Download or read book The Effect of Vane Trailing Edge Flow on Inter Stage Turbine Sealing written by Ivan Monge-Concepcion and published by . This book was released on 2021 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Modern gas turbine development is moving towards increased engine efficiency and decreased emissions driven, in part, by a continual increase of combustor exit temperatures. To thermally protect critical engine components from catastrophic component failure, a significant fraction of the compressor flow is bypassed around the combustor and used in secondary flow systems. Use of this secondary flow results in a reduced amount of work, which prompts engine designers to optimize the use of these secondary flows. Two applications of the secondary airflow system is a sealing flow for the inter-stage gap and as a cooling flow used in film cooling holes and vane trailing edge flow. The use of sealing flow in the inter-stage gap between the stator vane wall and the rotating disk wall has been widely studied by previous researchers. These studies have built a fundamental understanding of the flow physics involved in hot gas ingestion and is currently applied in the design of overlapping geometries, called rim seals, to deter ingestion. Vane trailing edge (VTE) flows are another type of cooling flow in the secondary airflow system whose main purpose is aimed at optimizing the aerodynamics of the rotor blades by filling in the lower pressure wake region downstream of the stationary vanes. Although there is a vast amount of research in the open literature on the optimal use of purge flows, there are no open studies on the impact of vane trailing edge flows on rim sealing performance. The research presented in this dissertation bridges the gap between the secondary flow used to seal the turbine rim cavity between turbine stages and the influence of vane trailing edge flow (VTE), which is the first presented in the open literature. The measured results confirm the presence of VTE flow in the turbine wheelspace cavity between the stationary vanes and rotating blades. Results show that VTE flow migrates from the main gas path and is entrained into the wheelspace cavity which improves rim cooling effectiveness in the wheelspace cavities. By using a tracer gas, this study found that a superposition relationship exists between the individual secondary flows. Flowfield data confirmed a significant migration of VTE flow occurred over a range of conditions. Through the use of fast-responding pressure transducers, low-pressure cells that did not correspond with the number airfoils were identified and did not change with the presence of the VTE flow. Results were compared with current ingestion prediction models to and found that current prediction models underpredict the entrainment of VTE flow into the rim seal cavity and consequently the cooling fluid potential of VTE flow. The potential of improving VTE flow prediction tools can potentially optimize the use of sealing and VTE flows to offset the detrimental effect of hot gas ingestion.
Download or read book Axial Turbine Aerodynamics for Aero engines written by Zhengping Zou and published by Springer. This book was released on 2018-01-11 with total page 572 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book is a monograph on aerodynamics of aero-engine gas turbines focusing on the new progresses on flow mechanism and design methods in the recent 20 years. Starting with basic principles in aerodynamics and thermodynamics, this book systematically expounds the recent research on mechanisms of flows in axial gas turbines, including high pressure and low pressure turbines, inter-turbine ducts and turbine rear frame ducts, and introduces the classical and innovative numerical evaluation methods in different dimensions. This book also summarizes the latest research achievements in the field of gas turbine aerodynamic design and flow control, and the multidisciplinary conjugate problems involved with gas turbines. This book should be helpful for scientific and technical staffs, college teachers, graduate students, and senior college students, who are involved in research and design of gas turbines.
Download or read book Naval Engineering written by Dennis L. Richardson and published by AuthorHouse. This book was released on 2016-11-04 with total page 219 pages. Available in PDF, EPUB and Kindle. Book excerpt: Naval Engineering: Principles and Theory of Gas Turbine Engines is a technical publication for professional engineers to assist in understanding the history and development of gas turbine engines including the thermodynamic processes known as the Brayton cycle. Common principles of various gas turbine nomenclatures, technical designs, applications, and performance conditions that affect the capabilities and limitations of marine operations are provided. It enables the ability to describe the principal components of gas turbines and their construction. This book will enable the reader to increase professional knowledge through the understanding of navy engineering principles and theory of gas turbine engines. The reader will learn the operation and maintenance of the gas turbine modules (GTMs), gas turbine generators (GTGs), reduction gears, and associated equipment such as pumps, valves, oil purifiers, heat exchangers, shafts, and shaft bearings. Inside this book, you will find technical information such as electronic control circuitry, interfaces such as signal conditioners, control consoles, and designated electrical equipment associated with shipboard propulsion and electrical powergenerating plants. When every detail of engineering work is performed with integrity and reliability, technical leadership know-how will improve.
Download or read book An Investigation of the Effects of Nozzle Guide Vane Trailing Edge Cooling on Rotor Heat Transfer in a Transonic Turbine Stage written by Aaron James Gleixner and published by . This book was released on 1992 with total page 330 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Influence of Blade Leading Edge Geometry and Upstream Blowing on the Heat mass Transfer in a Turbine Cascade written by Marco Papa and published by . This book was released on 2006 with total page 534 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Advanced technologies in flow dynamics and combustion in propulsion and power volume II written by Lei Luo and published by Frontiers Media SA. This book was released on 2023-02-09 with total page 216 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Turbine Vane Coolant Flow Variations and Calculated Effects on Metal Temperatures written by Frederick C. Yeh and published by . This book was released on 1975 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1992 with total page 304 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Gas Turbine Heat Transfer and Cooling Technology Second Edition written by Je-Chin Han and published by CRC Press. This book was released on 2012-11-27 with total page 892 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive reference for engineers and researchers, Gas Turbine Heat Transfer and Cooling Technology, Second Edition has been completely revised and updated to reflect advances in the field made during the past ten years. The second edition retains the format that made the first edition so popular and adds new information mainly based on selected published papers in the open literature. See What’s New in the Second Edition: State-of-the-art cooling technologies such as advanced turbine blade film cooling and internal cooling Modern experimental methods for gas turbine heat transfer and cooling research Advanced computational models for gas turbine heat transfer and cooling performance predictions Suggestions for future research in this critical technology The book discusses the need for turbine cooling, gas turbine heat-transfer problems, and cooling methodology and covers turbine rotor and stator heat-transfer issues, including endwall and blade tip regions under engine conditions, as well as under simulated engine conditions. It then examines turbine rotor and stator blade film cooling and discusses the unsteady high free-stream turbulence effect on simulated cascade airfoils. From here, the book explores impingement cooling, rib-turbulent cooling, pin-fin cooling, and compound and new cooling techniques. It also highlights the effect of rotation on rotor coolant passage heat transfer. Coverage of experimental methods includes heat-transfer and mass-transfer techniques, liquid crystal thermography, optical techniques, as well as flow and thermal measurement techniques. The book concludes with discussions of governing equations and turbulence models and their applications for predicting turbine blade heat transfer and film cooling, and turbine blade internal cooling.
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.
Download or read book An Adverse Effect of Film Cooling on the Suction Surface of a Turbine Vane written by Herbert J. Gladden and published by . This book was released on 1974 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Paper written by and published by . This book was released on 1999 with total page 598 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Cold air Annular cascade Investigation of Aerodynamic Performance of Core engine cooled Turbine Vanes written by Kerry L. McLallin and published by . This book was released on 1976 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Sealing Effectiveness of a Turbine Rim Seal at Engine Relevant Conditions written by Kenneth Clark and published by . This book was released on 2016 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Gas turbines are characterized by high efficiencies compared to other power generation systems, but even small efficiency gains can result in huge reductions in fuel costs and emissions. Overall pressure ratios for gas turbines continue to rise to achieve higher efficiencies, resulting in increasingly extreme thermal conditions in the hot section of the engine. Secondary air, bled from the compressor, is used to cool turbine components and seal the inter-stage cavities from the hot main gas path to maintain component durability. Unsealed cavities lead to hot gas ingestion, which can degrade critical components or, in extreme cases, can be catastrophic to engines. Providing adequate sealing flow is required to maintain component life, but efficient use of the secondary air is required to maintain the thermodynamic efficiency of the engine. To fully optimize these competing requirements, experiments at engine-relevant conditions are required to validate new designs and computational tools. This dissertation presents sealing effectiveness measurements for an engine-realistic turbine rim seal operated at engine-relevant conditions.A new facility providing continuous flow for a 1.5 stage turbine was designed, constructed, and commissioned to study hot gas ingestion for at engine-relevant conditions. Sealing effectiveness was determined through concentration measurements, whereby CO2 was used as a tracer gas in the secondary air supply, and sampled throughout the turbine rim seal and rim cavity. The turbine design was representative of a modern turbine with engine-realistic purge flow delivery and leakage flows, resulting in complex flow fields in the cavities. The measurements indicated that sealing effectiveness depended on the number of purge holes at and inboard of the purge injection location, with more purge holes exhibiting higher effectiveness than fewer purge holes. Outboard of the purge location, the sealing effectiveness was not affected by the number of purge holes. The boundary layer on the rotating disk entrained the purge flow, and the rotor and stator pumping distributed the purge flow throughout the cavity reducing the amount of ingestion. The results indicated that the well-accepted orifice models used to predict sealing effectiveness throughout the industry are successful for some cases; however, the results in this dissertation showed that those models are unsuccessful in predicting sealing effectiveness for the complex engine-realistic geometries and purge flow delivery methods. These findings highlight the need to obtain sealing effectiveness data at engine-relevant conditions, using engine-realistic hardware to develop ingestion models applicable to gas turbine engines.
Download or read book Proceedings of the 13th Intersociety Energy Conversion Engineering Conference San Diego California August 20 25 1978 written by and published by . This book was released on 1978 with total page 938 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1986 with total page 1072 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book ASME Technical Papers written by and published by . This book was released on 1999 with total page 508 pages. Available in PDF, EPUB and Kindle. Book excerpt:
