proceed through the formation of turbulent spots in the free shear layer as evidenced in the intermittency profiles for Re = 35,000, 70,000 and 100,000. Spectral data show no evidence of Kelvin-Helmholtz or Tollmien-Schlichting instability waves in the free shear layer over a separation bubble (bypass transition). However, the flow visualization revealed the large vortex structures just outside of the bubble and their development to turbulent flow for Re = 50,000, which is similar to that in the free shear layer (separated-flow transition). Therefore, it is fair to say that the bypass and separated-flow transition modes coexist in the transitional flows over the separation bubble for certain conditions. Transition onset and end locations and length determined from intermittency profiles decrease as Reynolds number and freestream turbulence levels increase. Sohn, Ki Hyeon and DeWitt, Kenneth J. Glenn Research Center NCC3-288...

Book Study of Boundary Layer Development in a Two Stage Low Pressure Turbine

Download or read book Study of Boundary Layer Development in a Two Stage Low Pressure Turbine written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-11 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental data from jet-engine tests have indicated that unsteady blade row interactions and separation can have a significant impact on the efficiency of low-pressure turbine stages. Measured turbine efficiencies at takeoff can be as much as two points higher than those at cruise conditions. Several recent studies have revealed that Reynolds number effects may contribute to the lower efficiencies at cruise conditions. In the current study numerical simulations have been performed to study the boundary layer development in a two-stage low-pressure turbine, and to evaluate the transition models available for low Reynolds number flows in turbomachinery. The results of the simulations have been compared with experimental data, including airfoil loadings and integral boundary layer quantities. The predicted unsteady results display similar trends to the experimental data, but significantly overestimate the amplitude of the unsteadiness. The time-averaged results show close agreement with the experimental data.Dorney, Daniel J. and Ashpis, David E. and Halstead, David E. and Wisler, David C.Glenn Research CenterJET ENGINES; TWO STAGE TURBINES; COMPUTERIZED SIMULATION; BALDWIN-LOMAX TURBULENCE MODEL; BOUNDARY LAYER TRANSITION; TRANSITION FLOW; FLOW VISUALIZATION; BOUNDARY LAYER SEPARATION; SEPARATED FLOW; ROTOR BLADES (TURBOMACHINERY); TAKEOFF; CRUISING FLIGHT; COMPUTATIONAL GRIDS; NOZZLE FLOW; SKIN FRICTION; TURBINE BLADES; REYNOLDS NUMBER; FLOW CHARACTERISTICS; FLOW DISTRIBUTION

Book Experimental Study of Transitional Flow Behavior in a Simulated Low Pressure Turbine

Download or read book Experimental Study of Transitional Flow Behavior in a Simulated Low Pressure Turbine written by Nasa Technical Reports Server (Ntrs) and published by BiblioGov. This book was released on 2013-07 with total page 230 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Technical Reports Server (NTRS) houses half a million publications that are a valuable means of information to researchers, teachers, students, and the general public. These documents are all aerospace related with much scientific and technical information created or funded by NASA. Some types of documents include conference papers, research reports, meeting papers, journal articles and more. This is one of those documents.

Book STUDY OF BOUNDARY LAYER DEVELOPMENT IN A TWO STAGE LOW PRESSURE TURBINE NASA TM 1999 208913 MAR 1 1999

Download or read book STUDY OF BOUNDARY LAYER DEVELOPMENT IN A TWO STAGE LOW PRESSURE TURBINE NASA TM 1999 208913 MAR 1 1999 written by United States. National Aeronautics and Space Administration and published by . This book was released on 1999* with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book On the Physics of Flow Separation Along a Low Pressure Turbine Blade Under Unsteady Flow Conditions

Download or read book On the Physics of Flow Separation Along a Low Pressure Turbine Blade Under Unsteady Flow Conditions written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-20 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: The present study, which is the first of a series of investigations dealing with specific issues of low pressure turbine (LPT) boundary layer aerodynamics, is aimed at providing detailed unsteady boundary flow information to understand the underlying physics of the inception, onset, and extent of the separation zone. A detailed experimental study on the behavior of the separation zone on the suction surface of a highly loaded LPT-blade under periodic unsteady wake flow is presented. Experimental investigations were performed at Texas A&M Turbomachinery Performance and Flow Research Laboratory using a large-scale unsteady turbine cascade research facility with an integrated wake generator and test section unit. To account for a high flow deflection of LPT-cascades at design and off-design operating points, the entire wake generator and test section unit including the traversing system is designed to allow a precise angle adjustment of the cascade relative to the incoming flow. This is done by a hydraulic platform, which simultaneously lifts and rotates the wake generator and test section unit. The unit is then attached to the tunnel exit nozzle with an angular accuracy of better than 0.05 , which is measured electronically. Utilizing a Reynolds number of 110,000 based on the blade suction surface length and the exit velocity, one steady and two different unsteady inlet flowconditions with the corresponding passing frequencies, wake velocities and turbulence intensities are investigated using hot-wire anemometry. In addition to the unsteady boundary layer measurements, blade surface pressure measurements were performed at Re=50,000, 75,000, 100,000, and 125,000 at one steady and two periodic unsteady inlet flow conditions. Detailed unsteady boundary layer measurement identifies the onset and extent of the separation zone as well as its behavior under unsteady wake flow. The results presented in ensemble-averaged and contour plot forms contribute to understanding t

Book An Experimental Investigation of Pressure Driven Three dimensional Turbulent Boundary Layers

Download or read book An Experimental Investigation of Pressure Driven Three dimensional Turbulent Boundary Layers written by Stanford University. Thermosciences Division and published by . This book was released on 1987 with total page 390 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Study of Boundary Layer Development in a Two Stage Low Pressure Turbine

Download or read book Study of Boundary Layer Development in a Two Stage Low Pressure Turbine written by Daniel J. Dorney and published by . This book was released on 1999 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book An Experimental Investigation Into the Behaviour of the Turbulent Boundary Layer with Distributed Suction in Regions of Adverse Pressure Gradient

Download or read book An Experimental Investigation Into the Behaviour of the Turbulent Boundary Layer with Distributed Suction in Regions of Adverse Pressure Gradient written by B. G. J. Thompson and published by . This book was released on 1970 with total page 69 pages. Available in PDF, EPUB and Kindle. Book excerpt: