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Computational Study Of Losses In A Shrouded Transonic Turbine Blade Passage With Tip Clearance
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Book Synopsis Computational Study of Losses in a Shrouded Transonic Turbine Blade Passage with Tip Clearance by : Wayne Strasser
Download or read book Computational Study of Losses in a Shrouded Transonic Turbine Blade Passage with Tip Clearance written by Wayne Strasser and published by . This book was released on 2003 with total page 280 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analysis of Turbine Rotor Tip Clearance Losses and Parametric Optimization of Shroud by : William V. Banks (III)
Download or read book Analysis of Turbine Rotor Tip Clearance Losses and Parametric Optimization of Shroud written by William V. Banks (III) and published by . This book was released on 2019 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic losses due to tip leakage in a High Pressure Turbine (HPT) rotor setting are analyzed using the commercial CFD software Star-CCM+. The compressible RANS equations were solved over unstructured polyhedral grids of 11 to 17 million cells, with turbulence resolved using the k-w SST model. A study of 3 blade tip/casing configurations at tip clearances between 0% and 4% of blade span is performed, with resulting mass-flow Reynolds #'s of 2.4-2.7 million and levels of reaction of 0.13-0.17. A flat-tip blade experienced a linear correlation between tip clearance and efficiency. The same blade with recessed casing was more efficient for small clearances, but large shear losses were seen to nullify this advantage at high clearances. A shrouded blade was more efficient than both at all clearances, displaying asymptotic behavior at high clearances. Various pressure and velocity monitoring techniques are employed to evaluate leakage flow and loss. Location and strength of leakage vortices are discussed, as these are closely tied with efficiency. A parametric study was performed on the shroud geometry, examining seal angle, number of seals, seal wear, and shroud axial gap. Efficiencies were compared between each study point at clearances of 2% and 4% of blade span. Total pressure loss was tracked across the blade and split between the main flow path and tip gap to distinguish between Profile and Internal Gap Shear losses. Axial gap was seen to have the greatest impact on efficiency, as a narrower gap acts as additional tip flow blockage and increases efficiency. At lower clearances, seal wear produced a negative impact as well.
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 488 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Book Synopsis Turbine Blade Tip Design and Tip Clearance Treatment by : Tony Arts
Download or read book Turbine Blade Tip Design and Tip Clearance Treatment written by Tony Arts and published by . This book was released on 2004 with total page 586 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Turbine Tip Clearance Loss Mechanisms by : Steven Andrew Mazur
Download or read book Turbine Tip Clearance Loss Mechanisms written by Steven Andrew Mazur and published by . This book was released on 2013 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: Three-dimensional numerical simulations (RANS and URANS) were used to assess the impact of two specific design features, and of aspects of the actual turbine environment, on turbine blade tip loss. The calculations were carried out for a subsonic high pressure turbine stage. The loss mechanism examined is that due to tip clearance vortex mixing. The effects examined were three-dimensional blade stacking, downstream transition duct geometry, and unsteadiness due to an upstream nozzle guide vane. Tip leakage loss changes due to three-dimensional blade stacking (bowing or reverse bowing) are verified to be associated with changes in the magnitude of blade tip loading, which create differences in the leakage flow exit velocities. The effect of a downstream diffusing transition duct on tip leakage losses is small; there was a 3.6% increase in tip leakage loss for a 65% increase in duct exit-to-inlet area ratio compared to a constant area duct. For unsteadiness arising from an upstream nozzle guide vane, it is shown that substantial temporal fluctuations in vortex core velocity and loss generation exist. However, the time average tip leakage loss differed less than 5% from the tip leakage loss calculated on a steady flow basis. Based on the computations, the mechanism for tip leakage vortex loss in the three different situations examined appears to be similar to that which is seen for an isolated turbine blade.
Book Synopsis Turbine Design and Application by : Arthur J. Glassman
Download or read book Turbine Design and Application written by Arthur J. Glassman and published by . This book was released on 1972 with total page 282 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of Using Tip Leakage Interrupter and Blade Slit to Mitigate Aerodynamic Losses in Axial Turbine Stage by : Veerandra Chakkarava Andichamy
Download or read book An Investigation of Using Tip Leakage Interrupter and Blade Slit to Mitigate Aerodynamic Losses in Axial Turbine Stage written by Veerandra Chakkarava Andichamy and published by . This book was released on 2019 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The flow field near the blade tip in a turbine stage is highly three dimensional with multiple vortical systems. They are a major source of energy loss in the turbine passage. The current study uses two new concepts called Blade Slit and Tip Leakage Interrupters (TLI) to mitigate some of the adverse effects of these vortical structures and improve the efficiency of an axial turbine stage.A Blade Slit is a small cut (slit) is made on the blade to facilitate high momentum fluid on the pressure side of the blade to pass through the blade and reach the suction side. This flow, on reaching the suction side, acts as a jet and interacts with the local vortical structures. The slit, when strategically placed, facilitates the jet to impinge the core of the low momentum vortex systems. This interaction effectively reduces the strength of these vortices and thereby reduces the aerodynamic loss in the turbine passage.TLIs are a system of vortex generators attached to the suction side of the turbine blade tip. They operate by inducing controlled vortical structures originating from strategically shaped/oriented multiple and sub-miniature vortex generators. They also act as a flow obstruction for the existing vortex system in the passage. When properly placed on the blade surface, these TLIs interact with the tip leakage vortex and passage vortex present in the turbine passage. This interaction reduces the damaging aerodynamic effects of these vortices. Both of these designs are developed as proof of concepts and their aerodynamic loss mitigation characteristics are studied in this thesis. In this investigation, the design parameters associated with these concepts such as their local orientation and location on the blade surface are varied. The influence of these design parameters over the loss reduction properties of the Blade Slit and TLI is studied. Both of these designs are experimentally and computationally analyzed in this study. The experiments in this study are carried out in a single-stage, low-speed axial turbine facility, while the computational work is performed using one to one computational model of the experimental configuration. The results from the Blade Slit design show that not all the fluid exiting the slit imparts high momentum to the vortical structures. Some of these fluids interact with the main flow on the suction side and creates additional aerodynamic losses in the turbine passage. In the case of TLI, the orientation of TLI with respect to the local blade surface determines the nature of interaction between the TLI and the vortical structures in the passage and hence its ability to reduce the aerodynamic losses. The study draws conclusions about the significance of individual design parameters associated with Blade Slit and TLI. It also shows that significant loss reduction might be possible with simple modifications to the blade geometry. All the modifications on the blade should be limited to the highly vortical region near the blade tip. Any modification which changes the flow properties of the main flow results in an additional aerodynamic loss in the turbine passage. In addition to analyzing Blade Slit and TLI design, the aerodynamic influence of blade tip modifications and the blade tip clearances in a turbine passage have also been studied.
Book Synopsis Combined Experimental/computational Study of Flow in Turbine Blade Cooling Passage: Part II - Numerical Simulations by : Diane M. McGrath
Download or read book Combined Experimental/computational Study of Flow in Turbine Blade Cooling Passage: Part II - Numerical Simulations written by Diane M. McGrath and published by . This book was released on 1995 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine and Aeroengine Congress and Exposition, Houston, Texas - June 5-8, 1995.
Book Synopsis Radial Flow Turbocompressors by : Michael Casey
Download or read book Radial Flow Turbocompressors written by Michael Casey and published by Cambridge University Press. This book was released on 2021-06-10 with total page 789 pages. Available in PDF, EPUB and Kindle. Book excerpt: An introduction to the theory and engineering practice that underpins the component design and analysis of radial flow turbocompressors. Drawing upon an extensive theoretical background and years of practical experience, the authors provide descriptions of applications, concepts, component design, analysis tools, performance maps, flow stability, and structural integrity, with illustrative examples. Features wide coverage of all types of radial compressor over many applications unified by the consistent use of dimensional analysis. Discusses the methods needed to analyse the performance, flow, and mechanical integrity that underpin the design of efficient centrifugal compressors with good flow range and stability. Includes explanation of the design of all radial compressor components, including inlet guide vanes, impellers, diffusers, volutes, return channels, de-swirl vanes and side-streams. Suitable as a reference for advanced students of turbomachinery, and a perfect tool for practising mechanical and aerospace engineers already within the field and those just entering it.
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1975 with total page 1000 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Combined Experimental/computational Study of Flow in Turbine Blade Cooling Passage by :
Download or read book A Combined Experimental/computational Study of Flow in Turbine Blade Cooling Passage written by and published by . This book was released on 1994 with total page 192 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Combined Experiment/computational Study of Flow in Turbine Blade Cooling Passage by :
Download or read book A Combined Experiment/computational Study of Flow in Turbine Blade Cooling Passage written by and published by . This book was released on 1994 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Three-Dimensional Flow Field Measurements in a Transonic Turbine Cascade by : P. W. Geil
Download or read book Three-Dimensional Flow Field Measurements in a Transonic Turbine Cascade written by P. W. Geil and published by . This book was released on 1996 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine and Aeroengine Congress & Exhibition Birmingham, UK - June 10-13, 1996.
Book Synopsis Loss Mechanisms in Turbine Tip Clearance Flows by : Arthur C. Huang
Download or read book Loss Mechanisms in Turbine Tip Clearance Flows written by Arthur C. Huang and published by . This book was released on 2011 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: Numerical simulations of tip clearance ow have been carried out to dene the loss generation mechanisms associated with tip leakage in unshrouded axial turbines. Mix- ing loss between the leakage, which takes the form of a strong embedded streamwise vortex (u=ux 1 in the vortex core), and the mainstream ow is found to be the main source of loss. Vortex line contraction, and consequent vortex core expansion, and also vortex breakdown, are identied as the two important mechanisms that determine mixing loss. Because of these vortex dynamic features, the behavior is dierent from the conventional view of the effect of pressure level on mixing of non- uniform flows. More specifically, it is shown, through control volume arguments and axisymmetric computations, that as a strongly swirling ow passes through a pres- sure rise, the mixed-out loss can either decrease or increase, the latter occurring if the deceleration becomes large enough to initiate vortex breakdown. It is further shown that tip vortices in turbines experience pressure rises large enough to cause vortex breakdown. The effect of pressure distribution on tip leakage losses is illustrated through examination of two turbine blades, one designed with a forward loaded tip and one with an aft loaded tip. The computations show a 16% difference in tip clearance loss between the two, due to the lower pressure rise encountered by the clearance vortex, and hence lower vortex breakdown losses, with the forward loaded blade. Other computational experiments, on the effects of blade loading, incidence, and solidity, are also shown to be consistent with the ideas developed about blade pressure distribution effects on vortex breakdown and hence clearance mixing loss.
Book Synopsis Computation of Three-dimensional Viscous Transonic Turbine Stage Flow Including Tip Clearance Effects by : Rudiger Merz
Download or read book Computation of Three-dimensional Viscous Transonic Turbine Stage Flow Including Tip Clearance Effects written by Rudiger Merz and published by . This book was released on 1995 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine and Aeroengine Congress and Exposition, Houston, Texas - June 5-8, 1995.
Book Synopsis Heat Transfer in Gas Turbine Systems by : Richard J. Goldstein
Download or read book Heat Transfer in Gas Turbine Systems written by Richard J. Goldstein and published by . This book was released on 2001 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Explores recent developments in heat transfer and thermal control applied to modern high-temperature gas turbine systems. It examines experimental results and techniques computational studies and methods and design recommendations. Aspects of heat transfer in rotating machinery are studied as well as thermal aspects of other sections of the turbine (e.g. the compressor). Proceedings of an August 2000 conference.
Download or read book NASA SP. written by and published by . This book was released on 1992 with total page 332 pages. Available in PDF, EPUB and Kindle. Book excerpt:
