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Dissertations / Theses on the topic 'Turbine blade cooling'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

Barry, Pamela S. (Pamela Sue). "Rotational effects on turbine blade cooling." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/12114.

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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1994.<br>Title as it appears in the June 1994 MIT Graduate List: Rotational effects of turbine cooling.<br>Includes bibliographical references (leaves 102-103).<br>by Pamela S. Barry.<br>M.S.

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2

Ryley, Joshua Claydon. "Turbine blade mid-chord internal cooling." Thesis, University of Oxford, 2014. http://ora.ox.ac.uk/objects/uuid:14469a51-517c-400c-b477-4fb432c8b648.

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Modern gas turbine engines operate at temperatures well above the melting point of the metal components. This has driven manufactures to develop sophisticated cooling methods which minimise the use of coolant to maximise engine efficiency by enabling further increases in operating temperature. This thesis investigates the cooling performance of engine representative mid-chord internal cooling passages for turbine blades. The work forms part of a larger E.C. FP7 project ERICKA (Engine Representative Internal Cooling Knowledge Applications).This thesis provides detailed maps of heat transfer coe

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3

Telisinghe, Janendra C. "Film cooling of turbine blade trailing edges." Thesis, University of Oxford, 2013. http://ora.ox.ac.uk/objects/uuid:86c06246-16e9-4378-9a61-e09317d31a92.

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In modern gas turbine engines, film cooling is extensively used to cool the components exposed to the hot mainstream gas path. In implementing film cooling on modern gas turbine engines, the trailing edge film poses a particularly challenging design problem. From an aerodynamic point of view, the trailing edge of a blade is designed to be as thin as possible. However, this conflicts with the implementation of the cooling design. The most common method of film cooling the trailing edge is via late pressure surface discrete film cooling holes. Another method of cooling the trailing edge is by us

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4

Choi, Jungho. "An experimental investigation of turbine blade heat transfer and turbine blade trailing edge cooling." Texas A&M University, 2004. http://hdl.handle.net/1969.1/1377.

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This experimental study contains two points; part1 turbine blade heat transfer under low Reynolds number flow conditions, and part 2 trailing edge cooling and heat transfer. The effect of unsteady wake and free stream turbulence on heat transfer and pressure coefficients of a turbine blade was investigated in low Reynolds number flows. The experiments were performed on a five blade linear cascade in a low speed wind tunnel. A spoked wheel type wake generator and two different turbulence grids were employed to generate different levels of the Strouhal number and turbulence intensity, respec

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5

Joo, Jongwook. "Eddy simulation of turbine blade trailing edge cooling /." May be available electronically:, 2008. http://proquest.umi.com/login?COPT=REJTPTU1MTUmSU5UPTAmVkVSPTI=&clientId=12498.

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6

Chambers, Andrew. "An investigation of impingement cooling applied to turbine blade cooling passages." Thesis, University of Oxford, 2003. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.400071.

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7

Fransen, Rémy. "LES based aerothermal modeling of turbine blade cooling systems." Phd thesis, Toulouse, INPT, 2013. http://oatao.univ-toulouse.fr/10012/1/fransen.pdf.

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This PhD dissertation, conducted as part of a CIFRE research project between TURBOMECA and CERFACS in partnership with the VKI, deals with improving performance of axial turbines from helicopter engines. One of the most critical design points of such engines is the control of the high pressure turbine blade lifetime which face the high temperatures from the combustor. Today, industrial numerical aerothermal predictions of the flows around the blade (in the vein and in its cooling system) are performed with the Reynolds Averaged Navier-Stokes (RANS). Thanks to the increasing computational power

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8

Long, K. "Aluminide-based coatings for turbine blade internal cooling passages." Thesis, Cranfield University, 2004. http://dspace.lib.cranfield.ac.uk/handle/1826/11002.

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The development of aero-gas turbines is moving towards more efficient engines with higher pressure ratios and increased Turbine Entry Temperatures. This leads to increases in overall turbine blades temperatures which has resulted in the widescale development of turbine blades with film cooling and Thermal Barrier Coatings (TBCs) which reduce the metal temperature of the blade. The air used for film cooling is directed around the blade by internal passages within the blade, current engines are experiencing hot corrosion in areas of these internal passages, even with internal aluminide coatings.

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9

Tang, Brian M. T. "Unshrouded turbine blade tip heat transfer and film cooling." Thesis, University of Oxford, 2011. http://ora.ox.ac.uk/objects/uuid:f8479e89-9cd1-4aa7-b5c8-8068ad80de54.

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This thesis presents a joint computational and experimental investigation into the heat transfer to unshrouded turbine blade tips suitable for use in high bypass ratio, large civil aviation turbofan engines. Both the heat transfer to the blade tip and the over-tip leakage flow over the blade tip are characterised, as each has a profound influence on overall engine efficiency. The study is divided into two sections; in the first, computational simulations of a very large scale, low speed linear cascade with a flat blade tip were conducted. These simulations were validated against experimental d

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10

Gillespie, David R. H. "Intricate internal cooling systems for gas turbine blading." Thesis, University of Oxford, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.365831.

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11

Wang, Zuolan. "The application of thermochromic liquid crystals to detailed turbine blade cooling measurements." Thesis, University of Oxford, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.303677.

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12

Al-Zurfi, Nabeel. "Large eddy simulation of cooling practices for improved film cooling performance of a gas turbine blade." Thesis, University of Manchester, 2017. https://www.research.manchester.ac.uk/portal/en/theses/large-eddy-simulation-of-cooling-practices-for-improved-film-cooling-performance-of-a-gas-turbine-blade(966b0252-4b0e-45de-9c1f-effe007261b0).html.

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The Large Eddy Simulation approach is employed to predict the flow physics and heat transfer characteristics of a film-cooling problem that is formed from the interaction of a coolant jet with a hot mainstream flow. The film-cooling technique is used to protect turbine blades from thermal failure, allowing the gas inlet temperature to be increased beyond the failure temperature of the turbine blade material in order to enhance the efficiency of gas turbine engines. A coolant fluid is injected into the hot mainstream through several rows of injection holes placed on the surface of a gas turbine

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13

Ricklick, Mark. "CHARACTERIZATION OF AN INLINE ROW IMPINGEMENT CHANNEL FOR TURBINE BLADE COOLING APPLICATIONS." Doctoral diss., University of Central Florida, 2009. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/2696.

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Gas turbines have become an intricate part of today's society. Besides powering practically all 200,000+ passenger aircraft in use today, they are also a predominate form of power generation when coupled with a generator. The fact that they are highly efficient, and capable of large power to weight ratios, makes gas turbines an ideal solution for many power requirement issues faced today. Designers have even been able to develop small, micro-turbines capable of producing efficient portable power. Part of the turbine's success is the fact that their efficiency levels have continuously risen sin

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14

Yang, Huitao. "Investigations of flow and film cooling on turbine blade edge regions." Texas A&M University, 2006. http://hdl.handle.net/1969.1/4338.

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The inlet temperature of modern gas turbine engines has been increased to achieve higher thermal efficiency and increased output. The blade edge regions, including the blade tip, the leading edge, and the platform, are exposed to the most extreme heat loads, and therefore, must be adequately cooled to maintain safety. For the blade tip, there is tip leakage flow due to the pressure gradient across the tip. This leakage flow not only reduces the blade aerodynamic performance, but also yields a high heat load due to the thin boundary layer and high speed. Various tip configurations, such as plan

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15

Chattuchai, Songphol. "Analytical and numerical investigations of a new turbine blade cooling method." FIU Digital Commons, 1998. http://digitalcommons.fiu.edu/etd/2115.

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The turbine blade cooling has been considered to be a unique solution to increase the efficiency of the gas turbine engine. There are many difference methods for turbine blade cooling which have received serious attention and research effort. Most of them use basically the same method that passes the amount of cooling air through the turbine blade. These methods can disturb the hot gas since the cooling air is injected into the main stream gas, which may reduce the turbine engine's efficiency. A new turbine cooling method is studied in this thesis. This method employs the cooling air that pass

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16

Jones, Andrew. "The effects of rotation on heat transfer in turbine blade cooling." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/11675.

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17

Effendy, Marwan. "Investigation of turbine blade trailing edge cooling and thermal mixing characteristics." Thesis, Kingston University, 2014. http://eprints.kingston.ac.uk/30604/.

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The present computation investigates a turbine blade with trailing-edge cutback coolant ejection designs, aiming for a comparison study of aerothermal performances such as discharge coefficient and film cooling effectiveness due to the change of trailing-edge geometries and blowing ratios. The shear-stress transport (SST) k-w turbulence model is adopted and numerical studies are carried out by two-stage investigations:- firstly, validation of an existing cutback blade model with staggered circular pin-fins array inside the cooling passage that has been extensively studied by other researchers

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18

Couch, Eric L. "Measurements of Cooling Effectiveness Along the Tip of a Turbine Blade." Thesis, Virginia Tech, 2003. http://hdl.handle.net/10919/76815.

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In a gas turbine engine, turbine blades are exposed to temperatures above their melting point. Film-cooling and internal cooling techniques can prolong blade life and allow for higher engine temperatures. This study examines a novel cooling technique called a microcircuit, which combines internal convection and pressure side injection on a turbine blade tip. Holes on the tip called dirt purge holes expel dirt from the blade, so other holes are not clogged. Wind tunnel tests are used to observe how effectively dirt purge and microcircuit designs cool the tip. Tip gap size and blowing ratio are

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19

MISHRA, SUMAN. "Single-Hole Film Cooling on a Turbine-Blade Leading-Edge Model." University of Cincinnati / OhioLINK, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1205156648.

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20

Khaldi, A. "Discharge coefficient of film cooling holes with rounded entries or exits." Thesis, University of Nottingham, 1987. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.378758.

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21

Christophel, Jesse Reuben. "Comparison of the Thermal Performance of Several Tip Cooling Designs for a Turbine Blade." Thesis, Virginia Tech, 2003. http://hdl.handle.net/10919/76870.

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Gas turbine blades are subject to harsh operating conditions that require innovative cooling techniques to insure reliable operation of parts. Film-cooling and internal cooling techniques can prolong blade life and allow for higher engine temperatures. This study examines several unique methods of cooling the turbine blade tip. The first method employs holes placed directly in the tip which inject coolant onto the blade tip. The second and third methods used holes placed on the pressure side of a blade near the tip representative of two different manufacturing techniques. The fourth method

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22

Wright, Lesley Mae. "Experimental investigation of turbine blade platform film cooling and rotational effect on trailing edge internal cooling." [College Station, Tex. : Texas A&M University, 2006. http://hdl.handle.net/1969.1/ETD-TAMU-1826.

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23

Elder, Erin N. "Internal Heat Transfer and External Effectiveness Measurements for a Novel Turbine Blade Cooling Design." Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/77004.

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Efficiency and power output of gas turbines improve with an increase in turbine inlet temperatures, and blade designers continually seek out new methods of increasing these temperatures. Increases in turbine inlet temperatures are achieved by utilizing a combination of internal convective cooling and external film-cooling. This study will evaluate several novel cooling schemes for turbine airfoils, called microcircuits. Microcircuits are placed inside the turbine blade wall, and the features turbulate the air and increase heat transfer surface area, thereby augmenting convective cooling. The c

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24

Morland, Lawrence Christopher. "Mathematical models for a fluid flow arising in turbine blade cooling passages." Thesis, University of Oxford, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.330029.

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25

Nagaiah, Narasimha. "Multiobjective Design Optimization of Gas Turbine Blade with Emphasis on Internal Cooling." Doctoral diss., University of Central Florida, 2012. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/5350.

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In the design of mechanical components, numerical simulations and experimental methods are commonly used for design creation (or modification) and design optimization. However, a major challenge of using simulation and experimental methods is that they are time-consuming and often cost-prohibitive for the designer. In addition, the simultaneous interactions between aerodynamic, thermodynamic and mechanical integrity objectives for a particular component or set of components are difficult to accurately characterize, even with the existing simulation tools and experimental methods. The current r

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26

Roy, Rajkumar. "Adaptive search and the preliminary design of gas turbine blade cooling systems." Thesis, University of Plymouth, 1997. http://hdl.handle.net/10026.1/2664.

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This research concerns the integration of Adaptive Search (AS) technique such as the Genetic Algorithms (GA) with knowledge based software to develop a research prototype of an Adaptive Search Manager (ASM). The developed approach allows to utilise both quantitative and qualitative information in engineering design decision making. A Fuzzy Expert System manipulates AS software within the design environment concerning the preliminary design of gas turbine blade cooling systems. Steady state cooling hole geometry models have been developed for the project in collaboration with Rolls Royce plc. T

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27

Vettigunta, Uday Kumar. "Micro cooling of a Gas Turbine Blade with a Shell-Spar Design." Thesis, Southern Illinois University at Edwardsville, 2019. http://pqdtopen.proquest.com/#viewpdf?dispub=10975690.

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<p> The cooling effectiveness with the skin cooled micro cooling of a single gas turbine blade is analyzed numerically. The study use Hypermesh to generate a comprehensive 3D mesh of the domain that consists of air around the blade, skin layer of the blade, the cooling channels that wrap around the blade and the core metallic blade inner core. The micro channels were rectangular channel width of 2.54 mm x 0.39mm and heat transfer coefficient varying from (800and 1100 W/m2K) with the channel inlet velocity being constant. The study examined the flow pattern and the local heat transfer effect

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28

Townsend, Jessica Lee. "Experimental evaluation and modeling of a turbine blade with potassium evaporative cooling." Thesis, Massachusetts Institute of Technology, 2004. http://hdl.handle.net/1721.1/17831.

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Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2004.<br>Page 148 blank.<br>Includes bibliographical references (p. 145-147).<br>A new method of turbine blade cooling, the Return Flow Cascade, has been developed in which vaporization of a liquid metal such as potassium is used to maintain the blade surface at a nearly uniform temperature. Turbine blades cooled using this technology have lower blade temperature levels compared to that available with conventional air cooling, potentially resulting in higher firing temperatures or a choice of a wider

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29

Virdi, Amandeep Singh. "Aero-thermal performance and enhanced internal cooling of unshrouded turbine blade tips." Thesis, University of Oxford, 2015. https://ora.ox.ac.uk/objects/uuid:62c3e94a-a1ff-47a8-bb81-e870b0013f11.

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The tips of unshrouded, high-pressure turbine blades are prone to significantly high heat loads. The gap between the tip and over-tip casing is the root cause of undesirable over-tip leakage flow that is directly responsible for high thermal material degradation and is a major source of aerodynamic loss within a turbine. Both must be minimised for the safe working and improved performance of future gas-turbines. A joint experimental and numerical study is presented to understand and characterise the heat transfer and aerodynamics of unshrouded blade tips. The investigation is undertaken with t

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30

Hohlfeld, Erik Max. "Film Cooling Predictions Along the Tip and Platform of a Turbine Blade." Thesis, Virginia Tech, 2003. http://hdl.handle.net/10919/76781.

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Turbine airfoils are exposed to the hottest temperatures in the gas turbine with temperatures typically exceeding the melting point of the blade material. Cooling methods investigated in this computational study included parasitic cooling flow losses, which are inherent to engines, and microcircuit channels. Parasitic losses included dirt purge holes, located along the blade tip, and platform leakage flow, which result from gaps between various turbine components. Microcircuits are a novel cooling technique involving small air passages placed near the airfoil surface to enhance internal coo

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31

Bubb, James Vernon. "The Influence of Pressure Ratio on Film Cooling Performance of a Turbine Blade." Thesis, Virginia Tech, 1999. http://hdl.handle.net/10919/34023.

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The relationship between the plenum to freestream total pressure ratio on film cooling performance is experimentally investigated. Measurements of both the heat transfer coefficient and the adiabatic effectiveness were made on the suction side of the center blade in a linear transonic cascade. Entrance and exit Mach numbers were 0.3 and 1.2 respectively. Reynolds number based on chord and exit conditions is 3 x 10^6. The blade contour is representative of a typical General Electric first stage, high turning, turbine blade. Tunnel freestream conditions were 10 psig total pressure and appro

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32

Land, Camron C. "Effects of Sand Ingestion on the Cooling of Turbine Blade Outer Air Seals." Thesis, Virginia Tech, 2006. http://hdl.handle.net/10919/76893.

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Modern gas turbine engines operate in environments where particle ingestion, especially sand ingestion, can affect the cooling of various turbine parts. The most critical areas are in the combustor and the first stage components of the turbine. Gas temperatures in these areas are the highest compared to other areas and exceed the melting points of the constituent metals. To extend the life of hot section components, internal convective cooling and external film-cooling are required. This study examined the effects of sand ingestion on various cooling geometries. The first part investigate

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33

YANG, LIANFENG. "AEROTHERMODYNAMIC INVESTIGATION OF THE TURBINE BLADE FILM COOLING WITH LARGE EDDY SIMULATION METHOD." Doctoral thesis, Università degli studi di Genova, 2022. http://hdl.handle.net/11567/1093755.

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Gas turbines have been widely used in the aviation, marine, power plant, etc., which plays an indispensable role in modern industries. Nowadays, higher efficiency and larger output power is demanded, consequently, the turbine inlet temperature (TIT) has to be increased to up to 2260K in some turbofan engines. The turbine blades or vanes operate in a harsh environment and the operating temperature significantly surpasses the melting point of the turbine blade material. Therefore, the turbine cooling technology is of vital importance aiming to guarantee the lifespan of the turbine blades and the

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34

Ahn, Jaeyong. "Film cooling effectiveness measurements on rotating and non-rotating turbine components." Texas A&M University, 2005. http://hdl.handle.net/1969.1/4664.

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Detailed film cooling effectiveness distributions were measured on the stationary blade tip and on the leading edge region of a rotating blade using a Pressure Sensitive Paint technique. Air and nitrogen gas were used as the film cooling gases and the oxygen concentration distribution for each case was measured. The film cooling effectiveness information was obtained from the difference of the oxygen concentration between air and nitrogen gas cases by applying the mass transfer analogy. In the case of the stationary blade tip, plane tip and squealer tip blades were used while the film cooling

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35

Su, Guoguang. "Numerical simulation of flow and heat transfer of internal cooling passage in gas turbine blade." Texas A&M University, 2005. http://hdl.handle.net/1969.1/4957.

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A computational study of three-dimensional turbulent flow and heat transfer was performed in four types of rotating channels. The first type is a rotating rectangular channel with V-shaped ribs. The channel aspect ratio (AR) is 4:1, the rib height-to-hydraulic diameter ratio (e/Dh) is 0.078 and the rib pitch-to-height ratio (P/e) is 10. The rotation number and inlet coolant-to-wall density ratio were varied from 0.0 to 0.28 and from 0.122 to 0.40, respectively, while the Reynolds number was varied from 10,000 to 500,000. Three channel orientations (90 degrees, -135 degrees, and 135 degrees fro

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36

LITZLER, JEFFREY W. "COMPUTATIONAL SIMULATION AND ANALYSIS OF FILM COOLING FOR THE LEADING-EDGE MODEL OF A TURBINE BLADE." University of Cincinnati / OhioLINK, 2007. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1179521120.

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37

Wagner, Guillaume. "Experimental investigations of showerhead film cooling on the leading edge of a turbine blade /." Lausanne : EPFL, 2008. http://library.epfl.ch/theses/?nr=3755.

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Stenger, Douglas. "Three-Dimensional Numerical Simulation of Film Cooling on a Turbine Blade Leading-Edge Model." University of Cincinnati / OhioLINK, 2009. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1236053109.

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Jiang, Zhengyi. "Design, development and testing of an automated system for measuring wall thicknesses in turbine blades with cooling channels." Thesis, University of Manchester, 2016. https://www.research.manchester.ac.uk/portal/en/theses/design-development-and-testing-of-an-automated-system-for-measuring-wall-thicknesses-in-turbine-blades-with-cooling-channels(895ac153-e310-40e2-87c6-4e40654c9d5d).html.

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Cooling channels are designed in blades to protect the blades from damage at high temperature in a gas turbine. ELE Advanced Technology Ltd. is a UK company specialised in machining cooling channels in turbine blades using electro-chemical techniques. The wall thicknesses between these cooling channels and the surface of the turbine blade influences the performance of cooling channels and are required to be accurately machined and then inspected. At present, the company measures the wall thicknesses using a hand-held contact ultrasonic probe, which is time-consuming and not very accurate. In t

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40

Guy, Ashley Ray. "Effect of Blowing Ratio on the Nusselt Number and Film Cooling Effectiveness Distributions of a Showerhead Film Cooled Blade in a Transonic Cascade." Thesis, Virginia Tech, 2007. http://hdl.handle.net/10919/43764.

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This paper investigates the effect of blowing ratio on the film cooling performance of a showerhead film cooled first stage turbine blade. The blade was instrumented with double-sided thin film heat flux gages to experimentally characterize the Nusselt number and film cooling effectiveness distributions over the surface of the blade. The blade was arranged in a two-dimensional, linear cascade within a transonic, blowdown type wind tunnel. The wind tunnel freestream conditions were varied over two exit Mach numbers, Me=0.78 and Me=1.01, with an inlet freestream turbulence intensity of 12% ,

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Lynch, Stephen P. "The Effect of Endwall Contouring On Boundary Layer Development in a Turbine Blade Passage." Diss., Virginia Tech, 2011. http://hdl.handle.net/10919/77202.

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Increased efficiency and durability of gas turbine components is driven by demands for reduced fuel consumption and increased reliability in aircraft and power generation applications. The complex flow near the endwall of an axial gas turbine has been identified as a significant contributing factor to aerodynamic loss and increased part temperatures. Three-dimensional (non-axisymmetric) contouring of the endwall surface has been shown to reduce aerodynamic losses, but the effect of the contouring on endwall heat transfer is not well understood. This research focused on understanding the gen

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42

Byerley, Aaron R. "Heat transfer near the entrance to a film cooling hole in a gas turbine blade." Thesis, University of Oxford, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.329915.

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43

Biegger, Christoph [Verfasser]. "Flow and Heat Transfer Investigations in Swirl Tubes for Gas Turbine Blade Cooling / Christoph Biegger." München : Verlag Dr. Hut, 2017. http://d-nb.info/1135595984/34.

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44

Sidwell, Carroll Vincent 1972. "On the impact of variability and assembly on turbine blade cooling flow and oxidation life." Thesis, Massachusetts Institute of Technology, 2004. http://hdl.handle.net/1721.1/17814.

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Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2004.<br>Includes bibliographical references (leaves 77-79).<br>The life of a turbine blade is dependent on the quantity and temperature of the cooling flow sup- plied to the blade. The focus of this thesis is the impact of variability on blade cooling flow and, subsequently, its impact on oxidation life. A probabilistic analysis is performed on a commercial jet engine to quantify the variability in blade flow and oxidation life due to variability in ambient conditions, main gaspath conditions, the c

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Viswanathan, Aroon Kumar. "Detached Eddy Simulation of Turbulent Flow and Heat Transfer in Turbine Blade Internal Cooling Ducts." Diss., Virginia Tech, 2006. http://hdl.handle.net/10919/28518.

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Detached Eddy Simulations (DES) is a hybrid URANS-LES technique that was proposed to obtain computationally feasible solutions of high Reynolds number flows undergoing massive separation with reliable accuracy. Since its inception, DES has been applied to a wide variety of flow fields, but mostly limited to unbounded external aerodynamic flows. This is the first study to apply and validate DES to predict the internal flow and heat transfer in non-canonical flows of industrial relevance. The prediction capabilities of DES in capturing the effects of Coriolis forces, which are induced by rotatio

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Song, Keun Min. "Wall Modeled Large-Eddy Simulations in Rotating Systems for Applications to Turbine Blade Internal Cooling." Thesis, Virginia Tech, 2012. http://hdl.handle.net/10919/31080.

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Large-Eddy Simulations (LES or wall-resolved LES, WRLES) has been used extensively in capturing the physics of anisotropic turbulent flows. However, near wall turbulent scales in the inner layer in wall bounded flows makes it unfeasible for large Reynolds numbers due to grid requirements. This study evaluates the use of a wall model for LES (WMLES) on a channel with rotation at ã Reã _b = 34,000 from ã Roã _b = 0 to 0.38, non-staggered 90Â° ribbed duct with rotation at ã Reã _b = 20,000 from ã Roã _b = 0 to 0.70, stationary 45Â° staggered ribbed duct at ã Reã _b = 49,000, and two-pas

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Al-Aabidy, Qahtan. "Modelling of turbulent flow and heat transfer in porous media for gas turbine blade cooling." Thesis, University of Manchester, 2018. https://www.research.manchester.ac.uk/portal/en/theses/modelling-of-turbulent-flow-and-heat-transfer-in-porous-media-for-gas-turbine-blade-cooling(f7781d8e-bb1e-4bb7-a57e-4e77875ad6d6).html.

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This thesis focuses on the study of flow and heat transfer in porous media in both laminar and turbulent flow regimes, by using Volume Averaged Reynolds Navier Stokes (VARNS) approach. The main concern is to investigate the possibility of using porous media for the gas turbine blade cooling. Very recently, using this technique in blade cooling, particularly with internal cooling, has motivated many researchers due to an effective enhancement in the blade cooling. In this study turbulence is represented by using the Launder-Sharma low-Reynolds-number k-Îμ turbulence model, which is modified vi

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Morris, Angela. "Experimental and Computational Study of Heat Transfer on a Turbine Blade Tip with a Shelf." Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/76906.

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Cooling of turbine parts in a gas turbine engine is necessary for operation as the temperature of combustion gases is higher than the melting temperature of the turbine materials. The gap between rotating turbine blades and the stationary shroud provides an unintended flow path for hot gases. Gases that flow through the tip region cause pressure losses in the turbine section and high heat loads to the blade tip. This thesis studies the heat transfer on an innovative tip geometry intended to help reduce aerodynamic losses. The blade tip has a depression (shelf) on the tip surface along much of

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49

Rupakula, Venkata Panduranga Praveen. "Determination of heat (mass) transfer from blockages with round and elongated holes in a wide rectangular channel." Texas A&M University, 2005. http://hdl.handle.net/1969.1/4977.

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Mass transfer experiments were conducted to study the thermal performance characteristics of blockages with round and elongated holes, positioned in a 12:1 rectangular channel. Naphthalene sublimation technique was adopted to conduct experiments with four different blockage configurations, flow rates corresponding to Reynolds numbers (based on channel hydraulic diameter) of 7,000 and 17,000, and at three blockage locations. The hole area to channel area ratio for all four blockage configurations was the same at 0.196. The hole width was half the channel height, and the distance between consecu

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Mhetras, Shantanu. "Experimental study of gas turbine blade film cooling and internal turbulated heat transfer at large Reynolds numbers." [College Station, Tex. : Texas A&M University, 2006. http://hdl.handle.net/1969.1/ETD-TAMU-1820.

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