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Author : Tony Arts
Publisher :
ISBN 13 :
Total Pages : 586 pages
Book Rating : 4.0/5 ( download)
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:
Author : Tony Arts
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
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 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Steven Andrew Mazur
Publisher :
ISBN 13 :
Total Pages : 98 pages
Book Rating : 4.:/5 (862 download)
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.
Author : M. J. Ford
Publisher :
ISBN 13 :
Total Pages : 80 pages
Book Rating : 4.:/5 (227 download)
Download or read book Design, Fabrication, and Demonstration of a Miniaturized Tip Clearance Measuring Device written by M. J. Ford and published by . This book was released on 1974 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes the design, fabrication, and demonstration of a miniaturized turbine blade tip clearance measurement system for use with small gas turbine engines during engine operation. This system was originated by Pratt and Whitney Aircraft and uses laser light that is focused on the blade tips. The light reflected from the blade tips is imaged onto an output device. The relationship between the change in tip clearance and the change in position of the output light spot provides a direct indication of tip clearance. (Modified author abstract).
Author : Scott B. Lattime
Publisher :
ISBN 13 :
Total Pages : 32 pages
Book Rating : 4.:/5 (317 download)
Download or read book Test Rig for Evaluating Active Turbine Blade Tip Clearance Control Concepts written by Scott B. Lattime and published by . This book was released on 2003 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Dean Andrew Ward
Publisher :
ISBN 13 :
Total Pages : 332 pages
Book Rating : 4.:/5 (282 download)
Download or read book Turbine Blade Tip Film Cooling Measurements written by Dean Andrew Ward and published by . This book was released on 1992 with total page 332 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : S. Szczecinski
Publisher :
ISBN 13 :
Total Pages : 11 pages
Book Rating : 4.:/5 (227 download)
Download or read book Effect of Aircraft-Engine Turbine Design on the Size of Blade Tip Clearance written by S. Szczecinski and published by . This book was released on 1969 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt: The optimal selection of turbine blade tip clearances is one of the most complex and critical problems in the design and operation of aircraft turbine engines. In addition to the ambient temperature, the tip clearance of rotor blades in the cold state is affected by the temperature variation under various operating conditions. Some stresses on turbine components depend on the angular velocity; the deformation will vary for different rpm, which must be considered in determining the necessary tip clearance. In general, the accepted tip clearance is 2 percent of the mean blade length in a given turbine stage. It has been found that in turboprop engines, the casing and rotor stresses increase as the rotor velocity increases. In turbojet engines, the stresses are relatively high at low rpm, followed by a decrease and then increase again reaching the maximum magnitude at high rpm. These stress variations are caused by gas temperature changes. The minimum tip clearance depends mainly on the turbine design, and, in some cases, it is possible to achieve a practically constant tip clearance. Heat resistant turbine casing linings do not seem to be necessary in all cases. (Author).
Author : Gary McDonald
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (89 download)
Download or read book Measurement of Tip Clearance Pressure Distributions and Heat Transfer on a Turbine Blade at Realistic Blade Velocities written by Gary McDonald and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Sharef Aly Abdel-Fattah
Publisher :
ISBN 13 :
Total Pages : 260 pages
Book Rating : 4.:/5 (544 download)
Download or read book Blade Tip Clearance Effect on the Performance and Flow Field of a Three Stage Axial Turbine written by Sharef Aly Abdel-Fattah and published by . This book was released on 2003 with total page 260 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 101 pages
Book Rating : 4.:/5 (946 download)
Download or read book Methods of Desensitizing Tip Clearance Effects in Turbines written by and published by . This book was released on 2000 with total page 101 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study is an attempt to reduce the effect of the leakage vortex in axial flow turbines. A 3D Navier-Stokes CFD solver with two equation turbulence modeling was used to compute the flow through an axial flow turbine with modified blade tip designs. The three modified blade tip designs each involved adding a chamfer to the tip of the blade, in an attempt to diffuse the leakage flow through the gap and obstruct the leakage flow with the outer casing's shear layer. A baseline flat tip case and three modified tip cases were simulated and the leakage flow and vortex for each was analyzed in detail. By chamfering the blade tip near the trailing edge of the gap, the leakage flow inside the gap was turned toward the direction of the blade's camber. This turning resulted in a decrease in the size and strength of the leakage vortex and its subsequent losses, while at the same time, did not reduce the blade loading by an appreciable amount.
Author : J. Van Den Andel
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (137 download)
Download or read book Turbine Blade Tip Clearance Measurements in a Large Industrial Two-shaft Gas Turbine written by J. Van Den Andel and published by . This book was released on 1982 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Describes the distortions of an inner cylinder were first measured outside the turbine by placing it on a horizontal boring mill while heating the inner diameter.
Author : Wayne Strasser
Publisher :
ISBN 13 :
Total Pages : 280 pages
Book Rating : 4.:/5 (559 download)
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:
Author : Veerandra Chakkarava Andichamy
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (113 download)
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.
Author : Md. Hamidur Rahman
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (462 download)
Download or read book Numerical Analysis of Blade Tip Leakage Flow and Shroud Heat Transfer in Gas Turbine Engines written by Md. Hamidur Rahman and published by . This book was released on 2008 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: One of the most critical components of gas turbine engines, rotor blade tip and casing, is exposed to high thermal load. It is a significant challenge to the designer to protect the turbine material from this severe situation. Leakage flow over the blade tip is also one of the important issues to improve the turbine performance. To understand the detailed phenomena and natures of the heat transfer on the turbine blade tip and casing in association with the tip leakage flow under actual turbine operating conditions, both steady and unsteady simulations have been conducted. A single stage gas turbine engine was modeled and simulated using commercial CFD solver ANSYS CFX R.11. The modeled turbine stage has 30 vanes and 60 blades with a pressure ratio of 3.2 and a rotational speed of 9500 rpm. The predicted isentropic Mach number and adiabatic wall temperature on the casing showed good agreement with available experimental data under the close operating condition. Through the steady simulations, the typical tip leakage flow structures and heat transfer rate distributions were analyzed. The tip leakage flow separates and recirculates just around the pressure side edge of the blade tip. This coverage of the recirculating flow results in low heat transfer rates on the tip surface. The leakage flow then reattaches on the tip surface beyond the flow separation zone. This flow reattachment has shown enhanced heat transfer rates on the tip. The leakage flow interaction with the reverse cross flow, induced by relative casing motion, is found to have significant effect on the casing heat transfer rate distribution. Critical region of high heat transfer rate on the casing exists near the blade tip leading edge and along the pressure side edge. Whereas near the suction side the heat transfer rates are relatively low due to the coverage of the reverse cross flow. The effects of the tip clearance heights and rotor rotating speeds were also investigated. The region of recirculating flow increases with the increase of clearance heights. The flow incidence changes and the casing relative motion is enhanced with higher rotation speeds. As a result, the high heat transfer rate regions have been changed with these two parameters. Unsteady simulations have been performed to investigate time dependent behaviors of the leakage flow structures and heat transfer on the rotor casing and blade tip. The effects of different time steps, number of sub iteration and number of rotor vane passing were firstly examined. The periodicity of the tip leakage flow and heat transfer rate distribution is observed for each vane passing. The relative change in the position of the vane and the vane trailing edge shock alters the inlet flow conditions of the rotor part. It results in the periodic variations of the leakage flow structures and heat transfer rate distributions. The higher heat transfer rates were observed at the region where the trailing edge shock reached. The maximum amplitude of the pressure fluctuation in the tip region is about 20% of the averaged rotor inlet pressure. The maximum amplitude of the heat transfer rate fluctuation on the blade tip, caused by the unsteady leakage flow variations, reaches up to about 25% of the mean heat transfer rate. The effects of tip clearance heights and rotor speeds have also been analyzed and compared one with respect to others. Same typical patterns of leakage flow structures and heat transfer rate distribution can be obtained in both steady and unsteady simulations. However, steady simulation underpredicted the highest heat transfer rate. Because it couldn't capture the critical local high heat transfer phenomena caused by the unsteady stator-rotor interactions.
Author : Peter Jansohn
Publisher : Elsevier
ISBN 13 : 0857096060
Total Pages : 849 pages
Book Rating : 4.8/5 (57 download)
Download or read book Modern Gas Turbine Systems written by Peter Jansohn and published by Elsevier. This book was released on 2013-08-31 with total page 849 pages. Available in PDF, EPUB and Kindle. Book excerpt: Modern gas turbine power plants represent one of the most efficient and economic conventional power generation technologies suitable for large-scale and smaller scale applications. Alongside this, gas turbine systems operate with low emissions and are more flexible in their operational characteristics than other large-scale generation units such as steam cycle plants. Gas turbines are unrivalled in their superior power density (power-to-weight) and are thus the prime choice for industrial applications where size and weight matter the most. Developments in the field look to improve on this performance, aiming at higher efficiency generation, lower emission systems and more fuel-flexible operation to utilise lower-grade gases, liquid fuels, and gasified solid fuels/biomass. Modern gas turbine systems provides a comprehensive review of gas turbine science and engineering. The first part of the book provides an overview of gas turbine types, applications and cycles. Part two moves on to explore major components of modern gas turbine systems including compressors, combustors and turbogenerators. Finally, the operation and maintenance of modern gas turbine systems is discussed in part three. The section includes chapters on performance issues and modelling, the maintenance and repair of components and fuel flexibility. Modern gas turbine systems is a technical resource for power plant operators, industrial engineers working with gas turbine power plants and researchers, scientists and students interested in the field. Provides a comprehensive review of gas turbine systems and fundamentals of a cycle Examines the major components of modern systems, including compressors, combustors and turbines Discusses the operation and maintenance of component parts
Author : Chaoqun Liu
Publisher : Springer Nature
ISBN 13 : 3030702170
Total Pages : 479 pages
Book Rating : 4.0/5 (37 download)
Download or read book Liutex and Third Generation of Vortex Definition and Identification written by Chaoqun Liu and published by Springer Nature. This book was released on 2021-07-26 with total page 479 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book collects papers presented in the Invited Workshop, “Liutex and Third Generation of Vortex Definition and Identification for Turbulence,” from CHAOS2020, June 9-12, 2020, which was held online as a virtual conference. Liutex is a new physical quantity introduced by Prof. Chaoqun Liu of the University of Texas at Arlington. It is a vector and could give a unique and accurate mathematical definition for fluid rotation or vortex. The papers in this volume include some Liutex theories and many applications in hydrodynamics, aerodynamics and thermal dynamics including turbine machinery. As vortex exists everywhere in the universe, a mathematical definition of vortex or Liutex will play a critical role in scientific research. There is almost no place without vortex in fluid dynamics. As a projection, the Liutex theory will play an important role on the investigations of the vortex dynamics in hydrodynamics, aerodynamics, thermodynamics, oceanography, meteorology, metallurgy, civil engineering, astronomy, biology, etc. and to the researches of the generation, sustenance, modelling and controlling of turbulence.
Author : Lawrence C. Baker
Publisher :
ISBN 13 :
Total Pages : 177 pages
Book Rating : 4.:/5 (796 download)
Download or read book Turbine tip clearance measurement written by Lawrence C. Baker and published by . This book was released on 1981 with total page 177 pages. Available in PDF, EPUB and Kindle. Book excerpt:
