The Effect of Clearance on Unshrouded Ceramic Matrix Composite High Pressure Turbine Blade at Two Different Solidities

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ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (134 download)

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Book Synopsis The Effect of Clearance on Unshrouded Ceramic Matrix Composite High Pressure Turbine Blade at Two Different Solidities by : Prashanth Mohana Sundaram

Download or read book The Effect of Clearance on Unshrouded Ceramic Matrix Composite High Pressure Turbine Blade at Two Different Solidities written by Prashanth Mohana Sundaram and published by . This book was released on 2021 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A numerical study was conducted to evaluate the effect of varying tip clearances on the aerodynamic performance of an unshrouded first stage high pressure turbine ceramic matrix composite rotor blade. The analysis was carried out for three values of clearances (1%, 2% and 3% of blade span). The inlet temperature, pressure and blade rotational speed used for the analysis were specified by NASA for a notional single aisle aircraft engine to be available in the N+3 time frame, beyond 2030. As a measure for aerodynamic performance, we evaluated the total pressure loss coefficient, blade row efficiency/stage efficiency and examined other flow characteristics around the blade. In addition, we also analyzed the effect of increase in blade count (increase in solidity) on the aerodynamic performance at different tip clearances. The efficiency varied linearly with clearances larger than 1% Span for both solidity cases. Moreover, by increasing the solidity, we found the separation on the suction side of the surface for the lower solidity case vanished. This translated to a ~1% increase in efficiency for the higher solidity case over the lower solidity. Pressure loss profiles vs blade span were also compared, providing insight into the flow dynamics of the different clearances for both solidity cases.

Effect of Chord Size on Weight and Cooling Characteristics of Air-cooled Turbine Blades

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ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.3/5 (91 download)

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Book Synopsis Effect of Chord Size on Weight and Cooling Characteristics of Air-cooled Turbine Blades by : Jack B. Esgar

Download or read book Effect of Chord Size on Weight and Cooling Characteristics of Air-cooled Turbine Blades written by Jack B. Esgar and published by . This book was released on 1957 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis has been made to determine the effect of chord size on the weight and cooling characteristics of shell-supported, air-cooled gas-turbine blades. In uncooled turbines with solid blades, the general practice has been to design turbines with high aspect ratio (small blade chord) to achieve substantial turbine weight reduction. With air-cooled blades, this study shows that turbine blade weight is affected to a much smaller degree by the size of the blade chord.

Loss Mechanisms in Turbine Tip Clearance Flows

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ISBN 13 :
Total Pages : 110 pages
Book Rating : 4.:/5 (758 download)

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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.

Parametric Study of Turbine Blade Internal Cooling and Film Cooling

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ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (689 download)

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Book Synopsis Parametric Study of Turbine Blade Internal Cooling and Film Cooling by : Akhilesh P. Rallabandi

Download or read book Parametric Study of Turbine Blade Internal Cooling and Film Cooling written by Akhilesh P. Rallabandi and published by . This book was released on 2010 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Gas turbine engines are extensively used in the aviation and power generation industries. They are used as topping cycles in combined cycle power plants, or as stand alone power generation units. Gains in thermodynamic efficiency can be realized by increasing the turbine inlet temperatures. Since modern turbine inlet temperatures exceed the melting point of the constituent superalloys, it is necessary to provide an aggressive cooling system. Relatively cool air, ducted from the compressor of the engine is used to remove heat from the hot turbine blade. This air flows through passages in the hollow blade (internal cooling), and is also ejected onto the surface of the blade to form an insulating film (film cooling). Modern land-based gas turbine engines use high Reynolds number internal flow to cool their internal passages. The first part of this study focuses on experiments pertaining to passages with Reynolds numbers of up to 400,000. Common turbulator designs (45degree parallel sharp-edged and round-edged) ribs are studied. Older correlations are found to require corrections in order to be valid in the high Reynolds number parameter space. The effect of rotation on heat transfer in a typical three-pass serpentine channel is studied using a computational model with near-wall refinement. Results from this computational study indicate that the hub experiences abnormally high heat transfer under rotation. An experimental study is conducted at Buoyancy numbers similar to an actual engine on a wedge shaped model trailing edge, roughened with pin-fins and equipped with slot ejection. Results show an asymmetery between the leading and trailing surfaces due to rotation - a difference which is subdued due to the provision of pin-fins. Film cooling effectiveness is measured by the PSP mass transfer analogy technique in two different configurations: a flat plate and a typical high pressure turbine blade. Parameters studied include a step immediately upstream of a row of holes; the Strouhal number (quantifying rotor-stator interaction) and coolant to mainstream density ratio. Results show a deterioration in film cooling effectiveness with on increasing the Strouhal number. Using a coolant with a higher density results in higher film cooling effectiveness.

Effect of Dimple Pattern on the Suppression of Boundary Layer Separation on a Low Pressure Turbine Blade

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ISBN 13 : 9781423517092
Total Pages : 201 pages
Book Rating : 4.5/5 (17 download)

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Book Synopsis Effect of Dimple Pattern on the Suppression of Boundary Layer Separation on a Low Pressure Turbine Blade by : John P. Casey

Download or read book Effect of Dimple Pattern on the Suppression of Boundary Layer Separation on a Low Pressure Turbine Blade written by John P. Casey and published by . This book was released on 2004-03-01 with total page 201 pages. Available in PDF, EPUB and Kindle. Book excerpt: Three dimple patterns were investigated to ascertain their relative effectiveness on controlling boundary layer separation from a low-pressure turbine blade. The three cases included a single row of dimples at 65% of the axial chord with 2.22 cm spacing, a single row of dimples at 65% of the axial chord with 4.44 cm spacing, and a two-row staggered pattern with rows at 65% and 76% of the axial chord with 4.44 cm spacing. The multiple row case was such that the center of the upstream dimple set at the midpoint between two downstream dimples. The dimple spacing was measured center-on-center. Each of the dimple patterns was studied and compared to an unmodified blade at axial chord Reynolds numbers based on inlet velocity of 25k, 45k, and 100k. Experimental data was collected in a low-speed, draw down wind tunnel containing a linear turbine cascade of 8 Pak-B blades. Measurements of surface pressure, boundary layer parameters, wake velocity, and total pressure losses were made to examine the flow. No dimple pattern dramatically outperformed the others. Each of the dimple patterns studied improved the average total pressure loss coefficient by 34% for Re 25k and 1% Tu. Complementing the experimental effort was a three-dimensional computational fluid dynamics study. Four models were built and analyzed. The models included an unmodified blade, blades with dimples at 65% of the axial chord with 2 cm or 4 cm spacing, respectively, and a multiple row case consisting of dimples at 65% and 76% of the axial chord with 2 cm spacing. Again the upstream dimple set at the midpoint between two downstream dimples. The computational fluid dynamics study provided detailed flow visualization in and around the dimples as well as a comparison to experimental data for solver verification. It was shown that the computational and experimental results showed similar trends in wake loss and boundary layer traverses.

Three-dimensional Unsteady Flow in Oscillating Turbine Blade Row

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ISBN 13 :
Total Pages : 173 pages
Book Rating : 4.:/5 (912 download)

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Book Synopsis Three-dimensional Unsteady Flow in Oscillating Turbine Blade Row by :

Download or read book Three-dimensional Unsteady Flow in Oscillating Turbine Blade Row written by and published by . This book was released on 2006 with total page 173 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Experimental Assessment of Droplet Impact Erosion of Low Pressure Steam Turbine Blades

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ISBN 13 : 9783832286033
Total Pages : 124 pages
Book Rating : 4.2/5 (86 download)

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Book Synopsis Experimental Assessment of Droplet Impact Erosion of Low Pressure Steam Turbine Blades by : Mansoor Ahmad

Download or read book Experimental Assessment of Droplet Impact Erosion of Low Pressure Steam Turbine Blades written by Mansoor Ahmad and published by . This book was released on 2009 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Effect of Aircraft-Engine Turbine Design on the Size of Blade Tip Clearance

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ISBN 13 :
Total Pages : 11 pages
Book Rating : 4.:/5 (227 download)

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Book Synopsis Effect of Aircraft-Engine Turbine Design on the Size of Blade Tip Clearance by : S. Szczecinski

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).

Use of Dimples to Suppress Boundary Layer Separation on a Low Pressure Turbine Blade

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ISBN 13 : 9781423506430
Total Pages : 202 pages
Book Rating : 4.5/5 (64 download)

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Book Synopsis Use of Dimples to Suppress Boundary Layer Separation on a Low Pressure Turbine Blade by : Kurt P. Rouser

Download or read book Use of Dimples to Suppress Boundary Layer Separation on a Low Pressure Turbine Blade written by Kurt P. Rouser and published by . This book was released on 2002-12-01 with total page 202 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flow separation on a low pressure turbine blade is explored at Reynolds numbers of 25k, 45k and 100k, Experimental data is collected in a low- speed, draw-down wind tunnel using a cascade of eight Pak-B blades, Flow is examined from measurements of blade surface pressures, boundary layer parameters, exit velocities, and total pressure losses across the blade, Two recessed dimple shapes are assessed for suppressing flow separation and associated losses, One dimple is spherical, and the second is asymmetric, formed from a full dimple spanwise half-filled, A single row of each dimple shape is tested at 50%, 55% and 65% axial chord, Symmetric dimples reduce separation losses by as much as 28%, while asymmetric dimples reduce losses by as much as 23%, A complementary three-dimensional computational study is conducted to visualize local flow structure, Computational analysis uses Gridgen v13,3 as a mesh generator, Fluent v6,O as a flow solver and FIELDVIEW - v8,0 for graphic display and analysis, Computational results for Pak-B blades at a Reynolds number of 25k indicate that both dimple shapes cause a span-wise vortex to rollup within the dimple and provide a localized pressure drop,

An Experimental Investigation of Turbine Blade Heat Transfer and Turbine Blade Trailing Edge Cooling

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ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (585 download)

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Book Synopsis An Experimental Investigation of Turbine Blade Heat Transfer and Turbine Blade Trailing Edge Cooling by : Jungho Choi

Download or read book An Experimental Investigation of Turbine Blade Heat Transfer and Turbine Blade Trailing Edge Cooling written by Jungho Choi and published by . This book was released on 2005 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: This experimental study contains two points; part 1 - 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, respectively. The cascade inlet Reynolds number based on blade chord length was varied from 15,700 to 105,000, and the Strouhal number was varied from 0 to 2.96 by changing the rotating wake passing frequency (rod speed) and cascade inlet velocity. A thin foil thermocouple instrumented blade was used to determine the surface heat transfer coefficient. A Liquid crystal technique based on hue value detection was used to measure the heat transfer coefficient on a trailing edge film cooling model and internal model of a gas turbine blade. It was also used to determine the film effectiveness on the trailing edge. For the internal model, Reynolds numbers based on the hydraulic diameter of the exit slot and exit velocity were 5,000, 10,000, 20,000, and 30,000 and corresponding coolant-to-mainstream velocity ratios were 0.3, 0.6, 1.2, and 1.8 for the external models, respectively. The experiments were performed at two different designs and each design has several different models such as staggered / inline exit, straight / tapered entrance, and smooth / rib entrance. The compressed air was used in coolant air. A circular turbulence grid was employed to upstream in the wind tunnel and square ribs were employed in the inlet chamber to generate turbulence intensity externally and internally, respectively.

Heat Transfer in a Complex Trailing Edge Passage for a High Pressure Turbine Blade. Part 2

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Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721526673
Total Pages : 28 pages
Book Rating : 4.5/5 (266 download)

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Book Synopsis Heat Transfer in a Complex Trailing Edge Passage for a High Pressure Turbine Blade. Part 2 by : National Aeronautics and Space Administration (NASA)

Download or read book Heat Transfer in a Complex Trailing Edge Passage for a High Pressure Turbine Blade. Part 2 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-19 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: A combined experimental and numerical study to investigate the heat transfer distribution in a complex blade trailing edge passage was conducted. The geometry consists of a two pass serpentine passage with taper toward the trailing edge, as well as from hub to tip. The upflow channel has an average aspect ratio of roughly 14:1, while the exit passage aspect ratio is about 5:1. The upflow channel is split in an interrupted way and is smooth on the trailing edge side of the split and turbulated on the other side. A turning vane is placed near the tip of the upflow channel. Reynolds numbers in the range of 31,000 to 61,000, based on inlet conditions, were simulated numerically. The simulation was performed using the Glenn-HT code, a full three-dimensional Navier-Stokes solver using the Wilcox k-omega turbulence model. A structured multi-block grid is used with approximately 4.5 million cells and average y+ values on the order of unity. Pressure and heat transfer distributions are presented with comparison to the experimental data. While there are some regions with discrepancies, in general the agreement is very good for both pressure and heat transfer. Rigby, David L. and Bunker, Ronald S. Glenn Research Center NASA/CR-2002-211701, NAS 1.26:211701, ASME-2002-GT-30213, E-13430

The Combined Effects of Freestream Turbulence, Pressure Gradients, and Surface Roughness on Turbine Aerodynamics

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ISBN 13 : 9781423511243
Total Pages : 99 pages
Book Rating : 4.5/5 (112 download)

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Book Synopsis The Combined Effects of Freestream Turbulence, Pressure Gradients, and Surface Roughness on Turbine Aerodynamics by : Christine P. Ellering

Download or read book The Combined Effects of Freestream Turbulence, Pressure Gradients, and Surface Roughness on Turbine Aerodynamics written by Christine P. Ellering and published by . This book was released on 2002-03-01 with total page 99 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work used scaled facsimiles of real turbine blade surfaces to characterize correlations between turbine blade roughness, freestream turbulence, pressure gradients and skin friction (Cf). Addition of roughness caused Cf to increase: up to 300% for the roughest surface. Addition of freestream turbulence resulted in 125% increase for the same surface. The combined effects showed increases up to 380%. Although decreasing roughness, freestream turbulence, and Reynolds number resulted in less dramatic results, it was concluded that the Cf increases due to combined effects were consistently higher than their corresponding sum of the parts. The combined effects of roughness and pressure gradients yielded inconclusive results, however, limited observations seem to corroborate the trends seen during zero pressure gradient tests.

Experimental Study of Gas Turbine Blade Film Cooling and Internal Turbulated Heat Transfer at Large Reynolds Numbers

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ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (69 download)

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Book Synopsis Experimental Study of Gas Turbine Blade Film Cooling and Internal Turbulated Heat Transfer at Large Reynolds Numbers by : Shantanu Mhetras

Download or read book Experimental Study of Gas Turbine Blade Film Cooling and Internal Turbulated Heat Transfer at Large Reynolds Numbers written by Shantanu Mhetras and published by . This book was released on 2010 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Film cooling effectiveness on a gas turbine blade tip on the near tip pressure side and on the squealer cavity floor is investigated. Optimal arrangement of film cooling holes, effect of a full squealer and a cutback squealer, varying blowing ratios and squealer cavity depth are also examined on film cooling effectiveness. The film-cooling effectiveness distributions are measured on the blade tip, near tip pressure side and the inner pressure and suction side rim walls using a Pressure Sensitive Paint (PSP) technique. A blowing ratio of 1.0 is found to give best results on the pressure side whereas the other tip surfaces give best results for blowing ratios of 2. Film cooling effectiveness tests are also performed on the span of a fully-cooled high pressure turbine blade in a 5 bladed linear cascade using the PSP technique. Film cooling effectiveness over the entire blade region is determined from full coverage film cooling, showerhead cooling and from each individual row with and without an upstream wake. The effect of superposition of film cooling effectiveness from each individual row is then compared with full coverage film cooling. Results show that an upstream wake can result in lower film cooling effectiveness on the blade. Effectiveness magnitudes from superposition of effectiveness data from individual rows are comparable with that from full coverage film cooling. Internal heat transfer measurements are also performed in a high aspect ratio channel and from jet array impingement on a turbulated target wall at large Reynolds numbers. For the channel, three dimple and one discrete rib configurations are tested on one of the wide walls for Reynolds numbers up to 1.3 million. The presence of a turbulated wall and its effect on heat transfer enhancement against a smooth surface is investigated. Heat transfer enhancement is found to decrease at high Re with the discrete rib configurations providing the best enhancement but highest pressure losses. Experiments to investigate heat transfer and pressure loss from jet array impingement are also performed on the target wall at Reynolds numbers up to 450,000. The heat transfer from a turbulated target wall and two jet plates is investigated. A target wall with short pins provides the best heat transfer with the dimpled target wall giving the lowest heat transfer among the three geometries studied.

Turbine Blade Surface Roughness Effects on Shear Drag and Heat Transfer

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ISBN 13 : 9781423530220
Total Pages : 203 pages
Book Rating : 4.5/5 (32 download)

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Book Synopsis Turbine Blade Surface Roughness Effects on Shear Drag and Heat Transfer by : Jess W. Drab

Download or read book Turbine Blade Surface Roughness Effects on Shear Drag and Heat Transfer written by Jess W. Drab and published by . This book was released on 2001-03-01 with total page 203 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work used scaled samples of actual turbine blade surfaces to characterize correlations between turbine surface roughness, friction coefficient, and convective heat transfer rate-parameters which affect an engine's efficiency and the blade's lifes an. For erosion/deposits, friction coefficients up to 250 times higher and convective heat transfer coefficients of up to 150 times higher were found when to compared to a flat plate baseline. Other roughness types (pitting and fuel deposits) yielded less dramatic results. These results did not follow existing friction coefficient-to-heat transfer coefficient correlations, such as the Reynolds analogy. While these analytical and empirical correlations hold for flat plates, they may be inadequate to describe the highly irregular surface roughness found on real in-service turbine blades.

Control of Flow Separation on a Turbine Blade by Utilizing Tail Extensions

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ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (946 download)

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Book Synopsis Control of Flow Separation on a Turbine Blade by Utilizing Tail Extensions by :

Download or read book Control of Flow Separation on a Turbine Blade by Utilizing Tail Extensions written by and published by . This book was released on 1999 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental study was conducted in a two-dimensional linear cascade, focusing on the suction surface of a low pressure turbine blade. Flow Reynolds numbers, based on exit velocity and suction surface length were varied from 50,000 to 300,000. The axial chord of the blades was varied using tail extenders from 0% to 15% beyond design. The effects of Reynolds number on a low pressure turbine cascade blade with tail extensions was investigated. This study has shown that for certain cases, changing the axial chord of a low pressure turbine blade by utilizing tail extensions provided a clear improvement in boundary layer behavior which results in better overall performance. There was no additional advantage when the tail extensions were longer than 6.1% of the axial chord. The shortest tail extension resulted in the greatest zone of performance enhancement. The longer tail extension resulted in a smaller region of performance enhancement.

Aerothermal Impact of Low Emission Combustion on the Turbine Blade Tip

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ISBN 13 : 9783844074826
Total Pages : pages
Book Rating : 4.0/5 (748 download)

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Book Synopsis Aerothermal Impact of Low Emission Combustion on the Turbine Blade Tip by : Manuel Wilhelm

Download or read book Aerothermal Impact of Low Emission Combustion on the Turbine Blade Tip written by Manuel Wilhelm and published by . This book was released on 2020 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Effects of Toughened Matrix Resins on Composite Materials for Wind Turbine Blades

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ISBN 13 :
Total Pages : 256 pages
Book Rating : 4.:/5 (468 download)

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Book Synopsis Effects of Toughened Matrix Resins on Composite Materials for Wind Turbine Blades by : Ricardo Orozco

Download or read book Effects of Toughened Matrix Resins on Composite Materials for Wind Turbine Blades written by Ricardo Orozco and published by . This book was released on 1999 with total page 256 pages. Available in PDF, EPUB and Kindle. Book excerpt: